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Technology
Category of spacecraft.

Subtopics

Kaituo Satellite from Shenzen DFH Company, also called XY 2 (Xinyan-2 or NewTech-2), which tested electric propulsion Hall thrusters. Deployed the DCBB subsatellite.

Pujiang Pujiang, the Chinese Technology Experiment Satellite, was designed to promote the construction of smart cities in China, by monitoring urban weather, traffic and population density. It was the first Chinese satellite to use 3D printing for the titanium structure of its antenna. It included a Wi-Fi router providing a communication network between the three Tianwang cubesats released on the same launch.

AAM The Dual Launch Adapter housed the secondary payload, an Advanced Avionics Module for future use on Indian launch vehicles. The AAM remained attached to the PSLV fourth stage.

Almasat Student satellite from the University of Bologna, testing a cold gas microthruster system and the platform for a future Earth observing satellite.

Astro-200 Null

CAST1000 The CAST1000 bus was a microsatellite class (30-200 kg) platform designed to satisfy missions including earth observation, atmospheric exploration, electromagnetic exploration, technological demonstration, on-orbit service, and LEO communication, while supporting use in satellite constellations and formation flying.

CAST2000 The CAST2000 bus was in the minisatellite class (200-400 kg bus mass; 300-600 kg payload capacity). It was designed for diverse missions, including earth observation, technological demonstration, scientific exploration, earth environmental exploration, formation flight and networking, meteorological research and application, communications, and navigation.

CUSat Cornell University satellite; carried a differential GPS navigation system and pulsed plasma thrusters. The defunct-before-launch CUSAT 2/Top satellite remained attached to the Falcon 9 second stage. CUSAT (formerly CUSAT 1/Bottom) was launched attached to CUSAT 2 and separated from it after orbit insertion.

DESPATCH Also known as ArtSat-2; from Tama Art University. The yellowish, tapered-helix assembly was intended mainly as a work of art although it also carries an amateur radio communications payload with a limited range. In a 0.915 AU x 1.089 AU x 6.8 deg solar orbit.

EDUSAT Technology satellite built by the Universita di Roma la Sapienza.

Fastsat Developed by NASA-Marshall and subcontractors in Huntsville; carried ionospheric and atmospheric experiments, a USAF experiment, and the Nanosail-D2 solar sail.

Ginrei Microsatellite from Shinshu University to study use of LED's for long-distance communication.

Horyu Kyushu Institute of Technology satellite to study spacecraft charging effects and test a camera payload for Surrey Satellite (which observed the second stage after payload deployment to support development of improved propellant insulation).

Ikaros Solar sail test vehicle. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg. Deployed sail by 11 June, and acceleration due to the pressure of the light from the sun was as expected. Launched 2010.05.20,

IXV ESA's Intermediate Experimental Vehicle was a reentry vehicle designed to study hypersonic aerothermodynamics.

LARES Support System Remained attached to the AVUM upper stage. Included extensive instrumentation to monitor the launch vehicle during ascent. It also deployed seven 1U Cubesats from three P-POD deployers

MiniSil Project for On-Board Autonomy technology satellite. Launched 2009.11.02,

Nanosat Nanosatellite by INTA, Spain.

ORS-3 The ORS-3 Minotaur final stage carried an experimental launch tracking system and a drag device to reduce the amount of time it spent in orbit.

Prisma Prototype Research Instruments and Space Mission technology Advancement satellite to test space rendezvous and formation-flight technologies. Consisted of 140 kg primary satellite and 40 kg target. Launched 2010.06.15.

PSSC Picosatellite Solar Cell Testbed 2. Ejected from STS-135 prior to re-entry.

Ratsat Payload for the first successful launch of low-cost Falcon launch vehicle. The second stage demonstrated restart. The payload was a dummy mass which remained attached to the stage.

RPP National Reconnaissance Office Rapid Pathfinder Program technology satellites were built in less than two years, for under $20 million, to test classified sensors.

Shin'en Communications payload designed to demonstrate deep space communications with a small spacecraft from a 0.915 AU x 1.089 AU x 6.8 deg solar orbit.

SKRL Calibration sphere.

SPROUT Microsatellite with a Nihon University experiment to deploy a 1.5m inflatable triangular membrane.

STARS-2 Microsatellite from Kagawa University. Composed of two sections and a tether, deployed length 300 metres. Believed to have succeeded based on later orbital decay rate.

Sumbandila South African imaging satellite with a ground resolution of 6.25 m.

TET DLR Technologieerprobungsträger 1, as part of their On-Orbit Verification Program. Tested new space components; carried an imaging payload.

Tiantuo Technology satellite for the National University of Defense Technology; carried an payloads such as an imager, an atomic oxygen sensor, and an AIS (maritime tracking) receiver.

Tianxun Technology satellite built by the Nanjing University of Aeronautics and Astronautics with a small Earth observing CCD camera.

Unitec Space qualification of university-built computers. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg. Launched 2010.05.20,

Vesselsat OHB LuxSpace of Luxembourg satllite to provide AIS (ship tracking) services for Orbcomm.

XY-1 Technology mission.

Project 581 Chinese technology satellite. Study 1959. First Chinese satellite project, with the objective of placing a satellite in orbit by 1959.

Sputnik 1 Russian technology satellite. Tikhonravov's 1.4 metric ton ISZ satellite was to have been launched by the new R-7 ICBM as the Soviet Union's first satellite, during the International Geophysical Year.

Vanguard 1 American technology satellite. An engineering test satellite. Based on orbital position data derived from its transmissions, the shape of the earth was refined.

ARTV American re-entry vehicle technology satellite. 3 launches, 1958.04.24 (ARTV 1) to 1958.07.23 (ARTV 3). Suborbital advanced reentry test vehicle.

Pilot satellite American technology satellite. 6 launches, 1958.07.25 (Pilot 1) to 1958.08.28 (Pilot 6). Pilot launches were deep-black tests of the US Navy's 1950's reconnaissance satellite and ASAT designs.

Beacon 1 American technology satellite.

Score American communications technology satellite. Signal Communication by Orbiting Relay Equipment; first communications satellite; transmitted taped messages for 13 days.

Echo American passive communications satellite. The Echo satellites were NASA's first experimental communications satellite project.

Courier American communications technology satellite. Experimental communications.

Lofti American communications technology satellite. The Low Frequency Trans-Ionospheric (LOFTI) satellites were produced as a cooperative effort with the Radio Division.

Hi-Hoe American technology satellite. 3 launches, 1961.10.05 (Hi-Hoe 1) to 1962.07.26 (Hi-Hoe 3). US antisatellite tests.

DS-1 Ukrainian technology satellite. Technology test version of the original DS light satellite design. Primary mission was to test launch vehicle.

Radio Test Spacecraft American tracking network technology satellite. Mercury-Scout 1. Small satellite was to have verified the readiness of the worldwide Mercury tracking network

TRAAC American technology satellite. Transit Research and Attitude Control.

Program 661A American ion engine technology satellite. Study 1961. In November of 1961, Electro-Optical Systems was awarded a contract by the U. S. Air Force to develop a 8.9 mN, cesium-contact ionization IPS for three sub-orbital flight tests.

DS-2 Ukrainian technology satellite.

1MS Russian technology satellite. Early Kosmos launcher payloads of unknown purpose, possibly from Korolev OKB.

2MS Russian technology satellite. Early Kosmos launcher payloads of unknown purpose, possibly from Korolev OKB.

Ariel American earth magnetosphere satellite. Ionospheric studies; returned X-ray, ionospheric, cosmic ray data.

Beanstalk American technology satellite. One launch, 1962.05.31. Suborbital.

TAVE American technology satellite. Thor Agena Vibration Experiment

DS-A1 Ukrainian navigation technology satellite.

Relay American communications technology satellite.

Syncom American communications technology satellite. Experimental telecommunications satellite.

P 11 American technology satellite.

Omega Russian technology satellite. Early Cosmos satellite, evidently using the Yuzhnoye DS satellite bus. Payload developed by the VNIIEM to test electric gyrodyne orientation systems.

Dash American military technology satellite.

TRS American technology satellite. TRS satellites undertook a range of engineering experiments related to radiation-hardening of solar cells and spacecraft electronics.

DS-MT Ukrainian technology satellite. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays.

GGSE American gravity gradient technology satellite. 5 launches, 1964.01.11 (GGSE 1) to 1967.05.31 (GGSE 5). Developed designs and deployment techniques later applied to the NOSS / Whitecloud naval reconnaissance satellites.

AFP-43 American military technology satellite.

Echo 2 American passive communications satellite. Passive communications satellite; balloon; 1st joint US/USSR space mission.

Jupiter nose cone American re-entry vehicle technology satellite. Saturn 5. Launch vehicle test.

DS-MG Ukrainian technology satellite. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also studied magnetosphere of the earth.

FIRE American re-entry vehicle technology satellite. 2 launches, 1964.04.14 (FIRE 1) and 1965.05.22 (FIRE 2). Suborbital re-entry test program that used a subscale model of the Apollo Command Module to verify the configuration at high reentry speed.

LES American communications technology satellite.

Snapshot American ion engine technology satellite. Carried SNAP-9A nuclear power source. The on-board reactor provided electrical power for a 2.2-lb ion engine.

DS-U2-V Ukrainian military technology satellite. Military technology development satellite - mission still classified.

Asterix French technology satellite. First French satellite. Launched from Hammaguir (Algeria) in order to test the "Diamant" launching vehicle for the first time.

DS-U2-M Ukrainian technology satellite. Development tests of atomic clocks.

DS-K-40 Ukrainian communications technology satellite. Development of systems for the later operational Tselina satellites.

DS-U5 Ukrainian technology satellite. Cancelled 1965. Light satellite with propulsion for periodic correction of orbit. Cancelled in 1965 and never flown.

D French earth geodetic satellite. Small French science and technology satellites used on early Diamant launch vehicle tests.

GGTS American gravity gradient technology satellite. Gravity gradient stabilization tests.

Ohsumi Japanese technology satellite. Small engineering test satellites lofted by Japan's first indigenous launch vehicle.

OV4 American technology satellite. Whispering gallery experiments.

ATS-1 American communications technology satellite. ATS 1. During its 18 year lifetime, ATS-1 examined spin stabilization techniques, investigated the geostationary environment, and performed several communications experiments.

DS-MO Ukrainian technology satellite. Used in development of aerodynamic systems for stabilization and orientation of spacecraft. Also carried military optical equipment experiments.

ATS-2 American communications technology satellite. ATS 2. ATS-2 was placed into an undesirable orbit due to a launch vehicle failure.

ESRO European technology satellite. The ESRO series were small Scout-launched probes of near-earth space.

Timation American navigation technology satellite.

DODGE American gravity gradient technology satellite. The Navy's 195 kg DODGE (Department Of Defense Gravity Experiment) satellite had the primary mission to explore gravity gradient stabilization at near synchronous altitude.

IS-A Russian military anti-satellite system. First operational ASAT. Tested in 1967-1971 and deployed through the late 1970's. Design as revised by Yangel and Korolev from Chelomei's original.

ATS-3 American communications technology satellite. ATS 3. The goals for ATS-3 included investigations of spin stabilization techniques and VHF and C-band communications experiments.

Apollo LTA American technology satellite. 3 launches, 1967.11.09 (LTA-10R) to 1968.12.21 (LTA-B). Apollo Lunar module Test Articles were simple mass/structural models of the Lunar Module.

TTS American tracking network technology satellite. Tested Apollo tracking network.

ATS-4 American communications technology satellite. ATS 4. A launch vehicle failure stranded ATS-4 in a much lower than planned orbit, making the satellite nearly useless.

RADCAT American military technology satellite.

STV European technology satellite. Satellite Test Vehicle.

Boost Glide Re-entry Vehicle American re-entry vehicle technology satellite. The Boost Glide Re-entry Vehicle investigated related technological problems, particularly hypersonic maneuvering after re-entry into the atmosphere.

TACSAT American communications technology satellite. TACSAT was designed to experimentally test and develop tactical communications concepts for all US military services.

PAC American technology satellite. Package Attitude Control; semi-active gravity gradient stabilization tests.

ATS-5 American communications technology satellite.

TETR American tracking network technology satellite. Test satellite for NASA's Manned Space Flight Network.

DFH-1 Chinese communications technology satellite. First Chinese satellite. The initial satellite was flown for purely propaganda purposes, using a tune generator to play the 'East is Red'.

Molniya-Yu Russian tracking network technology satellite. Study 1969. This was a modification of the Molniya-1 satellite to test deep space radio-based tracking methods for the Soviet Lunar program.

Orbital Scanner American navigation technology satellite. Study 1969.

SERT American ion engine technology satellite. Electric ion engine tests.

Osumi Japanese technology satellite. Ohsumi 5. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E.

Dial MIKA French technology satellite. Engineering package; monitored launch vehicle performance.

DIAL WIKA German technology satellite. DIAL-WIKA.

Strela-1M Russian military store-dump communications satellite. 3

Tansei Japanese technology satellite. Series of spacecraft of varying configurations built for engineering tests of scientific satellite equipment.

SESP American military technology satellite.

PAET American military technology satellite. One launch, 1971.06.20. Suborbital.

Gridsphere American technology satellite.

Musketball American technology satellite.

Mylar American technology satellite.

ASTEX American technology satellite. Space Test Program; technology experiments.

STV 4 French technology satellite.

TD-1A European technology satellite. Sixth satellite of ESRO.

SRET French technology satellite. Test satellite.

Radsat American military technology satellite.

Sphinx American military technology satellite. Space Plasma High Voltage Interaction Experiment. Research payload carried on test flight of Titan 3E booster.

Miranda British technology satellite. Satellite technology. Anticipated life: longer than 50 years.

ATS-6 American communications technology satellite. ATS 6. In addition to its technology experiments, ATS-6 became the world's first educational satellite.

NTS American navigation technology satellite. Demonstrated navigation technologies.

FSW Chinese military surveillance satellite.

Intasat Spanish communications technology satellite. Spanish communications satellite.

Symphonie French communications technology satellite. Experimental telecommunications satellite, constructed jointly by France and the Federal Republic of Germany.

Parus Russian navigation satellite. Military satellite which provided navigation information and store-dump radio communications to Soviet naval forces and ballistic missile submarines.

P 72 American military technology satellite. Unknown satellite lost on a single Atlas launch failure. Evidently not repeated.

COS European technology satellite. CERS/ESRO satellite, first European Space Agency satellite. Studied extraterrestrial gamma radiation in the 25 MeV to 1 GeV energy range.

ETS Japanese technology satellite.

Corsa A Japanese technology satellite. Japanese technology satellite.

P 76 American communications technology satellite. Communications propagation experiments.

AUOS Ukrainian spacecraft bus. Standardized bus for low earth orbit scientific studies and testing of new systems and components of satellite under space flight conditions.

GAS NASA's GetAway Special program, officially known as the Small, Self-Contained Payloads program, offered interested individuals or groups opportunities to fly small experiments aboard the space shuttle.

Signe French technology satellite.

Sirio Italian communications technology satellite. SIRIO was a spin stabilized geostationary experimental communications satellite with a nominal life of two years.

ECS/OTS European communications satellite.

PIX American technology satellite. Plasma Interaction Experiment.

Yuri Japanese communications technology satellite. Medium-scale broadcasting satellite for experimental purposes.

OTS European communications technology satellite. Study 1978. Communications experiments satellite of the European Space Agency.

SCATHA American communications technology satellite.

Ayame Japanese communications technology satellite. Experimental Communications Satellite (ECS). Communications and propagation experiments of satellite-communication systems.

KRT-10 Russian space radio telescope. 10 m diameter radio telescope. Attached to Salyut 6 docking hatch and deployed after separation of Progress from Mir.

SJ Chinese communications technology satellite. SJ (Shijian; 'Practice') series were Chinese scientific research, technological experiment and military operational satellites of a variety of configurations.

Rohini 1A Indian technology satellite.

CAT European technology satellite.

Firewheel French technology satellite. Multiple European technology test satellites launched on the first Ariane.

LIPS American tether technology satellite.

Rohini 2 Indian technology satellite.

SSTL-70 British microsatellite bus. 1 Basic Surrey Microsat bus.

IRT American technology satellite. Deployed from STS 41B 2/5/84.

Strela-3 Russian military store-dump communications satellite. Said to have initially been developed for the GRU.

OEX Target American technology satellite. Shuttle autopilot software test target.

MABES Japanese technology satellite. MABES (Jindai). Experiment on the levitation of the magnetic bearing flywheel under zero-g condition.

Plazma-A Russian ion engine technology satellite. In 1987 two experimental Plazma-A satellites (Cosmos 1818 and 1867) were launched with new-generation Topaz reactors.

FY-1 Chinese earth weather satellite. The Feng Yun 1 meteorological satellites were launched into sun-synchronous 900 km, 99 deg inclination orbits by CZ-4 boosters from Taiyuan.

Ofeq 1-2 Israeli technology satellite. Ofeq, meaning 'Horizon', was a technology demonstration satellite developed by IAI (Israel Aircraft Industries) for ISA (Israel Space Agency).

37KB Russian manned space station module. Carried in the payload bay of the Buran space shuttle. They could remain attached to the bay or (modified to the 37KBI configuration) be docked to the Mir-2 station.

Olympus European communications technology satellite. This communications technology demonstration satellite tested direct television broadcast beams and was also equipped with conventional communications transponders.

HS 601 American communications satellite bus. 3-axis unified ARC 22 N and one Marquardt 490 N bipropellant thrusters, Sun and Barnes Earth sensors and two 61 Nms 2-axis gimbaled momentum bias wheels.

Debut Japanese communications technology satellite. Boom, umbrella test. DEBUT "Orizuru". Experiment of extending and contracting boom; experiment of expanding and contracting aerodynamic brake. Launching organization NASDA.

Stacksat P87-2 American technology satellite. 3 launched, 1990.04.11 (USA 56) to (USA 58). The U. S. military's STACKSAT mission involved the launch of three similar spacecraft, POGS, TEX and SCE.

Badr Pakistani communications technology satellite. Pakistani experimental series with a variety of payloads.

Italsat Italian communications satellite.talian communications satellite.

AFP-675 American military technology satellite.

IBSS American satellite. Sensor technology test; retrieved 5/2/91.

MPEC American military technology satellite. USA 70. Spacecraft engaged in research and exploration of the upper atmosphere or outer space.

Microsat American military communications satellite. Satellites used in a DARPA test of an LEO quick-reaction network for global communications.

Orbcomm Orbital Communications Corp, Dulles, USA. Orbcomm was a commercial venture to provide global messaging services using a constellation of 26 low-Earth orbiting satellites.

Tubsat Germany's Technical University of Berlin (TUB) built a successful series of 40 kg 'Tubsat' experimental technology satellites. Germany's Technical University of Berlin (TUB) built a successful series of 40 kg 'Tubsat' experimental technology satellites.

S80/T French communications technology satellite. Study 1992. Experimental communications satellite.

CTA Canadian technology satellite. Canadian Target Assembly; deployed from STS-52 10/22/92.

Znamya Russian ground reflector. Reflector mirror, deployed from Progress M-15 after separation from Mir space station.

CDS American communications technology satellite. Orbcomm OXP-1. Experimental spacecraft.

SCD Brazilian communications technology satellite. Environmental data relay.

Start satellite Russian communications technology satellite. Experimental satellite carried on test flight of the Start-1 carrier rocket, a new booster based on SS-25 ICBM.

SEDS Students for the Exploration and Development of Space, USA. Built tether technology satellite.

PMG American tether technology satellite. Plasma Motor Generator

Temisat Italian communications technology satellite. Temisat's primary mission was demonstration of a data relay system.

ACTS American communications technology satellite. One launch, 1993.09.12. NASA experimental communications; Advanced Communications Technology Satellite.

Kitsat South Korean technology satellite. South Korean indigenous 50-kg-class small satellite series, developed originally with technology transfer from Surrey Satellite Technology Ltd.

ISA Interstage Adapter ISA (Interstage Adapter) satellite launched with Clementine placed in a highly eccentric Earth orbit. It carried a set of space environment experiments.

ISAS satellite Interstage Adapter Subsystem, consisting of the STAR-37M solid rocket motor, the Interstage Adapter for Clementine, and radiation detectors. It transmitted radiation data on the Van Allen Radiation belts for three months. American military technology satellite. One launch, 1994.01.25.

BremSat German re-entry vehicle technology satellite. Atomic oxygen, dust particle, microgravity, reentry experiments.

OREX Japanese re-entry vehicle technology satellite. NASDA ballistic capsule used to test materials and acquire data related to atmospheric re-entry for use in design of Japanese HOPE spaceplane. Launch vehicle H-2.

VEP Japanese technology satellite. Monitored H-2 launch vehicle performance. National name MYOJO.

DFH-3 Chinese satellite bus used for geosynchronous communications and navigation satellites and deep space probes. Total mass, payload mass, and payload power improved through three versions from 2320 kg to 3800 kg; 230 kg to 450 kg; and 1000 W to 4000 W.

DARPASAT American technology satellite. USA 102. GPS receiver and data processor technology tests.

STRV British technology satellite.

APEX American technology satellite. P90-6 APEX.

EKA Russian technology satellite. Eksperimentalniy Kosmicheskiy Apparat - dummy of test satellite.

Gurwin Israeli technology satellite. Gurwin satellites were built by the Technion Institute of Technology, Israel.

Microstar American communications technology satellite. Small satellite bus, specially designed for multiple launch by Pegasus or Taurus family launch vehicles.

STEP Space Test Experiment Program; series of USAF technology test satellites.

LBSAT Spanish communications technology satellite. UPM/LBSAT 1. Universidad Politecnia de Madrid Satellite; experimental communications, microgravity experiments.

MicroSat-100 British microsatellite bus. Enlarged version of the basic Surrey Microsat-70 bus.

SURFSAT-1 American technology satellite. SURFSAT. SURFSAT-1 was a small satellite built by undergraduate college students and the Jet Propulsion Laboratory to support experiments by NASA's Deep Space Network.

Skipper Russian technology satellite. Aerobraking investigation; satellite provided by Russia, instruments by Utah State University; solar array shorted immediately following deployment and ended mission.

OAST-Flyer American technology satellite. GPS receiver, amateur radio tests; examined effect of solar radiation on satellite explosive devices; deployed from STS 72 1/14/96; retrieved 1/16/96.

TSS The Italian Tethered Satellite System was mounted in the shuttle payload bay and consisted of a 1.6-m-diameter satellite, a conducting tether, and a tether deployment/retrieval system. The system would reel out a satellite on a 22-km long tether. After a failed attempt to deploy it in 1992, there was an inadvertent launch on the second attempt in 1996 when the tether broke.

TiPS American tether technology satellite. The 53 kg satellite consisted of 2 end masses connected by a 4 km tether. NRO (the National Reconnaissance Office) provided funding for the TiPS project.

IAE satellite American technology satellite. Deployed from Spartan 207 5/20/96; test of inflatable antenna technology. Reentered May 22.

PAMS American technology satellite. Passive attitude control technology test. Deployed from shuttle STS-77 on 5/22/96; Re-entered Oct 26.

SAC-B Argentinian solar satellite. SAC-B, an Argentine / US mission, was designed to study solar physics and astrophysics through the examination of solar flares, gamma-ray burst sources and the diffuse soft X-ray cosmic background.

Minisat American technology satellite. The Minisat spacecraft were built for the Spanish space Agency by CASA.

FORTE American earth magnetosphere satellite. FORTE - 'Fast On-orbit Recording of Transient Events' - was a US Los Alamos National Laboratory satellite designed to study natural and artificial radio emissions from the ionosphere.

Mirka German re-entry vehicle technology satellite. German miniature re-entry vehicle attached to exterior of Russian Resurs satellite. After release from Resurs landed in Kazakhstan Oct 23.

Falcon Gold American navigation technology satellite. US Air Force Academy experiment to demonstrate use of GPS navigation in geosynchronous orbit.

MAQSAT European technology satellite. MAQSATs were mass model and technology satellites built by Kayser-Threde, Munich, and lofted during the test flights of the Ariane 5.

YES European tether technology satellite. Young Engineers Satellite sponsored by the European Space Tech.

ETS-7 Japanese rendezvous technology satellite. Hikoboshi. Technology satellite, to accomplish remote automatic rendezvous and docking.

ETS-7 Target Japanese rendezvous technology satellite. Orihime. Attached to Hikoboshi. Docking target for ETS-7.

SNOE American technology satellite.

Kwangmyongsong North Korean communications technology satellite. Payload of the first attempted North Korean satellite launch.

STEX American tether technology satellite. STEX's (Space Technology EXperiments) main equipment was provided by the Naval Research Laboratory.

ARD French re-entry vehicle technology satellite. The ARD was an 80 percent scale model of the Apollo Command Module, and a technology test for a possible International Space Station Crew Rescue Vehicle.

SEDSAT American technology satellite. The SEDSAT micro-satellite was built by the Huntsville, Alabama chapter of SEDS (the Students for the Exploration and Development of Space).

SAC-A Argentinian technology satellite. The Scientific Applications Satellite-S (SAC-A) was a small, ejectable, low cost Argentinian satellite that was launched during the STS-88 Space Shuttle Endeavour mission.

MightySat 1 American military technology satellite.

Elf Russian technology satellite. Study 1998. Elf was a micro satellite platform developed by KB Arsenal. With a platform weight of 80 kg it could provide 20 W power to 30 kg instrument payloads.

ARGOS American ion engine technology satellite. ARGOS was the USAF Space Test Program P91-1 technology satellite by Boeing/Seal Beach.

Sunsat South African technology satellite. Sunsat was built by students at Stellenbosch University, South Africa and carried a small imager and a message relay payload.

Minibus British technology satellite. Study 1999. UoSAT-12 was the first test of the Minibus platform, at 325 kg a larger spacecraft than earlier 50 kg Surrey UoSATs. It carried a mobile radio experiment (MERLION), a GPS receiver, and imaging cameras.

MiniSat-400 British technology satellite. Basic Surrey Minisat bus.

Megsat MegSat, Gruppo Meggiorin, Brescia, Italy. Builder of the first private Italian satellites, Megsats were microsatellites designed to transmit scientific and commercial data. Italian communications technology satellite.

TERRIERS American earth ionosphere satellite.

Starshine American technology satellite. The small Starshine satellite, built by NRL, was to be observed by students as part of an educational exercise.

SACI Brazilian technology satellite. INPE experimental scientific satellites; carried a magnetometer, particle detectors and an atmospheric experiment.

KOMPSAT South Korean communications technology satellite. KOMPSAT was the first joint spacecraft development project for the South Korean aerospace agency KARI (Korea Aerospace Research Institute).

HS 702 American communications satellite bus.

ASUSAT American technology satellite. Arizona State University satellite with an Earth imager and an amateur radio transponder.

FalconSat American technology satellite. The JAWSAT/FalconSat payloads were developed as a joint effort between the Air Force Academy and Weber State University.

JAK American technology satellite, launched, 2000.01.27. Three picosatellites (JAK, Thelma, and Louise), developed by the Artemis team of women undergraduates at Santa Clara University, were deployed from the OPAL satellite.

JAWSAT American technology satellite. The JAWSAT/FalconSat payloads are being developed as a joint effort between the Air Force Academy and Weber State University.

MEMS American communications technology satellite. DARPA/Aerospace Corp. MEMS (Micro Electro-mechanical Systems) were 0.

OCSE American technology satellite. Optical Calibration Sphere Experiment, a 3.5m diameter inflatable sphere built by L'Garde Inc. for calibrating the lasers at the AFRL Starfire Optical Range.

OPAL American technology satellite. Stanford University Orbiting Picosat Automated Launcher.

STENSAT American technology satellite. Picosat built by built by the AMSAT-NA (Amateur Satellite, North America) group, and carried an amateur radio transponder.

IRDT Russian manned rescue spacecraft. Inflatable re-entry and descent technology vehicle designed to return payloads from space to the earth or another planet. Tested three times, with only one partially successful recovery.

Simsat Russian technology satellite. 2 launched, 2000.05.16. 660 kg dummy satellite.

SSTL-10 Surrey Satellite Technology Ltd (SSTL) SNAP-1 Surrey Nanosatellite Applications Platform could accommodate 6-10 kg satellites complete with imagers and propulsion.

MITA Italian technology satellite. MITA was an Italian Space Agency experimental microsatellite built by Carlo Gavazzi Space of Milano and carried the NINA particle detector and an experimental attitude control system.

Rubin German technology microsatellite. Rubin was developed by OHB and students of the Hochschule Bremen.

Cluster 2 European earth magnetosphere satellite.

SA-200 The Spectrum Astro SA-200 satellite bus provided a flexible platform for satellites launched by the Pegasus booster.he Spectrum Astro SA-200 satellite bus provided a flexible platform for satellites launched by the Pegasus booster.

Saudisat Saudi amateur radio communications satellite.

UniSat Italian technology satellite developed by the GAUSS (Gruppo di Astrodinamica dell' Universita degli Studi 'la Sapienza') in Roma.

Munin Swedish technology satellite. Small 6 kg Munin nanosatellite was built by Swedish students in collaboration with the Swedish Institute for Space Physics (IRF) and carried a particle detector, a spectrometer, and an auroral camera.

LDREX Japanese communications technology satellite. Japan's NASDA space agency sponsored the LDREX experimental antenna.

X-37 American unmanned spaceplane. The Boeing X-37 Space Maneuver Vehicle began as a subscale version of a proposed USAF manned 21st Century spaceplane. The smaller-scale X-40 tested some technologies prior to completion of the X-37A. The X-37B was the reusable space vehicle.

Artemis European communications technology satellite. One launch, 2001.07.12. Artemis was a European Space Agency satellite to test new communications technologies.

Picosat American tether technology satellite. Picosat 7/Picosat 8 were ejected from the Mightysat II.1 satellite. The 0.25 kg satellites were connected by a 30 m tether and were deployed a year after launch.

SBD American technology satellite. SBD, the Orbital Corporation Special Bus Design, was a 73 kg test version of an enlarged Microstar bus.

Sapphire American technology satellite. SAPPHIRE (a US DoD-funded microsatellite) was built by Stanford University students and carried experimental infrared horizon sensors, a voice synthesizer and a digital camera.

Kompas Russian earth seismology satellite.

Reflektor Russian technology satellite. The 8 kg Reflektor was built by NII KP in Russia for space debris studies in a joint experiment with the Air Force Research Lab.

DASH 2002 Japanese re-entry vehicle technology satellite. DASH. DASH (Demonstrator of Atmospheric Reentry System and Hypervelocity) was a small secondary payload built by ISAS, the scientific space agency which was to merge with NASDA.

MDS Japanese technology satellite. MDS (Mission Demonstration Satellite) was a technology demonstrator to flight-qualify commercial subsystems.

Kolibri Russian technology satellite. Kolibri was a joint Russian-Australian educational project to allow school children to monitor low frequency waves and particle fluxes in low orbit.

HTSTL Chinese technology satellite.hinese technology satellite. 50 kg test satellite, built by university students, was to have been placed in a 300 km polar orbit.

MEPSI American tether technology satellite. MEPSI (Micro-Electromechanical-based Picosat Satellite Inspection Experiment) consisted of two 1 kg boxes attached to each other by a 15-m tether.

Mu-Labsat Japanese technology satellite. Technology satellite, which released two tiny subsatellites in an experiment to test an onboard tracking imager for inspector satellites.

Yamsat Taiwanese technology satellite. Study 2002. Taiwan's NSPO developed this 1 kg picosatellite at a cost of $289,000 pico-class satellite in collaboration with Stanford University, USA. It was planned for launch on a Russian Dnepr booster in May 2002.

Coriolis American earth sea satellite.

XSS American rendezvous technology satellite.

Cubesat American low-cost nanosatellite bus. Used in dozens of launches.

SATEC Brazilian technology satellite.

Unosat Brazilian technology satellite.

Larets Russian radar calibration satellite. No information publicly released. TASS claimed this was a radar calibration satellite.

SMART-1 European lunar orbiter. Insat 3E. ESA's SMART-1 was to test miniaturization technology while exploring the Moon from orbit.

STSat South Korean technology satellite, built by KAIST.

CX-1 Chinese communications technology satellite.

SERVIS Japanese technology satellite.

OlympicSat Chinese technology satellite. One launch, 2004.04.18, Naxing 1. It was announced in July 2001 would China will launch two small satellites on one rocket. The first would be an engineering test satellite developed by Tsinghua University.

Shiyan Chinese civilian surveillance satellite. The first 'Experiment Satellite', with a mass of 204 kg, was China's first transmission-type small satellite capable of stereo mapping.

SJ-6 Chinese military surveillance satellite constellation. Each launch was said to consist of a primary satellite using the CAST968 bus and a subsatellite built by SAST Shanghai. Five pairs were launched from ?Taiyuan by the CZ-4B launch vehicle into 590 km, 97.7 deg inclination sun synchronous orbits from 2009. Reported to carry systems for optically tracking satellites in orbit. In 2013 SJ-15 was launched from Jiuquan, and SJ-16 from Taiyuan, in very similar but slightly different orbits. These may have been the essor system.

Nanosat 01 Spanish technology satellite. Experimental nanosat built by the Spanish space agency (INTA).

3CSat American technology satellite. 2 launched, 2004.12.21. The Three-Corner Sat mission was to obtain stereo images of clouds and test artificial intelligence software.

MS-1 Ukrainian earth land resources satellite. Ukrainian microsatellite bus that could be equipped with imaging or other scientific or technical equipment.

Universitetskiy Russian technology satellite. Student satellite for radiation studies, ejected from Cosmos 2414.

SLOSHSAT Dutch technology satellite. Test satellite to study the sloshing of fluids in zero gravity, developed by the Netherlands Aerospace Laboratory. Equipped with a tank with 33.5 liters of water and an attitude control system.

Nanosputnik Russian technology satellite. Nanosatellite delivered by Progress M-52 to the International Space Station. 30 cm long, it was released from during a spacewalk on 28 March 2005.

DART American rendezvous technology satellite. Autonomous Rendezvous Technology mission, planned to guide itself to within a few meters of a US satellite.

Kirari Japanese communications satellite. Optical Inter-Orbit Communications Engineering Test Satellite. Its laser communications experiment was be used in with ESA's Artemis geostationary satellite.

Reimei Japanese technology satellite. Plasma Science Technology. INDEX, renamed Reimei ("Dawn") after launch, was a test satellite with new lightweight satellite components, and a demonstration auroral imager payload.

Fotino European tether technology satellite. Study 2005. European re-entry capsule experiment planned to be carried on Foton-M2, but not ready in time for launch.

Safir Iran Iranian technology satellite. Study 2005. Minimum satellite equipped like the first Sputnik with only a transmitter to confirm that it achieved orbit. Planned for launch by the Iranian Shahab-3 launcher in early 2005.

DS2000 Japanese communications satellite bus. Mitsubishi Electric developed the DS2000 standard satellite platform based on a design originally created for the DRTS and ETS-8 platforms for NASDA.

Cute Japanese technology satellite. Student subsatellites.

ST5 American technology satellite. 3 launched, 2006.03.22 (ST5-A) to (ST5-C).

Mitex American military anti-satellite system. 3 launched, 2006.06.21 (USA 187) to (USA 189).

Genesis Pathfinder American technology satellite. One third scale version of the Nautilus inflatable human space habitat module.

Hitsat Japanese technology satellite.

SSSat Japanese technology satellite. Solar sail experiment.

USA 193 American military technology satellite. US shoots down failed USA 193 satellite. Classified NRO mission of uncertain objectives, possibly military observation with a mixed payload.

Tacsat ORS American military surveillance satellite. The Tactical Satellite / Operationally Responsive Satellite program's objective was to demonstrate techniques to dramatically shorten the development time for small satellites.

Guardian American technology satellite. Cancelled 2006. 45% scale version of the Nautilus inflatable human space habitat module, designed to prove the ECS system.

Mesbah Iranian technology satellite. Study 2006. Technology satellite with imaging and communications payloads. Planned as the operational payload of the Iranian Shahab-3 orbital launch vehicle. The satellite would be cube-shaped, 50 cm on a side.

Pehuensat Argentinian technology satellite. Experimental satellite developed by the Universidad Nacional del Comahue and AMSAT-LU. The satellite remained attached to the PSLV's Dual Launch Adapter.

SRE Indian re-entry vehicle technology satellite. Indian experimental subscale Discoverer-type re-entry capsule. A test bed for a projected $ 3 billion Indian project to orbit a manned spacecraft by 2014.

Midstar American technology satellite.

Orbital Express Astro American rendezvous technology satellite. Astro. The active satellite of the Defense Advanced Research Projects Agency's Orbital Express program.

RS-300 American technology satellite bus. Ball Aerospace's RS-300 was a small, low-cost spacecraft aimed at cost-capped principle investigator led missions for Earth or space science.

STPSat American technology satellite. Operational, first launch 2007.03.09.

Zheda Pixing Chinese technology satellite. Experimental microelectronics research picosatellite. Launched 2007.05.25,

Can X Canadian technology satellite. 2 launched, 2008.04.28 (Can X-6 ) and (Can X-2 ).

Compass German technology satellite. One launch, 2008.04.28. Fachhochschule Aachen nanosat.

Delfi Dutch technology satellite. One launch, 2008.04.28. Technical University of Delft nanosat.

SEEDS Japanese technology satellite. One launch, 2008.04.28. Nihon University at Tokyo nanosat.

Nanosail American technology satellite. Launched 2008.08.03,

PreSat American technology satellite. Launched 2008.08.03,

Trailblazer American technology satellite. Launched 2008.08.03,

Omid Iranian technology satellite.ranian technology satellite. First Iranian-built, Iranian-launched satellite.

SSTL-150 German civilian surveillance satellite. Surrey satellite bus, notably used for the RapidEye constellation of five environmental monitoring satellites. Mass of 152 kg including 12 kg of propellant.

Ban Xing Chinese technology satellite. BX-1. Ban Xing (companion satellite) subsatellite released by Shenzhou. If maneuvered away and back to the Shenzhou orbital module after the mission.

Galaxy space station module The Galaxy subscale space station module was scheduled to fly in 2008. It would be twice as large as its Genesis predecessors and represent a 50% scale model of the Sundancer manned inflatable space station.

JAXA SDS Japanese technology satellite. SDS-1. JAXA Small Demonstration Satellite, a microsatellite with a camera, GPS receiver and sun sensor.

Kagayaki Japanese technology satellite. Technology satellite built by Sorun Corporation, Tokyo, with several technology payloads.

Kukai Japanese tether technology satellite. Also named STARS, a Kagawa University picosatellite demonstrating a tethered space robot. It consisted of two tethered box-shaped packages, dubbed Ku and Kai.

SpinSat The Japanese JEM-RMS robot arm extracted the SSIKLOPS (Cyclops) deployer and its attached SpinSat satellite from the Kibo airlock and positioned it for deployment. The Cyclops then ejected SpinSat into orbit. SpinSat was a Naval Research Lab satellite to test new microthrusters for attitude control.

Nose-Cone-Test American re-entry vehicle technology satellite. Suborbital.

Engines: Fastrac. Stages: Fregat.

1950 July 19 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral. LV Family: V-2. Launch Vehicle: V-2.
  • First attempted launch from Cape Canaveral. - . Payload: WAC-Corporal. Nation: USA. Related Persons: von Braun. Program: Bumper. Class: Technology. Type: Navigation technology satellite. Pad abort on 19 July of Bumper No. 8, a German V-2 with a 320 kg Army-JPL Wac Corporal. Launch scrubbed first due to emergency landing of aircraft in the range; second attempt, no lift, main chamber did not ignite..

1955 August 1 - . LV Family: Vanguard. Launch Vehicle: Vanguard.
  • Vanguard selected to launch first US satellite. - . Nation: USA. Related Persons: von Braun. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1. Ad Hoc Committee on Special Capabilities rejects Army/Von Brauns's Project Orbiter (Redstone) and USAF Atlas proposals; selects Navy/Vanguard for first US satellite..

1955 October 7 - . LV Family: Vanguard. Launch Vehicle: Vanguard.
  • Vanguard contract awarded. - . Nation: USA. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1. Prime contract for Project Vanguard awarded the Martin Co..

1956 June - . LV Family: R-7. Launch Vehicle: R-7.
  • Zenit preliminary design complete - . Nation: Russia. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit satellite. Design was original concept of Zenit reconnaisance spacecraft. The effort would later be included in the Vostok program under the name of Zenit..

1957 May 1 - . LV Family: Vanguard. Launch Vehicle: Vanguard.
  • Vanguard suborbital test. - . Nation: USA. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1. Vanguard Test Vehicle (TV-1), a modified Martin Viking first-stage and Vanguard solid-propellant third-stage Grand Central Rocket as second-stage, launched with instrumented nose cone to an altitude of 121 miles and met all test objectives..

1957 October 1 - . LV Family: Vanguard. Launch Vehicle: Vanguard.
  • Vanguard tracking system operational. - . Nation: USA. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1. Project Vanguard world-wide tracking system (minitrack) became operational..

1957 October 4 - . 19:28 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Sputnik 8K71PS.
  • Sputnik 1 - . Payload: PS. Mass: 84 kg (185 lb). Nation: Russia. Agency: MVS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Sputnik 1. Spacecraft: Sputnik 1. Decay Date: 1958-01-03 . USAF Sat Cat: 2 . COSPAR: 1957-Alpha-2. Apogee: 945 km (587 mi). Perigee: 227 km (141 mi). Inclination: 65.0000 deg. Period: 96.10 min.

    First artificial satellite; transmitted signals for 21 days. Launching of first ever artificial satellite of the Earth; physical study of the atmosphere; remained in orbit until January 4, 1958. This event began the space race by galvanizing interest and action on the part of the American public to support an active role in space research, technology, and exploration.


1957 October 9 - . LV Family: Vanguard. Launch Vehicle: Vanguard.
  • Vanguard supported by Eisenhower. - . Nation: USA. Related Persons: Eisenhower. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1.

    President Eisenhower in a White House press release congratulated the Soviet scientists on SPUTNIK I. He gave a brief history of the development of the U.S.-IGY satellite program and pointed to the separation of Project Vanguard from work on ballistic missiles.


1957 December 6 - . 16:44 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18A. Launch Pad: LC18A. LV Family: Vanguard. Launch Vehicle: Vanguard. FAILURE: Vehicle lost thrust and exploded after 2 seconds.. Failed Stage: 1.
  • Vanguard 1A - . Payload: Vanguard Test Satellite. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USN. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1. Decay Date: 1957-12-06 . First US orbital attempt. IGY Vanguard (TV-3), the first with three live stages, failed to launch a test satellite..

1958 February 5 - . 07:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18A. Launch Pad: LC18A. LV Family: Vanguard. Launch Vehicle: Vanguard. FAILURE: Control system malfunction - control lost after 57 sec.. Failed Stage: G.
  • Vanguard 1B - . Payload: Vanguard Test Satellite. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USN. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1. Decay Date: 1958-02-05 . Apogee: 6.00 km (3.70 mi). Trial firing of IGY Vanguard (TV-3Bu) satellite..

1958 March 17 - . 12:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18A. Launch Pad: LC18A. LV Family: Vanguard. Launch Vehicle: Vanguard.
  • Vanguard 1 - . Payload: Vanguard 1C / Vanguard Test Satellite. Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: USN. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1. USAF Sat Cat: 5 . COSPAR: 1958-Beta-2. Apogee: 3,868 km (2,403 mi). Perigee: 654 km (406 mi). Inclination: 34.2000 deg. Period: 133.20 min. Transmitted pear-shaped earth data. Life expectancy of perhaps a 1,000 years. The satellite had a mass of 1.6 kg and a diameter of 175 cm..

1958 April 29 - . 02:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18A. Launch Pad: LC18A. LV Family: Vanguard. Launch Vehicle: Vanguard. FAILURE: Third Stage failed to ignite.. Failed Stage: 3.
  • Vanguard 2A - . Payload: X-ray-environmental satellite. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USN. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1. Decay Date: 1958-04-28 . Apogee: 550 km (340 mi).

1958 July 25 - . Launch Site: Santa Barbara Channel DZ. Launch Pad: 34.2 N x 120.0 W. Launch Platform: F4D-1 747. LV Family: Project Pilot. Launch Vehicle: Project Pilot. FAILURE: Radio contact lost; possibly reached orbit.. Failed Stage: U.
  • Pilot 1 - . Payload: Diagnostic Payload 1. Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Pilot. Spacecraft: Pilot. Decay Date: 1958-07-25 . Apogee: 12 km (7 mi). Air dropped in Santa Barbara Channel DZ..

1958 August 12 - . Launch Site: Santa Barbara Channel DZ. Launch Pad: 34.2 N x 120.0 W. Launch Platform: F4D-1 747. LV Family: Project Pilot. Launch Vehicle: Project Pilot. FAILURE: Vehicle exploded at ignition.. Failed Stage: 1.
  • Pilot 2 - . Payload: Diagnostic Payload 2. Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Pilot. Spacecraft: Pilot. Decay Date: 1958-08-12 . Apogee: 12 km (7 mi). Air dropped in Santa Barbara Channel DZ..

1958 August 18 - . Launch Site: Baikonur. Launch Complex: Baikonur. LV Family: R-7. Launch Vehicle: Vostok-L 8K72.
  • Luna launch delayed. - . Nation: Russia. Class: Technology. Type: Navigation technology satellite.

    Planned August launch rescheduled after failure of American lunar probe on August 17. Inability to complete final tests of the new engines and malfunctions during pre-launch preparations indicated a lot of work had to be done on the new launch vehicle before the first launch could be attempted.


1958 August 22 - . Launch Site: Santa Barbara Channel DZ. Launch Pad: 34.2 N x 120.0 W. Launch Platform: F4D-1 747. LV Family: Project Pilot. Launch Vehicle: Project Pilot. FAILURE: Radio contact lost; possibly reached orbit.. Failed Stage: U.
  • Pilot 3 - . Payload: Diagnostic Payload 3. Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Pilot. Spacecraft: Pilot. Decay Date: 1958-08-22 . Apogee: 0 km (0 mi). Air dropped in Santa Barbara Channel DZ..

1958 August 25 - . Launch Site: Santa Barbara Channel DZ. Launch Pad: 34.2 N x 120.0 W. Launch Platform: F4D-1 747. LV Family: Project Pilot. Launch Vehicle: Project Pilot. FAILURE: Vehicle exploded after 0.75sec.. Failed Stage: 1.
  • Pilot 4 - . Payload: Radiation Payload 1. Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Pilot. Spacecraft: Pilot. Decay Date: 1958-08-25 . Apogee: 12 km (7 mi). Air dropped in Santa Barbara Channel DZ..

1958 August 26 - . Launch Site: Santa Barbara Channel DZ. Launch Pad: 34.2 N x 120.0 W. Launch Platform: F4D-1 747. LV Family: Project Pilot. Launch Vehicle: Project Pilot. FAILURE: Stage failed to ignite, vehicle fell into Pacific.. Failed Stage: 1.
  • Pilot 5 - . Payload: Radiation Payload 2. Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Pilot. Spacecraft: Pilot. Decay Date: 1958-08-26 . Apogee: 12 km (7 mi). Air dropped in Santa Barbara Channel DZ..

1958 August 28 - . Launch Site: Santa Barbara Channel DZ. Launch Pad: 34.2 N x 120.0 W. Launch Platform: F4D-1 747. LV Family: Project Pilot. Launch Vehicle: Project Pilot. FAILURE: One first stage motor failed to ignite, causing structural failure.. Failed Stage: 1.
  • Pilot 6 - . Payload: Radiation Payload 3. Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Pilot. Spacecraft: Pilot. Decay Date: 1958-08-28 . Apogee: 12 km (7 mi). Air dropped in Santa Barbara Channel DZ..

1958 October 23 - . 03:21 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC5. LV Family: Redstone. Launch Vehicle: Jupiter C. FAILURE: Upper stages separated prior to burnout. Structural failure after 149 sec due to vibration disturbances generated by the spinning payload.. Failed Stage: 2.
  • Beacon 1 - . Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: NASA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Beacon 1. Spacecraft: Beacon 1. Decay Date: 1958-10-22 .

    NASA¾with the Army as executive agent¾attempted to launch a 12-foot-diameter inflatable satellite of micro-thin plastic covered with aluminum foil known as BEACON. Launched from AMR by a Juno I¾a modified Redstone, the payload prematurely separated prior to booster burnout.


1958 December 18 - . 23:02 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC11. LV Family: Atlas. Launch Vehicle: Atlas B.
  • Score - . Mass: 70 kg (154 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Score. Spacecraft: Score. Decay Date: 1959-01-21 . USAF Sat Cat: 10 . COSPAR: 1958-Zeta-1. Apogee: 1,484 km (922 mi). Perigee: 185 km (114 mi). Inclination: 32.3000 deg. Period: 101.50 min.

    Signal Communication by Orbiting Relay Equipment; first commsat; transmitted taped messages for 13 days. Project Score, Atlas rocket placed in orbit carrying communications equipment which relayed President Eisenhower's Christmas message to the world from outer space. (AF Ballistic Missiles Program Status Report.)


1959 August 15 - . 00:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC26B. LV Family: Jupiter. Launch Vehicle: Juno II. FAILURE: First stage shut down too early; no attitude control for upper stages.. Failed Stage: 1.
  • Beacon 2 - . Mass: 5.00 kg (11.00 lb). Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Beacon 1. Spacecraft: Beacon 1. Decay Date: 1959-08-14 .

1960 March 17 - . LV Family: Vanguard. Launch Vehicle: Vanguard.
  • Vanguard second anniversary. - . Nation: USA. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1. VANGUARD I still in orbit and transmitting on its second anniversary after traveling 131,318,211 miles. NASA reported that VANGUARD I orbit was being altered by solar pressure..

1960 August 12 - . 09:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.
  • Echo 1 - . Payload: A-11. Mass: 76 kg (167 lb). Nation: USA. Agency: NASA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Echo. Spacecraft: Echo. Decay Date: 1968-05-24 . USAF Sat Cat: 49 . COSPAR: 1960-Iota-1. Apogee: 2,157 km (1,340 mi). Perigee: 966 km (600 mi). Inclination: 47.3000 deg. Period: 117.30 min.

    A Thor/Delta was launched from Cape Canaveral carrying NASA's Echo I, the first passive communications satellite to be placed into orbit. Balloon; passively relayed TV and voice transmissions. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).


1960 October 4 - . 17:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar.
  • Courier 1B - . Mass: 230 kg (500 lb). Nation: USA. Agency: US Army. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Courier. Spacecraft: Courier. USAF Sat Cat: 58 . COSPAR: 1960-Nu-1. Apogee: 1,214 km (754 mi). Perigee: 967 km (600 mi). Inclination: 28.3000 deg. Period: 107.10 min. Experimental communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1961 March 17 - . LV Family: Vanguard. Launch Vehicle: Vanguard.
  • Vanguard third anniversary. - . Nation: USA. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vanguard 1. Spacecraft: Vanguard 1.

    Vanguard I completed third year in orbit and was still transmitting. Vanguard I provided much useful data on orbits, including the slight pear-shape of the Earth and the effect of solar pressure. Vanguard also provided the second stage for the Able, Delta, and Able-Star, as well as the third stage of Scout, pioneering solid-propellant stages used in Polaris and Minuteman.


1961 October 27 - . 16:30 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: First stage failed.. Failed Stage: 1.
  • DS-2 s/n 1 - . Payload: DS-1. Mass: 300 kg (660 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-1. Failed first attempt to launch a DS-1 technology test version of the DS satellite atop a Cosmos 63S1 small launch vehicle. The boster didn't reach orbital velocity due to the failure of an acceleration integrator in the velocity regulation control..

1961 October 29 - .
  • Mercury-Scout launch announced. - . Nation: USA. Program: Mercury. Class: Technology. Type: Tracking network technology satellite. Spacecraft Bus: Radio Test Spacecraft. Spacecraft: Radio Test Spacecraft. NASA announced that first Mercury-Scout launch to verify the readiness of the worldwide Mercury tracking network would take place at Atlantic Missile Range..

1961 November 1 - . 15:32 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Scout. Launch Vehicle: Blue Scout II. FAILURE: Failure. Failed Stage: U.
  • Mercury MS-1 - . Payload: Radio Test Spacecraft. Nation: USA. Agency: USAF. Program: Mercury. Class: Technology. Type: Tracking network technology satellite. Spacecraft Bus: Radio Test Spacecraft. Spacecraft: Radio Test Spacecraft.

    Small satellite was to have verified the readiness of the worldwide Mercury tracking network. An attempt was made to launch Mercury-Scout 1 (MS-1) into orbit with a communications package further to qualify the radar tracking of the Mercury global network prior to manned orbital flight. Shortly after lift-off, the launch vehicle developed erratic motions and attending high aerodynamic loads, and was destroyed by the Range Safety Officer after 43 seconds of flight. No further attempts were planned. The Mercury-Atlas 4 (MA-4) mission and the successful Mercury-Atlas 5 (MA-5), flown on November 29, 1961, disclosed that the network met all requirements.


1961 November 15 - . 22:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar.
  • TRAAC - . Mass: 109 kg (240 lb). Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: TRAAC. Spacecraft: TRAAC. USAF Sat Cat: 205 . COSPAR: 1961-A-Eta-2. Apogee: 1,107 km (687 mi). Perigee: 956 km (594 mi). Inclination: 32.4000 deg. Period: 105.80 min. Transit Research and Attitude Control. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1961 December 21 - . 12:30 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: Second stage failed 354 seconds after launch.. Failed Stage: 2.
  • DS-1 s/n 1 - . Payload: DS-1. Mass: 300 kg (660 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-1.

    Second attempted launch of Cosmos 63S1 small launch vehicle 2LK with a DS-1 satgellite. This time the new second stage failed. The oxidiser was exhausted before orbital velocity could be reached due to uncontrolled pumping of liquid oxygen into the combustion chamber. The upper stage and satellite impacted in the Kurile Islands. An Expert Commission headed by Ustinov was convened to review the program.


1962 March 16 - . 11:59 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 1 - . Payload: DS-2 s/n 2. Mass: 47 kg (103 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-2. Completed Operations Date: 1962-03-26 . Decay Date: 1962-05-25 . USAF Sat Cat: 266 . COSPAR: 1962-Theta-1. Apogee: 649 km (403 mi). Perigee: 207 km (128 mi). Inclination: 49.0000 deg. Period: 93.10 min.

    After five months of further work and tests to improve the reliability of the second stage, Yangel's team felt it was ready to again attempt a launch of the 63S1 booster. 63S1 s/n 6LK put a DS-2 satellite into orbit, which conducted studies of the ionosphere. This was the first successful launch of the Kosmos 63S1 launch vehicle. A decision was made after two unsuccessful launches of the DS-1 to create a simplified DS-2 spacecraft based on the equipment and structural elements of DS-1 spacecraft. The cylindrical section for mission avionics was completely omitted.


1962 April 6 - . 17:15 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 2 - . Payload: 1MS s/n 1. Mass: 285 kg (628 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 1MS. Decay Date: 1963-08-20 . USAF Sat Cat: 269 . COSPAR: 1962-Iota-1. Apogee: 1,485 km (922 mi). Perigee: 207 km (128 mi). Inclination: 49.0000 deg. Period: 101.80 min. Radiation, cosmic ray data. Decay date suspect Investigation of the upper atmosphere and outer space; development of elements in the design of space craft. .

1962 April 24 - . 04:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 3 - . Payload: 2MS s/n 1. Mass: 330 kg (720 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 2MS. Decay Date: 1962-10-17 . USAF Sat Cat: 281 . COSPAR: 1962-Nu-1. Apogee: 707 km (439 mi). Perigee: 216 km (134 mi). Inclination: 49.0000 deg. Period: 93.80 min. Cosmic ray, radiation data. Investigation of the upper atmosphere and outer space; development of elements in the design of space craft. .

1962 May 28 - . 03:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 5 - . Payload: 2MS s/n 2. Mass: 280 kg (610 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 2MS. Decay Date: 1963-05-02 . USAF Sat Cat: 297 . COSPAR: 1962-Upsilon-1. Apogee: 1,578 km (980 mi). Perigee: 192 km (119 mi). Inclination: 49.1000 deg. Period: 102.60 min. Monitored artificial radiation. Investigation of the upper atmosphere and outer space; development of elements in the design of space craft. .

1962 August 31 - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA3. LV Family: Scout. Launch Vehicle: Scout X-3A. FAILURE: Late stage 3 ignition.. Failed Stage: 3.
  • Reentry 2 - . Nation: USA. Agency: NASA. Class: Technology. Type: Re-entry test vehicle. Decay Date: 1962-08-31 . Apogee: 217 km (134 mi).

1962 October 20 - . 04:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 11 - . Payload: DS-A1 s/n 1. Mass: 315 kg (694 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1962-10-28 . Decay Date: 1964-05-18 . USAF Sat Cat: 441 . COSPAR: 1962-B-Theta-1. Apogee: 858 km (533 mi). Perigee: 240 km (140 mi). Inclination: 48.9000 deg. Period: 95.60 min.

    Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.


1962 October 25 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: Launch vehicle failed to orbit - unknown cause.. Failed Stage: U.
  • 1MS - . Mass: 285 kg (628 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 1MS.

1962 December 13 - . 23:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta B.
  • Relay 1 - . Payload: NASA A-15. Mass: 78 kg (171 lb). Nation: USA. Agency: NASA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Relay. Spacecraft: Relay. USAF Sat Cat: 503 . COSPAR: 1962-B-Upsilon-1. Apogee: 7,440 km (4,620 mi). Perigee: 1,319 km (819 mi). Inclination: 47.5000 deg. Period: 185.10 min. Communications satellite technology tests. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1963 February 14 - . 05:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta B.
  • Syncom I; Syncom 1 - . Payload: Syncom 1. Mass: 39 kg (85 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Syncom. Spacecraft: Syncom. Completed Operations Date: 1963-02-14 . USAF Sat Cat: 553 . COSPAR: 1963-004A. Apogee: 36,739 km (22,828 mi). Perigee: 34,392 km (21,370 mi). Inclination: 33.3000 deg. Period: 1,425.50 min.

    Experimental commsat; lost contact following orbital injection. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Four score. Last known longitude (10 March 1987) 172.58 deg E drifting at 2.429 deg E per day.


1963 April 13 - . 11:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 14 - . Payload: DS-U / Omega-1. Mass: 347 kg (765 lb). Nation: Russia. Agency: MO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: Omega. Decay Date: 1963-08-29 . USAF Sat Cat: 567 . COSPAR: 1963-010A. Apogee: 410 km (250 mi). Perigee: 250 km (150 mi). Inclination: 48.9000 deg. Period: 91.10 min. Tested VNIIEM electric gyrodyne satellite orientation technology..

1963 May 9 - . 20:06 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3E. LV Family: Atlas. Launch Vehicle: Atlas Agena B.
  • TRS 2 - . Payload: ERS 5. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: TRS. Spacecraft: TRS. Decay Date: 1973-07-31 . USAF Sat Cat: 579 . COSPAR: 1963-014B. Apogee: 4,902 km (3,045 mi). Perigee: 2,269 km (1,409 mi). Inclination: 87.2000 deg. Period: 165.00 min. Solar cells damage data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • TRS 3 - . Payload: ERS 6. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: TRS. Spacecraft: TRS. USAF Sat Cat: 608 . COSPAR: 1963-014C. Apogee: 3,691 km (2,293 mi). Perigee: 3,591 km (2,231 mi). Inclination: 87.3000 deg. Period: 166.40 min. Solar cells damage data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • Dash 1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: Dash. Spacecraft: Dash. USAF Sat Cat: 589 . COSPAR: 1963-014D. Apogee: 3,724 km (2,313 mi). Perigee: 3,558 km (2,210 mi). Inclination: 87.3000 deg. Period: 166.30 min.

1963 May 22 - . 03:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 17 - . Payload: DS-A1 s/n 2. Mass: 322 kg (709 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1963-05-30 . Decay Date: 1965-06-02 . USAF Sat Cat: 580 . COSPAR: 1963-017A. Apogee: 658 km (408 mi). Perigee: 251 km (155 mi). Inclination: 48.9000 deg. Period: 93.70 min.

    Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.


1963 June 1 - . 02:50 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: First stage failed 4 seconds after launch.. Failed Stage: 1.
  • DS-MT s/n 1 - . Payload: DS-MT. Mass: 340 kg (740 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MT. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays..

1963 June 15 - . 14:29 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena D.
  • Lofti 2A - . Mass: 26 kg (57 lb). Nation: USA. Agency: USN. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Lofti. Spacecraft: Lofti. Decay Date: 1963-07-18 . USAF Sat Cat: 601 . COSPAR: 1963-021B. Apogee: 876 km (544 mi). Perigee: 170 km (100 mi). Inclination: 69.9000 deg. Period: 95.10 min. VLF experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1963 July 19 - . 03:51 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3E. LV Family: Atlas. Launch Vehicle: Atlas Agena B.
  • TRS 4 - . Payload: ERS 9. Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: TRS. Spacecraft: TRS. USAF Sat Cat: 635 . COSPAR: 1963-030B. Apogee: 3,736 km (2,321 mi). Perigee: 3,661 km (2,274 mi). Inclination: 88.4000 deg. Period: 167.80 min. Radiation damage data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • Dash 2 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: Dash. Spacecraft: Dash. Decay Date: 1971-04-12 . USAF Sat Cat: 624 . COSPAR: 1963-030D. Apogee: 3,839 km (2,385 mi). Perigee: 3,573 km (2,220 mi). Inclination: 88.5000 deg. Period: 168.00 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1963 July 26 - . 14:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta B.
  • Syncom 2 - . Mass: 39 kg (85 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Syncom. Spacecraft: Syncom. Completed Operations Date: 1969-04-01 . USAF Sat Cat: 634 . COSPAR: 1963-031A. Apogee: 35,891 km (22,301 mi). Perigee: 35,891 km (22,301 mi). Inclination: 32.7000 deg. Period: 1,441.50 min.

    NASA's Syncom II synchronous communications satellite was placed in orbit by a Thor/Delta launched from Cape Canaveral. Experimental commsat; 1st geosynchronous satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 55 deg W in 1963; 26 deg W in 1965. Last known longitude (19 July 1995) 68.47 deg E drifting at 0.089 deg W per day.


1963 August 22 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: First stage failed.. Failed Stage: 1.
  • DS-A1 s/n 3 - . Payload: DS-A1. Mass: 30 kg (66 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1.

    Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.


1963 October 17 - . 02:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC13. LV Family: Atlas. Launch Vehicle: Atlas Agena D.
  • TRS 5 - . Payload: ERS 12. Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: TRS. Spacecraft: TRS. Decay Date: 1963-06-30 . USAF Sat Cat: 675 . COSPAR: 1963-039B. Apogee: 102,372 km (63,610 mi). Perigee: 953 km (592 mi). Inclination: 35.9000 deg. Period: 2,319.40 min. Decay date suspect Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

1963 October 24 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: Second stage failed 353 seconds after launch.. Failed Stage: 2.
  • DS-A1 s/n 4 - . Payload: DS-A1. Mass: 30 kg (66 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1.

    Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.


1963 December 13 - . 14:15 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 23 - . Payload: DS-U / Omega-1. Mass: 347 kg (765 lb). Nation: Russia. Agency: MO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: Omega. Decay Date: 1964-03-27 . USAF Sat Cat: 707 . COSPAR: 1963-050A. Apogee: 560 km (340 mi). Perigee: 232 km (144 mi). Inclination: 48.9000 deg. Period: 92.40 min. Tested VNIIEM electric gyrodyne satellite orientation technology..

1964 January 19 - . 10:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D.
  • OPS 3367A - . Payload: DAPP / OPS 3367 A. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: AFP-43. Spacecraft: AFP-43. USAF Sat Cat: 734 . COSPAR: 1964-002B. Apogee: 810 km (500 mi). Perigee: 789 km (490 mi). Inclination: 99.0000 deg. Period: 100.90 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • OPS 3367B - . Payload: DAPP / OPS 3367 B. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: AFP-43. Spacecraft: AFP-43. USAF Sat Cat: 735 . COSPAR: 1964-002C. Apogee: 815 km (506 mi). Perigee: 791 km (491 mi). Inclination: 99.0000 deg. Period: 100.90 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1964 January 21 - . 21:14 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta B.
  • Relay 2 - . Payload: Relay B. Mass: 78 kg (171 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Relay. Spacecraft: Relay. USAF Sat Cat: 737 . COSPAR: 1964-003A. Apogee: 7,540 km (4,680 mi). Perigee: 1,961 km (1,218 mi). Inclination: 46.4000 deg. Period: 194.70 min. Experimental commsat. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1964 January 25 - . 13:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena B.
  • Echo 2 - . Payload: Echo C A-12. Mass: 256 kg (564 lb). Nation: USA. Agency: NASA Langley. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Echo. Spacecraft: Echo 2. Decay Date: 1969-06-07 . USAF Sat Cat: 740 . COSPAR: 1964-004A. Apogee: 1,315 km (817 mi). Perigee: 1,030 km (640 mi). Inclination: 81.5000 deg. Period: 108.80 min. Passive commsat; balloon; 1st joint US/USSR space mission. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1964 January 29 - . 16:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Saturn I.
  • Saturn 5 - . Payload: Saturn-SA 5. Mass: 17,100 kg (37,600 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Class: Technology. Type: Re-entry test vehicle. Spacecraft Bus: Jupiter nose cone. Spacecraft: Jupiter nose cone. Decay Date: 1966-04-30 . USAF Sat Cat: 744 . COSPAR: 1964-005A. Apogee: 740 km (450 mi). Perigee: 274 km (170 mi). Inclination: 31.4000 deg. Period: 94.80 min.

    First first mission of Block II Saturn with two live stages. SA-5, a vehicle development flight, was launched from Cape Kennedy Complex 37B at 11:25:01.41, e.s.t. This was the first flight of the Saturn I Block II configuration (i.e., lengthened fuel tanks in the S-1 and stabilizing tail fins), as well as the first flight of a live (powered) S-IV upper stage. The S-1, powered by eight H-1 engines, reached a full thrust of over 680,400 kilograms (1.5 million pounds) the first time in flight. The S-IV's 41,000 kilogram (90,000-pound-thrust cluster of six liquid-hydrogen RL-10 engines performed as expected. The Block II SA-5 was also the first flight test of the Saturn I guidance system.


1964 March 18 - . 15:07 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 26 - . Payload: DS-MG s/n 1. Mass: 365 kg (804 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MG. Completed Operations Date: 1964-04-01 . Decay Date: 1964-09-28 . USAF Sat Cat: 766 . COSPAR: 1964-013A. Apogee: 376 km (233 mi). Perigee: 268 km (166 mi). Inclination: 48.9000 deg. Period: 91.00 min. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also obtained radiation data..

1964 June 6 - . 06:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 31 - . Payload: DS-MT s/n 2. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MT. Completed Operations Date: 1964-06-23 . Decay Date: 1964-10-20 . USAF Sat Cat: 803 . COSPAR: 1964-028A. Apogee: 485 km (301 mi). Perigee: 221 km (137 mi). Inclination: 48.9000 deg. Period: 91.70 min. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays..

1964 June 18 - . 04:56 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D.
  • OPS 4467A - . Payload: DAPP / OPS 4467 A. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: AFP-43. Spacecraft: AFP-43. USAF Sat Cat: 812 . COSPAR: 1964-031A. Apogee: 820 km (500 mi). Perigee: 812 km (504 mi). Inclination: 99.8000 deg. Period: 101.20 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • OPS 4467B - . Payload: DAPP / OPS 4467 B. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: AFP-43. Spacecraft: AFP-43. USAF Sat Cat: 813 . COSPAR: 1964-031B. Apogee: 822 km (510 mi). Perigee: 814 km (505 mi). Inclination: 99.8000 deg. Period: 101.30 min.

1964 July 17 - . 08:22 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC13. LV Family: Atlas. Launch Vehicle: Atlas Agena D.
  • TRS 6 - . Payload: ERS 13. Mass: 12 kg (26 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: TRS. Spacecraft: TRS. Decay Date: 1966-07-01 . USAF Sat Cat: 838 . COSPAR: 1964-040C. Apogee: 104,665 km (65,035 mi). Perigee: 217 km (134 mi). Inclination: 36.7000 deg. Period: 2,366.20 min. Decay date suspect Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

1964 August 19 - . 12:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta D.
  • Syncom 3 - . Payload: Syncom C. Mass: 39 kg (85 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Syncom. Spacecraft: Syncom. Completed Operations Date: 1974-12-29 . USAF Sat Cat: 858 . COSPAR: 1964-047A. Apogee: 35,792 km (22,240 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.1000 deg. Period: 1,436.20 min.

    NASA's Syncom III synchronous communi- cations satellite was launched into orbit by a Thrust Augmented Thor/Delta (TAD) launch vehicle in its first use as a space booster. By the end of August, Experimental commsat; carried Star Flash experiment. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 64 deg W in 1964; 180 deg E in 1964; 25 deg W in 1965; 165 deg E in 1966-1969. Last known longitude (6 December 1974) 6.08 deg W drifting at 0.188 deg W per day.


1964 October 24 - . 05:16 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar Mayak-2. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 49 - . Payload: DS-MG s/n 2. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MG. Completed Operations Date: 1964-11-09 . Decay Date: 1965-08-21 . USAF Sat Cat: 913 . COSPAR: 1964-069A. Apogee: 472 km (293 mi). Perigee: 260 km (160 mi). Inclination: 48.9000 deg. Period: 91.90 min. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also studied measured Earth infrared and ultraviolet flux..

1964 December 1 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: Payload shroud did not separate.. Failed Stage: U.
  • DS-2 s/n 2 - . Payload: DS-2. Mass: 315 kg (694 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-2. A decision was made after two unsuccessful launches of the DS-1 to create a simplified DS-2 spacecraft based on the equipment and structural elements of DS-1 spacecraft. The cylindrical section for mission avionics was completely omitted..

1964 December 9 - . 23:02 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 51 - . Payload: DS-MT s/n 3. Mass: 350 kg (770 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MT. Completed Operations Date: 1965-01-04 . Decay Date: 1965-11-14 . USAF Sat Cat: 947 . COSPAR: 1964-080A. Apogee: 537 km (333 mi). Perigee: 258 km (160 mi). Inclination: 48.8000 deg. Period: 92.60 min. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays, and measured the luminosity of the starry sky..

1965 January 30 - . 09:36 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 53 - . Payload: DS-A1 s/n 5. Mass: 310 kg (680 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1965-02-09 . Decay Date: 1966-08-12 . USAF Sat Cat: 983 . COSPAR: 1965-006A. Apogee: 1,172 km (728 mi). Perigee: 221 km (137 mi). Inclination: 48.7000 deg. Period: 98.70 min.

    Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.


1965 February 11 - . 15:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC20. LV Family: Titan. Launch Vehicle: Titan IIIA.
  • LES 1 - . Mass: 31 kg (68 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: LES. Spacecraft: LES. USAF Sat Cat: 1002 . COSPAR: 1965-008C. Apogee: 2,809 km (1,745 mi). Perigee: 2,783 km (1,729 mi). Inclination: 32.1000 deg. Period: 145.80 min.

    Titan IIIA, Vehicle #3, was launched from Cape Canaveral. In a maneuverability test involving three separate orbits, the Transtage and two satellites were successfully placed into their programmed orbits. The primary objective of the mission was the triple ignition of the Transtage engine that was required for the three separate orbits. When it placed the Lincoln Experimental Satellite (LES-1) into orbit, the vehicle became the first Titan III to inject an operational payload into orbit. Lincoln Experimental Satellite; communications experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).


1965 February 20 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: First stage failed 64 seconds after launch.. Failed Stage: 1.
  • DS-A1 s/n 6 - . Payload: DS-A1. Mass: 30 kg (66 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1.

    Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.


1965 April 3 - . 21:24 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D.
  • Snapshot - . Payload: SNAP 10A / Agena D / OPS 4682. Mass: 440 kg (970 lb). Nation: USA. Agency: AEC, USAF. Class: Technology. Type: Ion engine technology satellite. Spacecraft Bus: Snapshot. Spacecraft: Snapshot. USAF Sat Cat: 1314 . COSPAR: 1965-027A. Apogee: 1,314 km (816 mi). Perigee: 1,270 km (780 mi). Inclination: 90.3000 deg. Period: 111.40 min.

    The 6595th Aerospace Test Wing launched an Atlas/Agena which boosted the Atomic Energy Commission (AEC) Snapshot spacecraft into orbit carrying the SNAP-10A satellite nuclear power supply experiment. The onboard nuclear reactor was used to provide electric power for an ion engine, marking the first attempt to test a reactor-ion system in orbit. Only nuclear reactor ever orbited by the United States. The SNAP-10A reactor provided electrical power for an 8.5 mN ion engine using cesium propellant. The engine was shut off after one hour of operation when high-voltage spikes created electromagnetic interference with the satellite's attitude control system sensors. The reactor continued in operation, generating 39 kWt and more than 500 watts of electrical power for 43 days before the spacecraft telemetry failed.


1965 May 6 - . 15:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC20. LV Family: Titan. Launch Vehicle: Titan IIIA.
  • LES 2 - . Mass: 37 kg (81 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: LES. Spacecraft: LES. USAF Sat Cat: 1360 . COSPAR: 1965-034B. Apogee: 14,810 km (9,200 mi). Perigee: 2,771 km (1,721 mi). Inclination: 32.2000 deg. Period: 309.90 min.

    The fourth Titan IIIA flight test missile (Vehicle #6) was launched from Complex 20 at Cape Canaveral in a maneuverability test for the Transtage. The primary aim was for the Transtage engine to accomplish four separate ignitions, something never before attempted. In the process of successfully completing its four programmed ignitions and burns, the Transtage placed two satellites into orbit - a Lincoln Experimental Satellite (LES-2) and a hollow aluminum radar calibration sphere (LCS-1). By completing its assigned tasks, the Transtage extended the capabilities of the Titan IIIA beyond it's specific requirements. Because of this highly productive mission, the planned fifth Titan IIIA (Vehicle 7/4) launch was cancelled and the booster was converted to a Titan IIIC configuration. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).


1965 July 2 - . 06:30 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 63S1.
  • Cosmos 70 - . Payload: DS-A1 s/n 7. Mass: 250 kg (550 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1965-07-12 . Decay Date: 1966-12-18 . USAF Sat Cat: 1431 . COSPAR: 1965-052A. Apogee: 1,176 km (730 mi). Perigee: 223 km (138 mi). Inclination: 48.8000 deg. Period: 98.80 min.

    Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.


1965 October 19 - . 05:44 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 11K63.
  • Cosmos 93 - . Payload: DS-U2-V s/n 1. Mass: 305 kg (672 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Military technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-V. Completed Operations Date: 1965-12-16 . Decay Date: 1966-01-03 . USAF Sat Cat: 1629 . COSPAR: 1965-084A. Apogee: 513 km (318 mi). Perigee: 216 km (134 mi). Inclination: 48.4000 deg. Period: 91.80 min. Military technology development satellite - mission still classified..

1965 November 4 - . 05:31 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 11K63.
  • Cosmos 95 - . Payload: DS-U2-V s/n 2. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Military technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-V. Completed Operations Date: 1965-11-04 . Decay Date: 1966-01-18 . USAF Sat Cat: 1706 . COSPAR: 1965-088A. Apogee: 521 km (323 mi). Perigee: 211 km (131 mi). Inclination: 48.4000 deg. Period: 91.90 min. Military technology development satellite - mission still classified..

1965 November 26 - . 12:14 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 11K63.
  • Cosmos 97 - . Payload: DS-U2-M s/n 1. Mass: 267 kg (588 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-M. Completed Operations Date: 1966-01-23 . Decay Date: 1967-04-02 . USAF Sat Cat: 1777 . COSPAR: 1965-095A. Apogee: 2,144 km (1,332 mi). Perigee: 214 km (132 mi). Inclination: 48.4000 deg. Period: 108.90 min. Development tests of atomic clocks..

1965 November 26 - . 14:47 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Diamant A.
  • Asterix 1 - . Payload: A 1. Mass: 42 kg (92 lb). Nation: France. Agency: CNES. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Asterix. Spacecraft: Asterix. USAF Sat Cat: 1778 . COSPAR: 1965-096A. Apogee: 1,697 km (1,054 mi). Perigee: 527 km (327 mi). Inclination: 34.3000 deg. Period: 107.50 min. First French satellite. French scientific satellite 'A-I'. Launched from Hammaguir (Algeria) in rder to test the 'Diamant' launching vehicle for the first time..

1965 December 21 - . 14:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. LV Family: Titan. Launch Vehicle: Titan IIIC.
  • LES 4 - . Mass: 52 kg (114 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: LES. Spacecraft: LES. Decay Date: 1977-08-01 . USAF Sat Cat: 1870 . COSPAR: 1965-108B. Apogee: 33,632 km (20,897 mi). Perigee: 189 km (117 mi). Inclination: 26.6000 deg. Period: 589.20 min. Lincoln Experimental Satellite; experimental commsat; transmitted in X-band. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • LES 3 - . Mass: 16 kg (35 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: LES. Spacecraft: LES. Decay Date: 1968-04-06 . USAF Sat Cat: 1941 . COSPAR: 1965-108D. Apogee: 4,829 km (3,000 mi). Perigee: 267 km (165 mi). Inclination: 26.5000 deg. Period: 139.90 min. Radio signal source for commsat tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1965 December 28 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: First stage failed.. Failed Stage: 1.
  • DS-K-40 s/n 1 - . Payload: DS-K-40. Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-K-40. Development of systems for the later operational Tselina satellites..

1966 February 21 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 63S1. FAILURE: First stage failed 83 seconds after launch.. Failed Stage: 1.
  • DS-K-40 s/n 2 - . Payload: DS-K-40. Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-K-40. Development of systems for the later operational Tselina satellites..

1966 June 16 - . 14:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. LV Family: Titan. Launch Vehicle: Titan IIIC.
  • GGTS 1 - . Mass: 47 kg (103 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Gravity gradient technology satellite. Spacecraft Bus: GGTS. Spacecraft: GGTS. USAF Sat Cat: 2207 . COSPAR: 1966-053A. Apogee: 33,858 km (21,038 mi). Perigee: 33,663 km (20,917 mi). Inclination: 4.2000 deg. Period: 1,334.00 min. Gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1966 September 26 - . 02:58 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. FAILURE: Fourth stage attitude control failed.. Failed Stage: 4.
  • Ohsumi 1 - . Payload: L-4S-1. Mass: 26 kg (57 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Ohsumi. Spacecraft: Ohsumi. Decay Date: 1966-09-26 . Apogee: 400 km (240 mi).

1966 November 3 - . 13:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan IIIC.
  • OV4-03 - . Mass: 109 kg (240 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: OV4. Spacecraft: OV4. Decay Date: 1967-01-09 . USAF Sat Cat: 2524 . COSPAR: 1966-099A. Apogee: 305 km (189 mi). Perigee: 298 km (185 mi). Inclination: 32.8000 deg. Period: 90.40 min.

    A Titan IIIC (Vehicle #9), the ninth research and development Titan III and sixth Titan IIIC to be launched from Cape Canaveral, completed the most difficult flight plan and most successful mission to date. The primary objective of injecting a modified Gemini spacecraft into a suborbital trajectory to test the reentry heat shield for the Manned Orbiting Laboratory (MOL) program was accomplished. After dipping down to 80 nautical miles to eject the MOL load, the Transtage pitched up and placed a canister containing 11 experiments into a 160-nautical mile circular orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

  • OV4-01R - . Mass: 109 kg (240 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: OV4. Spacecraft: OV4. Decay Date: 1967-01-05 . USAF Sat Cat: 2526 . COSPAR: 1966-099B. Apogee: 292 km (181 mi). Perigee: 289 km (179 mi). Inclination: 32.8000 deg. Period: 90.30 min. Whispering gallery experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
  • OV4-01T - . Mass: 109 kg (240 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: OV4. Spacecraft: OV4. Decay Date: 1967-01-11 . USAF Sat Cat: 2528 . COSPAR: 1966-099D. Apogee: 317 km (196 mi). Perigee: 289 km (179 mi). Inclination: 32.8000 deg. Period: 90.60 min. Whispering gallery experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1966 December 7 - . 02:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC12. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D.
  • ATS 1 - . Payload: ATS B. Mass: 352 kg (776 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: ATS. Spacecraft: ATS-1. Completed Operations Date: 1985-04-01 . USAF Sat Cat: 2608 . COSPAR: 1966-110A. Apogee: 35,783 km (22,234 mi). Perigee: 35,728 km (22,200 mi). Inclination: 12.5000 deg. Period: 1,434.50 min.

    Applications Technology Satellite; communications and meteorological experiments. Positioned in geosynchronous orbit over the Americas at 151 deg W in 1966-1968?; over the Americas at 149 deg W in 1968-1982; over the Pacific Ocean 170 deg E in 1982-1985 As of 3 September 2001 located at 167.30 deg E drifting at 0.065 deg E per day. As of 2007 Mar 9 located at 59.28W drifting at 0.332E degrees per day.


1966 December 20 - . 02:20 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. FAILURE: Fourth stage failed to ignite.. Failed Stage: 4.
  • Ohsumi 2 - . Payload: L-4S-2. Mass: 26 kg (57 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Ohsumi. Spacecraft: Ohsumi. Decay Date: 1966-12-19 . Apogee: 400 km (240 mi).

1967 March 3 - . 06:44 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 11K63.
  • Cosmos 145 - . Payload: DS-U2-M s/n 2. Mass: 250 kg (550 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-M. Completed Operations Date: 1967-04-30 . Decay Date: 1968-03-08 . USAF Sat Cat: 2697 . COSPAR: 1967-019A. Apogee: 2,107 km (1,309 mi). Perigee: 226 km (140 mi). Inclination: 48.4000 deg. Period: 108.70 min. Development tests of atomic clocks..

1967 March 21 - . 10:07 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: R-12. Launch Vehicle: Kosmos 11K63.
  • Cosmos 149 - . Payload: DS-MO s/n 1. Mass: 321 kg (707 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MO. Completed Operations Date: 1967-04-08 . Decay Date: 1967-04-07 . USAF Sat Cat: 2714 . COSPAR: 1967-024A. Apogee: 284 km (176 mi). Perigee: 246 km (152 mi). Inclination: 48.4000 deg. Period: 89.80 min. Used in development of aerodynamic systems for stabilisation and orientation of spacecraft. Also carried military optical equipment experiments..

1967 April 6 - . 03:23 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC12. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D. FAILURE: Partial Failure.. Failed Stage: U.
  • ATS 2 - . Payload: ATS A. Mass: 370 kg (810 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: ATS. Spacecraft: ATS-2. Decay Date: 1969-09-02 . USAF Sat Cat: 2743 . COSPAR: 1967-031A. Apogee: 11,119 km (6,909 mi). Perigee: 177 km (109 mi). Inclination: 28.4000 deg. Period: 218.80 min. Launch vehicle failure left in useless orbit; communications tests..

1967 April 13 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. FAILURE: Fourth stage failed to ignite.. Failed Stage: 4.
  • Ohsumi 3 - . Payload: L-4S-3. Mass: 26 kg (57 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Ohsumi. Spacecraft: Ohsumi. Decay Date: 1967-04-13 . Apogee: 200 km (120 mi).

1967 May 5 - . 16:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout A.
  • Ariel 3 - . Payload: UK 3 (UK-E). Mass: 90 kg (198 lb). Nation: UK. Agency: SRC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Ariel. Spacecraft: Ariel. Decay Date: 1970-12-14 . USAF Sat Cat: 2773 . COSPAR: 1967-042A. Apogee: 604 km (375 mi). Perigee: 499 km (310 mi). Inclination: 80.6000 deg. Period: 95.60 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1967 May 30 - . 02:06 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout B. FAILURE: Third stage failure.. Failed Stage: 3.
  • ESRO 2A - . Payload: Iris 1. Mass: 74 kg (163 lb). Nation: Europe. Agency: ESRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ESRO. Spacecraft: ESRO. Decay Date: 1967-05-29 .

1967 May 31 - . 09:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D.
  • Timation 1 - . Mass: 700 kg (1,540 lb). Nation: USA. Agency: NRL. Program: Navstar. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Timation. Spacecraft: Timation. USAF Sat Cat: 2847 . COSPAR: 1967-053E. Apogee: 900 km (550 mi). Perigee: 894 km (555 mi). Inclination: 70.0000 deg. Period: 102.90 min. Navigation experiments leading eventually to Navstar/GPS system. Operated for 74 months..

1967 July 1 - . 13:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. LV Family: Titan. Launch Vehicle: Titan IIIC.
  • DODGE 1 - . Mass: 102 kg (224 lb). Nation: USA. Agency: USN NASC. Class: Technology. Type: Gravity gradient technology satellite. Spacecraft Bus: DODGE. Spacecraft: DODGE. USAF Sat Cat: 2867 . COSPAR: 1967-066F. Apogee: 33,670 km (20,920 mi). Perigee: 33,257 km (20,664 mi). Inclination: 12.0000 deg. Period: 1,319.10 min.

    A Titan IIIC booster (Vehicle #14) launched from Cape Canaveral placed a multiple payload of six satellites into orbit. Three of the satellites completed the Pacific link of the Initial Defense Satellite Communication System (IDSCS) program between Washington D.C., and South Vietnam. A fourth was a special communications satellite, the Despun Antenna Test Satellite (DATS), designed to test a despun antenna system for possible use on future communications satellites. DATS was designed to transmit 75 percent of radio signal strength to earth stations compared to the 15 percent for previous systems. Also included in the payload were a Defense Department Gravity Gradient Experiment (DODGE) satellite and a Lincoln Experimental Satellite, LES-5, the first all solid-state Ultra-high Frequency (UHF) band communication satellite intended to test communications with frontline troops. Gravity gradient experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

  • LES 5 - . Mass: 194 kg (427 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: LES. Spacecraft: LES. USAF Sat Cat: 2866 . COSPAR: 1967-066E. Apogee: 33,609 km (20,883 mi). Perigee: 33,196 km (20,626 mi). Inclination: 12.0000 deg. Period: 1,316.00 min. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1967 November 5 - . 23:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC12. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D.
  • ATS 3 - . Payload: ATS C. Mass: 365 kg (804 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: ATS. Spacecraft: ATS-3. USAF Sat Cat: 3029 . COSPAR: 1967-111A. Apogee: 35,837 km (22,268 mi). Perigee: 35,736 km (22,205 mi). Inclination: 14.5000 deg. Period: 1,436.10 min.

    Communications tests. Positioned in geosynchronous orbit over the Atlantic Ocean at 45 deg W in-100 deg W in 1968-1970; over the Americas at 69 deg W in 1971-1976; over the Americas at 105 deg W in 1977-1998 As of 4 September 2001 located at 105.90 deg W drifting at 0.003 deg W per day. As of 2007 Mar 10 located at 105.23W drifting at 0.006W degrees per day.


1967 December 13 - . 14:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.
  • TTS 1 - . Payload: TTS A. Mass: 20 kg (44 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Tracking network technology satellite. Spacecraft Bus: TTS. Spacecraft: TTS. Decay Date: 1968-04-28 . USAF Sat Cat: 3067 . COSPAR: 1967-123B. Apogee: 490 km (300 mi). Perigee: 287 km (178 mi). Inclination: 32.9000 deg. Period: 92.20 min. Test and Training Satellite; tested Apollo tracking network. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1967 December 26 - . 09:01 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/4. LV Family: R-12. Launch Vehicle: Kosmos 11K63.
  • Cosmos 197 - . Payload: DS-U2-V s/n 3. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Military technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-V. Completed Operations Date: 1968-01-30 . Decay Date: 1968-01-30 . USAF Sat Cat: 3079 . COSPAR: 1967-126A. Apogee: 486 km (301 mi). Perigee: 217 km (134 mi). Inclination: 48.4000 deg. Period: 91.50 min. Military technology development satellite - mission still classified..

1968 February 20 - . 10:03 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/4. LV Family: R-12. Launch Vehicle: Kosmos 11K63.
  • Cosmos 202 - . Payload: DS-U2-V s/n 4. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Military technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-V. Decay Date: 1968-03-24 . USAF Sat Cat: 3128 . COSPAR: 1968-010A. Apogee: 488 km (303 mi). Perigee: 210 km (130 mi). Inclination: 48.4000 deg. Period: 91.50 min. Military technology development satellite - mission still classified..

1968 May 17 - . 02:06 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout B.
  • ESRO 2B - . Payload: IRIS. Mass: 75 kg (165 lb). Nation: Europe. Agency: ESRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ESRO. Spacecraft: ESRO. Decay Date: 1971-05-08 . USAF Sat Cat: 3233 . COSPAR: 1968-041A. Apogee: 1,085 km (674 mi). Perigee: 334 km (207 mi). Inclination: 97.2000 deg. Period: 99.00 min.

1968 August 10 - . 22:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. LV Family: Atlas. Launch Vehicle: Atlas SLV-3C Centaur. FAILURE: Centaur oxidizer leak. No restart.. Failed Stage: U.
  • ATS 4 - . Payload: ATS D. Mass: 391 kg (862 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: ATS. Spacecraft: ATS-4. Decay Date: 1968-08-10 . USAF Sat Cat: 3344 . COSPAR: 1968-068A. Apogee: 769 km (477 mi). Perigee: 220 km (130 mi). Inclination: 29.1000 deg. Period: 94.50 min.

    Applications Technology Satellite that was to have been put into a geosynchronous transfer orbit, instead was left in a nearly-useless LEO orbit. ATS-4 included two cesium contact ion engines. Flight test objectives were to measure thrust and to examine electromagnetic compatibility with other spacecraft subsystems. The 5 cm diameter thrusters were designed to operate at 0.02 kW and provide about 89 microN thrust at about 6700 s specific impulse. The thrusters had the capability to operate at 5 setpoints from 18 to 89 microN. Thrusters were configured so they could be used for East-West station-keeping. Prior to launch, a 5 cm cesium thruster was life tested for 2245 hours at the 67 microN thrust level. However the Centaur upper stage did not achieve a second burn and the spacecraft remained attached to the Centaur in a 218 km by 760 km orbit. It was estimated that the pressure at these altitudes was between 10^-6 and 10^-8 Torr. Each of the two engines was tested on at least two occasions each over the throttling range. Combined test time of the two engines was about 10 hours over a 55 day period. The spacecraft re-entered the atmosphere on October 17, 1968. TheATS-4 flight was the first successful orbital test of an ion engine. There was no evidence of IPS electromagnetic interference related to spacecraft subsystems. Measured values of neutralizer emission current were much less than the ion beam current, implying inadequate neutralization. The spacecraft potential was about -132V which was much different than the anticipated value of about -40V.


1968 September 26 - . 07:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. LV Family: Titan. Launch Vehicle: Titan IIIC.
  • LES 6 - . Mass: 163 kg (359 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: LES. Spacecraft: LES. Completed Operations Date: 1976-01-01 . USAF Sat Cat: 3431 . COSPAR: 1968-081D. Apogee: 35,839 km (22,269 mi). Perigee: 35,776 km (22,230 mi). Inclination: 12.8000 deg. Period: 1,437.20 min.

    A Titan ITIC space booster (Vehicle #5) was launched from Complex 41 at the Eastern Test Range and inserted four satellites into separate earth orbits. The primary payload was the Lincoln Experimental Satellite (LES-6) which was the second all-solid-state ultrahigh frequency (UHF) band communication satellite to be placed into a synchronous orbit. It was designed to test communications with aircraft, ships, and ground forces. The other three satellites were Office of Aerospace Research (OAR) payloads - two Experimental Research Satellites (ERS-21 and ERS-28) and an Orbiting Vehicle (OV 2-5) research satellite. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit over the Atlantic Ocean at 38 deg W in 1968-1975 As of 26 August 2001 located at 61.90 deg W drifting at 0.101 deg E per day. As of 2007 Mar 9 located at 73.59W drifting at 0.201E degrees per day.


1968 October 3 - . 20:49 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout B.
  • ESRO 1A - . Payload: Aurorae. Mass: 81 kg (178 lb). Nation: Europe. Agency: ESRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ESRO. Spacecraft: ESRO. Decay Date: 1970-06-26 . USAF Sat Cat: 3459 . COSPAR: 1968-084A. Apogee: 1,538 km (955 mi). Perigee: 258 km (160 mi). Inclination: 93.8000 deg. Period: 103.00 min. Aurora, polar ionosphere investigations. .

1968 November 8 - . 09:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.
  • TTS 2; TATS 2 (TETR 2) - . Payload: TETR 2. Mass: 40 kg (88 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Tracking network technology satellite. Spacecraft Bus: TTS. Spacecraft: TTS. Decay Date: 1979-09-19 . USAF Sat Cat: 3534 . COSPAR: 1968-100B. Apogee: 945 km (587 mi). Perigee: 375 km (233 mi). Inclination: 32.9000 deg. Period: 98.00 min. Test and Training Satellite; test vehicle for NASA Manned Space Flight Network. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1968 November 29 - . 23:12 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA6A. LV Family: Blue Streak. Launch Vehicle: Europa I. FAILURE: Third stage exploded.. Failed Stage: 3.
  • STV 1 / Europa F-7 - . Mass: 249 kg (548 lb). Nation: Europe. Agency: ELDO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STV. Spacecraft: STV. Decay Date: 1968-11-30 . Apogee: 230 km (140 mi). First attempt by ELDO to launch a satellite to orbit. Satellite Test Vehicle payload..

1969 February 9 - . 21:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. LV Family: Titan. Launch Vehicle: Titan IIIC.
  • Tacsat 1 - . Mass: 730 kg (1,600 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: TACSAT. Spacecraft: Tacsat. Completed Operations Date: 1977-01-01 . USAF Sat Cat: 3691 . COSPAR: 1969-013A. Apogee: 36,044 km (22,396 mi). Perigee: 35,939 km (22,331 mi). Inclination: 1.0000 deg. Period: 1,446.60 min.

    Air Force Titan IIIC, Vehicle #17, was launched from Cape Canaveral and placed the 1,600-pound experimental Tactical Communications Satellite, TACSAT I, into a near-synchronous orbit at an altitude of 19,300 nautical miles above the equator. TACSAT I, built by Hughes Aircraft Company under SAMSO management, was the largest communications satellite yet launched and placed in orbit by the United States. It was to determine the feasibility of using satellite communications repeaters with small mobile ground tactical communications equipment. In addition, using the technology already developed with earlier Despun Antenna Test System (DATS) and Lincoln Experimental Satellites (LES) test spacecraft, TACSAT I would test the feasibility of satellite communications over great distances while also testing the new gyrostat stabilization system. The satellite could handle transmission of television or multiple telephone/ teletype communications channels. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit over the Americas at 107 deg W in 1969?-1970; over the Pacific Ocean 173 deg W in 1970; over the Pacific Ocean 179 deg W in 1971-1972; over the Pacific Ocean170 deg E in 1972 Last known longitude (9 June 1995) 176.44 deg E drifting at 0.150 deg E per day.


1969 July 2 - . 22:55 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA6A. LV Family: Blue Streak. Launch Vehicle: Europa I. FAILURE: Third stage failed.. Failed Stage: 3.
  • Europa F-8 / STV 2 - . Payload: STV 2. Mass: 249 kg (548 lb). Nation: Europe. Agency: ELDO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STV. Spacecraft: STV. Apogee: 300 km (180 mi).

1969 August 9 - . 07:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta N.
  • PAC 1 - . Mass: 120 kg (260 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: PAC. Spacecraft: PAC. Decay Date: 1977-04-28 . USAF Sat Cat: 4066 . COSPAR: 1969-068B. Apogee: 552 km (342 mi). Perigee: 486 km (301 mi). Inclination: 32.9000 deg. Period: 95.00 min. Package Attitude Control; semi-active gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1969 August 12 - . 11:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. LV Family: Atlas. Launch Vehicle: Atlas SLV-3C Centaur.
  • ATS 5 - . Payload: ATS E. Mass: 821 kg (1,809 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: ATS. Spacecraft: ATS-5. Completed Operations Date: 1984-01-01 . USAF Sat Cat: 4068 . COSPAR: 1969-069A. Apogee: 36,024 km (22,384 mi). Perigee: 35,992 km (22,364 mi). Inclination: 14.5000 deg. Period: 1,447.40 min.

    Applications Technology Satellite; communications tests. Launch vehicle successfully put the payload into a geosynchronous transfer orbit. The spacecraft maneuvered into geostationary orbit at 108 degrees W. The purpose of this flight was to demonstrate North-South Stationkeeping of a geosynchronous satellite. ATS-5 was equipped with an ion engine package identical to that on ATS-4. Once in geosynchronous orbit the spacecraft could not be despun as planned, and thus the spacecraft gravity gradient stabilization could not be implemented. The spacecraft spin rate was about 76 revolutions per minute, and this caused an effective 4g acceleration on the cesium feed system. The high g-loading on the cesium feed system caused flooding of the discharge chamber, and normal operation of the thruster with ion beam extraction could not be performed. The IPS was instead be operated as a neutral plasma source, without high-voltage ion extraction, along with the wire neutralizer to examine spacecraft charging effects. The neutralizer was also operated by itself to provide electron injection for the spacecraft charging experiments. Positioned in geosynchronous orbit over the Americas at 105 deg W in 1969-1977; over the Americas at 70 deg W in 1977-1983. As of 1 September 2001 located at 15.48 deg E drifting at 2.807 deg W per day. As of 2007 Mar 10 located at 111.70E drifting at 2.819W degrees per day.


1969 September 22 - . 02:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. FAILURE: Fourth stage control system malfunction after third stage collided with fourth stage.. Failed Stage: 4.
  • Ohsumi 4 - . Payload: L-4S-4. Mass: 25 kg (55 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Ohsumi. Spacecraft: Ohsumi. Decay Date: 1969-09-22 . Apogee: 400 km (240 mi).

1969 September 30 - . 13:40 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.
  • Timation 2 - . Mass: 700 kg (1,540 lb). Nation: USA. Agency: NRL. Program: Navstar. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Timation. Spacecraft: Timation. USAF Sat Cat: 4257 . COSPAR: 1969-082C. Apogee: 925 km (574 mi). Perigee: 898 km (557 mi). Inclination: 70.0000 deg. Period: 103.20 min. Navigation experiments leading eventually to Navstar/GPS system. Operated for 6 years..

1969 October 1 - . 22:29 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout B. FAILURE: Partial Failure.. Failed Stage: 4.
  • ESRO 1B - . Payload: Boreas. Mass: 80 kg (176 lb). Nation: Europe. Agency: ESRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ESRO. Spacecraft: ESRO. Decay Date: 1969-11-23 . USAF Sat Cat: 4114 . COSPAR: 1969-083A. Apogee: 378 km (234 mi). Perigee: 298 km (185 mi). Inclination: 85.0000 deg. Period: 91.30 min.

    Ionospheric and auroral investigations; lower than planned orbit. Fourth satellite of ESRO. Also registered by the United States in A/AC.105/INF.220 as United States space object 1969-83A, with category B and orbital parameters 90.6 min, 280 x 339 km x 85.1 deg.


1969 November 16 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2A. LV Family: DF-3. Launch Vehicle: Chang Zheng 1. FAILURE: The program distributor in the second stage broke down. The rocket crashed into the earth within view of the launch site after 69 seconds of flight.. Failed Stage: 2.
  • First Chinese satellite launch attempt ends in failure. - . Payload: DFH 1. Mass: 170 kg (370 lb). Nation: China. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DFH-1. Spacecraft: DFH-1. COSPAR: F691116Z.

    The launch vehicle arrived at the site on 18 March 1969. The objective was to launch China's first satellite before Japan lofted its counterpart. Ren Xinmin had obtained this specific order from Deng Hsiao Peng. Great difficulties were encountered in the middle of the Cultural Revolution, including the sending of most of the satellite engineers to work on irrigation ditch construction in the provinces. The skirt for the satellite, designed to make it easily visible to ground observors, had to be made from a special silk produced in a factory without the knowledge of the Red Guards. The engineers went by bus to a department store in Beijing to study an imported folding umbrella as a model for the deployment mechanism -- they could not afford to buy it. The entire launch was kept secret until a documentary was released in 2001.


1970 January 16 - . 10:59 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/4. LV Family: R-12. Launch Vehicle: Kosmos 11K63.
  • Cosmos 320 - . Payload: DS-MO s/n 3. Mass: 375 kg (826 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MO. Completed Operations Date: 1970-02-10 . Decay Date: 1970-02-10 . USAF Sat Cat: 4301 . COSPAR: 1970-005A. Apogee: 326 km (202 mi). Perigee: 247 km (153 mi). Inclination: 48.4000 deg. Period: 90.20 min. Used in development of aerodynamic systems for stabilisation and orientation of spacecraft. Also carried military optical equipment experiments..

1970 February 4 - . 02:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.
  • SERT 2 - . Mass: 1,404 kg (3,095 lb). Nation: USA. Agency: NASA Cleveland. Class: Technology. Type: Ion engine technology satellite. Spacecraft Bus: SERT. Spacecraft: SERT. USAF Sat Cat: 4327 . COSPAR: 1970-009A. Apogee: 1,046 km (649 mi). Perigee: 1,039 km (645 mi). Inclination: 99.2000 deg. Period: 106.00 min.

    Space Electric Rocket Test; the ion engines aboard were operated until 1981. The SERT 2 development program started in 1966 and included thruster ground tests of 6742 hours and 5169 hours duration. A prototype version of the SERT 2 spacecraft was ground-tested for a period of 2400 hours with an operating ion engine. In addition to diagnostic equipment and related ion engine hardware, the spacecraft had two identical 15 cm diameter, mercury ion engines. Flight objectives included in-space operation for a period of 6 months, measurement of thrust, and demonstration of electromagnetic compatibility. The thruster maximum power level was 0.85 kW, and this provided operation at a 28 mN thrust level at 4200 s specific impulse. Flight data were obtained from 1970 to 1981 with an ion engine operating intermittently in one of three different modes, namely, HV ion extraction, discharge chamber operation only, or just neutralizer operation. Major results were that two mercury engines thrusted for periods of 3781 hours and 2011 hours. Test duration was limited due to shorts in the ion optical system. Thrust measured in space and on the ground agreed within the measurement uncertainties. Up to 300 thruster restarts were demonstrated. One power-processing unit accumulated nearly 17,900 hours during the course of the mission. Additionally, the ion propulsion system was electromagnetically compatible with all other spacecraft systems.


1970 February 11 - . 04:25 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S.
  • Ohsumi 5 - . Payload: L-4S-5. Mass: 12 kg (26 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Osumi. Spacecraft: Osumi. Decay Date: 2003-08-02 . USAF Sat Cat: 4330 . COSPAR: 1970-011A. Apogee: 2,440 km (1,510 mi). Perigee: 323 km (200 mi). Inclination: 31.0000 deg. Period: 113.40 min. Engineering tests. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E .

1970 March 10 - . 12:20 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant B.
  • DIAL-WIKA - . Payload: DIAL Wissenschaftliche Kapsel. Mass: 63 kg (138 lb). Nation: Germany. Agency: BMW, CNES. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DIAL WIKA. Spacecraft: Dial WIKA. Decay Date: 1978-10-05 . USAF Sat Cat: 4344 . COSPAR: 1970-017A. Apogee: 1,631 km (1,013 mi). Perigee: 301 km (187 mi). Inclination: 5.4000 deg. Period: 104.20 min. Engineering package..
  • Dial MIKA - . Payload: DIAL Mini Kapsel/P068. Mass: 52 kg (114 lb). Nation: France. Agency: BMW, CNES. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Dial MIKA. Spacecraft: Dial MIKA. Decay Date: 1974-09-09 . USAF Sat Cat: 4345 . COSPAR: 1970-017B. Apogee: 1,638 km (1,017 mi). Perigee: 310 km (190 mi). Inclination: 5.4000 deg. Period: 104.56 min. Engineering package; monitored launch vehicle performance. .

1970 April 24 - . 13:35 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2A. LV Family: DF-3. Launch Vehicle: Chang Zheng 1.
  • DFH Mao 1 - . Payload: DFH 1. Mass: 173 kg (381 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DFH-1. Spacecraft: DFH-1. USAF Sat Cat: 4382 . COSPAR: 1970-034A. Apogee: 2,162 km (1,343 mi). Perigee: 434 km (269 mi). Inclination: 68.4000 deg. Period: 111.60 min.

    The final campaign to launch China's first satellite began on April 1, 1970, when two DFH-1 satellites and the CZ-1 rocket arrived by train at the Jiuquan Satellite Launch Centre. This was over a year after the first attempt in 1969. Ren Xinmin was project leader and Qi Faren was leader of the DFH-1 experiment team. On April 2 Premier Zhou Enlai called a special meeting in the Great Hall of the People in Beijing for a final readiness review of the satellite and the launch vehicle. Zhou wanted special guarantees that the satellite would transmit the march 'The East is Red' from orbit.

    On the morning of April 24, 1970, the first and second stages of CZ-1 were loaded with propellant and stacked. The satellite was mated to the spin-stabilized solid-propellant third stage, and the launcher entered the final eight hours of launch preparation. Weather forecast for the launch at 9:30 p.m. called for clouds at above 7,000 meters and a wind speed of less than 4 to 5 meters per second.

    The historic launch came at 9:35 p.m. local time (13:35 UTC). Upon hearing the command "ignition", a launch controller pressed the button to start the rocket engines. The three-stage CZ-1, which was 29.46 meters tall and had a maximum diameter of 2.25 meters, lifted off the launch pad with a thrust of 104 tonnes. Liftoff weight of the CZ-1 was 81.5 tonnes. Rocket expert Shen Jianan recounted that "..as soon as I saw the liftoff on the TV screen inside the bunker, I ran outside. I could only see the beautiful rocket lighting up the night sky and streaking towards the southeast. I ran back inside to listen to the transmissions. Broadcasting on the speaker were status reports like 'capturing target', 'nominal tracking', 'nominal flight', 'nominal second and third stage separation'..." Thirteen minutes after launch, at 9:48 p.m., mission control announced "...satellite and rocket stage separation, satellite enters orbit...the bunker was filled with cheers".

    China became the fifth nation after the former Soviet Union, the United States, France and Japan to achieve an indigenous space launch capability. At 9:50 p.m., the National Broadcasting Bureau announced the acquisition of the tune 'East is Red' from the satellite loud and clear. In the following days, the People's Central Broadcasting radio and newspapers in Beijing announced and printed worldwide times of DFH-1 and CZ-1 third stage passages, and directions of travel in the sky. Senior officials in Beijing dispatched a chartered plane to JSLC to bring back Qi and other scientists. In the International Labour Day celebration on May 1, Chairman Mao and Premier Zhou warmly welcomed them at the Tiananmen Square.


1970 June 12 - . 01:10 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA6A. LV Family: Blue Streak. Launch Vehicle: Europa I. FAILURE: Payload fairing failed to separate.. Failed Stage: S.
  • Europa F-9 / STV 3 - . Mass: 249 kg (548 lb). Nation: Europe. Agency: ELDO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STV. Spacecraft: STV. Decay Date: 1970-06-12 . COSPAR: F700612A. Apogee: 2,000 km (1,200 mi).

1971 February 16 - . 04:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-4S.
  • Tansei 1 - . Payload: MS T1. Mass: 62 kg (136 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Tansei. Spacecraft: Tansei. USAF Sat Cat: 4952 . COSPAR: 1971-011A. Apogee: 1,106 km (687 mi). Perigee: 986 km (612 mi). Inclination: 29.7000 deg. Period: 106.10 min. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E .

1971 March 3 - . 12:15 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2A. LV Family: DF-3. Launch Vehicle: Chang Zheng 1.
  • SJ-1 - . Payload: Shi Jian 1. Mass: 221 kg (487 lb). Nation: China. Agency: MAI. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: DFH-1. Spacecraft: DFH-1. Decay Date: 1979-06-17 . USAF Sat Cat: 5007 . COSPAR: 1971-018A. Apogee: 1,833 km (1,138 mi). Perigee: 265 km (164 mi). Inclination: 69.8000 deg. Period: 106.10 min. Similar in appearance to the American Telstar and conducted communications technology tests..

1971 June 8 - . 14:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.
  • SESP 70-1 - . Payload: P70-1 / Burner II No. 12 / OPS 3850. Mass: 260 kg (570 lb). Nation: USA. Agency: USAF STP. Class: Technology. Type: Military technology satellite. Spacecraft Bus: SESP. Spacecraft: SESP. Decay Date: 1982-01-31 . USAF Sat Cat: 5285 . COSPAR: 1971-054A. Apogee: 580 km (360 mi). Perigee: 544 km (338 mi). Inclination: 90.2000 deg. Period: 95.80 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1971 August 7 - . 00:11 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576A2. LV Family: Atlas. Launch Vehicle: Atlas F.
  • Gridsphere 2 - . Payload: AVL-802 Grid Sphere 7-2. Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Gridsphere. Spacecraft: Gridsphere. Decay Date: 1979-03-18 . USAF Sat Cat: 5401 . COSPAR: 1971-067G. Apogee: 915 km (568 mi). Perigee: 783 km (486 mi). Inclination: 87.6000 deg. Period: 101.90 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • Gridsphere 1 - . Payload: AVL-802 Grid Sphere 7-1. Mass: 37 kg (81 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Gridsphere. Spacecraft: Gridsphere. USAF Sat Cat: 5398 . COSPAR: 1971-067E. Apogee: 856 km (531 mi). Perigee: 756 km (469 mi). Inclination: 87.6000 deg. Period: 101.00 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • Musketball 1 - . Payload: RTDS. Nation: USA. Agency: USAF STP. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Musketball. Spacecraft: Musketball. Decay Date: 1971-09-19 . USAF Sat Cat: 5383 . COSPAR: 1971-067D. Apogee: 859 km (533 mi). Perigee: 134 km (83 mi). Inclination: 87.6000 deg. Period: 94.60 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • Mylar Balloon - . Payload: AVL-802 Mylar Sphere. Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Mylar. Spacecraft: Mylar. Decay Date: 1981-09-01 . USAF Sat Cat: 5410 . COSPAR: 1971-067P. Apogee: 912 km (566 mi). Perigee: 791 km (491 mi). Inclination: 87.6000 deg. Period: 101.90 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1971 September 29 - . 09:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta N.
  • TETR 3 - . Payload: TETR D. Mass: 20 kg (44 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Tracking network technology satellite. Spacecraft Bus: TETR. Spacecraft: TETR. Decay Date: 1978-09-19 . USAF Sat Cat: 5492 . COSPAR: 1971-083B. Apogee: 570 km (350 mi). Perigee: 403 km (250 mi). Inclination: 33.0000 deg. Period: 94.30 min. Test satellite for NASA's Manned Space Flight Network. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1971 October 17 - . 13:36 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.
  • ASTEX - . Payload: P71-2 / Agena D. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF STP. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ASTEX. Spacecraft: ASTEX. USAF Sat Cat: 5560 . COSPAR: 1971-089A. Apogee: 761 km (472 mi). Perigee: 738 km (458 mi). Inclination: 92.7000 deg. Period: 99.80 min.

    Space Test Program Flight 71-2 (STP 71-2), a Thorad/Agena launch vehicle, inserted four payloads into orbit from Vandenberg. Space Test Program; technology experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).


1971 November 5 - . 13:00 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA1. Launch Pad: CECLES. LV Family: Blue Streak. Launch Vehicle: Europa II. FAILURE: Structural failure of third stage. Guidance signals were reversed.. Failed Stage: 3.
  • Europa F-11 / STV 4 - . Nation: Europe. Agency: ELDO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STV 4. Spacecraft: STV 4. Decay Date: 1971-11-05 . Apogee: 27 km (16 mi).

1972 March 12 - . 01:55 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta N.
  • TD-1A; Thor Delta 1A - . Payload: TD 1A. Mass: 472 kg (1,040 lb). Nation: Europe. Agency: ESRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: TD-1A. Spacecraft: TD-1A. Decay Date: 1980-01-09 . USAF Sat Cat: 5879 . COSPAR: 1972-014A. Apogee: 550 km (340 mi). Perigee: 523 km (324 mi). Inclination: 97.6000 deg. Period: 95.40 min. Sixth satellite of ESRO. Also registered as US object 1972-14A in A/AC.105/INF.255 with orbit 95.3 min, 525 x 548 km x 97.5 deg, category B. .

1972 April 4 - . 20:38 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/4. LV Family: R-7. Launch Vehicle: Molniya 8K78M.
  • SRET 1 - . Payload: MAS/SRET 1. Mass: 15 kg (33 lb). Nation: France. Agency: CNES. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SRET. Spacecraft: SRET. Decay Date: 1974-02-26 . USAF Sat Cat: 5928 . COSPAR: 1972-025B. Apogee: 39,250 km (24,380 mi). Perigee: 458 km (284 mi). Inclination: 65.6000 deg. Period: 704.70 min. Test satellite. Investigation of the upper atmosphere and outer space..

1972 October 2 - . 20:09 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576A1. LV Family: Atlas. Launch Vehicle: Atlas Burner 2.
  • RADCAT - . Payload: Radsat / Radcat / OPS 8180. Mass: 208 kg (458 lb). Nation: USA. Agency: US Army. Class: Technology. Type: Military technology satellite. Spacecraft Bus: RADCAT. Spacecraft: RADCAT. Decay Date: 2012-08-02 . USAF Sat Cat: 6212 . COSPAR: 1972-076A. Apogee: 638 km (396 mi). Perigee: 627 km (389 mi). Inclination: 98.6000 deg. Period: 97.40 min.

    An Atlas F/Burner IIA launch vehicle, carrying SAMSO's Space Test Program Flight 72-1, was launched from Vandenberg. This was the first use of this booster/upper stage combination. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

  • Radsat - . Payload: P 72-1 / OPS 8180. Mass: 726 kg (1,600 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: Radsat. Spacecraft: Radsat. USAF Sat Cat: 6217 . COSPAR: 1972-076B. Apogee: 705 km (438 mi). Perigee: 688 km (427 mi). Inclination: 98.7000 deg. Period: 98.70 min.

    An Atlas F/Burner IIA launch vehicle, carrying SAMSO's Space Test Program Flight 72-1, was launched from Vandenberg. This was the first use of this booster/upper stage combination. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).


1972 November 22 - . 00:17 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout D-1.
  • ESRO 4 - . Mass: 114 kg (251 lb). Nation: Europe. Agency: ESRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ESRO. Spacecraft: ESRO. Decay Date: 1974-04-15 . USAF Sat Cat: 6285 . COSPAR: 1972-092A. Apogee: 1,173 km (728 mi). Perigee: 245 km (152 mi). Inclination: 91.1000 deg. Period: 99.00 min. Polar ionosphere investigations. Seventh ESRO satellite. Mass 115 kg. Also registered by the United States as 1972-92A, in A/AC.105/INF.267, with orbital parameters 98.8 min, 244 x 1160 km x 91.1 deg, category B. .

1973 May 21 - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant B. FAILURE: Failure - fairing did not jettison.. Failed Stage: S.
  • Castor (D 5A) - . Payload: D 5A. Nation: France. Agency: CNES. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: D. Spacecraft: D. Decay Date: 1972-05-21 . COSPAR: F730521A.

1974 February 16 - . 05:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C.
  • Tansei 2 - . Payload: MS T2. Mass: 65 kg (143 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Tansei. Spacecraft: Tansei. Decay Date: 1983-01-22 . USAF Sat Cat: 7122 . COSPAR: 1974-008A. Apogee: 3,231 km (2,007 mi). Perigee: 284 km (176 mi). Inclination: 31.2000 deg. Period: 121.70 min. Attitude control satellite (performance test of launch vehicle). .

1974 March 9 - . 02:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout D-1.
  • Miranda - . Payload: X-4. Mass: 93 kg (205 lb). Nation: UK. Agency: Royal Aerospace Establishment. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Miranda. Spacecraft: Miranda. USAF Sat Cat: 7213 . COSPAR: 1974-013A. Apogee: 866 km (538 mi). Perigee: 677 km (420 mi). Inclination: 97.9000 deg. Period: 100.30 min. Satellite technology. Miranda was launched at 02:22:11.4 GMT on 1974 Mar 9. Interjection point 13.9N, 126.0E. Anticipated life: longer than 50 years. .

1974 May 30 - . 13:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan IIIC.
  • ATS 6 - . Payload: ATS F. Mass: 930 kg (2,050 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: ATS. Spacecraft: ATS-6. Completed Operations Date: 1979-08-02 . USAF Sat Cat: 7318 . COSPAR: 1974-039A. Apogee: 35,444 km (22,023 mi). Perigee: 35,184 km (21,862 mi). Inclination: 13.1000 deg. Period: 1,412.00 min.

    An Air Force Titan IIIC boosted NASA's Applications Technology Satellite (ATS-F) into orbit from Cape Canaveral. Built by Application Technology Satellite; experimental communications satellite. The purpose of the ATS-6 flight experiment was to demonstrate north-south stationkeeping of a geosynchronous satellite using two cesium ion engine systems. Thruster development tests included a life test of 2614 hours and 471 cycles. Thruster input power was 0.15 kW, which resulted in a thrust of 4.5 mN at a specific impulse of 2500 s. One of the ion engines operated for about one hour and the other for 92 hours. Both of the engines failed to provide thrust on restart due to discharge chamber cesium flooding. The feed system flooding problem caused overloading of the discharge and high voltage power supplies. This failure mechanism was verified through a series of ground tests. However engine operation demonstrated an absence of EMI related to spacecraft systems, verified predictions of spacecraft potential with engines operating, and demonstrated compatibility with the spacecraft's star tracker. It was found that the ion engines or just the neutralizer could discharge large negative spacecraft potentials at all times. Positioned in geosynchronous orbit over the Americas at 94 deg W in 1974-1975; over the Indian Ocean 35 deg E in 1975-1976; over the Americas at 140 deg W in 1976-1979. As of 2 September 2001 located at 172.56 deg W drifting at 6.144 deg E per day. As of 2007 Mar 8 located at 29.12W drifting at 6.125E degrees per day.


1974 July 14 - . 05:17 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Atlas. Launch Vehicle: Atlas F/PTS.
  • NTS 1 - . Payload: Timation 3 / OPS 7518. Mass: 293 kg (645 lb). Nation: USA. Agency: USAF. Program: Navstar. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: NTS. Spacecraft: NTS. USAF Sat Cat: 7369 . COSPAR: 1974-054A. Apogee: 13,774 km (8,558 mi). Perigee: 13,446 km (8,354 mi). Inclination: 125.2000 deg. Period: 468.70 min. Demonstrated navigation technologies leading eventually to Navstar/GPS system. Operated for 5 years..

1974 October 29 - . 19:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Titan. Launch Vehicle: Titan IIID.
  • SESP 73-5 - . Payload: P 73 5 / OPS 8452. Mass: 260 kg (570 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: SESP. Spacecraft: SESP. Decay Date: 1975-05-26 . USAF Sat Cat: 7499 . COSPAR: 1974-085C. Apogee: 2,888 km (1,794 mi). Perigee: 150 km (90 mi). Inclination: 96.9000 deg. Period: 116.30 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1974 November 15 - . 17:11 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2310.
  • Intasat 1 - . Payload: Intasat. Mass: 20 kg (44 lb). Nation: Spain. Agency: INTA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Intasat. Spacecraft: Intasat. USAF Sat Cat: 7531 . COSPAR: 1974-089C. Apogee: 1,459 km (906 mi). Perigee: 1,442 km (896 mi). Inclination: 101.8000 deg. Period: 114.90 min.

1974 December 19 - . 02:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.
  • Symphonie 1 - . Payload: Symphonie MV1. Mass: 221 kg (487 lb). Nation: France. Agency: CNES, DFVLR. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Symphonie. Spacecraft: Symphonie. Completed Operations Date: 1983-08-03 . USAF Sat Cat: 7578 . COSPAR: 1974-101A. Apogee: 35,893 km (22,302 mi). Perigee: 35,853 km (22,277 mi). Inclination: 14.9000 deg. Period: 1,440.50 min.

    Experimental commsat. Jointly registered by the Federal Republic of Germany (A/AC.105/INF.305) and France (A/AC.105/INF.306). Symphonie flying model no. 1, constructed jointly by France and the Federal Republic of Germany. Description: Experimental teleco mmunications satellite. Orbit: geostationary. Positioned in geosynchronous orbit over the Atlantic Ocean at 11 deg W in 1975-1977; over the Indian Ocean 49 deg E in 1977-1983 As of 25 August 2001 located at 179.98 deg E drifting at 1.086 deg W per day. As of 2007 Mar 11 located at 72.77E drifting at 1.184W degrees per day.


1975 April 13 - . 00:51 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Atlas. Launch Vehicle: Atlas F. FAILURE: First stage failure due to explosion in flame pit at lift-off.. Failed Stage: 1.
  • P 72-2 - . Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: P 72. Spacecraft: P 72. Decay Date: 1975-04-12 .

    Space Test Program flight P72-2 was launched; it carried two infrared radiometers and three other payloads. The launch failed when the Atlas F launch vehicle malfunctioned. A lack of deluge water and collection in the flame bucket of a kerosene/liquid oxygen gel led to the explosion of the gel on lift-off, damaging one of the Atlas engines and leading to complete engine failure during the ascent.


1975 June 5 - . 01:38 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Molniya 8K78M.
  • SRET 2 - . Payload: SRET 2 (MAS 2). Mass: 30 kg (66 lb). Nation: France. Agency: CNES. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SRET. Spacecraft: SRET. Decay Date: 1988-07-10 . USAF Sat Cat: 7910 . COSPAR: 1975-049B. Apogee: 40,825 km (25,367 mi). Perigee: 513 km (318 mi). Inclination: 62.8000 deg. Period: 737.80 min.

    SRET 2 technological research and study satellite. Launched from Soviet Union with a Soviet launch vehicle with the Molniya satellite. Mass 30 kg. Study of the behaviour of a passive cryogenic radiation system, study of the aging of thermal casings and pl astic films.


1975 August 9 - . 01:48 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2913.
  • COS-B - . Payload: COS B. Mass: 280 kg (610 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: COS. Spacecraft: COS. Decay Date: 1986-01-18 . USAF Sat Cat: 8062 . COSPAR: 1975-072A. Apogee: 99,002 km (61,516 mi). Perigee: 442 km (274 mi). Inclination: 90.3000 deg. Period: 2,203.90 min.

    Eighth CERS/ESRO satellite, first European Space Agency satellite. Launch time 0147:59 GMT. Argument of perigee 344.7 deg. Also registered by the United States in A/AC.105/INF.331 as 1975-72A, category B satellite with orbit 2203.9 min, 442 x 99002 km x 9 0.3 deg.


1975 September 9 - . 05:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.
  • Kiku 1 - . Payload: ETS 1 (JETS). Mass: 85 kg (187 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS. Spacecraft: ETS. USAF Sat Cat: 8197 . COSPAR: 1975-082A. Apogee: 1,103 km (685 mi). Perigee: 975 km (605 mi). Inclination: 47.0000 deg. Period: 106.00 min.

    JETS-1 (Japanese Engineering Test Satellite -1, national name 'Kiku') is intended for preliminary experiments for confirmation of the launching technologies, acquiring the satellite tracking and control technologies, and for extension tests of the extenda ble antennas, measurement of satellite environment, measurement of satellite attitudes, etc. Launch time 0530 GMT.


1976 February 4 - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. FAILURE: Stage 2 thrust vector control failure.. Failed Stage: 2.
  • Corsa A - . Mass: 92 kg (202 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Corsa A. Spacecraft: Corsa A. Decay Date: 1976-02-04 .

1976 March 15 - . 01:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan IIIC.
  • LES 8 - . Mass: 454 kg (1,000 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: LES. Spacecraft: LES. Completed Operations Date: 1992-01-01 . USAF Sat Cat: 8746 . COSPAR: 1976-023A. Apogee: 35,835 km (22,266 mi). Perigee: 35,728 km (22,200 mi). Inclination: 11.4000 deg. Period: 1,435.80 min.

    A Titan IIIC carrying a Space Test Program payload, Flight P74-1, was successfully launched from LC-40, Eastern Test Range. Flight P74-1 was made up of Lincoln Experimental Satellite 8 and 9 (LES 8/9) and Solar Radiation satellites 11A and B (SOLRAD 11A/B). Spacecraft engaged in practical applications and uses of space technology such as weather or communication. Also tested pulsed plasma engines. Positioned in geosynchronous orbit over the Atlantic Ocean at 1976-77; over the Americas at 106-110 deg W in 1978-1986; over the Atlantic Ocean 60-70 deg W in 1987-1991;over the Americas at 94-106 deg W in 1991-1992. As of 6 September 2001 located at 105.16 deg W drifting at 0.010 deg E per day. As of 2007 Mar 9 located at 107.51W drifting at 0.001E degrees per day.

  • LES 9 - . Mass: 454 kg (1,000 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: LES. Spacecraft: LES. Completed Operations Date: 1992-01-01 . USAF Sat Cat: 8747 . COSPAR: 1976-023B. Apogee: 35,825 km (22,260 mi). Perigee: 35,745 km (22,210 mi). Inclination: 17.0000 deg. Period: 1,436.00 min.

    Spacecraft engaged in practical applications and uses of space technology such as weather or communication. Also tested pulsed plasma engines. Positioned in geosynchronous orbit over the Atlantic Ocean at 30-40 deg W in 1976-78; over the Americas at 90-100 deg W in 1980-81; over the Americas at 100-106 deg W in 1981-1990; over the Atlantic Ocean 10 deg W in 1991; over the Americas at 105 deg W in 1992-on. As of 1 September 2001 located at 103.85 deg W drifting at 0.023 deg W per day. As of 2007 Mar 11 located at 107.07W drifting at 0.018W degrees per day.


1976 May 22 - . 07:42 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout B-1.
  • P 76-5 - . Mass: 73 kg (160 lb). Nation: USA. Agency: USAF STP. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: P 76. Spacecraft: P 76. USAF Sat Cat: 8860 . COSPAR: 1976-047A. Apogee: 1,044 km (648 mi). Perigee: 981 km (609 mi). Inclination: 99.6000 deg. Period: 105.40 min.

    A Scout vehicle carrying a Space Test Program spacecraft was successfully launched from SLC-5 at the Western Test Range. The spacecraft, Flight P76-5, carried a wideband signals experiment sponsored by the Defense Nuclear Agency. Communications propagation experiments.


1976 June 19 - . 16:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Intercosmos 15 - . Payload: AUOS-Z-T-IK. Mass: 550 kg (1,210 lb). Nation: Russia. Agency: IK. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. Completed Operations Date: 1976-07-26 . Decay Date: 1979-11-18 . USAF Sat Cat: 8903 . COSPAR: 1976-056A. Apogee: 520 km (320 mi). Perigee: 481 km (298 mi). Inclination: 74.0000 deg. Period: 94.60 min. Testing of new systems and components of satellite under space flight conditions. .

1976 July 8 - . 18:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Titan. Launch Vehicle: Titan IIID.
  • SESP 74-2 - . Payload: P 74-2 / OPS 3986. Mass: 260 kg (570 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft Bus: SESP. Spacecraft: SESP. Decay Date: 1986-04-24 . USAF Sat Cat: 9007 . COSPAR: 1976-065B. Apogee: 8,048 km (5,000 mi). Perigee: 236 km (146 mi). Inclination: 97.5000 deg. Period: 179.00 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1977 February 19 - . 05:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3H.
  • Tansei 3 - . Payload: MS T3. Mass: 230 kg (500 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Tansei. Spacecraft: Tansei. USAF Sat Cat: 9841 . COSPAR: 1977-012A. Apogee: 3,802 km (2,362 mi). Perigee: 799 km (496 mi). Inclination: 65.8000 deg. Period: 134.10 min.

    Tentative name before launching: MS-T3. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Radio frequencies: 136.725 MHz, tracking; 400.500 MHz, telemetry. Active life: two weeks. Function: (1) Test of the overall p erformance of the newly developed launch vehicle, M-3H-1. (2) Experiment of magnetic stabilization. (3) Observation of ultraviolet radiation.


1977 February 23 - . 08:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.
  • Kiku 2 - . Payload: ETS 2. Mass: 130 kg (280 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS. Spacecraft: ETS. Completed Operations Date: 1990-12-01 . USAF Sat Cat: 9852 . COSPAR: 1977-014A. Apogee: 35,860 km (22,280 mi). Perigee: 35,854 km (22,278 mi). Inclination: 11.9000 deg. Period: 1,439.70 min.

    Engineering test satellite. Engineering Test Satellite Type II (ETS II), Kiku 2. Launch by N launch vehicle no 3. Geographical longitude of the geostationary orbit: 130 deg E. Preliminary experiments to acquire technologies to launch,track, and control geostationary satellites. P ropagation experiment of millimetre and quasi-millimetre waves. Characteristics: Weight at launch 245 kg. Configuration: cylindrical. Height 191 cm including antenna. Diameter 141 cm. Attitude control: spin stabilization. Expected life at least 6 months. Positioned in geosynchronous orbit over the Pacific Ocean at 130 deg E in 1977-1990 As of 5 September 2001 located at 16.93 deg E drifting at 0.930 deg W per day. As of 2007 Mar 9 located at 85.65W drifting at 0.986W degrees per day.


1977 March 29 - . 23:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Cosmos 900 - . Payload: AUOS-Z-R-O Oval. Mass: 900 kg (1,980 lb). Nation: Russia. Agency: MO. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. Decay Date: 1979-10-11 . USAF Sat Cat: 9898 . COSPAR: 1977-023A. Apogee: 522 km (324 mi). Perigee: 457 km (283 mi). Inclination: 83.0000 deg. Period: 94.40 min. Investigation of the upper atmosphere and outer space. .

1977 June 17 - . 03:30 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC107/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Signe 3 - . Mass: 102 kg (224 lb). Nation: France. Agency: CNES. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Signe. Spacecraft: Signe. Decay Date: 1979-06-20 . USAF Sat Cat: 10064 . COSPAR: 1977-049A. Apogee: 522 km (324 mi). Perigee: 449 km (278 mi). Inclination: 50.7000 deg. Period: 94.30 min. This marked the first time the Kapustin Yar cosmodrome was opened to capitalist countries. 20 French specialists worked on the satellite..

1977 June 23 - . 09:16 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Atlas. Launch Vehicle: Atlas F/SVS.
  • NTS 2 - . Mass: 431 kg (950 lb). Nation: USA. Agency: USAF, USN. Program: Navstar. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: NTS. Spacecraft: NTS. USAF Sat Cat: 10091 . COSPAR: 1977-053A. Apogee: 20,256 km (12,586 mi). Perigee: 20,115 km (12,498 mi). Inclination: 63.9000 deg. Period: 718.10 min.

    An Atlas booster and a Global Positioning System Stage Vehicle launched Navigation Technology Satellite 2 into orbit from Vandenberg AFB, California. This was the first use of the GPS Stage Vehicle. Navigation Technical Satellite; GPS precursor. Operated 50% satisfactorily -- still operating 25 years later.


1977 August 25 - . 23:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2313.
  • Sirio 1 - . Mass: 220 kg (480 lb). Nation: Italy. Agency: CNR. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Sirio. Spacecraft: Sirio. Completed Operations Date: 1989-09-28 . USAF Sat Cat: 10294 . COSPAR: 1977-080A. Apogee: 35,869 km (22,287 mi). Perigee: 35,755 km (22,217 mi). Inclination: 9.6000 deg. Period: 1,437.40 min.

    Experimental commsat. SIRIO (Satellite Italiano Ricerca Industriale Orientata). Launch time 2350:00 GMT. Geographical longitude of geostationary orbit 15 deg W. SIRIO is a spin stabilized geostationary experimental communications satellite. Characteristics of satellite: Weight at launch 398 kg, in orbit 218 kg. Configuration - cylindrical, height 1.981m, diameter 1.433 m, nominal life two years. Positioned in geosynchronous orbit over the Atlantic Ocean at 15 deg W in 1977-1981; over the Atlantic Ocean 25 deg W in 1981-1983; over the Indian Ocean 65 deg E in 1983-1985 As of 4 September 2001 located at 86.65 deg E drifting at 0.265 deg E per day. As of 2007 Mar 11 located at 75.38E drifting at 0.003E degrees per day.


1977 September 13 - . 23:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914. FAILURE: Vehicle exploded, probably SRM case.. Failed Stage: 0.
  • OTS 1 - . Mass: 865 kg (1,906 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ECS/OTS. Spacecraft: ECS/OTS. Decay Date: 1977-09-13 . Orbital Test Satellite; failed to orbit..

1977 September 24 - . 16:30 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Intercosmos 17 - . Payload: AUOS-Z-R-E-IK. Mass: 550 kg (1,210 lb). Nation: Russia. Agency: IK. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. Completed Operations Date: 1979-01-16 . Decay Date: 1979-11-08 . USAF Sat Cat: 10376 . COSPAR: 1977-096A. Apogee: 514 km (319 mi). Perigee: 466 km (289 mi). Inclination: 83.0000 deg. Period: 94.40 min. Investigation of energetic charged and neutral particles and micrometeorite fluxes in circumterrestrial space. .

1978 March 5 - . 17:54 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2910.
  • PIX - . Payload: PIX 1 / Delta 139. Mass: 350 kg (770 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: PIX. Spacecraft: PIX. Decay Date: 1981-01-27 . USAF Sat Cat: 10704 . COSPAR: 1978-026C. Apogee: 920 km (570 mi). Perigee: 903 km (561 mi). Inclination: 99.1000 deg. Period: 103.20 min. Plasma Interaction Experiment. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1978 April 7 - . 22:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.
  • Yuri 1 - . Payload: BSE-1. Mass: 678 kg (1,494 lb). Nation: Japan. Agency: NASDA. Program: BS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Yuri. Spacecraft: Yuri. Completed Operations Date: 1982-01-28 . USAF Sat Cat: 10792 . COSPAR: 1978-039A. Apogee: 35,868 km (22,287 mi). Perigee: 35,736 km (22,205 mi). Inclination: 11.7000 deg. Period: 1,436.90 min.

    Experimental comsat. Medium-scale broadcasting satellite for experimental purposes (BSE). Launch vehicle Delta 2914-140. Launch time 2201 GMT. Location 110 deg E. Characteristics of satellite: Weight approx 355 kg in an early stage in orbit. Configuration - box shaped satelli te with 2 solar array panels with overall span of 8.95m. Height 3.09m, width 1.32m, length 1.19m. 3-axis stabilized attitude control. Expected life 3 years. Positioned in geosynchronous orbit over the Indian Ocean at 110 deg E in 1978-1982 As of 4 September 2001 located at 44.59 deg E drifting at 0.116 deg E per day. As of 2007 Mar 11 located at 108.19E drifting at 0.031E degrees per day.


1978 May 11 - . 22:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.
  • OTS 2 - . Payload: OTS 2. Mass: 865 kg (1,906 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ECS/OTS. Spacecraft: ECS/OTS. Completed Operations Date: 1991-01-02 . USAF Sat Cat: 10855 . COSPAR: 1978-044A. Apogee: 36,128 km (22,448 mi). Perigee: 36,085 km (22,422 mi). Inclination: 13.1000 deg. Period: 1,452.50 min.

    Orbital Test Satellite; replacement for OTS-A; communications experiments. European Space Agency satellite. Launch time 2259 GMT. Reached definitive position, 10 deg east longitude, on May 24 at 0800 GMT. Launch by US Delta rocket. Positioned in geosynchronous orbit over the Atlantic Ocean at 10 deg E in 1978-1982 over the Atlantic Ocean 5 deg E in 1982-1990 As of 30 August 2001 located at 18.51 deg W drifting at 4.070 deg W per day. As of 2007 Mar 9 located at 39.02E drifting at 4.083W degrees per day.


1978 October 24 - . 19:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Intercosmos 18 - . Payload: AUOS-Z-M-IK. Mass: 1,050 kg (2,310 lb). Nation: Russia. Agency: IK. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. Completed Operations Date: 1981-03-18 . Decay Date: 1981-03-17 . USAF Sat Cat: 11082 . COSPAR: 1978-099A. Apogee: 757 km (470 mi). Perigee: 403 km (250 mi). Inclination: 83.0000 deg. Period: 96.30 min.

    Conduct of complex investigations on the interaction between the magnetosphere and ionosphere of the earth. Launched under the Intercosmos programme by the USSR in cooperation with the Czechoslovak Socialist Republic, the German Democratic Republic, the H ungarian People's Republic, the Polish People's Republic and the Socialist Republic of Romania. On 14 Nov 1978, Magion, a small Czechoslovak scientific satellite, separated from object 1296.


1979 January 30 - . 21:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.
  • SCATHA - . Payload: P 78-2. Mass: 360 kg (790 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: SCATHA. Spacecraft: SCATHA. Completed Operations Date: 1991-05-28 . USAF Sat Cat: 11256 . COSPAR: 1979-007A. Apogee: 42,860 km (26,630 mi). Perigee: 28,018 km (17,409 mi). Inclination: 10.2000 deg. Period: 1,418.40 min.

    Flight P78-2 was successfully launched by SAMSO's Space Test Program. The mission was designated SCATHA (Spacecraft Charging at High Altitudes) and gathered data on the build-up of electrical charges on satellites operating at geosynchronous altitude. It was sponsored jointly by NASA and the Air Force. Spacecraft charging experiments. The SCATHA spacecraft had two charged particle injection systems, one of which was the Satellite Positive-Ion-Beam System (SPIBS). This was a xenon ion source which included some of the technologies used in thrusters: however, the discharge chamber was not performance optimized as was done with ion engines. Maximum operating power was 0.045 kW, and the ion source could produce a thrust of about 0.14 mN at a specific impulse of 350 s. Ions could be ejected at 1 keV or 2 keV. Neutralization was accomplished by a tantalum filament. The specific impulse was low because there was no attempt to optimize the propellant efficiency. The SPIBS system was ground-tested for a period of 600 hours. The SCATHA spacecraft was placed in a near geosynchronous orbit. Ion beam operations were performed intermittently over a 247 day period. The SCATHA flight demonstrated that a charged spacecraft, and the dielectric surfaces on it, could be safely discharged by emitting a very low energy (<50 eV) neutral plasma -- in effect shorting the spacecraft to the ambient plasma before dangerous charging levels could be reached. As of 28 August 2001 located at 153.98 deg W drifting at 4.513 deg E per day. As of 2007 Mar 8 located at 19.65W drifting at 4.513E degrees per day.


1979 February 6 - . 08:46 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1. FAILURE: Third stage collided with ECS a.. Failed Stage: 3.
  • Ayame 1 - . Payload: ECS a; ECS 1. Mass: 260 kg (570 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Ayame. Spacecraft: Ayame. Completed Operations Date: 1979-02-09 . USAF Sat Cat: 11261 . COSPAR: 1979-009A. Apogee: 37,278 km (23,163 mi). Perigee: 29,407 km (18,272 mi). Inclination: 5.6000 deg. Period: 1,313.10 min.

    Experimental Communications Satellite. Experimental Communications Satellite (ECS). Launch time 0846 GMT. ECS was injected into the planned transfer orbit. On 9 Feb, however, ECS ceased radio transmissions about 10 seconds after the apogee kick motor was fired. Communicat ions and propagation experiments of satellite-communication systems. Operation and control experiment for geostationary satellites. Mass at launch 260 kg. Configuration - cylindrical. Height 1.9m including antenna. Diameter 1.4m. Spin stabilized. Last known longitude (13 June 1995) 146.23 deg W drifting at 33.817 deg E per day.


1979 February 27 - . 17:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Intercosmos 19 - . Payload: AUOS-Z-I-IK. Mass: 1,015 kg (2,237 lb). Nation: Russia. Agency: IK. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. Completed Operations Date: 1982-04-27 . Decay Date: 2002-09-23 . USAF Sat Cat: 11285 . COSPAR: 1979-020A. Apogee: 711 km (441 mi). Perigee: 452 km (280 mi). Inclination: 74.0000 deg. Period: 96.30 min.

    Comprehensive investigations of the structure of the earth's ionosphere, the characteristics of wave processes and the propagation of radio waves in the ionospheric plasma. Launched under the Intercosmos programme by the USSR in cooperation with the Peopl e's Republic of Bulgaria, the Czechoslovak Socialist Republic, the Hungarian People's Republic and the Polish People's Republic. Additional Details: here....


1979 August 10 - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: ASLV. Launch Vehicle: SLV-3. FAILURE: Thrust vectoring of second stage failed.. Failed Stage: 2.
  • Rohini 1A - . Payload: Rohini RS-1. Nation: India. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Rohini 1A. Spacecraft: Rohini 1A. Decay Date: 1979-08-19 .

1979 November 1 - . 08:05 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Intercosmos 20 - . Payload: AUOS-Z-R-P-IK. Mass: 1,100 kg (2,400 lb). Nation: Russia. Agency: IK. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. Completed Operations Date: 1980-12-11 . Decay Date: 1981-03-03 . USAF Sat Cat: 11609 . COSPAR: 1979-096A. Apogee: 519 km (322 mi). Perigee: 462 km (287 mi). Inclination: 74.1000 deg. Period: 94.40 min.

    Testing of methods for comprehensive study of the oceans and the surface of the earth, and testing of automatic gathering of scientific information from experimental sea and land stations. Launched under the INTERCOSMOS programme by the Soviet Union toget her with the Czechoslovak Socialist Republic, the German Democratic Republic, the Hungarian People's Republic and the Socialist Republic of Romania.


1979 December 24 - . 17:14 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA1. LV Family: Ariane. Launch Vehicle: Ariane 1.
  • CAT 1 - . Payload: CAT 01. Mass: 1,602 kg (3,531 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: CAT. Spacecraft: CAT. Decay Date: 1982-11-14 . USAF Sat Cat: 11645 . COSPAR: 1979-104A. Apogee: 14,047 km (8,728 mi). Perigee: 125 km (77 mi). Inclination: 17.8000 deg. Period: 259.10 min.

    Launch vehicle test. Technological Capsule (CAT). ESA registration number: ESA/79/2. Principal mission of the technological capsule (with ballast), which was equipped with batteries having a lifetime of approximately 8 orbits, was to transmit back to earth technological data on the first developmental flight L01 of the ARIANE launch vehicle. When the batteries were exhausted, the capsule ended its radio transmissions, and it is now inoperative but still in orbit.


1980 February 17 - . 00:40 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3S.
  • Tansei 4 - . Payload: MS T4. Mass: 134 kg (295 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Tansei. Spacecraft: Tansei. Decay Date: 1983-05-12 . USAF Sat Cat: 11706 . COSPAR: 1980-015A. Apogee: 608 km (377 mi). Perigee: 517 km (321 mi). Inclination: 38.7000 deg. Period: 95.90 min.

1980 February 22 - . 08:35 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.
  • Ayame 2 - . Payload: ECS b; ECS 2. Mass: 260 kg (570 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Ayame. Spacecraft: Ayame. Completed Operations Date: 1980-02-24 . USAF Sat Cat: 11715 . COSPAR: 1980-018A. Apogee: 36,839 km (22,890 mi). Perigee: 32,785 km (20,371 mi). Inclination: 1.4000 deg. Period: 1,386.60 min. Last known longitude (17 November 1988) 146.47 deg W drifting at 12.888 deg E per day..

1980 May 23 - . 14:29 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA1. LV Family: Ariane. Launch Vehicle: Ariane 1. FAILURE: Stage 1 combustion instability.. Failed Stage: 1.
  • Firewheel - . Payload: Feuerrad. Nation: France. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Firewheel. Spacecraft: Firewheel. Decay Date: 1980-05-23 .

1981 February 6 - . 08:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Intercosmos 21 - . Payload: AUOS-Z-R-P-IK. Mass: 550 kg (1,210 lb). Nation: Russia. Agency: IK. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. Completed Operations Date: 1982-06-02 . Decay Date: 1982-07-07 . USAF Sat Cat: 12162 . COSPAR: 1981-011A. Apogee: 506 km (314 mi). Perigee: 469 km (291 mi). Inclination: 74.0000 deg. Period: 94.40 min.

    Oceanographic, terrestrial studies. Development of methods for comprehensive study of the oceans and the surface of the earth, and testing of the experimental system of automatic gathering of scientific information from sea and land stations. Launched under the INTERCOSMOS programme by the USSR together with the Czechoslovak Socialist Republic, the German Democratic Republic, the Hungarian People's Republic and the Socialist Republic of Romania.


1981 February 11 - . 08:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.
  • Kiku 3 - . Payload: ETS 4. Mass: 640 kg (1,410 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS. Spacecraft: ETS. USAF Sat Cat: 12295 . COSPAR: 1981-012A. Apogee: 16,237 km (10,089 mi). Perigee: 305 km (189 mi). Inclination: 28.5000 deg. Period: 294.10 min.

    Kiku 3 (ETS-IV). Launching organization NASDA. Acquisition of the technology to handle a large-scale heavy satellite and test of the functions of on-board equipment and devices, as well as confirmation of the launching capacity of the N-II launch vehicle. Also tested ion thruster.


1981 May 31 - . 05:00 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: ASLV. Launch Vehicle: SLV-3. FAILURE: Partial Failure.. Failed Stage: U.
  • Rohini 2 - . Payload: Rohini RS-D-1. Nation: India. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Rohini 2. Spacecraft: Rohini 2. Decay Date: 1981-05-31 . USAF Sat Cat: 12491 . COSPAR: 1981-051A. Apogee: 374 km (232 mi). Perigee: 181 km (112 mi). Inclination: 46.2000 deg. Period: 90.06 min. Orbit too low..

1981 June 19 - . 12:32 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA1. LV Family: Ariane. Launch Vehicle: Ariane 1.
  • CAT 3 - . Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: CAT. Spacecraft: CAT. USAF Sat Cat: 12546 . COSPAR: 1981-057C. Apogee: 26,528 km (16,483 mi). Perigee: 261 km (162 mi). Inclination: 10.7000 deg. Period: 461.20 min.

    Launch vehicle test payload. Technological capsule. ESA registration ESA/81/02. Launch time 1233:03 UT. The technological capsule, equipped with batteries for a lifetime of about six orbital revolutions, transmits to earth technological data about test flight L-03 of ARIANE. After di scharge of the battery the capsule will stop its transmissions and remain in orbit on inactive status. Frequency 136-138 MHz (transmission until 65h after launch only). Projected time of reentry 1986.


1981 September 19 - . 21:28 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: Feng Bao 1.
  • SJ-2A - . Payload: Shi Jian 2B. Mass: 257 kg (566 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SJ. Spacecraft: SJ. Decay Date: 1981-09-26 . USAF Sat Cat: 12842 . COSPAR: 1981-093A. Apogee: 1,598 km (992 mi). Perigee: 232 km (144 mi). Inclination: 59.5000 deg. Period: 103.30 min.
  • SJ-2B - . Payload: Shi Jian C. Mass: 28 kg (61 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SJ. Spacecraft: SJ. Decay Date: 1982-10-06 . USAF Sat Cat: 12843 . COSPAR: 1981-093B. Apogee: 1,615 km (1,003 mi). Perigee: 233 km (144 mi). Inclination: 59.4000 deg. Period: 103.50 min. Balloon for drag studies..
  • SJ-2 - . Payload: Shi Jian 2. Mass: 483 kg (1,064 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SJ. Spacecraft: SJ. Decay Date: 1982-08-17 . USAF Sat Cat: 12845 . COSPAR: 1981-093D. Apogee: 1,608 km (999 mi). Perigee: 232 km (144 mi). Inclination: 59.4000 deg. Period: 103.40 min.

1981 September 21 - . 13:10 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32/1. LV Family: R-36. Launch Vehicle: Tsiklon-3.
  • Oreol 3 - . Payload: AUOS-Z M-A-IK s/n 401. Mass: 1,000 kg (2,200 lb). Nation: France. Agency: RVSN. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. USAF Sat Cat: 12848 . COSPAR: 1981-094A. Apogee: 1,672 km (1,038 mi). Perigee: 394 km (244 mi). Inclination: 82.5000 deg. Period: 105.80 min.

    Carried Soviet/French magnetosphere and ionosphere experiments. Investigation of physical processes in the earth's magnetosphere and ionosphere, and study of the nature of polar aurorae. Carried scientific equipment developed by Soviet and French specialists under the joint Soviet-French project 'Arkad-3'.


1981 December 20 - . Launch Site: Kourou. Launch Complex: Kourou ELA1. LV Family: Ariane. Launch Vehicle: Ariane 1.
  • Tech. capsule - . Payload: CAT/Thesee. Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: CAT. Spacecraft: CAT. Decay Date: 1988-11-21 . USAF Sat Cat: 13025 . COSPAR: 1981-122C. Apogee: 36,051 km (22,401 mi). Perigee: 199 km (123 mi). Inclination: 10.6000 deg. Period: 636.00 min.

    Ariane L-04 technological capsule, ESA designator ESA/81/04. The technological capsule, equipped with batteries for a lifetime of about 6 orbital revolutions (65h), transmits to earth technological data about test flight L-04 of Ariane. After discharge of the battery the capsule will stop its transmissions and remain in orbit in an inactive status. Frequency 136-138 MHz, projected time of reentry before 1990.

  • CAT 4 - . Payload: MARECS 1 / CAT 4. Mass: 217 kg (478 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: CAT. Spacecraft: CAT. USAF Sat Cat: 13011 . COSPAR: 1981-122B. Apogee: 30,744 km (19,103 mi). Perigee: 259 km (160 mi). Inclination: 10.4000 deg. Period: 536.80 min. Launch vehicle test payload. .

1982 September 3 - . 05:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.
  • Kiku 4 - . Payload: ETS 3. Mass: 385 kg (848 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS. Spacecraft: ETS. USAF Sat Cat: 13492 . COSPAR: 1982-087A. Apogee: 1,006 km (625 mi). Perigee: 988 km (613 mi). Inclination: 44.6000 deg. Period: 105.10 min.

    Engineering test satellite. Engineering Test Satellite III (ETS-III) launched 0500 GMT 3 Sep 1982 from Osaki launch site, Tanegashima. Launching organization: National Space Development Agency of Japan (NASDA). Verification of three axis attitude control function; verification of so lar array paddle deployment function; verification of active thermal control function; functional test of mission equipment in the space. N launch vehicle flight no 9.


1984 February 3 - . 13:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: MLP2. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • IRT - . Payload: Challenger F4 / Westar 6 [PAM-D] / Palapa B2 [PAM-. Mass: 91 kg (200 lb). Nation: USA. Agency: NASA Houston. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: IRT. Spacecraft: IRT. Decay Date: 1984-02-11 . USAF Sat Cat: 14689 . COSPAR: 1984-011C. Apogee: 288 km (178 mi). Perigee: 279 km (173 mi). Inclination: 28.5000 deg. Period: 90.20 min. Deployed from STS 41B on 5 February 1984; Integrated Rendezvous Target..

1985 January 7 - . 19:26 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II.
  • SS-10 Sagikake - . Payload: MS T5. Mass: 141 kg (310 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Tansei. Spacecraft: Tansei. USAF Sat Cat: 15464 . COSPAR: 1985-001A.

    Sakigake ('Pioneer') was a test spacecraft similar to Suisei (Planet-A). Objectives were :verification of fundamental technology related to interplanetary missions, including deep-space communication, attitude control, attitude determination; study and observation of solar wind and plasma waves and interplanetary magnetic field. It carried three instruments to measure plasma wave spectra, solar wind ions, and interplanetary magnetic fields. The spacecraft was spin-stabilized at two different rates (5 and 0.2 rpm). It was equipped with hydrazine thrusters for attitude and velocity control, star and sun sensors for attitude determination, and a mechanically despun off-set parabolic dish for long-range communication. Launched into an initial heliocentric orbit with a period of 318.8 days, at 151.4 x 121.9 million km (0.815 x 1.012 AU), 1.439 degree inclination. Flew by Comet Halley on its sunward side at a distance of about 7 million kilometers on March 11, 1986. It later made an Earth swingby on January 8, 1992 with a closest approach of 88,997 km. This was the first planet-swingby for a Japanese spacecraft. During the approach, Sakigake observed the geotail, with passage occurring at 290 Re on 14 June 1993 before ISTP's multi-spacecraft investigation of that region. The second Earth swingby was on June 14, 1993 at 40 Re, and the third on October 28, 1994 at 86 Re. Almost no hydrazine remained so no further maneuvers were accomplished. Telemetry contact was lost on 15 November 1995 at a distance of 106 million km. Future mission planning had included a 23.6 km/s, 10,000 km flyby of Comet Honda-Mrkos-Pajdusakova on Feb 3, 1996 (approaching the nucleus along the tail) some 0.17 AU from the Sun, and a 14 million km passage of Comet Giacobini-Zinner on Nov 29, 1998.


1985 November 27 - . 00:29 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: MLP2. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • OEX Target - . Payload: Atlantis F2 / Aussat A2 [PAM-D] / Morelos 2 [PAM-D. Mass: 16 kg (35 lb). Nation: USA. Agency: NASA Houston. Program: STS. Class: Technology. Type: Technology satellite. Spacecraft Bus: OEX Target. Spacecraft: OEX Target. Decay Date: 1987-03-02 . USAF Sat Cat: 16277 . COSPAR: 1985-109E. Apogee: 386 km (239 mi). Perigee: 373 km (231 mi). Inclination: 28.4000 deg. Period: 92.10 min. Released from STS 61B 11/30/85; shuttle autopilot software test target. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1986 August 12 - . 20:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.
  • MABES - . Payload: Jindai/LE-5. Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MABES. Spacecraft: MABES. USAF Sat Cat: 16910 . COSPAR: 1986-061C. Apogee: 1,604 km (996 mi). Perigee: 1,483 km (921 mi). Inclination: 50.0000 deg. Period: 117.00 min. MABES (Jindai). Experiment on the levitation of the magnetic bearing flywheel under zero-g condition. .

1986 December 18 - . 08:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32. Launch Pad: LC32/2. LV Family: R-36. Launch Vehicle: Tsiklon-3.
  • Cosmos 1809 - . Payload: AUOS-Z Ionozond-E s/n 501. Mass: 700 kg (1,540 lb). Nation: Russia. Agency: MOM. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. USAF Sat Cat: 17241 . COSPAR: 1986-101A. Apogee: 961 km (597 mi). Perigee: 941 km (584 mi). Inclination: 82.5000 deg. Period: 104.10 min. Development of research apparatus and methods of remote sensing and monitoring of the Earth's ionosphere, and also study of the propagation of radio waves in the ionosphere. .

1987 August 27 - . 09:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.
  • Kiku 5 - . Payload: ETS 5. Mass: 550 kg (1,210 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS. Spacecraft: ETS. Completed Operations Date: 1997-09-10 . USAF Sat Cat: 18316 . COSPAR: 1987-070A. Apogee: 36,072 km (22,414 mi). Perigee: 36,029 km (22,387 mi). Inclination: 7.9000 deg. Period: 1,449.60 min.

    Stationed at 150 deg E. ETS-V (Kiku-5). Establishment of basic technology for bus systems needed for 3-axis stabilized geostationary satellites. Accumulation of key technologies required for high performance in the next generation of applications satellites; Experiment of mobile satellite communications for the control of aircrafts over the Pacific Ocean, and for the communication, navigational aid, search and rescue of ships. H-I (3-stage) launch vehicle. Launching organization NASDA. Launch time 0920 GMT. Positioned in geosynchronous orbit at 150 deg E in 1987-1997 As of 5 September 2001 located at 92.55 deg W drifting at 3.394 deg W per day. As of 2007 Mar 10 located at 49.74W drifting at 3.380W degrees per day.


1988 September 6 - . 20:30 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4.
  • FY-1A - . Payload: Feng Yun 1A. Mass: 750 kg (1,650 lb). Nation: China. Agency: MAI. Class: Technology. Type: Weather technology satellite. Spacecraft Bus: FY-1. Spacecraft: FY-1. USAF Sat Cat: 19467 . COSPAR: 1988-080A. Apogee: 895 km (556 mi). Perigee: 875 km (543 mi). Inclination: 98.8000 deg. Period: 102.70 min. Experimental weather satellite. First use of new launch site and launch vehicle. Failed after 38 days due to problems with attitude control system..

1988 September 19 - . 09:32 GMT - . Launch Site: Palmachim. LV Family: Jericho. Launch Vehicle: Shaviyt.
  • Ofeq-1 - . Mass: 155 kg (341 lb). Nation: Israel. Agency: ISA. Program: Ofeq. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Ofeq. Spacecraft: Ofeq 1-2. Decay Date: 1989-01-14 . USAF Sat Cat: 19519 . COSPAR: 1988-087A. Apogee: 1,149 km (713 mi). Perigee: 250 km (150 mi). Inclination: 142.9000 deg. Period: 98.80 min.

    First Israeli launch; possibly experimental surveillance mission. Experimental satellite 'Offeq-1'. Launch time 0934 GMT. Location: site on the coast south of Tel-Aviv. Launching organization: Israel Aircraft Industries, Ltd (IAI) and Israeli Space Agency (ISA). Function: 1) Experimentation in generation of solar power; 2) Experimentation in transmission reception from space; 3) Verification of system's ability to withstand vacuum and weightless conditions; 4) Data collection on space environment conditions and Earth's magnetic field.


1988 November 15 - . 03:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC110L. LV Family: Buran. Launch Vehicle: Buran launch vehicle.
  • 37KB module s/n 37070 - . Payload: 37KB s/n 37070. Mass: 7,150 kg (15,760 lb). Nation: Russia. Agency: UNKS. Program: Buran. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: 37K. Spacecraft: 37KB. COSPAR: 1988-100xx.

1989 July 12 - . 00:14 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA1. LV Family: Ariane. Launch Vehicle: Ariane 3.
  • Olympus-1 - . Payload: Olympus F1. Mass: 2,595 kg (5,720 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Olympus. Spacecraft: Olympus. Completed Operations Date: 1993-08-23 . USAF Sat Cat: 20122 . COSPAR: 1989-053A. Apogee: 35,817 km (22,255 mi). Perigee: 35,758 km (22,218 mi). Inclination: 1.2000 deg. Period: 1,436.20 min.

    Commsat technology demonstration;19 deg W. Olympus-1 is a multi-payload communications satellite for direct TV broadcast in the bands of the 1977 Geneva Plan of the International Telecommunications Union (ITU) (including a national beam to Italy) plus communication transponde rs in the 14/12 GHz, 2nd 30/20 GHz bands. The latter are also used for a data relay experiment with ESA's EURECA satellite. Position on geostationary orbit 341 deg E. Launch time 0014:00 UT. Positioned in geosynchronous orbit at 19 deg W in 1989-1991; 19 deg W in 1991-1993 As of 4 September 2001 located at 82.22 deg E drifting at 3.961 deg E per day. As of 2007 Mar 10 located at 118.63E drifting at 3.947E degrees per day.


1989 September 28 - . 00:04 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32/2. LV Family: R-36. Launch Vehicle: Tsiklon-3.
  • Intercosmos 24 - . Payload: AUOS-Z-AV-IK s/n 201. Mass: 1,000 kg (2,200 lb). Nation: Russia. Agency: MOM. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. Completed Operations Date: 1995-10-11 . USAF Sat Cat: 20261 . COSPAR: 1989-080A. Apogee: 2,414 km (1,499 mi). Perigee: 499 km (310 mi). Inclination: 82.6000 deg. Period: 115.00 min.

    US participation; particles and fields experiments; deployed Magion 2. Comprehensive study of the processes of propagation of low-frequency electromagnetic waves in the earth's magnetosphere and their interaction with charged particles of the radiation belts, in cooperation with Bulgaria, Czechoslovakia, the German Democrati c Republic, Hungary, Poland and Romania (the international scientific project entitled 'Aktivny'). Carrying the Czechoslovak Magion-2 satellite.


1990 February 7 - . 01:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.
  • Debut - . Payload: Orizuru. Mass: 50 kg (110 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Debut. Spacecraft: Debut. USAF Sat Cat: 20479 . COSPAR: 1990-013B. Apogee: 1,743 km (1,083 mi). Perigee: 911 km (566 mi). Inclination: 99.0000 deg. Period: 112.20 min. Boom, umbrella test. DEBUT 'Orizuru'. Experiment of extending and contracting boom; experiment of expanding and contracting aerodynamic brake. Launching organization NASDA. Launch time 0133 UT..

1990 April 3 - . 12:02 GMT - . Launch Site: Palmachim. LV Family: Jericho. Launch Vehicle: Shaviyt.
  • Ofeq-2 - . Mass: 160 kg (350 lb). Nation: Israel. Agency: ISA. Program: Ofeq. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Ofeq. Spacecraft: Ofeq 1-2. Decay Date: 1990-07-09 . USAF Sat Cat: 20540 . COSPAR: 1990-027A. Apogee: 251 km (155 mi). Perigee: 149 km (92 mi). Inclination: 143.2000 deg. Period: 88.50 min. Communication experiments. .

1990 April 11 - . 15:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Atlas. Launch Vehicle: Atlas E Altair.
  • USA 56 - . Payload: POGS & SSR. Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Stacksat P87-2. Spacecraft: Stacksat P87-2. USAF Sat Cat: 20560 . COSPAR: 1990-031A. Apogee: 745 km (462 mi). Perigee: 627 km (389 mi). Inclination: 89.8000 deg. Period: 98.48 min.

    Polar Orbiting Geomagnetic Survey satellite designed to measure the Earth's magnetic field vector as a function of position. Data from the experiment was used to improve Earth navigation systems, and was stored in an experimental solid state recorder. Six low cost ground stations were designed, built and located around the world to operate the spacecraft flown on this mission.

  • USA 58 - . Payload: SCE. Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Stacksat P87-2. Spacecraft: Stacksat P87-2. USAF Sat Cat: 20562 . COSPAR: 1990-031C. Apogee: 741 km (460 mi). Perigee: 627 km (389 mi). Inclination: 89.8000 deg. Period: 98.44 min. SCE (Selective Communications Experiment) carried a variable frequency transmitter to study ionospheric effects at various RF frequencies, and was also designed to demonstrate message store and forward techniques..
  • USA 57 - . Payload: TEX. Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Stacksat P87-2. Spacecraft: Stacksat P87-2. USAF Sat Cat: 20561 . COSPAR: 1990-031B. Apogee: 742 km (461 mi). Perigee: 627 km (389 mi). Inclination: 89.8000 deg. Period: 98.45 min. TEX (Transceiver EXperiment) carried a variable power transmitter used to study ionospheric effects on RF transmissions. Data from the experiment was used to determine minimum spacecraft transmitter power levels for transmission to ground receivers..

1990 July 16 - . 00:40 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: Chang Zheng 2E.
  • Badr-A - . Payload: Badr 1 + R&D. Mass: 52 kg (114 lb). Nation: Pakistan. Agency: Suparco. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Badr. Spacecraft: Badr. Decay Date: 1990-12-08 . USAF Sat Cat: 20685 . COSPAR: 1990-059A. Apogee: 988 km (613 mi). Perigee: 208 km (129 mi). Inclination: 28.5000 deg. Period: 96.70 min. First launch of new Chinese launch vehicle. Experimental Pakistani payload..

1990 September 3 - . 00:53 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4.
  • FY-1B - . Payload: Feng Yun 1B. Mass: 881 kg (1,942 lb). Nation: China. Agency: MAI. Class: Technology. Type: Weather technology satellite. Spacecraft Bus: FY-1. Spacecraft: FY-1. USAF Sat Cat: 20788 . COSPAR: 1990-081A. Apogee: 897 km (557 mi). Perigee: 875 km (543 mi). Inclination: 98.8000 deg. Period: 102.70 min. Experimental weather satellite. Operated for over a year..

1991 April 28 - . 11:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: MLP2. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • USA 70 - . Payload: MPEC. Nation: USA. Agency: DARPA. Program: STS. Class: Technology. Type: Military technology satellite. Spacecraft Bus: MPEC. Spacecraft: MPEC. USAF Sat Cat: 21262 . COSPAR: 1991-031C. Classified subsatellite released from shuttle..

1991 July 17 - . 01:46 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 40.
  • Tubsat-A - . Payload: Tubsat A. Mass: 38 kg (83 lb). Nation: Germany. Agency: Orbcomm. Program: Tubsat. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Tubsat. Spacecraft: Tubsat. USAF Sat Cat: 21577 . COSPAR: 1991-050D. Apogee: 772 km (479 mi). Perigee: 762 km (473 mi). Inclination: 98.5000 deg. Period: 100.20 min.

    Tubsat-A was the first satellite built at Germany's Technical University of Berlin was intended primarily to test attitude control subsystems and give students practice in the design, construction and operation of a satellite. Tubsat-A was launched piggyback with the first ERS mission, and because of it's near polar orbit, the spacecraft became an important communications tool for arctic and Antarctic expeditions. The spacecraft also acted as a testbed for some industry technology including GaAs cells and a transputer. Payload: Star Sensor, Sun Sensor, 3-Axis Magnetic Field Sensor, Magnetorquer, Store & Forward Communication. Dimensions: 38x38x38 cm. Mass: 35 kg. Still in operation as of 2003.

  • Orbcomm-X - . Payload: ERS 1 Orbcomm X. Mass: 22 kg (48 lb). Nation: USA. Agency: ESIEESPA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Orbcomm. Spacecraft: Orbcomm. USAF Sat Cat: 21576 . COSPAR: 1991-050C. Apogee: 771 km (479 mi). Perigee: 764 km (474 mi). Inclination: 98.5000 deg. Period: 100.20 min. Store and forward communication..

1991 July 17 - . 17:33 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Edwards.. Launch Platform: NB-52 008. LV Family: Pegasus. Launch Vehicle: Pegasus/HAPS. Failed Stage: G.
  • Microsat 1 - . Payload: Microsat 1 / ... / Microsat 7. Mass: 22 kg (48 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Microsat. Spacecraft: Microsat. Decay Date: 1992-01-23 . USAF Sat Cat: 21580 . COSPAR: 1991-051A. Apogee: 454 km (282 mi). Perigee: 356 km (221 mi). Inclination: 82.0000 deg. Period: 92.70 min. Test of LEO network for global communications. Air dropped in Point Arguello WADZ..
  • Microsat 2 - . Mass: 22 kg (48 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Microsat. Spacecraft: Microsat. Decay Date: 1992-01-23 . USAF Sat Cat: 21581 . COSPAR: 1991-051B. Apogee: 454 km (282 mi). Perigee: 355 km (220 mi). Inclination: 82.0000 deg. Period: 92.70 min. Test of LEO network for global communications. Air dropped in Point Arguello WADZ..
  • Microsat 3 - . Mass: 22 kg (48 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Microsat. Spacecraft: Microsat. Decay Date: 1992-01-24 . USAF Sat Cat: 21582 . COSPAR: 1991-051C. Apogee: 454 km (282 mi). Perigee: 355 km (220 mi). Inclination: 82.0000 deg. Period: 92.70 min. Test of LEO network for global communications. Air dropped in Point Arguello WADZ..
  • Microsat 4 - . Mass: 22 kg (48 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Microsat. Spacecraft: Microsat. Decay Date: 1992-01-23 . USAF Sat Cat: 21583 . COSPAR: 1991-051D. Apogee: 454 km (282 mi). Perigee: 355 km (220 mi). Inclination: 82.0000 deg. Period: 92.70 min. Test of LEO network for global communications. Air dropped in Point Arguello WADZ..
  • Microsat 5 - . Mass: 22 kg (48 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Microsat. Spacecraft: Microsat. Decay Date: 1992-01-24 . USAF Sat Cat: 21584 . COSPAR: 1991-051E. Apogee: 455 km (282 mi). Perigee: 355 km (220 mi). Inclination: 82.0000 deg. Period: 92.70 min. Test of LEO network for global communications. Air dropped in Point Arguello WADZ..
  • Microsat 6 - . Mass: 22 kg (48 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Microsat. Spacecraft: Microsat. Decay Date: 1992-01-25 . USAF Sat Cat: 21585 . COSPAR: 1991-051F. Apogee: 454 km (282 mi). Perigee: 355 km (220 mi). Inclination: 82.0000 deg. Period: 92.70 min. Test of LEO network for global communications. Air dropped in Point Arguello WADZ..
  • Microsat 7 - . Mass: 22 kg (48 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Microsat. Spacecraft: Microsat. Decay Date: 1992-01-23 . USAF Sat Cat: 21586 . COSPAR: 1991-051G. Apogee: 452 km (280 mi). Perigee: 358 km (222 mi). Inclination: 82.0000 deg. Period: 92.70 min. Test of LEO network for global communications. Air dropped in Point Arguello WADZ..

1991 December 18 - . 03:54 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32/2. LV Family: R-36. Launch Vehicle: Tsiklon-3.
  • Intercosmos 25 - . Payload: AUOS-Z APEKS-IK s/n 301. Mass: 1,000 kg (2,200 lb). Nation: Russia. Agency: MOM. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. USAF Sat Cat: 21819 . COSPAR: 1991-086A. Apogee: 2,969 km (1,844 mi). Perigee: 436 km (270 mi). Inclination: 82.6000 deg. Period: 120.50 min.

    Solar activity monitoring; hosted experiments from Germany, Romania, Bulgaria, Poland, Hungary. Comprehensive study of the effects of artificial impact of modulated electron flows and plasma beams on the ionosphere and magnetosphere of the Earth (forming part of the Apex international scientific project, conducted jointly with Bulgaria, Czechoslovak ia, Germany, Hungary, Poland and Romania.) Launched with the Czechoslovak satellite Magion-3, separated from the space object Intercosmos-25 on 28 Dec 1991, in accordance with the scientific programme of the Apex project.


1992 October 22 - . 17:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39B. Launch Platform: MLP3. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • CTA - . Payload: Columbia F13 / Lageos 2 [Iris] / CTA. Mass: 82 kg (180 lb). Nation: Canada. Agency: CSA. Program: STS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: CTA. Spacecraft: CTA. Decay Date: 1992-11-01 . USAF Sat Cat: 22214 . COSPAR: 1992-070C. Apogee: 219 km (136 mi). Perigee: 212 km (131 mi). Inclination: 28.5000 deg. Period: 88.80 min. Canadian Target Assembly; deployed from STS-52 10/22/92. .

1993 March 30 - . 03:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.
  • SEDS 1 - . Payload: SEDS 1 End Mass/Tether. Mass: 25 kg (55 lb). Nation: USA. Agency: NASA Huntsville. Class: Technology. Type: Tether technology satellite. Spacecraft Bus: SEDS. Spacecraft: SEDS. Decay Date: 1993-03-30 . USAF Sat Cat: 22582 . COSPAR: 1993-017B. Apogee: 719 km (446 mi). Perigee: 183 km (113 mi). Inclination: 36.0000 deg. Period: 93.62 min. Small Expendable-tether Deployer System. .

1994 January 25 - . 00:25 GMT - . Launch Site: Plesetsk. LV Family: R-36. Launch Vehicle: Tsiklon-3.
  • Tubsat-B - . Mass: 40 kg (88 lb). Nation: Germany. Agency: TUB. Program: Tubsat. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Tubsat. Spacecraft: Tubsat. USAF Sat Cat: 22970 . COSPAR: 1994-003B. Apogee: 1,210 km (750 mi). Perigee: 1,184 km (735 mi). Inclination: 82.6000 deg. Period: 109.40 min.

    Following the success of the magnetic torque attitude control system that flew on Tubsat-A, researchers and students at Germany's Technical University of Berlin constructed Tubsat-B to test and demonstrate attitude control with a star sensor and three reaction wheels. An on-board 1m telescope was used for astronomy and for Earth observation at 10m resolution. Dimensions of the satellite were 38x38x50 cm, mass 40 kg. Unfortunately communications with the satellite were lost after 39 Days


1994 January 25 - . 16:34 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4W. LV Family: Titan. Launch Vehicle: Titan II SLV.
  • ISA - . Payload: ISA. Nation: USA. Agency: BMDO. Class: Technology. Type: Military technology satellite. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: ISA Interstage Adapter. Decay Date: 1994-06-08 . USAF Sat Cat: 22987 . COSPAR: 1994-004C. Apogee: 126,958 km (78,887 mi). Perigee: 396 km (246 mi). Inclination: 65.8000 deg. Period: 3,075.57 min. ISA (Interstage Adapter) satellite launched with Clementine placed in a highly eccentric Earth orbit. It carried a set of space environment experiments..

1994 February 3 - . 12:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: MLP3. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • BremSat 1 - . Payload: Discovery F18 / WSF 1 / BremSat 1 / ODERACS A, .... Mass: 63 kg (138 lb). Nation: Germany. Agency: Bremen, DARA. Class: Technology. Type: Re-entry test vehicle. Spacecraft Bus: BremSat. Spacecraft: BremSat. Decay Date: 1995-02-12 . USAF Sat Cat: 22998 . COSPAR: 1994-006H. Apogee: 160 km (90 mi). Perigee: 156 km (96 mi). Inclination: 57.0000 deg. Period: 87.70 min. Atomic oxygen, dust particle, microgravity, reentry experiments. .

1994 February 3 - . 22:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II.
  • OREX - . Payload: Ryusei. Mass: 865 kg (1,906 lb). Nation: Japan. Class: Technology. Type: Re-entry test vehicle. Spacecraft Bus: OREX. Spacecraft: OREX. Decay Date: 1994-02-03 . USAF Sat Cat: 22978 . COSPAR: 1994-007A. Apogee: 451 km (280 mi). Perigee: 450 km (270 mi). Inclination: 30.5000 deg. Period: 93.50 min. Orbital Reentry Experiment. Orbital Re-entry Experiment Vehicle (OREX) Ryusei. Acquisition of data related to atmospheric reentry. Launch vehicle H-II rocket test flight H-II 1F. Launching organization NASDA. Launch time 2220:00 UT. .
  • VEP - . Payload: Myojo / LAPS. Mass: 2,391 kg (5,271 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: VEP. Spacecraft: VEP. USAF Sat Cat: 22979 . COSPAR: 1994-007B. Apogee: 36,261 km (22,531 mi). Perigee: 449 km (278 mi). Inclination: 28.6000 deg. Period: 645.00 min.

    Vehicle Evaluation Payload; monitored H-2 performance. Vehicle Evaluation Payload (VEP) MYOJO. Provides a ranging function as well as functions to measure the acceleration and deformation, in order to confirm the accuracy of the H-II rocket orbit injection and understand the environment of the payload equipme nt. Launch vehicle H-II rocket test flight H-II 1F. Launching organization NASDA. Launch time 2220:00 UT.


1994 February 8 - . 08:34 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: Chang Zheng 3A.
  • KF-1 - . Payload: Kua Fu 1 / DFH-3 mockup. Mass: 2,200 kg (4,800 lb). Nation: China. Agency: CASC. Program: Chinastar. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DFH-3. Spacecraft: DFH-3. Decay Date: 2002-02-07 . USAF Sat Cat: 23009 . COSPAR: 1994-010B. Apogee: 36,046 km (22,397 mi). Perigee: 178 km (110 mi). Inclination: 28.5000 deg. Period: 635.69 min. Mass model of DFH-3 satellite..

1994 March 2 - . 03:25 GMT - . Launch Site: Plesetsk. LV Family: R-36. Launch Vehicle: Tsiklon-3.
  • Intercosmos 26 - . Payload: AUOS-SM-KI-IK. Mass: 2,160 kg (4,760 lb). Nation: Russia. Agency: RAKA. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AUOS. Spacecraft: AUOS. Decay Date: 2001-03-04 . USAF Sat Cat: 23019 . COSPAR: 1994-014A. Apogee: 541 km (336 mi). Perigee: 501 km (311 mi). Inclination: 82.5000 deg. Period: 94.70 min.

    Solar and space physics. Conduct of comprehensive investigations of the sun under the Koronas-I international project developed by Russian and Ukranian experimts in cooperation with specialists from Poland, the Czech Republic, the Slovak Republic, Bulgaria, France, and the United Kingdom.


1994 March 13 - . 22:32 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Taurus. Launch Vehicle: ARPA Taurus.
  • USA 102 - . Payload: DarpaSat. Mass: 203 kg (447 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DARPASAT. Spacecraft: DARPASAT. USAF Sat Cat: 23031 . COSPAR: 1994-017B. Apogee: 556 km (345 mi). Perigee: 532 km (330 mi). Inclination: 105.0000 deg. Period: 95.50 min. GPS receiver and data processor technology tests. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1994 June 17 - . 07:07 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44LP.
  • STRV-1B - . Mass: 50 kg (110 lb). Nation: UK. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STRV. Spacecraft: STRV. USAF Sat Cat: 23125 . COSPAR: 1994-034B. Apogee: 31,817 km (19,770 mi). Perigee: 278 km (172 mi). Inclination: 7.5000 deg. Period: 557.00 min. 50 cm cube; Space Technology and Research Vehicle; included solar cell tests..
  • STRV-1A - . Mass: 53 kg (116 lb). Nation: UK. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STRV. Spacecraft: STRV. USAF Sat Cat: 23126 . COSPAR: 1994-034C. Apogee: 31,321 km (19,461 mi). Perigee: 273 km (169 mi). Inclination: 7.4000 deg. Period: 547.70 min. 50 cm cube; Space Technology and Research Vehicle; included solar cell tests..

1994 August 3 - . 14:38 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Edwards.. Launch Platform: NB-52 008. LV Family: Pegasus. Launch Vehicle: Pegasus.
  • P90-6 APEX - . Payload: APEX/Orion 38. Mass: 260 kg (570 lb). Nation: USA. Agency: USAF STP. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: APEX. Spacecraft: APEX. USAF Sat Cat: 23191 . COSPAR: 1994-046A. Apogee: 2,534 km (1,574 mi). Perigee: 360 km (220 mi). Inclination: 69.9800 deg. Period: 114.82 min. Advanced Photovoltaic and Electronic Experiments; studied radiation and plasma effects on solar power systems. Air dropped in Point Arguello WADZ..

1994 August 28 - . 07:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. FAILURE: LAPS apogee kick motor failed to ignite. Partial Failure.. Failed Stage: 3.
  • Kiku 6 - . Payload: ETS 6. Mass: 3,800 kg (8,300 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS. Spacecraft: ETS. USAF Sat Cat: 23230 . COSPAR: 1994-056A. Apogee: 38,677 km (24,032 mi). Perigee: 8,565 km (5,322 mi). Inclination: 13.2300 deg. Period: 861.84 min. Failed to reach geostationary orbit; Engineering Test Satellite; partial mission success. Also tested ion engines for NSSK..

1995 March 28 - . 10:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC158. LV Family: Topol. Launch Vehicle: Start. FAILURE: Fell in Sea of Okhotsk.. Failed Stage: 3.
  • Gurwin 1 - . Payload: TECHSAT-1. Mass: 50 kg (110 lb). Nation: Israel. Agency: RVSN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Gurwin. Spacecraft: Gurwin. Decay Date: 1995-03-28 .
  • EKA - . Payload: EKA-2. Nation: Russia. Agency: RVSN. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: EKA. Spacecraft: EKA. Eksperimentalniy Kosmicheskiy Apparat - dummy of test satellite..

1995 June 22 - . 19:58 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Vandenberg.. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL. FAILURE: Second stage failure; destroyed by range safety.. Failed Stage: 2.
  • STEP 3 - . Payload: STEP M3. Mass: 267 kg (588 lb). Nation: USA. Agency: USAF. Program: STEP. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STEP. Spacecraft: STEP. Decay Date: 1995-06-22 . Apogee: 144 km (89 mi). Space Test Experiment Platform. Air dropped in Point Arguello WADZ..

1995 July 7 - . 16:23 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 40.
  • UPM/LBSAT 1 - . Mass: 47 kg (103 lb). Nation: Spain. Agency: UPM. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: LBSAT. Spacecraft: LBSAT. USAF Sat Cat: 23607 . COSPAR: 1995-033C. Apogee: 676 km (420 mi). Perigee: 663 km (411 mi). Inclination: 98.1000 deg. Period: 98.10 min. Universidad Politecnia de Madrid Satellite; experimental communications, microgravity experiments..

1995 November 4 - . 14:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10.
  • SURFSAT - . Payload: SURFSAT/Delta 229. Mass: 55 kg (121 lb). Nation: USA. Agency: MDAC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SURFSAT-1. Spacecraft: SURFSAT-1. USAF Sat Cat: 23711 . COSPAR: 1995-059B. Apogee: 1,494 km (928 mi). Perigee: 934 km (580 mi). Inclination: 100.6000 deg. Period: 109.70 min. Test satellite for NASA's Deep Space Network..

1995 December 28 - . 06:45 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Molniya 8K78M.
  • Skipper - . Mass: 250 kg (550 lb). Nation: Russia. Agency: BMDO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Skipper. Spacecraft: Skipper. USAF Sat Cat: 23752 . COSPAR: 1995-072B. Apogee: 813 km (505 mi). Perigee: 804 km (499 mi). Inclination: 98.6000 deg. Period: 101.10 min. Aerobraking investigation; satellite provided by Russia, instruments by Utah State University; solar array shorted immediately following deployment and ended mission..

1996 January 11 - . 09:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39B. Launch Platform: MLP1. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • OAST-Flyer - . Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: OAST-Flyer. Spacecraft: OAST-Flyer. Decay Date: 1996-01-20 . USAF Sat Cat: 23763 . COSPAR: 1996-001B. Apogee: 311 km (193 mi). Perigee: 301 km (187 mi). Inclination: 28.5000 deg. Period: 90.60 min. GPS receiver, amateur radio tests; examined effect of solar radiation on satellite explosive devices; deployed from STS 72 1/14/96; retrieved 1/16/96..

1996 February 22 - . 20:18 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39B. Launch Platform: MLP3. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • TSS-1 - . Payload: TSS-1R. Nation: Italy. Agency: ASI. Program: STS. Class: Technology. Type: Tether technology satellite. Spacecraft Bus: TSS. Spacecraft: TSS. Decay Date: 1996-03-19 . USAF Sat Cat: 23805 . COSPAR: 1996-012B. Apogee: 189 km (117 mi). Perigee: 173 km (107 mi). Inclination: 28.5000 deg. Period: 88.10 min. LEO. Tether deployment test; 20 km long tether; satellite unintentionally deployed when tether broke 2/25/96 Reentered Mar 19..

1996 May 12 - . 21:32 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Titan. Launch Vehicle: Titan 403A.
  • USA 123 - . Payload: TIPS Ralph. Mass: 54 kg (119 lb). Nation: USA. Agency: NRL, NRO. Class: Technology. Type: Tether technology satellite. Spacecraft Bus: TiPS. Spacecraft: TIPS. USAF Sat Cat: 23936 . COSPAR: 1996-029E. Apogee: 1,032 km (641 mi). Perigee: 1,010 km (620 mi). Inclination: 63.4000 deg. ??? .
  • USA 124 - . Payload: TIPS Norton. Mass: 54 kg (119 lb). Nation: USA. Agency: NRL, NRO. Class: Technology. Type: Tether technology satellite. Spacecraft Bus: TiPS. Spacecraft: TIPS. USAF Sat Cat: 23937 . COSPAR: 1996-029F. Apogee: 1,032 km (641 mi). Perigee: 1,010 km (620 mi). Inclination: 63.4000 deg.

1996 May 19 - . 10:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39B. Launch Platform: MLP1. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • IAE - . Payload: Inflatable Antenna Experiment. Nation: USA. Agency: JPL. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: IAE satellite. Spacecraft: IAE satellite. Decay Date: 1996-05-22 . USAF Sat Cat: 23872 . COSPAR: 1996-032C. Apogee: 201 km (124 mi). Perigee: 180 km (110 mi). Inclination: 39.1000 deg. Period: 88.30 min. LEO. Inflatable Antenna Experiment; deployed from Spartan 207 5/20/96; test of inflatable antenna technology. Reentered May 22..
  • PAMS STU - . Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: PAMS. Spacecraft: PAMS. Decay Date: 1996-10-26 . USAF Sat Cat: 23876 . COSPAR: 1996-032D. Apogee: 138 km (85 mi). Perigee: 132 km (82 mi). Inclination: 39.0000 deg. Period: 87.20 min. LEO. Passive Aerodynamically Stabilized Magnetically Damped Satellite; deployed from STS 77 5/22/96; attitude control technology test. Reentered Oct 26..

1996 November 4 - . 17:08 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island DZ. Launch Pad: RW04/22. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL. FAILURE: The rocket functioned perfectly but the separation system failed to release the payload..
  • SAC-B - . Nation: Argentina. Agency: CONAE. Program: SAC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SAC-B. Spacecraft: SAC-B. Decay Date: 2002-04-07 . USAF Sat Cat: 24645 . COSPAR: 1996-061A. Apogee: 555 km (344 mi). Perigee: 487 km (302 mi). Inclination: 38.0000 deg. Period: 95.00 min. Air dropped in Wallops Island DZ..

1997 April 21 - . 11:59 GMT - . Launch Site: Gando. Launch Complex: Gran Canaria DZ. Launch Pad: 27.0 N x 15.3 W. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL.
  • Minisat-01 - . Mass: 209 kg (460 lb). Nation: USA. Agency: INTA. Manufacturer: CASA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Minisat. Spacecraft: Minisat. Decay Date: 2002-02-26 . USAF Sat Cat: 24779 . COSPAR: 1997-018A. Apogee: 580 km (360 mi). Perigee: 561 km (348 mi). Inclination: 151.0000 deg. Period: 96.00 min. Minisat-01 carried the EURD extreme ultraviolet spectrograph to study interstellar gas, the LEGRI gamma ray burst detector, and the CPLM microacceleration in liquids experiment. Air dropped in Gran Canaria DZ..

1997 August 29 - . 15:02 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Vandenberg.. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL.
  • FORTE - . Nation: USA. Agency: USAF STP. Manufacturer: Los Alamos. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: FORTE. Spacecraft: FORTE. USAF Sat Cat: 24920 . COSPAR: 1997-047A. Apogee: 833 km (517 mi). Perigee: 799 km (496 mi). Inclination: 70.0000 deg. Period: 101.20 min.

    FORTE - 'Fast On-orbit Recording of Transient Events' - was a US Los Alamos National Laboratory satellite designed to study natural and artificial radio emissions from the ionosphere. This data was needed to develop technology for monitoring nuclear test ban treaties. Air dropped in Point Arguello WADZ.


1997 October 9 - . 17:59 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/3. LV Family: R-7. Launch Vehicle: Soyuz-U-PVB.
  • Mirka - . Nation: Germany. Agency: DLR. Manufacturer: Kayser-Threde. Class: Technology. Type: Re-entry test vehicle. Spacecraft Bus: Mirka. Spacecraft: Mirka. Decay Date: 1997-10-23 . USAF Sat Cat: 25006 . COSPAR: 1997-060xx. Apogee: 363 km (225 mi). Perigee: 218 km (135 mi). Inclination: 62.8000 deg. Period: 90.30 min. Landed in Kazakstan Oct 23.

1997 October 25 - . 00:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. LV Family: Atlas. Launch Vehicle: Atlas IIA.
  • Falcon Gold - . Nation: USA. Agency: Lockheed. Manufacturer: USAF Colorado Springs. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Falcon Gold. Spacecraft: Falcon Gold. Decay Date: 1998-09-27 . USAF Sat Cat: 25020 . COSPAR: 1997-065B. Apogee: 34,457 km (21,410 mi). Perigee: 151 km (93 mi). Inclination: 26.2000 deg. Period: 185.80 min. US Air Force Academy experiment to demonstrate use of GPS navigation in geosynchronous orbit..

1997 October 30 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G.
  • MAQSAT-H/TEAMSAT - . Payload: MAQSAT-H. Nation: Europe. Agency: ESA. Manufacturer: Kayser-Threde. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MAQSAT. Spacecraft: MAQSAT. USAF Sat Cat: 25023 . COSPAR: 1997-066A. Apogee: 26,504 km (16,468 mi). Perigee: 545 km (338 mi). Inclination: 7.6000 deg. Period: 465.70 min. Dummy communications satellite instrumented to report the actual payload bay environment during launch. It included the TEAMSAT technology experiment payload, developed by ESTEC.
  • YES - . Payload: Young Engineers Satellite. Nation: Europe. Agency: ESA. Manufacturer: ESTEC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: YES. Spacecraft: YES. USAF Sat Cat: 25025 . COSPAR: 1997-066C. Apogee: 26,604 km (16,530 mi). Perigee: 558 km (346 mi). Inclination: 7.6000 deg. Period: 467.70 min. Young Engineers Satellite with several technology experiments. Ejected from MAQSAT-H/TEAMSAT..
  • MAQSAT-B/EPS - . Payload: MAQSAT-B. Nation: Europe. Agency: ESA. Manufacturer: Kayser-Threde. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MAQSAT. Spacecraft: MAQSAT. USAF Sat Cat: 25024 . COSPAR: 1997-066B. Apogee: 26,549 km (16,496 mi). Perigee: 541 km (336 mi). Inclination: 7.6000 deg. Period: 466.40 min. Dummy satellite in the lower bay of the SPELTRA dual launch adapter..

1997 November 2 - . 12:25 GMT - . Launch Site: Alcantara. Launch Complex: Alcantara VLS. LV Family: Sonda. Launch Vehicle: VLS-1. FAILURE: Destroyed during launch.. Failed Stage: 1.
  • SCD-2A - . Mass: 115 kg (253 lb). Nation: Brazil. Agency: AEB. Manufacturer: INPE. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SCD. Spacecraft: SCD. Apogee: 3.00 km (1.80 mi). The SCD-2A (Data Collection Satellite 2A) was a Brazilian satellite designed for the collection of meteorological data relayed by data collection platforms spread throughout the Brazilian territory..

1997 November 27 - . 21:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II.
  • Hikoboshi - . Payload: ETS-7. Nation: Japan. Agency: NASDA. Manufacturer: Toshiba. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS-7. Spacecraft: ETS-7. Decay Date: 2015-11-13 . USAF Sat Cat: 25064 . COSPAR: 1997-074B. Apogee: 548 km (340 mi). Perigee: 545 km (338 mi). Inclination: 35.0000 deg. Period: 95.50 min.

    The Orihime and Hikoboshi satellites undocked and redocked on July 7 1998 in the FP-1 test of automated docking systems. Despite claims of the NASDA space agency that this is a first, automated Russian craft have docked on many occasions since the Kosmos-186/188 docking in 1968.

  • Orihime - . Payload: ETS-7 Target. Nation: Japan. Agency: NASDA. Manufacturer: Toshiba. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS-7 Target. Spacecraft: ETS-7 Target. Decay Date: 1999-01-27 . USAF Sat Cat: 25424 . COSPAR: 1997-074E. Apogee: 458 km (284 mi). Perigee: 346 km (214 mi). Inclination: 34.5000 deg. Period: 92.60 min. Attached to Hikoboshi. It would later separate and serve as a passive docking target for the Hikobishi active automatic docking technology spacecraft..

1998 July 10 - . 06:30 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC45/1. LV Family: Zenit. Launch Vehicle: Zenit-2.
  • Gurwin Techsat 1B - . Mass: 50 kg (110 lb). Nation: Israel. Agency: RVSN. Manufacturer: Technion. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Gurwin. Spacecraft: Gurwin. USAF Sat Cat: 25397 . COSPAR: 1998-043D. Apogee: 819 km (508 mi). Perigee: 817 km (507 mi). Inclination: 98.8000 deg. Period: 101.30 min. Built by Technion-Israel Institute of Technology. Replaced earlier Russian-launched Techsat which failed to orbit in 1995..

1998 August 31 - . 03:07 GMT - . Launch Site: Gitdaeryung. LV Family: Nodong 1. Launch Vehicle: Paektusan 1. FAILURE: Third stage failure.. Failed Stage: 3.
  • Kwangmyongsong 1 - . Nation: Korea North. Agency: Choson. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Kwangmyongsong. Spacecraft: Kwangmyongsong.

    North Korea reported the launch of its first satellite on the first of September. This announcement was followed on September 14 by the release of a photograph of the satellite and the claim that the satellite had completed its 100th orbit of the earth between 08:24 and 11:17 local time (2017 GMT) on September 13. Video of the launch, the satellite, and an animation of the satellite in orbit around the earth were distributed to foreign news agencies the following weekend. The satellite appeared almost identical to the first Chinese test satellite (which itself appeared almost identical to the US Telstar).

    Despite these claims no foreign observer ever detected the satellite visually, by radar, or picked up its radio signals. The Pentagon at first claimed it was an ICBM launch, and that the satellite story was just a cover for the test. However on further analysis of the data collected on the launch they admitted nearly a month later that there had been some a satellite launch attempt. What seems to have happened is that the third stage either failed and fell into the Pacific or misfired and put the satellite into a low orbit where it decayed very quickly before it could be detected by foreign observers. Additional Details: here....


1998 October 3 - . 10:04 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Taurus. Launch Vehicle: ARPA Taurus.
  • STEX - . Payload: STEX. Nation: USA. Agency: NRO. Manufacturer: NRL. Class: Technology. Type: Ion engine technology satellite. Spacecraft Bus: STEX. Spacecraft: STEX. USAF Sat Cat: 25489 . COSPAR: 1998-055A. Apogee: 759 km (472 mi). Perigee: 744 km (462 mi). Inclination: 84.9859 deg. Period: 99.77 min.

    Tested TAL-D55 plasma engine and was to be part of the NRO's ATex tether experiment. The ATeX lower end mass was meant to remain attached to the STEX parent spacecraft, but with only 21 m of tether deployed, it appeared the tether was so far off vertical that automatic safety systems jettisoned the base to protect the remainder of the STEX satellite. Thus, the upper and lower ATeX end masses were in orbit as one object connected by a 21 m tether, and designated USA 141 (1998-055C). The main STEX satellite was in orbit as a separate object, 1998-055A.

  • USA 141 - . Payload: ATEX. Mass: 54 kg (119 lb). Nation: USA. Agency: NRL, NRO. Class: Technology. Type: Tether technology satellite. Spacecraft Bus: TiPS. Spacecraft: TiPS. USAF Sat Cat: 25615 . COSPAR: 1998-055C. Apogee: 766 km (476 mi). Perigee: 750 km (466 mi). Inclination: 84.9910 deg. Period: 99.90 min.

    NRO's ATeX (Advanced Tether eXperiment) reportedly failed on January 16. The ATeX lower end mass was meant to remain attached to the STEX parent spacecraft, but with only 21 m of tether deployed, it appeared the tether was so far off vertical that automatic safety systems jettisoned the base to protect the remainder of the STEX satellite. Thus, the upper and lower ATeX end masses were in orbit as one object connected by a 21 m tether, and designated USA 141 (1998-055C). The main STEX satellite was in orbit as a separate object, 1998-055A.


1998 October 20 - . 07:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. Launch Pad: SLC36A. LV Family: Atlas. Launch Vehicle: Atlas IIA.
  • USA 140 - . Payload: UHF F/O F9. Mass: 3,200 kg (7,000 lb). Nation: USA. Agency: USN. Manufacturer: El Segundo. Program: UHF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: HS 601. Spacecraft: HS 601. USAF Sat Cat: 25501 . COSPAR: 1998-058A. Apogee: 35,806 km (22,248 mi). Perigee: 35,773 km (22,228 mi). Inclination: 3.8000 deg. Period: 1,436.20 min.

    The orbit at burnout of the Centaur was 286 km x 25866 km x 27.0 degree. Modification of the orbit to a geostationary 38,300 km circular x 0.0 degree inclination was accomplished by the Marquardt R-4D liquid propellant motor on the HS-601 spacecraft. The satellite carried UHF and EHF transponders for naval communications, and a Ka-band Global Broadcast Service video relay package. Launch mass of 3200 kg dropped to 1550 kg once geostationary orbit was reached. UHF F/O F9 was placed over the Atlantic Ocean in geosynchronous orbit at 174 deg W in 1998; 22 deg W in 1999. Additional Details: here....


1998 October 21 - . 16:37 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G.
  • Maqsat 3 - . Nation: France. Agency: ESA. Manufacturer: Kayser-Threde. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MAQSAT. Spacecraft: MAQSAT. USAF Sat Cat: 25503 . COSPAR: 1998-059A. Apogee: 35,491 km (22,053 mi). Perigee: 1,017 km (631 mi). Inclination: 7.5000 deg. Period: 641.20 min.

    Maqsat 3 was an instrumentation package used to monitor performance of the Ariane 5 booster. At T+12:43 the Speltra adapter cover separated revealing Maqsat-3. At T+15:14 the EPS stage Aestus engine ignited and burned until T+31:00. At this point on a normal mission the satellite would separate from the EPS, but to avoid creating space debris Maqsat remained attached to the EPS. The EPS/Maqsat-3 was placed in a 1027 km x 35863 km x 7.0 degree geostationary transfer orbit.

  • ARD - . Payload: Atmospheric Reentry Demonstrator. Nation: France. Agency: Arianespace. Program: ISS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ARD. Spacecraft: ARD. COSPAR: 1998-059S.

    The ARD was an 80 percent scale model of the Apollo Command Module, and a technology test for a possible International Space Station Crew Rescue Vehicle. Equipment included a TDRS satellite communications system; a GPS navigation system; 7 DASA 40 kgf hydrazine attitude control thrusters; a 2.8 m diameter heat shield; three 23 metre diameter parachutes, and a SARSAT recovery beacon. The ARD separated from the Ariane EPS upper stage at 12 minutes 2 seconds after launch. ARD and the EPC stage manoeuvred into a 1 km x 830 km orbit, guaranteeing re-entry at the end of the first orbit. The spacecraft splashed down in the Pacific at 3.69 degrees N, 153.35 degrees W, and was successfully recovered by the French Navy.


1998 October 24 - . 12:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7326-9.5.
  • SEDSAT 1 - . Nation: USA. Agency: Boeing. Manufacturer: SEDS. Program: STS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SEDSAT. Spacecraft: SEDSAT. USAF Sat Cat: 25509 . COSPAR: 1998-061B. Apogee: 1,050 km (650 mi). Perigee: 544 km (338 mi). Inclination: 31.4000 deg. Period: 100.80 min.

    Following separation of the third stage and the primary Deep Space 1 payload, the Delta second stage manoeuvred from its 185 km parking orbit to a 174 km x 2744 km x 28.5 degree orbit. It then released the SEDSAT micro-satellite, built by the Huntsville, Alabama chapter of SEDS (the Students for the Exploration and Development of Space). SEDSAT has two amateur radio transponders and an earth imaging camera.


1998 December 4 - . 08:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: MLP3. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • Mightysat 1 - . Mass: 320 kg (700 lb). Nation: USA. Agency: USAF. Manufacturer: McLean. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MightySat 1. Spacecraft: Mightysat 1. Decay Date: 1999-11-21 . USAF Sat Cat: 25551 . COSPAR: 1998-069C. Apogee: 395 km (245 mi). Perigee: 381 km (236 mi). Inclination: 51.6000 deg. First flight of a USAF Philips Laboratory/Space Experiments Directorate ejectable technology demonstration platform. Four advanced technologies demonstrated, including composite structure, advanced solar cells, advanced electronics, and a shock device..
  • SAC-A - . Mass: 68 kg (149 lb). Nation: Argentina. Agency: CONAE. Manufacturer: INVAP. Program: SAC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SAC-A. Spacecraft: SAC-A. Decay Date: 1999-10-25 . USAF Sat Cat: 25550 . COSPAR: 1998-069B. Apogee: 398 km (247 mi). Perigee: 381 km (236 mi). Inclination: 51.6000 deg. SAC-A was to provide engineering bench testing for new space science technology instruments and equipment that will be used in a more complex spacecraft for the Argentine space program..

1999 February 23 - . 10:29 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10.
  • ARGOS - . Payload: P91-1. Nation: USA. Agency: USAF SM. Manufacturer: Seal Beach. Class: Technology. Type: Ion engine technology satellite. Spacecraft Bus: ARGOS. Spacecraft: ARGOS. USAF Sat Cat: 25634 . COSPAR: 1999-008A. Apogee: 836 km (519 mi). Perigee: 821 km (510 mi). Inclination: 98.9000 deg. Period: 101.50 min. ARGOS was a USAF Space Test Program P91-1 technology satellite, equipped with an ion engine, ionosphere, x-ray, and dust detectors. Much delayed, it finally was placed into orbit on the eleventh (!) launch attempt..
  • Sunsat - . Nation: South Africa. Agency: Boeing. Manufacturer: Stellenbosch. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Sunsat. Spacecraft: Sunsat. USAF Sat Cat: 25636 . COSPAR: 1999-008C. Apogee: 852 km (529 mi). Perigee: 641 km (398 mi). Inclination: 96.5000 deg. Period: 99.80 min. Sunsat was built by students at Stellenbosch University, South Africa and carried a small imager and a message relay payload..

1999 March 28 - . 01:29 GMT - . Launch Site: Kiritimati. Launch Pad: 0.0 N x 154.0 W. Launch Platform: Odyssey. LV Family: Zenit. Launch Vehicle: Zenit-3SL.
  • DemoSat - . Payload: HS 702. Mass: 4,500 kg (9,900 lb). Nation: USA. Agency: SeaLaunch. Manufacturer: Kent. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: HS 702. Spacecraft: HS 702. USAF Sat Cat: 25661 . COSPAR: 1999-014A. Apogee: 36,045 km (22,397 mi). Perigee: 658 km (408 mi). Inclination: 0.7000 deg. Period: 645.00 min.

    The first Boeing Sea Launch mission. The Zenit-3SL lifted off from the Odyssey floating platform on the equator at 154 degrees West longitude. The DemoSat payload was an instrumented dynamic model of an HS-702 satellite built by Boeing Commercial Space/Kent. 13 minutes after launch, the Block DM-SL upper stage completed its first burn and entered a 180 km x 735 km x 1.2 degree parking orbit. A second burn 47 minutes after launch placed DemoSat in a 638 km x 36,064 km x 1.2 degree geostationary transfer orbit. Three hours later, a third DM-SL burn lowered the stage's perigee so that it would re-enter quickly.


1999 April 21 - . 04:59 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. Launch Pad: LC109/95. LV Family: R-36M. Launch Vehicle: Dnepr.
  • UoSAT-12 - . Mass: 325 kg (716 lb). Nation: UK. Agency: Surrey. Manufacturer: Surrey. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MiniSat-400. Spacecraft: MiniSat-400. USAF Sat Cat: 25693 . COSPAR: 1999-021A. Apogee: 654 km (406 mi). Perigee: 639 km (397 mi). Inclination: 64.6000 deg. Period: 97.70 min.

    First launch of Russia's Dnepr launch vehicle, a converted R-36M2 ICBM. The Dnepr was launched from a silo. The third stage maneuvring bus (used on the ICBM for dispensing multiple warheads) placed UoSAT-12 into a 638 km x 652 km x 64.6 deg orbit. The third stage separated from the payload at 05:13 GMT and then made a burn into a 599 km x 1403 km x 64.6 deg orbit. UoSAT-12 was the first test of the Minibus platform, at 325 kg a larger spacecraft than earlier 50 kg Surrey UoSATs. It carried a mobile radio experiment (MERLION), a GPS receiver, and imaging cameras.


1999 April 28 - . 20:30 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC107/1. Launch Pad: LC107/pad?. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Megsat-0 - . Mass: 35 kg (77 lb). Nation: Italy. Agency: RVSN. Manufacturer: MegSat. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Megsat. Spacecraft: Megsat. Decay Date: 2003-11-04 . USAF Sat Cat: 25722 . COSPAR: 1999-022B. Apogee: 597 km (370 mi). Perigee: 544 km (338 mi). Inclination: 48.5000 deg. A small technology satellite which carried an experimental high rate data transmission payload..

1999 May 18 - . 05:09 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Vandenberg.. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL/HAPS.
  • TERRIERS - . Nation: USA. Agency: NASA Greenbelt. Manufacturer: AeroAstro. Class: Technology. Type: Military technology satellite. Spacecraft Bus: TERRIERS. Spacecraft: TERRIERS. USAF Sat Cat: 25735 . COSPAR: 1999-026A. Apogee: 493 km (306 mi). Perigee: 484 km (300 mi). Inclination: 97.1000 deg. Period: 94.40 min.

    TERRIERS was part of NASA's Student Explorer Demonstration Initiative (STEDI), which was a precursor program to the UNEX (University Explorer) series. STEDI was managed by USRA (the Universities Space Research Association) for NASA, while UNEX was to be more directly managed by NASA-GSFC. TERRIERS was to be operated by the space physics group at Boston University for ionosphere studies, and carried TESS, a set of extreme ultraviolet (EUV) spectrographs to get electron density and thermosphere emission profiles. The GISSMO instrument measured the solar EUV flux. The spacecraft was built by AeroAstro and based on HETE. TERRIERS was placed in the correct orbit, but it failed to orient its solar panel to the Sun and ran out of battery power by May 20. Controllers were optimistic that when its orbit processes to a better sun angle the satellite could be revived. Air dropped in Point Arguello WADZ. Additional Details: here....


1999 May 27 - . 10:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39B. Launch Platform: MLP2. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • Starshine - . Nation: USA. Agency: NASA Greenbelt. Program: ISS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Starshine. Spacecraft: Starshine. Decay Date: 2000-02-18 . USAF Sat Cat: 25769 . COSPAR: 1999-030B. Apogee: 324 km (201 mi). Perigee: 311 km (193 mi). Inclination: 51.6000 deg.

    At 0:721 GMT on June 5 the Starshine satellite was ejected into a 379 x 396 km x 51.6 degree orbit from a canister at the rear of STS-96 Space Shuttle Discovery's payload bay. The small Starshine satellite, built by NRL, was to be observed by students as part of an educational exercise.


1999 October 14 - . 03:15 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.
  • SACI 1 - . Nation: Brazil. Agency: SISE. Manufacturer: INPE. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SACI. Spacecraft: SACI. USAF Sat Cat: 25941 . COSPAR: 1999-057B. Apogee: 731 km (454 mi). Perigee: 719 km (446 mi). Inclination: 98.7000 deg. Period: 99.30 min. INPE experimental scientific satellite with a magnetometer, particle detectors and an atmospheric experiment. INPE reportedly lost contact with the satellite in mid-October..

1999 December 11 - . 18:25 GMT - . Launch Site: Alcantara. Launch Complex: Alcantara VLS. LV Family: Sonda. Launch Vehicle: VLS-1. FAILURE: Second stage failed to ignite; destroyed by range safety.. Failed Stage: 2.
  • SACI-2 - . Mass: 80 kg (176 lb). Nation: Brazil. Agency: AEB. Manufacturer: INPE. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SACI. Spacecraft: SACI. Apogee: 10 km (6 mi). Second attempted launch of Brazil's indigenous launcher..

2000 January 27 - . 03:03 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC8. LV Family: Minuteman. Launch Vehicle: Minotaur 1.
  • JAWSAT - . Payload: P98-1. Mass: 64 kg (141 lb). Nation: USA. Agency: USAF AFMC. Manufacturer: Weber. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: JAWSAT. Spacecraft: JAWSAT. USAF Sat Cat: 26061 . COSPAR: 2000-004A. Apogee: 805 km (501 mi). Perigee: 753 km (468 mi). Inclination: 100.1976 deg. Period: 100.36 min. Joint USAF Academy/Weber State Satellite. Payloads included a plasma experiment, a particle detector, and a technology test..
  • Picosat 2 - . Mass: 0 kg (0 lb). Nation: USA. Agency: DARPA. Manufacturer: Aerospace. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MEMS. Spacecraft: MEMS. USAF Sat Cat: 26080 . COSPAR: 2000-004H. Apogee: 779 km (484 mi). Perigee: 733 km (455 mi). Inclination: 100.2000 deg. Period: 100.00 min.

    Deployed by the OPAL satellite on February 7 at 0334:16 GMT. Picosat 1 and 2 were each 0.25 kg DARPA/Aerospace Corp. MEMS (Micro Electro-mechanical Systems) picosatellites, each carrying intersatellite communications experiment and connected by a 30-m tether.

  • Louise - . Mass: 68 kg (149 lb). Nation: USA. Agency: SCREEM. Manufacturer: Santa Clara. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: JAK. Spacecraft: JAK. USAF Sat Cat: 26092 . COSPAR: 2000-004K. Apogee: 781 km (485 mi). Perigee: 731 km (454 mi). Inclination: 100.2000 deg. Period: 100.00 min.

    Three picosatellites (JAK, Thelma, and Louise), developed by the Artemis team of women undergraduates at Santa Clara University, were deployed from the OPAL satellite. Mass 0.5 kg; size around 0.1-0.2m. Carried a VLF wave experiment. Ejected from OPAL on February 12; unfortunately no data was received thereafter.

  • Thelma - . Mass: 68 kg (149 lb). Nation: USA. Agency: SCREEM. Manufacturer: Santa Clara. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: JAK. Spacecraft: JAK. USAF Sat Cat: 26091 . COSPAR: 2000-004J. Apogee: 767 km (476 mi). Perigee: 723 km (449 mi). Inclination: 100.2000 deg. Period: 99.70 min.

    Three picosatellites (JAK, Thelma, and Louise), developed by the Artemis team of women undergraduates at Santa Clara University, were deployed from the OPAL satellite. Mass 0.5 kg; size around 0.1-0.2m. Carried a VLF wave experiment. Ejected from OPAL on February 12; unfortunately no data was received thereafter.

  • STENSAT - . Mass: 0 kg (0 lb). Nation: USA. Agency: AmSat. Manufacturer: STENSAT. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STENSAT. Spacecraft: STENSAT. USAF Sat Cat: 26094 . COSPAR: 2000-004M. Apogee: 783 km (486 mi). Perigee: 734 km (456 mi). Inclination: 100.2000 deg. Period: 100.00 min. Picosat. Built by built by the AMSAT-NA (Amateur Satellite, North America) group, and carried an amateur radio transponder. Ejected from OPAL on February 11; unfortunately no data was received thereafter..
  • JAK - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: SCREEM. Manufacturer: Santa Clara. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: JAK. Spacecraft: JAK. USAF Sat Cat: 26093 . COSPAR: 2000-004L. Apogee: 763 km (474 mi). Perigee: 716 km (444 mi). Inclination: 100.2000 deg. Period: 99.60 min.

    Three picosatellites (JAK, Thelma, and Louise), developed by the Artemis team of women undergraduates at Santa Clara University, were deployed from the OPAL satellite. . JAK is the initials of the infant son of the Artemis' team's advisor Mass 0.2 kg; size around 0.1 - 0.2m. Carried a VLF wave experiment. Ejected from OPAL on February 11; unfortunately no data was received thereafter.

  • Falconsat - . Mass: 52 kg (114 lb). Nation: USA. Agency: USAF AFMC. Manufacturer: USAF Colorado Springs. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: FalconSat. Spacecraft: Falconsat. USAF Sat Cat: 26064 . COSPAR: 2000-004D. Apogee: 810 km (503 mi). Perigee: 754 km (468 mi). Inclination: 100.2003 deg. Period: 100.41 min. USAF Academy satellite, carried the CHAWS-LD (Charging Hazards and Wake Studies-Long Duration) experiment to measure spacecraft charging effects in LEO..
  • OPAL - . Payload: Orbiting Picosat Launcher. Mass: 13 kg (28 lb). Nation: USA. Agency: USAF AFMC. Manufacturer: Stanford. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: OPAL. Spacecraft: OPAL. USAF Sat Cat: 26063 . COSPAR: 2000-004C. Apogee: 808 km (502 mi). Perigee: 754 km (468 mi). Inclination: 100.1991 deg. Period: 100.39 min.

    Stanford University Orbiting Picosat Automated Launcher. Carried an acclerometer, a magnetometer, and six small picosatellites - Picosat 1 and 2, Stensat, and the Artemis triplets (JAK, Thelma, and Louise). The first two were deployed on February 7 at 0334:16 GMT. OPAL transmitter problems delayed the initial release.

  • Picosat 1 - . Mass: 0 kg (0 lb). Nation: USA. Agency: DARPA. Manufacturer: Aerospace. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MEMS. Spacecraft: MEMS. USAF Sat Cat: 26080 . COSPAR: 2000-004H. Apogee: 779 km (484 mi). Perigee: 733 km (455 mi). Inclination: 100.2000 deg. Period: 100.00 min.

    Deployed by the OPAL satellite on February 7 at 0334:16 GMT. Picosat 1 and 2 were each 0.25 kg DARPA/Aerospace Corp. MEMS (Micro Electro-mechanical Systems) picosatellites, each carrying intersatellite communications experiment and connected by a 30-m tether.

  • OCSE - . Payload: Optical Calibration Sphere. Mass: 22 kg (48 lb). Nation: USA. Agency: USAF SOR. Manufacturer: L'Garde. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: OCSE. Spacecraft: OCSE. Decay Date: 2001-03-05 . USAF Sat Cat: 26062 . COSPAR: 2000-004B. Apogee: 711 km (442 mi). Perigee: 677 km (421 mi). Inclination: 100.2240 deg. Period: 98.57 min.

    Optical Calibration Sphere Experiment, a 3.5m diameter inflatable sphere built by L'Garde Inc. for calibrating the lasers at the AFRL Starfire Optical Range. The 0.48m long 0.41m diameter OCSE canister was ejected from the JAWSAT stack; 42 seconds later, with the canister clear of the other payloads, the canister door opened and 10 seconds after that inflation of the sphere began. The canister remains attached to the inflated sphere. Once inflated, the sphere's material becomes rigidized

  • ASUSAT - . Mass: 5.00 kg (11.00 lb). Nation: USA. Agency: USAF AFMC. Manufacturer: Arizona. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ASUSAT. Spacecraft: ASUSAT. USAF Sat Cat: 26065 . COSPAR: 2000-004E. Apogee: 809 km (502 mi). Perigee: 754 km (468 mi). Inclination: 100.2009 deg. Period: 100.40 min. Arizona State University satellite with an Earth imager and an amateur radio transponder..

2000 February 8 - . 23:20 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz-U-PVB.
  • IRDT - . Mass: 110 kg (240 lb). Nation: Russia. Agency: ESA. Manufacturer: Lavochkin bureau. Class: Technology. Type: Re-entry test vehicle. Spacecraft Bus: Rescue. Spacecraft: IRDT. COSPAR: 2000-009x. Apogee: 613 km (381 mi). Perigee: 580 km (361 mi). Inclination: 64.8545 deg. Period: 96.53 min.

    After four orbits around the Earth the test vehicle was powered by the launcher’s upper stage to re-enter the atmosphere for a landing about 1800 km northwest of the launch site. The heat shield was inflated and the IRDT separated from the upper stage. It then passed through the upper atmospheric layers that imposed the highest dynamic pressure, heat flux and acceleration loads onto the system. The IRDT landed inside the predicted area at 54 deg E and 51 deg N near the Kazakhstan border. Unfortunately, a tear occurred in the inflatable shield during descent resulting in a higher velocity and a heavier than expected impact on landing, resulting in some damage to the lower part of the IRDT. The IRDT was collected by helicopter so that the memory unit of the sensor package, with all recorded data, could be analysed. An initial data check confirmed that all experiments in the sensor package worked perfectly.

  • Dummy satellite - . Nation: Russia. Agency: Starsem. Manufacturer: Lavochkin bureau. Class: Technology. Type: Navigation technology satellite. USAF Sat Cat: 26086 . COSPAR: 2000-009A. Apogee: 613 km (381 mi). Perigee: 580 km (361 mi). Inclination: 64.8545 deg. Period: 96.53 min. .

2000 March 20 - . 18:28 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz-U-PVB.
  • Dumsat - . Mass: 2,382 kg (5,251 lb). Nation: Europe. Agency: Starsem. Manufacturer: Toulouse. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cluster 2. Spacecraft: Cluster 2. USAF Sat Cat: 26106 . COSPAR: 2000-015A. Apogee: 17,687 km (10,990 mi). Perigee: 332 km (206 mi). Inclination: 64.7000 deg. Period: 316.60 min. Cluster 2 Composite Mock-Up validation flight. Mass model of a pair of Cluster II scientific satellites built by Aerospatiale Matra. Second test launch of the Soyuz-Fregat launch vehicle..

2000 May 16 - . 08:27 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/1. Launch Pad: LC133/pad?. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Simsat-1 - . Mass: 657 kg (1,448 lb). Nation: Russia. Agency: Eurockot. Manufacturer: Chelomei bureau. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Simsat. Spacecraft: Simsat. USAF Sat Cat: 26365 . COSPAR: 2000-026A. Apogee: 562 km (350 mi). Perigee: 543 km (337 mi). Inclination: 86.3707 deg. Period: 95.62 min.

    First Rokot flight from Plesetsk, using a launch pad originally used for Kosmos rockets. The two-stage modified UR-100NUTTKh ICBM, delivered a Briz-KM upper stage to a suborbital trajectory. The first Briz burn was to an approximately 200 x 550 km transfer orbit; the second burn circularized at apogee. It placed two 660 kg dummy satellites in orbits similar to the parking orbit was used for the defunct Iridium program. The Briz-KM stage then made a third burn to lower its perigee to a 178 x 556 km x 86.4 deg disposal orbit.

  • Simsat-2 - . Mass: 657 kg (1,448 lb). Nation: Russia. Agency: Eurockot. Manufacturer: Chelomei bureau. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Simsat. Spacecraft: Simsat. USAF Sat Cat: 26366 . COSPAR: 2000-026B. Apogee: 557 km (346 mi). Perigee: 545 km (339 mi). Inclination: 86.3670 deg. Period: 95.59 min.

2000 June 28 - . 10:37 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • SNAP 1 - . Mass: 6.00 kg (13.20 lb). Nation: UK. Agency: Surrey. Manufacturer: Surrey. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SSTL-10. Spacecraft: SSTL-10. USAF Sat Cat: 26386 . COSPAR: 2000-033C. Apogee: 710 km (441 mi). Perigee: 691 km (429 mi). Inclination: 98.1358 deg. Period: 98.70 min.

    The SNAP-1 Surrey Nanosatellite Applications Platform was a 6 kg satellite with imager and propulsion. It was to test rendezvous techniques by formation flying with the Tsinghua satellite placed in orbit on the same launch. In October 2000 Surrey Satellite Technology Ltd (SSTL) released a picture of Tsinghua-1 taken in orbit by the SNAP-1 6.5 kg nanosatellite.

  • Tsinghua - . Mass: 50 kg (110 lb). Nation: China. Agency: Tsinghua. Manufacturer: Surrey. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SSTL-70. Spacecraft: SSTL-70. USAF Sat Cat: 26385 . COSPAR: 2000-033B. Apogee: 713 km (443 mi). Perigee: 687 km (427 mi). Inclination: 98.1397 deg. Period: 98.68 min.

    Tsinghua University of Beijing satellite equipped with an imager, communications payload, and momentum wheels for 3-axis stabilisation. The 50 kg, 0.69 x 0.36 x 0.36m box-shaped satellite used a standard Surrey SSTL microsat bus.Tsinghua-1 was the first demonstrator for the planned Disaster Monitoring Constellation and carried a multi-spectral Earth imaging camera providing 39-metre nadir ground resolution in 3 spectral bands. The satellite also carried out research in low Earth orbit using digital store-and-forward communications, a digital signal processing (DSP) experiment, a Surrey-built GPS space receiver and a new 3-axis microsat attitude control experiment. Tsinghua-1 used the SGR-10, with 12 channels and equipped with two receive antennas, to investigate the use of GPS signals in microsat on-board attitude and orbit determination. In October 2000 Surrey Satellite Technology Ltd (SSTL) released a picture of Tsinghua-1 taken in orbit by the SNAP-1 6.5 kg nanosatellite.


2000 July 15 - . 12:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • MITA - . Mass: 170 kg (370 lb). Nation: Italy. Agency: ASI. Manufacturer: Carlo Gavazzi. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MITA. Spacecraft: MITA. Decay Date: 2001-08-15 . USAF Sat Cat: 26404 . COSPAR: 2000-039A. Apogee: 475 km (295 mi). Perigee: 422 km (262 mi). Inclination: 87.2633 deg. Period: 93.48 min. MITA was an Italian Space Agency experimental microsatellite built by Carlo Gavazzi Space of Milano and carried the NINA particle detector and an experimental attitude control system..
  • Rubin - . Nation: Germany. Agency: RVSN. Manufacturer: Bremen. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Rubin. Spacecraft: Rubin. Decay Date: 2001-08-30 . USAF Sat Cat: 26406 . COSPAR: 2000-039C. Apogee: 463 km (288 mi). Perigee: 411 km (255 mi). Inclination: 87.2558 deg. Period: 93.23 min. Rubin was a microsatellite to measure launch vehicle parameters developed by OHB and students of the Hochschule Bremen. Rubin remained attached to the payload adapter of the Kosmos-3M final stage..

2000 August 23 - . 11:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 8930.
  • DM-F3 - . Payload: Dummy Payload. Mass: 4,348 kg (9,585 lb). Nation: USA. Agency: Seal Beach. Manufacturer: Douglas. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: HS 601. Spacecraft: HS 601. Decay Date: 2009-02-04 . USAF Sat Cat: 26475 . COSPAR: 2000-048A. Apogee: 19,547 km (12,145 mi). Perigee: 212 km (131 mi). Inclination: 27.6000 deg.

    Vehicle Demonstration. Return to flight following earlier failure. The third Boeing Delta III launch was financed by the company and carried a dummy payload in order to bolster customer confidence in the new launch vehicle. The second stage ignited at an altitude of 158 km and the RL-10 shut off as planned in a 157 x 1363 km x 29.5 deg parking orbit. The engine fired again until fuel depletion, to place the vehicle in a geostationary transfer orbit of 190 x 20,655 km x 27.6 deg. This was much lower than that planned (23,400 km plus or minus 3,000 km) due to the fuel temperature and atmospheric conditions on the day of launch. The DM-F3 dummy payload was a mass model of the Orion 3 HS-601 satellite launched on the second Delta 3. The 4348 kg model was a 2.0m diameter, 1.7m high cylinder with two circular end plates, painted with black and white patterns. It was to be used by US Air Force researchers as a calibration target.


2000 September 26 - . 10:05 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. Launch Pad: LC109/95. LV Family: R-36M. Launch Vehicle: Dnepr.
  • UniSat - . Mass: 10 kg (22 lb). Nation: Italy. Agency: Makeyev Design Bureau. Manufacturer: la Sapienza. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: UniSat. Spacecraft: UniSat. USAF Sat Cat: 26547 . COSPAR: 2000-057C. Apogee: 670 km (416 mi). Perigee: 643 km (399 mi). Inclination: 64.5585 deg. Period: 97.78 min.

    Experimental satellite developed by the GAUSS (Gruppo di Astrodinamica dell' Universita degli Studi 'la Sapienza') in Roma. Unisat was financed by ASI and MURST (Ministero dell'Universtia e della Ricerca Scientifica e Tecnologica). It carried NiMH batteries, a magnetometer, and a payload consisting of a space debris sensor and a camera.

  • MegSat-1 - . Mass: 50 kg (110 lb). Nation: Italy. Agency: Makeyev Design Bureau. Manufacturer: MegSat. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Megsat. Spacecraft: MegSat. USAF Sat Cat: 26546 . COSPAR: 2000-057B. Apogee: 649 km (403 mi). Perigee: 643 km (399 mi). Inclination: 64.5574 deg. Period: 97.56 min. Research satellite owned and built by MegSat Space Division, part of the Gruppo Meggiorin companies in Brescia, Italy..

2000 November 16 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G.
  • STRV-1c - . Mass: 4,758 kg (10,489 lb). Nation: UK. Agency: Arianespace. Manufacturer: Farnborough. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STRV. Spacecraft: STRV. USAF Sat Cat: 26610 . COSPAR: 2000-072C. Apogee: 39,218 km (24,368 mi). Perigee: 636 km (395 mi). Inclination: 6.3400 deg. Period: 707.65 min.

    The two small STRV cubes were then ejected from the Ariane EPS stage ASAP-5 secondary payload structure at 0141 GMT. STRV-1c and 1d were small satellites built by the DERA (former Royal Aircraft Establishment), Farnborough, England. Mass was around 95 kg each. STRV-1c performed accelerated life testing of new components and materials in the high radiation environment of geosynchronous transfer orbit.

  • STRV-1d - . Mass: 4,758 kg (10,489 lb). Nation: UK. Agency: Arianespace. Manufacturer: Farnborough. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STRV. Spacecraft: STRV. USAF Sat Cat: 26611 . COSPAR: 2000-072D. Apogee: 39,282 km (24,408 mi). Perigee: 605 km (375 mi). Inclination: 7.1000 deg. Period: 708.30 min.

    STRV-1c and 1d were small satellites built by the DERA (former Royal Aircraft Establishment), Farnborough, England. Mass was around 95 kg each. STRV-1d carries an NRL Space Test Program experiment (S97-2), a camera, and technology and computer experiments.


2000 November 21 - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10.
  • Munin - . Mass: 529 kg (1,166 lb). Nation: Sweden. Agency: Seal Beach. Manufacturer: SISP. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Munin. Spacecraft: Munin. USAF Sat Cat: 26621 . COSPAR: 2000-075C. Apogee: 1,797 km (1,116 mi). Perigee: 701 km (435 mi). Inclination: 95.4000 deg. Period: 110.50 min.

    The small 6 kg Munin nanosatellite was built by Swedish students in collaboration with the Swedish Insitute for Space Physics (IRF) and carried a particle detector, a spectrometer, and an auroral camera. After deployment of EO-1 and SAC-C a fourth burn put the Delta second stage in a 697 x 1800 km x 95.4 deg orbit, after which Munin was ejected from the stage.


2000 December 20 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G.
  • LDREX - . Mass: 1,414 kg (3,117 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: LDREX. Spacecraft: LDREX. Decay Date: 2010-03-21 . USAF Sat Cat: 26640 . COSPAR: 2000-081C. Apogee: 30,257 km (18,800 mi). Perigee: 241 km (149 mi). Inclination: 2.4000 deg. Period: 527.50 min.

    Ariane V138's EPS upper stage carried an ASAP5 small payload attachment ring with a special camera system and the LDREX experimental antenna for Japan's NASDA space agency. LDREX (Large-scale Deployable Reflector EXperiment) was a 6-m diameter antenna which was to have deployed 40 minutes after launch, to test the deployment mechanism for the larger antenna to be used on the ETS-8 satellite. After the test the antenna was to have been jettisoned. However the experiment failed and no deployment or jettison took place.


2001 July 12 - . 21:58 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G.
  • Artemis - . Mass: 3,105 kg (6,845 lb). Nation: Europe. Agency: ESA. Manufacturer: Alenia. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Italsat. Spacecraft: Italsat. USAF Sat Cat: 26863 . COSPAR: 2001-029A. Apogee: 32,586 km (20,247 mi). Perigee: 32,451 km (20,164 mi). Inclination: 1.1000 deg. Period: 1,272.40 min.

    Artemis was a European Space Agency satellite designed to test new communications technologies. The Ariane 510 vehicle failed to reach its correct orbit. The solid boosters and main stage worked as planned and put the EPS upper stage in the planned near-suborbital trajectory. The EPS stage then fired but the Aestus engine failed to reach full thrust and cut off 1 minute early. Instead of the planned 858 x 35853 km orbit, only a 592 x 17528 km orbit was reached. The 3.1 tonne (with fuel), 2.5 kW spacecraft carried two pairs of ion engines and had adequate xenon propellant for those engines to reach geosynchronous altitude. This was the first ever rescue of a satellite mission using electric propulsion. The satellite reached its operational orbit in 31 January 2003.using the four German RITA electric xenon thrusters. Artemis could then function as originally planned, as there remained sufficient chemical propellant for 10 years’ operation. Artemis was to provide voice and data communications between mobile phones in Europe and North America, and act as a relay satellite between low-Earth orbiters and ground stations. Eventually, as part of the planned EGNOS system (to be operational by about 2010) it was to provide navigation/location determination as an independent European counterpart to the GPS and GLONASS fleets. As of 2007 Mar 11 located at 21.40E drifting at 0.001W degrees per day.


2001 August 29 - . 07:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • VEP-2 - . Mass: 3,500 kg (7,700 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: VEP. Spacecraft: VEP. USAF Sat Cat: 26899 . COSPAR: 2001-038B. Apogee: 35,979 km (22,356 mi). Perigee: 291 km (180 mi). Inclination: 28.6000 deg. Period: 636.60 min. Vehicle Evaluation Payload-2 consisted of ballast and monitoring instrumentation that remained attached to the launch vehicle's second stage. It included a Doppler ranging experiment for orbit determination..

2001 September 7 - . 19:39 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC8. LV Family: Minuteman. Launch Vehicle: Minotaur 1.
  • Picosat 7/8 - . Mass: 0 kg (0 lb). Nation: USA. Agency: USAF AFSPC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Picosat. Spacecraft: Picosat. Decay Date: 2002-07-11 . USAF Sat Cat: 26929 . COSPAR: 2000-042C. Apogee: 286 km (177 mi). Perigee: 266 km (165 mi). Inclination: 97.8000 deg. Period: 90.00 min.

    Picosat 7/Picosat 8, were ejected from the Mightysat II.1 satellite on September 7 at 1939 UTC into a 511 x 539 km x 97.8 deg orbit. The 0.25 kg satellites were connected by a 30 m tether and were cataloged as a single object. Mightysat II.1 (Sindri) was launched in July 2000, and the deployment of the picosats was planned for a year after launch.


2001 September 21 - . 18:49 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Taurus. Launch Vehicle: Taurus 2110. FAILURE: A problem a few seconds after first stage separation caused the rocket to go off course; it recovered and the remainder of the stages fired, but final cutoff velocity was too low to reach a sustainable orbit..
  • SBD - . Mass: 368 kg (811 lb). Nation: USA. Agency: Orbimage. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SBD. Spacecraft: SBD. COSPAR: F010921C.

    SBD, the Orbital Sciences' Special Bus Design. The 73 kg satellite was a test version of an enlarged Microstar bus. It would have remained attached to the third stage, together with two Celestis burial canisters containing cremated human remains, and an experimental third stage avionics box.


2001 September 30 - . 02:40 GMT - . Launch Site: Kodiak. LV Family: Athena. Launch Vehicle: Athena-1.
  • Sapphire - . Mass: 67 kg (147 lb). Nation: USA. Agency: Lockheed. Manufacturer: Stanford. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Sapphire. Spacecraft: Sapphire. USAF Sat Cat: 26932 . COSPAR: 2001-043D. Apogee: 796 km (494 mi). Perigee: 790 km (490 mi). Inclination: 67.1000 deg. Period: 100.70 min. SAPPHIRE (a US DoD-funded microsatellite) was built by Stanford University students and carried experimental infrared horizon sensors, a voice synthesizer and a digital camera. The satellite was about 0.5m in size and had a mass of 16 kg..
  • Picosat - . Mass: 67 kg (147 lb). Nation: USA. Agency: USAF. Manufacturer: Surrey. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SSTL-70. Spacecraft: SSTL-70. USAF Sat Cat: 26930 . COSPAR: 2001-043B. Apogee: 795 km (493 mi). Perigee: 788 km (489 mi). Inclination: 67.0000 deg. Period: 100.70 min.

    STP P97-1 Picosat was built by Surrey Satellite for the USAF using a Uosat-type bus. The 68 kg satellite was to test electronic components/systems in space conditions. It carried four test payloads: Polymer Battery Experiment (PBEX), Ionospheric Occultation Experiment (IOX), Coherent Electromagnetic Radio Tomagraphy (CERTO) and an ultra-quiet platform (OPPEX). Called Picosat 9 by some Agencies although not related to other satellites in that series.


2001 December 10 - . 17:18 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC45/1. LV Family: Zenit. Launch Vehicle: Zenit-2.
  • Maroc-Tubsat - . Mass: 45 kg (99 lb). Nation: Morocco. Agency: RAKA. Manufacturer: TuB. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Tubsat. Spacecraft: Tubsat. USAF Sat Cat: 27004 . COSPAR: 2001-056D. Apogee: 1,014 km (630 mi). Perigee: 985 km (612 mi). Inclination: 99.2000 deg. Period: 105.10 min.

    Maroc-Tubsat was built by the Technical University of Berlin for the Centre Royal de Teledetection Spatiale, Morocco, and had a mass of 47 kg. It carried an imager and a store-forward communications test payload. The satellite measured 32x34x36,2 cm and was still in operation as of 2003.

  • Reflektor - . Mass: 8.00 kg (17.60 lb). Nation: Russia. Agency: RAKA. Manufacturer: NII KP. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Reflektor. Spacecraft: Reflektor. USAF Sat Cat: 27005 . COSPAR: 2001-056E. Apogee: 1,012 km (628 mi). Perigee: 985 km (612 mi). Inclination: 99.2000 deg. Period: 105.10 min.

    The 8 kg Reflektor was built by NII KP in Russia for space debris studies in a joint experiment with the Air Force Research Lab. The satellite consisted of of four triangular fins on a square base plus a deployable boom, with an array of laser retroreflectors. The satellite was 1.4 m long and 0.5 m wide but only 6 kg in mass. It will be used to calibrate laser imaging systems and other optical sensors.


2002 February 4 - . 02:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024.
  • MDS-1 - . Mass: 304 kg (670 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MDS. Spacecraft: MDS. USAF Sat Cat: 27367 . COSPAR: 2002-003A. Apogee: 35,753 km (22,215 mi). Perigee: 373 km (231 mi). Inclination: 28.3000 deg. Period: 633.80 min.

    Technology qualification flight - maiden flight of H-2A booster. Launch delayed from January 31 and February 3. The second stage began its first burn at 0251 UTC and at 0257 UTC entered a 500 km circular parking orbit. After a 12 minute coast the second burn put stage 2 in geostationary transfer orbit. At 0315 UTC the small DASH vehicle was meant to separate from the upper adapter, but this apparently did not occur. At 0325 UTC VEP-3/upper adapter/DASH combination separated from the second stage, followed by two semi-cylindrical side panels, revealing the previously enclosed MDS-1 technology satellite which was ejected at 0331 UTC. At 0425 UTC the second stage was scheduled to make a third burn to test engine restart, completing the H-2A-2F mission.

  • DASH - . Mass: 70 kg (154 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DASH 2002. Spacecraft: DASH 2002. USAF Sat Cat: 27368 . COSPAR: 2002-003B. Apogee: 35,778 km (22,231 mi). Perigee: 357 km (221 mi). Inclination: 28.3000 deg. Period: 634.00 min.

    The VEP-3 launch instrumentation package mounted on top of the DASH had a mass of 33 kg. The side adapter panels were halves of a 4.1m long 4.0m diameter cylinder. DASH (Demonstrator of Atmospheric Reentry System and Hypervelocity) was to test the reentry system for the MUSES-C asteroid probe. The plan was to fire the deorbit motor three days after launch, then separate the reentry capsule which would enter the Earth's atmosphere at 10 km/s and land in the Hodh el Gharbi region of Mauritania at about 8.5W 17.2N. Typical satellite reentries are at only 7.5 km/s, while hyperbolic (escape) velocity at the top of the atmosphere is over 11 km/s, so DASH would have been travelling much faster than typical reentry vehicles, but not quite at escape velocity.


2002 March 19 - . 22:28 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz-FG.
  • Kolibri - . Mass: 21 kg (46 lb). Nation: Russia. Agency: RAKA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Kolibri. Spacecraft: Kolibri. Decay Date: 2002-05-04 . USAF Sat Cat: 27394 . COSPAR: 2001-051C. Apogee: 388 km (241 mi). Perigee: 385 km (239 mi). Inclination: 51.6000 deg.

2002 September 15 - . 10:30 GMT - . Launch Site: Taiyuan. LV Family: DF-31. Launch Vehicle: KT-1. FAILURE: Second stage failure.. Failed Stage: 2.
  • HTSTL-1 - . Mass: 50 kg (110 lb). Nation: China. Manufacturer: Tsinghua. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: HTSTL. Spacecraft: HTSTL. First attempted launch of the all-solid-propellant KT-1 launch vehicle. The 50 kg test satellite, built by university students, was to have been placed in a 300 km polar orbit..

2002 November 24 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • MEPSI - . Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: NASA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MEPSI. Spacecraft: MEPSI. Decay Date: 2003-01-31 . USAF Sat Cat: 27562 . COSPAR: 2002-052B. Apogee: 349 km (216 mi). Perigee: 332 km (206 mi). Inclination: 51.7000 deg. Period: 91.30 min.

    MEPSI (Micro-Electromechanical-based Picosat Satellite Inspection Experiment) consisted of two 1 kg boxes attached to each other by a 15-m tether. The boxes included an imaging camera and a MEM transceiver. They were ejected from the PLA (Picosat Launch Assembly) of shuttle Endeavour, a 6 kg box attached to an Adaptive Payload Carrier (APC) on the payload bay side wall.


2002 November 28 - . 06:07 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Mozhaets - . Mass: 80 kg (176 lb). Nation: Russia. Agency: NCST. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Strela. Spacecraft: Strela-1M. USAF Sat Cat: 27560 . COSPAR: 2002-054B. Apogee: 746 km (463 mi). Perigee: 683 km (424 mi). Inclination: 98.2000 deg. Period: 99.10 min.

    Delayed from September 12, October 29. Mozhaets was a Russian experimental, 90-kg minisatellite. It was designed and built by the cadets and teachers of a military space academy to learn about spacecraft operations. It may have been based on the Strela-1M small communications satellite bus. It included a GLONASS/GPS receiver, a particle detector, and an amateur radio payload.

  • Rubin-3-DSI - . Mass: 80 kg (176 lb). Nation: Russia. Agency: NCST. Manufacturer: AKO Polyot, Bremen. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Rubin. Spacecraft: Rubin. USAF Sat Cat: 27561 . COSPAR: 2002-054C. Apogee: 748 km (464 mi). Perigee: 687 km (426 mi). Inclination: 98.2000 deg. Period: 99.10 min.

    Delayed from September 12, October 29. Rubin-3-DSI, with a mass of 45 kg, was built by PO Polyot of Omsk (builders of the Kosmos-3M) and OHB System of Bremen. It remained attached to the booster final stage and measured the launch vehicle environment and performance


2002 December 14 - . 23:04 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • Mu-Labsat - . Mass: 65 kg (143 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Mu-Labsat. Spacecraft: Mu-Labsat. USAF Sat Cat: 27598 . COSPAR: 2002-056B. Apogee: 806 km (500 mi). Perigee: 793 km (492 mi). Inclination: 98.7000 deg. Period: 100.90 min.

    Technology. In 2003 the satellite released two tiny subsatellites in an experiment to test an onboard tracking imager for inspector satellites. The RITE (Remote Inspection Technology Experiment) targets are disks about 0.1m in diameter. They were released from Micro-LabSat on 2003 Mar 14 at 0140 UTC and 2003 May 14 at 0150 UTC


2002 December 20 - . 17:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. Launch Pad: LC109/95. LV Family: R-36M. Launch Vehicle: Dnepr.
  • SaudiSat 1S - . Payload: SaudiSat 2. Mass: 10 kg (22 lb). Nation: Saudi Arabia. Agency: RSRI. Manufacturer: KACST. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Saudisat. Spacecraft: SaudiSat. USAF Sat Cat: 27607 . COSPAR: 2002-058C. Apogee: 690 km (420 mi). Perigee: 633 km (393 mi). Inclination: 64.6000 deg. Period: 98.00 min. Amateur store-forward communications payload..
  • UniSat 2 - . Mass: 10 kg (22 lb). Nation: Italy. Agency: Makeyev Design Bureau. Manufacturer: La Sapienza. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: UniSat. Spacecraft: UniSat. USAF Sat Cat: 27608 . COSPAR: 2002-058D. Apogee: 667 km (414 mi). Perigee: 636 km (395 mi). Inclination: 64.6000 deg. Period: 97.80 min.

2003 January 6 - . 14:19 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4W. LV Family: Titan. Launch Vehicle: Titan II SLV.
  • Coriolis - . Payload: SA-200HP, P98-2. Mass: 828 kg (1,825 lb). Nation: USA. Agency: USAF. Manufacturer: Gilbert. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Coriolis. Spacecraft: Coriolis. USAF Sat Cat: 27640 . COSPAR: 2003-001A. Apogee: 936 km (582 mi). Perigee: 742 km (461 mi). Inclination: 98.7362 deg. Period: 101.55 min.

    Coriolis was an Air Force Space Test Program three-year meteorological science mission to demonstrate the viability of using polarimetry to measure ocean surface wind speed and direction from space, and to demonstrate predictions of geomagnetic disturbances through continuous observation of Coronal Mass Ejections. Launch delayed from August 22, November 15, December 15, 16, 17 and 18, 2002 and January 5, 2003.


2003 January 29 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.
  • XSS-10 - . Mass: 28 kg (61 lb). Nation: USA. Manufacturer: USAF RL. Class: Technology. Type: Rendezvous technology satellite. Spacecraft Bus: XSS. Spacecraft: XSS. USAF Sat Cat: 27664 . COSPAR: 2003-005B. Apogee: 811 km (503 mi). Perigee: 524 km (325 mi). Inclination: 39.7540 deg. Period: 97.95 min.

    On-orbit servicing technology demonstrator. XSS-10, a 28 kilogram microsatellite, was launched as a secondary payload aboard the Delta 2 launch vehicle carrying a Global Positioning Satellite (GPS) satellite. The mission demonstrated the complex interactions of line-of-sight guidance with basic inertial maneuvering. The micro-satellite was attached to the Delta 2 second stage. Once the second stage separated from the GPS satellite, the microsatellite waited for a sunlit Air Force Space Control Network pass before ejecting from the second stage. Once ejected, the microsatellite commenced an autonomous inspection sequence around the second stage, and live video was transmitted to ground stations. The entire mission lasted only 24 hours. Launch delayed from June 11 and August 16, 2001; March 6, April 29, August 11 and November 7, 2002.


2003 June 30 - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • CanX-1 - . Mass: 1.00 kg (2.20 lb). Nation: Canada. Agency: Toronto. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 27847 . COSPAR: 2003-031H. Apogee: 831 km (516 mi). Perigee: 817 km (507 mi). Inclination: 98.7000 deg. Period: 101.40 min. 1U cubesat from the University of Toronto, carried a camera for attitude determination. Failed. No signal from spacecraft..
  • DTUSAT - . Mass: 1.00 kg (2.20 lb). Nation: Denmark. Agency: Danish Technical University. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 27842 . COSPAR: 2003-031C. Apogee: 831 km (516 mi). Perigee: 816 km (507 mi). Inclination: 98.7000 deg. Period: 101.40 min. Danish 1U cubesat DTUSat remained silent after release despite several attempts to contact it. Carried a 450-meter copper wire tether for lowering the satellite orbit..
  • Cute-1 - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: TIT. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 27844 . COSPAR: 2003-031E. Apogee: 833 km (517 mi). Perigee: 817 km (507 mi). Inclination: 98.7000 deg. Period: 101.40 min. CUTE-I carried engineering test equipment and was built by the Tokyo Institute of Technology..
  • Quakesat - . Mass: 3.00 kg (6.60 lb). Nation: USA. Agency: QuakeFinder. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 27845 . COSPAR: 2003-031F. Apogee: 834 km (518 mi). Perigee: 820 km (500 mi). Inclination: 98.7000 deg. Period: 101.40 min. 3U cubesat for Stanford University/Quakesat LLC Quakesat was to be used for detection of ELF radio emissions from seismic activity. Successful..
  • CubeSat XI-IV - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Tokyo. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 27848 . COSPAR: 2003-031J. Apogee: 833 km (517 mi). Perigee: 818 km (508 mi). Inclination: 98.7000 deg. Period: 101.40 min. Cubesat XI carried technology tests for the University of Tokyo..
  • AAU Cubesat - . Mass: 1.00 kg (2.20 lb). Nation: Denmark. Agency: Aalborg. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 27846 . COSPAR: 2003-031G. Apogee: 831 km (516 mi). Perigee: 816 km (507 mi). Inclination: 98.7000 deg. Period: 101.40 min. Aalborg University successfully contacted its AAU-Cubesat nanosatellite after it was separated. It carried a 100-meter-resolution Earth imaging camera..

2003 August 22 - . 16:30 GMT - . Launch Site: Alcantara. Launch Complex: Alcantara VLS. LV Family: Sonda. Launch Vehicle: VLS-1. FAILURE: Failure - Exploded on pad during final prelaunch processing. 21 people were killed, with none injured.. Failed Stage: 1.
  • SATEC - . Payload: SATEC. Mass: 57 kg (125 lb). Nation: Brazil. Agency: INPE. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SATEC. Spacecraft: SATEC. COSPAR: F20030822A.

    Launch was due on August 25. Was to have been on third qualification flight after two previous failures. The launch had already been delayed from October 2002, then May 7 and June 20 2003. It appeared that one of the strapon boosters ignited by accident. The two satellite payloads were also destroyed in the blast, as was the launch pad.

  • Unosat - . Payload: Unosat. Mass: 9.00 kg (19.80 lb). Nation: Brazil. Agency: Parana. Class: Technology. Type: Technology satellite. Spacecraft Bus: Unosat. Spacecraft: Unosat. COSPAR: F20030822B.

2003 September 27 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G.
  • SMART-1 - . Mass: 370 kg (810 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Space probe technology. Spacecraft Bus: SMART-1. Spacecraft: SMART-1. COSPAR: 2003-043x. Apogee: 35,803 km (22,246 mi). Perigee: 35,769 km (22,225 mi). Inclination: 0.0900 deg. Period: 1,436.06 min.

    European Space Agency satellite which was to use ion drive and gravity assists to reach lunar orbit. The spacecraft made its third lunar resonance gravity assist on October 12, 2004. The continued gravitational effect of the Moon resulted in lunar capture on November 15, 2004,, when SMART-1 entered a 4962 x 51,477 km orbit around the Moon inclined at 81 degrees to the lunar equator.


2003 September 27 - . 06:12 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Mozhaets 4 - . Mass: 64 kg (141 lb). Nation: Russia. Agency: Mozhaiskiy. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Strela. Spacecraft: Strela-1M. USAF Sat Cat: 27943 . COSPAR: 2003-042E. Apogee: 694 km (431 mi). Perigee: 677 km (420 mi). Inclination: 98.2000 deg. Period: 98.50 min. A modified NPO-PM Strela-1M satellite carrying experiments built by students at the Mozhaiskiy space engineering academy..
  • Larets - . Mass: 64 kg (141 lb). Nation: Russia. Agency: KVR. Class: Technology. Type: Education satellite. Spacecraft Bus: Larets. Spacecraft: Larets. USAF Sat Cat: 27944 . COSPAR: 2003-042F. Apogee: 693 km (430 mi). Perigee: 676 km (420 mi). Inclination: 98.2000 deg. Period: 98.50 min. No information publicly released. TASS claimed this was a radar calibration satellite..
  • Rubin 4-DSI - . Mass: 45 kg (99 lb). Nation: Germany. Agency: KVR. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Rubin. Spacecraft: Rubin. USAF Sat Cat: 27945 . COSPAR: 2003-042G. Apogee: 693 km (430 mi). Perigee: 676 km (420 mi). Inclination: 98.2000 deg. Period: 98.50 min.

    RUBIN-4-dsi remained attached to the Kosmos launch vehicle final stage. The orbital telematics experiment transmited information on the rocket’s acceleration, vibration load and position via e-mail using the Orbcomm satellite communications system. In this way, it will be possible to track the rocket in orbit reliably and without any data loss. RUBIN-4-dsi was the fourth micro-satellite from the RUBIN series developed and maintained by OHB.

  • STSat 1 (KaistSat 4, Uribyol 4) - . Mass: 100 kg (220 lb). Nation: Korea South. Agency: KAIST. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: STSat. Spacecraft: STSat. USAF Sat Cat: 27939 . COSPAR: 2003-042A. Apogee: 696 km (432 mi). Perigee: 676 km (420 mi). Inclination: 98.2000 deg. Period: 98.50 min. Launch delayed from July 28, September 26. Payloads included the FUV Imaging Spectrograph (FIMS); Solid State Telescope (SST); Data Collection System (DCS); and Narrow Angle Star Sensor (NAST)..

2003 October 21 - . 03:16 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.
  • Chuangxin-1 - . Payload: Chuang Xin 1. Mass: 90 kg (198 lb). Nation: China. Agency: CAS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: CX-1. Spacecraft: CX-1. USAF Sat Cat: 28058 . COSPAR: 2003-049B. Apogee: 759 km (471 mi). Perigee: 686 km (426 mi). Inclination: 98.5000 deg. Period: 99.20 min.

    Chuangxin-1 (or Innovation-1) was China's first experimental small satellite for store-and-forward short message data communications in low Earth orbit. With a mass less than 100 kg, the Chuangxin-1 was developed in light of national strategic demands. Starting from 1999 with support of the national Knowledge Innovation Program of the Chinese Academy of Sciences (CAS), the project was carried out jointly by researchers from the CAS Shanghai Institute of Microsystem Information Technology and the CAS Shanghai Institute of Technical Physics. The satellite used spread spectrum communication and subsystems included a communication transponder, onboard computer, attitude control, energy source, thermal control, and structure. The mission was to demonstrate data communications for such sectors as traffic and transportation, environment protection, oil and gas transportation, flood and drought control, detection of forest fire and earthquake monitoring.


2003 October 30 - . 13:43 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Servis-1 - . Mass: 840 kg (1,850 lb). Nation: Japan. Agency: USEF. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SERVIS. Spacecraft: SERVIS. USAF Sat Cat: 28060 . COSPAR: 2003-050A. Apogee: 1,016 km (631 mi). Perigee: 984 km (611 mi). Inclination: 99.5000 deg. Period: 105.10 min.

    The mission of the 'Space Environment Reliability Verification of Integrated System' was to flight test a range of commerical-grade spacecraft components including a computer, star tracker, battery, and laser gyro. The objective was to lower the cost of future satellites.


2004 April 18 - . 15:59 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. Launch Pad: LC1?. LV Family: CZ. Launch Vehicle: Chang Zheng 2C.
  • Tansuo 1 - . Payload: Shiyan 1. Mass: 204 kg (449 lb). Nation: China. Agency: Harbin. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Shiyan. Spacecraft: Shiyan. USAF Sat Cat: 28220 . COSPAR: 2004-012A. Apogee: 616 km (382 mi). Perigee: 598 km (371 mi). Inclination: 97.7000 deg. Period: 96.80 min.

    China's first transmission-type small satellite capable of stereo mapping. It was jointly designed by the Harbin Polytechnic University, Chinese Research Institute of Space Technology, Changchun Photomechanical Institute of the Chinese Academy of Sciences (CAS)and Xi'an Surveys and Designs Institute. The experiment satellite carried out photographic surveys of China's land resources, monitored the geographical environment and conducted scientific research on mapping. It was handed over for use to the Satellite Remote-Sensing Ground Station of CAS following the on-orbit testing.


2004 June 29 - . 06:30 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. Launch Pad: LC109/95. LV Family: R-36M. Launch Vehicle: Dnepr.
  • Saudisat 2 - . Mass: 35 kg (77 lb). Nation: Saudi Arabia. Agency: RSRI. Manufacturer: KACST. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Saudisat. Spacecraft: SaudiSat. USAF Sat Cat: 28371 . COSPAR: 2004-025F. Apogee: 736 km (457 mi). Perigee: 698 km (433 mi). Inclination: 98.3000 deg. Period: 99.10 min. Experimental technology satellite that included imaging with resolution better than 15 m for remote sensing..
  • Unisat 3 - . Mass: 12 kg (26 lb). Nation: Italy. Agency: La Sapienza. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: UniSat. Spacecraft: UniSat. USAF Sat Cat: 28373 . COSPAR: 2004-025H. Apogee: 800 km (490 mi). Perigee: 684 km (425 mi). Inclination: 98.3000 deg. Period: 99.80 min.

2004 September 8 - . 23:14 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.
  • SJ-6-01A SJ-6A - . Payload: Shi Jian 6B. Mass: 800 kg (1,760 lb). Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SJ-6. Spacecraft: SJ-6. USAF Sat Cat: 28413 . COSPAR: 2004-035A. Apogee: 593 km (368 mi). Perigee: 578 km (359 mi). Inclination: 97.7000 deg. Period: 96.40 min.

    It was announced that the two satellites had a design life of at least two years, and would be used to probe the space environment, radiation and its effects, record space physical environment parameters, and conduct other related space experiments. The two satellites were built by the Shanghai Academy of Space Flight Technology and Dongfanghong Satellite Company under subcontract to the China Aerospace Science and Technology Corporation. The scientific instruments aboard the satellites were mainly manufactured by the China Electronics Technology Corporation. Some Western observors believed the mission of the satellites included electronic intelligence technology tests.

  • SJ-6-01B SJ-6B - . Payload: Shi Jian 6B. Mass: 800 kg (1,760 lb). Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: CAST2000. Spacecraft: CAST2000. USAF Sat Cat: 28414 . COSPAR: 2004-035B. Apogee: 602 km (374 mi). Perigee: 593 km (368 mi). Inclination: 97.7000 deg. Period: 96.60 min. CAST968 platform. Released one minute after SJ-6A..

2004 December 18 - . 16:26 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5Gp.
  • Nanosat 01 - . Mass: 20 kg (44 lb). Nation: Spain. Agency: Arianespace. Manufacturer: INTA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Nanosat 01. Spacecraft: Nanosat 01. USAF Sat Cat: 28493 . COSPAR: 2004-049B. Apogee: 666 km (413 mi). Perigee: 658 km (408 mi). Inclination: 98.1000 deg. Period: 98.00 min. Experimental nanosat built by the Spanish space agency (INTA)..

2004 December 21 - . 21:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4H.
  • 3CSat 1 Sparkie - . Payload: Nanosat 2. Mass: 15 kg (33 lb). Nation: USA. Agency: USAF. Manufacturer: New Mexico. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: 3CSat. Spacecraft: 3CSat. COSPAR: 2004-050x.

    One of a pair of student-built nanosats for stero cloud imagery. The satellites did not contact the ground after separation from the booster in a lower-than-planned orbit and their fate was unclear. It was believed that they separated but re-entered rapidly from the 105 km perigee orbit.

  • 3CSat 2 Ralphie - . Payload: Nanosat 2. Mass: 15 kg (33 lb). Nation: USA. Agency: USAF. Manufacturer: Colorado. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: 3CSat. Spacecraft: 3CSat. COSPAR: 2004-050x.

2004 December 24 - . 11:20 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32/2. LV Family: R-36. Launch Vehicle: Tsiklon-3.
  • Mikron - . Payload: MK-1TS. Mass: 66 kg (145 lb). Nation: Ukraine. Agency: NKAU. Manufacturer: Yuzhnoye. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS-1. Spacecraft: MS-1. Decay Date: 2005-09-30 . USAF Sat Cat: 28507 . COSPAR: 2004-052C. Apogee: 650 km (400 mi). Perigee: 280 km (170 mi). Inclination: 82.5559 deg.

    The Mikron microsatellite was equipped with a small visible range video camera. The information from the satellite was to be used to provide remote sensing of topography and meteorology. However the main purpose of the experimental satellite was to test the MS-1 microsatellite bus created under the Ukrainian National Space Program. The satellites spectral range was from 0.45 to 0.90 mm; swath width was 253-391 km; resolution 124-191 m.


2005 January 20 - . 03:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Universitetskiy - . Payload: Tatyana. Mass: 30 kg (66 lb). Nation: Russia. Agency: KVR. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Universitetskiy. Spacecraft: Universitetskiy. USAF Sat Cat: 28523 . COSPAR: 2005-002C. Apogee: 969 km (602 mi). Perigee: 911 km (566 mi). Inclination: 83.0000 deg. Period: 103.80 min.

    Student satellite for radiation studies, ejected from Cosmos 2414. The satellite was built by students at MGU (Moskovskiy Gosudarstvenniy Universitet) for the university's 250th anniversary, and was nicknamed 'Tatyana' since the university's anniversary day is St. Tatyana's day


2005 February 12 - . 21:03 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • Maqsat-B2 - . Mass: 3,622 kg (7,985 lb). Nation: Europe. Agency: ESA. Manufacturer: Kayser-Threde. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MAQSAT. Spacecraft: Maqsat. Decay Date: 2012-12-03 . USAF Sat Cat: 28543 . COSPAR: 2005-005B. Apogee: 35,409 km (22,002 mi). Perigee: 258 km (160 mi). Inclination: 6.7000 deg. Period: 624.90 min. Maqsat was a test payload built by Kayser-Threde to study the Ariane 5ECA launch environment. Remained attached to the upper stage..
  • SLOSHSAT - . Payload: SLOSHSAT-FLEVO. Mass: 127 kg (279 lb). Nation: Netherlands. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SLOSHSAT. Spacecraft: SLOSHSAT. USAF Sat Cat: 28544 . COSPAR: 2005-005C. Apogee: 35,723 km (22,197 mi). Perigee: 268 km (166 mi). Inclination: 6.8000 deg. Period: 631.20 min. Test satellite to study the sloshing of fluids in zero gravity, developed by the Netherlands Aerospace Laboratory. Equipped with a tank with 33.5 liters of water and an attitude control system..

2005 February 28 - . 19:09 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz-U-PVB.
  • Nanosputnik - . Payload: TEKh-42 / TNS-0 s/n 1. Mass: 5.00 kg (11.00 lb). Nation: Russia. Agency: RKA. Program: ISS. Class: Technology. Type: Navigation technology satellite. Flight: Soyuz TMA-5. Spacecraft Bus: Nanosputnik. Spacecraft: Nanosputnik. Decay Date: 2005-08-30 . USAF Sat Cat: 28547 . COSPAR: 2005-007C. Apogee: 353 km (219 mi). Perigee: 341 km (211 mi). Inclination: 51.6000 deg. Period: 91.50 min. Nanosatellite delivered by Progress M-52 to the International Space Station. 30 cm long, it was released from during a spacewalk on 28 March 2005..

2005 April 11 - . 13:35 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC8. LV Family: Minuteman. Launch Vehicle: Minotaur 1.
  • USA 165 - . Payload: XSS-11. Mass: 145 kg (319 lb). Nation: USA. Agency: USAF RL. Manufacturer: Lockheed. Class: Technology. Type: Rendezvous technology satellite. Spacecraft Bus: XSS. Spacecraft: XSS. Decay Date: 2013-11-12 . USAF Sat Cat: 28636 . COSPAR: 2005-011A. Apogee: 872 km (541 mi). Perigee: 840 km (520 mi). Inclination: 98.8000 deg. Period: 102.10 min.

    Delayed from November 9, 2004; January 19, March 18, 2005. Military Autonomous Rendezvous Technology. It tested navigation technologies for rendezvous that directly measured relative position to the target satellite. It was have to rendezvoused with several defunct American satellites. However it was only known to have conducted operations with its own Minotaur upper stage


2005 April 15 - . 17:26 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Vandenberg.. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL/HAPS.
  • DART - . Mass: 360 kg (790 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Class: Technology. Type: Rendezvous technology satellite. Spacecraft Bus: DART. Spacecraft: DART. USAF Sat Cat: 28642 . COSPAR: 2005-014A. Apogee: 747 km (464 mi). Perigee: 395 km (245 mi). Inclination: 96.6000 deg. Period: 96.10 min.

    Delayed from April 15; October 18, 19, 26, 28; Nov. 4, 9 and 11; 2004, and March 2, 2005. Autonomous Rendezvous Technology mission, planned to guide itself to within a few metres of a US satellite. On April 16, DART closed within 100 m of the MUBLCOM satellite, then evidently began a series of out-of-control maneuvers resulting in an in-space collission and MUBLCOM being bumped into a 3 to 5 km higher orbit. Remarkably both satellites continued to function. DART then detected that it was running unexpectedly low on nitrogen cold gas used for orientation. Its autonomous software aborted further rendezvous operations and the DART was deorbited shortly thereafter. Air dropped in Point Arguello WADZ.


2005 June 21 - . 19:46 GMT - . Launch Site: Barents Sea Launch Area. Launch Pad: 69.5 N x 34.2 E. Launch Platform: K-496. LV Family: R-29. Launch Vehicle: Volna. FAILURE: Failure.
  • Cosmos 1 - . Payload: Solnechny Parus. Mass: 103 kg (227 lb). Nation: USA. Agency: Planetary Society. Manufacturer: Lavochkin bureau. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: KAUR-1. Spacecraft: Parus.

    Launched from SSBN Borisoglebsk. First orbital flight attempt of converted SLBM. Payload was solar sail demonstrator. Delayed from late 2001; March 20 and October 2002; late March, August 28 and October, 2003; February, March, April 6, May 20 and 31, 2005.


2005 August 23 - . 21:10 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. Launch Pad: LC109/95. LV Family: R-36M. Launch Vehicle: Dnepr.
  • Kirari - . Mass: 570 kg (1,250 lb). Nation: Japan. Agency: JAXA. Manufacturer: Toshiba. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Kirari. Spacecraft: Kirari. USAF Sat Cat: 28809 . COSPAR: 2005-031A. Apogee: 614 km (381 mi). Perigee: 596 km (370 mi). Inclination: 97.8000 deg. Period: 96.80 min.

    Moved from J-1A . Delayed from August 15. Optical Inter-Orbit Communications Engineering Test Satellite. Its laser communications experiment was be used in with ESA's Artemis geostationary satellite. The satellite was renamed Kirari (twinkle) after launch.

  • Reimei - . Payload: Index. Mass: 60 kg (132 lb). Nation: Japan. Agency: JAXA. Manufacturer: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Reimei. Spacecraft: Reimei. USAF Sat Cat: 28810 . COSPAR: 2005-031B. Apogee: 650 km (400 mi). Perigee: 601 km (373 mi). Inclination: 97.8000 deg. Period: 97.20 min. Plasma Science Technology. INDEX, renamed Reimei ("Dawn") after launch, was a test satellite with new lightweight satellite components, and a demonstration auroral imager payload..

2005 October 27 - . 06:52 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: R-14. Launch Vehicle: Kosmos 11K65M.
  • Cubesat XI-V - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Tokyo. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 28895 . COSPAR: 2005-043F. Apogee: 708 km (439 mi). Perigee: 682 km (423 mi). Inclination: 98.2000 deg. Period: 98.70 min. University of Tokyo cubesat. Released from SSETI Express..

2006 February 21 - . 21:28 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V.
  • Cute 1.7 - . Mass: 3.00 kg (6.60 lb). Nation: Japan. Agency: ISAS. Manufacturer: TIT. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cute. Spacecraft: Cute. Decay Date: 2009-10-25 . USAF Sat Cat: 28941 . COSPAR: 2006-005C. Apogee: 685 km (425 mi). Perigee: 297 km (184 mi). Inclination: 98.2000 deg. Period: 94.40 min. Student subsatellite ejected from the M-V-8 third stage at 21:45 GMT..

2006 March 22 - . 14:03 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Vandenberg.. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL.
  • ST5-A - . Mass: 22 kg (48 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ST5. Spacecraft: ST5. USAF Sat Cat: 28980 . COSPAR: 2006-008A. Apogee: 4,539 km (2,820 mi). Perigee: 302 km (187 mi). Inclination: 105.6000 deg. Period: 136.90 min.

    Space Technology 5 was one of NASA's New Millenium Program projects. It consisted of three small spacecraft, each a half meter in each dimension, with a small extensible magnetometer boom. Study of the magnetosphere was however secondary to the Nanosat Constellation Trailblazer technology mission. This was to demonstrate fully functional nanosatellites, which included a cold gas microthruster and miniaturized telemetry/command and power systems. The Pegasus rocket was dropped from the L-1011 carrier aircraft over the Pacific at 123 deg W x 36 deg N. Air dropped in Point Arguello WADZ.

  • ST5-B - . Mass: 22 kg (48 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ST5. Spacecraft: ST5. USAF Sat Cat: 28981 . COSPAR: 2006-008B. Apogee: 4,540 km (2,820 mi). Perigee: 301 km (187 mi). Inclination: 105.6000 deg. Period: 136.90 min. Air dropped in Point Arguello WADZ..
  • ST5-C - . Mass: 22 kg (48 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ST5. Spacecraft: ST5. USAF Sat Cat: 28982 . COSPAR: 2006-008C. Apogee: 4,539 km (2,820 mi). Perigee: 303 km (188 mi). Inclination: 105.6000 deg. Period: 136.90 min. Air dropped in Point Arguello WADZ..

2006 March 24 - . Launch Site: Kwajalein. Launch Complex: Kwajalein OM. LV Family: Falcon. Launch Vehicle: Falcon 1. FAILURE: Fuel leak at T+25 seconds caused a fire in the first stage engine area. Failed Stage: 1.
  • Falconsat-2 - . Mass: 20 kg (44 lb). Nation: USA. Agency: USAF Colorado Springs. Manufacturer: USAFA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: FalconSat. Spacecraft: Falconsat. The satellite fell through the roof of SpaceX's machine shop on the atoll..

2006 April 15 - . 01:40 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC8. LV Family: Minuteman. Launch Vehicle: Minotaur 1.
  • Formosat 3A FM6 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Microstar. Spacecraft: MicroStar. USAF Sat Cat: 29047 . COSPAR: 2006-011A. Apogee: 538 km (334 mi). Perigee: 496 km (308 mi). Inclination: 72.0000 deg. Period: 95.00 min.

    FORMOSAT-3 consisted of six small 62 kg Orbcomm-type satellites with GPS receivers which were to measure atmospheric conditions by studying the effect of the atmosphere on GPS satellite signals passing through it. The satellites, also known as COSMIC (Constellation Observing System for Meteorology, Ionosphere and Climate), each raised their orbits over several months, all but one reaching operational orbits of around 770 x 840 km by September 2007.

  • Formosat 3B FM1 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Microstar. Spacecraft: MicroStar. USAF Sat Cat: 29048 . COSPAR: 2006-011B. Apogee: 541 km (336 mi). Perigee: 500 km (310 mi). Inclination: 72.0000 deg. Period: 95.00 min.
  • Formosat 3C FM5 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Microstar. Spacecraft: MicroStar. USAF Sat Cat: 29049 . COSPAR: 2006-011C. Apogee: 681 km (423 mi). Perigee: 567 km (352 mi). Inclination: 72.0000 deg. Period: 97.20 min.
  • Formosat 3D FM3 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Microstar. Spacecraft: MicroStar. USAF Sat Cat: 29050 . COSPAR: 2006-011D. Apogee: 538 km (334 mi). Perigee: 496 km (308 mi). Inclination: 72.0000 deg. Period: 95.00 min. Became stuck in intermediate 675 x 750 km due to solar panel failure..
  • Formosat 3E FM4 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Microstar. Spacecraft: MicroStar. USAF Sat Cat: 29051 . COSPAR: 2006-011E. Apogee: 538 km (334 mi). Perigee: 496 km (308 mi). Inclination: 72.0000 deg. Period: 95.00 min.
  • Formosat 3F FM2 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Microstar. Spacecraft: MicroStar. USAF Sat Cat: 29052 . COSPAR: 2006-011F. Apogee: 542 km (336 mi). Perigee: 497 km (308 mi). Inclination: 72.0000 deg. Period: 95.00 min.

2006 May 26 - . 18:50 GMT - . Launch Site: Barents Sea Launch Area. Launch Pad: 69.5 N x 34.2 E. Launch Platform: K-84. LV Family: R-29. Launch Vehicle: Shtil'-1.
  • Kompass-2 - . Mass: 80 kg (176 lb). Nation: Russia. Agency: Izmiran. Manufacturer: Makeyev bureau. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Kompas. Spacecraft: Kompas. Decay Date: 2011-12-28 . USAF Sat Cat: 29157 . COSPAR: 2006-019A. Apogee: 492 km (305 mi). Perigee: 402 km (249 mi). Inclination: 78.9000 deg. Period: 93.50 min.

    Complex Orbital Magneto-Plasma Autonomous Small Satellite. Earthquake research satellite for the Moscow-based IZMIRAN science institute. The satellite carried detectors for electrons, UHF/VHF waves, UV emission and radiation, a radio frequency analyser for electric field waves, and a Mayak ionospheric beacon. Reports indicated that the satellite did not respond to ground commands and that its mission was abandoned.


2006 June 21 - . 22:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.
  • USA 187 - . Payload: MiTEx-A. Mass: 225 kg (496 lb). Nation: USA. Agency: DARPA. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Mitex. Spacecraft: Mitex. USAF Sat Cat: 29240 . COSPAR: 2006-024A. Apogee: 36,222 km (22,507 mi). Perigee: 184 km (114 mi). Inclination: 25.2500 deg. Period: 639.26 min.

    The Microsatellite Technology Experiment was a classified mission, believed to be a test of prototype inspect-and-disable satellites that would control the constellation of geostationary satellites on which the world depends for television reception and communications. Each microsatellite, one built by Orbital Sciences, and the other by Lockheed Martin, had a mass of about 250 kg. They were believed to be solar-powered and equipped with propulsion systems that would allow them to rendezvous with geosynchronous satellites. Once they had reached the satellite, they would presumably be capable of destroying, disabling, or jamming them. To deliver the two satellites to near-synchronous orbit, a Naval Research Laboratory liquid propellant bus equipped with a 400 N main engine and solar panels was used.

  • USA 188 - . Payload: MiTEx-B. Mass: 225 kg (496 lb). Nation: USA. Agency: DARPA. Manufacturer: Lockheed. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Mitex. Spacecraft: Mitex. USAF Sat Cat: 29241 . COSPAR: 2006-024B.
  • USA 189 - . Payload: MiTEx Vehicle. Mass: 250 kg (550 lb). Nation: USA. Agency: NRL. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Mitex. Spacecraft: Mitex. USAF Sat Cat: 29242 . COSPAR: 2006-024C.

2006 July 12 - . 14:53 GMT - . Launch Site: Dombarovskiy. LV Family: R-36M. Launch Vehicle: Dnepr.
  • Genesis 1 - . Mass: 1,360 kg (2,990 lb). Nation: USA. Agency: RVSN. Manufacturer: Bigelow. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Bigelow. Spacecraft: Genesis Pathfinder. USAF Sat Cat: 29252 . COSPAR: 2006-029A. Apogee: 565 km (351 mi). Perigee: 552 km (342 mi). Inclination: 64.5000 deg. Period: 95.80 min. One third scale version of the privately-financed Nautilus inflatable human space habitat module..

2006 July 26 - . 19:43 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. Launch Pad: LC109/95. LV Family: R-36M. Launch Vehicle: Dnepr. FAILURE: First stage engine failed. Failed Stage: 1.
  • BelKA, Baumanets, Unisat 4, PicPot, and 9 nanosats - . Mass: 360 kg (790 lb). Nation: Belarus. Agency: BNAS. Manufacturer: Korolev bureau. Class: Technology. Type: Navigation technology satellite. Payload consisted of 19 nanosats from academic institutions: BelKA; Baumanets; Unisat-4; PICPOT; ICECube-1; ION; RINCON; AeroCube-1; CalPoly CP1; SEEDS; nCube-1; HAUSAT-1; MEROPE; CalPoly CP2; KUTESat; SACRED; Voyager; ICECube 3.

2006 September 9 - . 07:00 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: Chang Zheng 2C.
  • SJ-8 - . Mass: 3,100 kg (6,800 lb). Nation: China. Agency: CASC. Manufacturer: SAST. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: FSW. Spacecraft: FSW. Duration: 14.82 days. Decay Date: 2006-11-01 . USAF Sat Cat: 29385 . COSPAR: 2006-035A. Apogee: 336 km (208 mi). Perigee: 173 km (107 mi). Inclination: 63.0000 deg. Period: 89.60 min. Long delayed Seed Satellite, an experiment in which a large payload of seeds were exposed to te space environment for two weeks. The modified FSW optical reconnaisance satellite capsule was recovered in Sichuan at 02:43 GMT on September 24..

2006 September 22 - . 21:36 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V.
  • Hitsat - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Manufacturer: Hokkaido. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Hitsat. Spacecraft: Hitsat. Decay Date: 2008-06-18 . USAF Sat Cat: 29484 . COSPAR: 2006-041F. Apogee: 659 km (409 mi). Perigee: 279 km (173 mi). Inclination: 98.3000 deg. Period: 94.00 min.
  • SSSat - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: JAXA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SSSat. Spacecraft: SSSat. Decay Date: 2008-06-18 . USAF Sat Cat: 29484 . COSPAR: 2006-041D. Apogee: 659 km (409 mi). Perigee: 279 km (173 mi). Inclination: 98.3000 deg. Period: 94.00 min. Solar sail experiment..

2006 October 13 - . 20:56 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • LDREX 2 - . Nation: Japan. Agency: JAXA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: LDREX. Spacecraft: LDREX. Decay Date: 2010-09-30 . USAF Sat Cat: 29496 . COSPAR: 2006-043C. Apogee: 26,980 km (16,760 mi). Perigee: 227 km (141 mi). Inclination: 7.2000 deg. Period: 468.50 min. LDREX-2 was attached to the upper stage. It deployed a 6.5-meter antenna design planned for the later ETS-8 satellite.

2006 December 14 - . 21:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.
  • USA 193 - . Nation: USA. Agency: Seal Beach. Class: Technology. Type: Military technology satellite. Spacecraft Bus: USA 193. Spacecraft: USA 193. Decay Date: 2008-02-29 . USAF Sat Cat: 29651 . COSPAR: 2006-057A. Apogee: 376 km (233 mi). Perigee: 354 km (219 mi). Inclination: 58.5000 deg. Period: 91.83 min.

    Classifed NRO mission of uncertain objectives, possibly military observation with a mixed payload. Later it was revealed the on-board propulsion system had completely failed, putting the satellite in a rapidly-decaying orbit. The Pentagon said that the hydrazine propellant aboard consituted a risk and announced they would shoot the satellite down. The real objective may have been to demonstrate US antisatellite capability after a Chinese test in 2007. In any case, on 21 February 2008 the satellite was down to a 242 km x 257 km orbit. At 03:26 GMT an SM-3 missile was fired from the Aegis cruiser USS Lake Erie stationed west of Hawaii to intercept the satellite. The hit-to-kill warhead successfully rammed the satellite, breaking it up into 153 catalogued items of debris with perigees of 170-250 km and apogees of up to 2700 km.


2006 December 16 - . 06:32 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 204.
  • Kiku 8 - . Payload: ETS-8. Mass: 5,817 kg (12,824 lb). Nation: Japan. Agency: JAXA. Manufacturer: Melco. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS2000. Spacecraft: DS2000. USAF Sat Cat: 29656 . COSPAR: 2006-059A. Apogee: 35,798 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0500 deg. Period: 1,436.11 min.

    Engineering Test Satellite-8 was a Japanese prototype/operational demonstration for a number of new technologies: a large satellite bus, large-scale deployable 40-m-span antennae, mobile satellite communications system, mobile satellite digital multimedia broadcasting, and basic positioning using high-accuracy time standard devices. It will be positioned in geosynchronous orbit at 146 degrees East. JAXA developed two portable terrestrial systems to communicate directly with the satellite - a tiny telephone and a portable laptop computer. The satellite was to have a lifetime of ten years. As of 2007 Mar 11 located at 145.97E drifting at 0.010W degrees per day.


2007 January 10 - . 04:16 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV.
  • SRE-1 - . Mass: 550 kg (1,210 lb). Nation: India. Agency: ISRO. Class: Technology. Type: Re-entry test vehicle. Spacecraft Bus: SRE. Spacecraft: SRE. Decay Date: 2007-01-22 . USAF Sat Cat: 29711 . COSPAR: 2007-001C. Apogee: 643 km (399 mi). Perigee: 620 km (380 mi). Inclination: 97.9000 deg. Period: 97.40 min.

    India's Space Recovery Experiment-1 India's SRE-1 first lowered to its orbit to 485 km x 643 km on January 20. A 10-minute deorbit burn began at 03:30 GMT on January 22, with re-entry beginning at 04:07 and a successful splashdown at 04:16 GMT in the Bay of Bengal near 13.3 N / 81.4E. The capsule was successfully recovered by the Indian Navy. The capsule returned two microgravity payloads as well as proving basic technologies for any eventual Indian manned space program. It was also announced that the capsule could be used to orbit further microgravity payloads at low cost to customers.

  • LAPAN Tubsat - . Mass: 56 kg (123 lb). Nation: Indonesia. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Tubsat. Spacecraft: Tubsat. USAF Sat Cat: 29709 . COSPAR: 2007-001A. Apogee: 638 km (396 mi). Perigee: 620 km (380 mi). Inclination: 97.9000 deg. Period: 97.30 min. Experimental satellite developed with assistance from TUB (Berlin Technical University. It carried a 5-meter-resolution surveillance camera..
  • Pehuensat - . Mass: 6.00 kg (13.20 lb). Nation: Argentina. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Pehuensat. Spacecraft: Pehuensat. USAF Sat Cat: 29712 . COSPAR: 2007-001D. Apogee: 641 km (398 mi). Perigee: 621 km (385 mi). Inclination: 97.9000 deg. Period: 97.30 min. Experimental satellite developed by the Universidad Nacional del Comahue and AMSAT-LU. The satellte remained attached to the PSLV's Dual Launch Adapter..

2007 March 9 - . 03:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 401.
  • STPSat-1 - . Mass: 170 kg (370 lb). Nation: USA. Manufacturer: AeroAstro. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Astro-200. Spacecraft: Astro-200. USAF Sat Cat: 30775 . COSPAR: 2007-006D. Apogee: 560 km (340 mi). Perigee: 558 km (346 mi). Inclination: 35.4000 deg. Period: 95.80 min. STPSat carried experiments to study the Earth's atmosphere, ionosphere and radiation environment. It also released the two MEPSI picosatellites..
  • Astro - . Mass: 1,090 kg (2,400 lb). Nation: USA. Agency: DARPA. Manufacturer: Boeing. Class: Technology. Type: Rendezvous technology satellite. Spacecraft Bus: Orbital Express Astro. Spacecraft: Orbital Express Astro. Decay Date: 2013-10-25 . USAF Sat Cat: 30772 . COSPAR: 2007-006A. Apogee: 498 km (309 mi). Perigee: 491 km (305 mi). Inclination: 46.0000 deg. Period: 94.50 min.

    The active satellite portion of DARPA's Orbital Express satellite servicing experiment. Following operational tests while still joined or grappled together, the first 10-m distance Nextsat free flight and redocking by Astro was conducted on 5 May. On the second free-flight test on 11 May a serious computer failure left the two spacecraft 6 km apart. The problem was solved, revised software was uploaded to Astro, and it redocked with Nextsat on 19 May.

  • NextSat - . Mass: 250 kg (550 lb). Nation: USA. Agency: DARPA. Manufacturer: Ball. Class: Technology. Type: Rendezvous technology satellite. Spacecraft Bus: RS-300. Spacecraft: RS-300. USAF Sat Cat: 30774 . COSPAR: 2007-006C. Apogee: 498 km (309 mi). Perigee: 491 km (305 mi). Inclination: 46.0000 deg. Period: 94.50 min. The passive satellite portion of DARPA's Orbital Express satellite servicing experiment. NextSat carried hydrazine for fluid transfer experiments, but no propulsion system. Attitude was controlled by momentum wheels supplemented by magnetic torquer rods..
  • Midstar 1 - . Mass: 120 kg (260 lb). Nation: USA. Agency: USN PGS. Manufacturer: USNA. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Midstar. Spacecraft: Midstar. USAF Sat Cat: 30773 . COSPAR: 2007-006B. Apogee: 498 km (309 mi). Perigee: 495 km (307 mi). Inclination: 46.0000 deg. Period: 94.50 min.

    MidSTAR-1 was flown under the DoD Space Test Program and carried the Internet Communications Satellite (ICSat) Experiment (SERB 2002-39) and the Configurable Fault Tolerant Processor (CFTP) Experiment for the Naval Postgraduate School (SERB 2002-34). Planned mission duration was two years.

  • Falconsat-3 - . Mass: 50 kg (110 lb). Nation: USA. Agency: Martin. Manufacturer: USAF Colorado Springs. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: FalconSat. Spacecraft: Falconsat. USAF Sat Cat: 30776 . COSPAR: 2007-006E. Apogee: 559 km (347 mi). Perigee: 558 km (346 mi). Inclination: 35.4000 deg. Period: 95.80 min. USAF Academy student satellite with ionospheric experiments and plasma atttiude control thrusters..
  • CFESat - . Payload: Heavily modified Surrey MicroSat-100. Mass: 159 kg (350 lb). Nation: USA. Agency: Los Alamos. Manufacturer: Surrey. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SSTL-150. Spacecraft: SSTL-150. USAF Sat Cat: 30777 . COSPAR: 2007-006F. Apogee: 563 km (349 mi). Perigee: 558 km (346 mi). Inclination: 35.4000 deg. Period: 95.90 min.

    The Cibola Flight Experiment satellites carried eight new technologies for space flight validation, including a new power supply, inflatable antennas, deployable booms, a new type of launch-vehicle separation system, and a high-density pack of AA lithium-ion batteries. Cibola's on-board field programmable gate array supercomputer processed data onboard, then beamed only the results rather than the raw data to the ground. The Cibola also had a science mission: the study of lightning, ionospheric disturbances, and other sources of radio frequency (RF) atmospheric noise.

  • MEPSI Picosat - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: DARPA. Manufacturer: Aerospace. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. COSPAR: 2007-006x. Apogee: 563 km (349 mi). Perigee: 558 km (346 mi). Inclination: 35.4000 deg. Released from STPSat..
  • MEPSI Picosat - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: DARPA. Manufacturer: Aerospace. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. COSPAR: 2007-006x. Apogee: 563 km (349 mi). Perigee: 558 km (346 mi). Inclination: 35.4000 deg. Period: 1,436.10 min. Released from STPSat..

2007 March 21 - . 01:10 GMT - . Launch Site: Kwajalein. Launch Complex: Kwajalein OM. LV Family: Falcon. Launch Vehicle: Falcon 1. FAILURE: Liquid oxygen slosh in the second stage created an oscillation, putting the stage in an uncontrollable roll, starving the engine from propellant.. Failed Stage: 2.
  • DemoFlight 2 - . Nation: USA. Agency: DARPA. Class: Technology. Type: Navigation technology satellite.

    An oscillation appeared in the upper stage control system 90 seconds into the burn. This instability grew and after 30 seconds induced a roll torque that exceeded the control capability of the second stage roll control thrusters. The propellants were centrifuged away from the outlets, causing flame-out of the Kestrel engine. LOX slosh was believed to be the primary contributor to this instability. Second stage slosh baffles would be included in future boosters to prevent reoccurence of the problem.


2007 April 17 - . 06:46 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. Launch Pad: LC109/95. LV Family: R-36M. Launch Vehicle: Dnepr.
  • CAPE 1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: Makeyev Design Bureau. Manufacturer: Louisiana. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 31130 . COSPAR: 2007-012P. Apogee: 793 km (492 mi). Perigee: 646 km (401 mi). Inclination: 98.1000 deg. Period: 99.20 min. Cajun Advanced Picosatellite Experiment by the University of Louisiana at Lafayette..
  • Aerocube 2 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: Makeyev Design Bureau. Manufacturer: Aerospace. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 31122 . COSPAR: 2007-012F. Apogee: 771 km (479 mi). Perigee: 648 km (402 mi). Inclination: 98.1000 deg. Period: 99.00 min. 1U cubesat for Aerospace Corporation. Failed. Solar converter malfunction on 18 April 2007..
  • CSTB 1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: Makeyev Design Bureau. Manufacturer: Boeing. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 31133 . COSPAR: 2007-012R. Apogee: 771 km (479 mi). Perigee: 648 km (402 mi). Inclination: 98.1000 deg. Period: 99.00 min. CubeSat TestBed for Boeing IDS/Advanced Systems, Huntington Beach, California..
  • CP 3 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: Makeyev Design Bureau. Manufacturer: Cal Poly. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 31128 . COSPAR: 2007-012M. Apogee: 793 km (492 mi). Perigee: 646 km (401 mi). Inclination: 98.1000 deg. Period: 99.20 min. California Polytechnic University cubesat, the backup for CP2 lost in a Dnepr launch failure in 2006..
  • CP 4 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: Makeyev Design Bureau. Manufacturer: Cal Poly. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 31132 . COSPAR: 2007-012Q. Apogee: 771 km (479 mi). Perigee: 648 km (402 mi). Inclination: 98.1000 deg. Period: 99.00 min. California Polytechnic University cubesat..
  • Libertad - . Mass: 1.00 kg (2.20 lb). Nation: Colombia. Agency: Makeyev Design Bureau. Manufacturer: Arboleda. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 31129 . COSPAR: 2007-012N. Apogee: 793 km (492 mi). Perigee: 646 km (401 mi). Inclination: 98.1000 deg. Period: 99.20 min. Picosat built and operated by the Universidad Sergio Arboleda, Bogota, Colombia..
  • MAST - . Mass: 3.00 kg (6.60 lb). Nation: USA. Agency: Tethers. Manufacturer: Stanford. Class: Technology. Type: Tether technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 31126 . COSPAR: 2007-012K. Apogee: 783 km (486 mi). Perigee: 647 km (402 mi). Inclination: 98.1000 deg. Period: 99.10 min.

    Multi Application Survivable Tether experiment, built by Tethers Unlimited Inc and Stanford University. MAST consisted of the TED (Tether Deployer) satellite, with a 1 km deployable multi-strand Hoytether; RALPH, a small end mass satellite; and between them, GADGET, an inspector 1U cubesat which could move along the tether. Before deployment the MAST package fit into a 0.3 m x 0.1 m module. Failed to deploy, but radio contact made.


2007 April 23 - . 10:00 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. LV Family: PSLV. Launch Vehicle: PSLV.
  • AAM - . Mass: 185 kg (407 lb). Nation: India. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: AAM. Spacecraft: AAM. USAF Sat Cat: 31136 . COSPAR: 2007-013B. Apogee: 549 km (341 mi). Perigee: 531 km (329 mi). Inclination: 2.5000 deg. Period: 95.50 min. The Dual Launch Adapter housed the secondary payload, an Advanced Avionics Module for future use on Indian launch vehicles. The AAM remained attached to the PSLV fourth stage..

2007 April 24 - . 06:48 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA0B. LV Family: Minuteman. Launch Vehicle: Minotaur 1.
  • NFIRE - . Payload: SA-200B. Mass: 494 kg (1,089 lb). Nation: USA. Manufacturer: Gilbert. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SA-200. Spacecraft: SA-200. Decay Date: 2015-11-04 . USAF Sat Cat: 31140 . COSPAR: 2007-014A. Apogee: 497 km (308 mi). Perigee: 489 km (303 mi). Inclination: 48.2000 deg. Period: 94.50 min.

    Near Field Infrared Experiment conducted by the US Missile Defense Agency. Its Track Sensor Payload included visible and short, medium and long wave infrared sensors to observe missiles launched from the ground, and obtain basic data to distinguish between the missile and its hot rocket exhaust plume for application to anti-ballistic missile systems. Secondary payloads included Tesat, a German laser communications terminal, and its hydrazine propulsion system. This was used to maneuver the satellite from its initial 255 km x 465 km x 48.2 deg orbit to 489 km x 497 km by 18 May. The orbit was changed to 243 km x 487 km on 9 August and by 23 August was 219 km x 450 km. The satellite had a dry mass of 380 kg dry, was 2.7 m long and 1.3 m in diameter.

    The first major sensor test occurred when Minotaur II rocket TLV-7, was fired at 08:30 GMT on 23 August from Vandenberg in NFIRE Mission 2a. The Minotaur II was aimed to pass within 4 and 20 km of the NFIRE satellite while its third stage motor burning, to allow NFIRE to get a close look at the rocket and its exhaust. The Missile Defense Agency reported that the experiment was successful.


2007 May 25 - . 07:12 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: Chang Zheng 2D.
  • Zheda Pixing 1 - . Mass: 2.00 kg (4.40 lb). Nation: China. Agency: Zhejiang. Manufacturer: SIMIT. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Zheda Pixing. Spacecraft: Zheda Pixing. COSPAR: 2007-019x. Experimental microelectronics research picosatellite..

2007 September 14 - . 11:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz-U-PVB.
  • YES-2 - . Payload: Young Engineers Satellite. Mass: 5.00 kg (11.00 lb). Nation: Europe. Agency: ESA. Manufacturer: ESTEC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: YES. Spacecraft: YES. COSPAR: 2007-040x.

    YES-2/Fotino space tether for re-entry experiment. The YES-2 tether was deployed from the Nauka module at the front end of Foton at 04:47 on 25 September, and releaed at 07:20 after reaching only 8.5 km of the planned 30 km tether length. The 5 kg Fotino reentry capsule separated from the MASS data support system at the end of the tether at around 07:30. The idea was to toss the Fotino against the direction of orbital motion to push it into a lower orbit and re-entry without the need for a retrorocket. Unfortunately the final outcome of the experiment remained unknown.


2008 April 28 - . 03:53 GMT - . Launch Site: Sriharikota. LV Family: PSLV. Launch Vehicle: PSLV.
  • Cute-1.7-APD-II - . Mass: 4.00 kg (8.80 lb). Nation: Japan. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 32785 . COSPAR: 2008-021C. Apogee: 635 km (394 mi). Perigee: 615 km (382 mi). Inclination: 98.0000 deg. Period: 97.20 min. 2U cubesat for Tokyo Institute of Technology. Separation system demonstration and Avalanche Photo Diode sensor experiment. Successful..
  • Compass 1 - . Mass: 1.00 kg (2.20 lb). Nation: Germany. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 32787 . COSPAR: 2008-021E. Apogee: 636 km (395 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.20 min. 1U cubesat for Fachhochschule Aachen nanosat. Demonstration of commercial off-the-shelf components and taking photos. Successful..
  • Delfi-C3 - . Mass: 5.00 kg (11.00 lb). Nation: Netherlands. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 32789 . COSPAR: 2008-021G. Apogee: 636 km (395 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.20 min. Technical University of Delft 3U cubesat. On-orbit testing of thin film solar cells (TFSC) and autonomous wireless sun sensor (AWSS). Demonstrated the world's first linear amateur radio transponder on a CubeSat..
  • SEEDS 2 - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 32791 . COSPAR: 2008-021J. Apogee: 637 km (395 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.20 min. 1U cubesat for Nihon University, Japan. Amateur radio experiments and preprogrammed message sending. Successful..

2008 August 3 - . 03:34 GMT - . Launch Site: Kwajalein. Launch Complex: Kwajalein OM. LV Family: Falcon. Launch Vehicle: Falcon 1. FAILURE: The new Merlin 1C first stage engine completed its burn, but the thrust took longer to decay than expected. It was still thrusting when stage 2 tried to separate, and the two stages collided, setting the second stage tumbling..
  • Nanosail-D - . Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: SpaceX. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. 3U cubesat for NASA. Technology mission..
  • PreSat - . Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: SpaceX. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. 3U cubesat for NASA. Technology mission..

2008 August 16 - . 19:32 GMT - . Launch Site: Semnan. LV Family: Nodong 1. Launch Vehicle: Safir. FAILURE: Second stage failed catastrophically..
  • Omid - . Nation: Iran. Agency: IRSA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Omid. Spacecraft: Omid. Apogee: 152 km (94 mi).

    Iranian suborbital launch in support of development of an indigenous satellite launch capability. Western analysts claimed it was a failed satellite launch attempt, and that the second stage of the launch vehicle failed catastrophically at 152 km altitude.


2008 August 22 - . 09:10 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA0B. LV Family: Pegasus. Launch Vehicle: ALV. FAILURE: Went off course and destroyed by range safety 27 seconds after launch..
  • HyBolt/SOAREX-VI - . Nation: USA. Agency: Clemson. Class: Technology. Type: Navigation technology satellite. Apogee: 3.50 km (2.10 mi). Carried HyBOLT and SOAREX-VI hypersonic research experiments..

2008 September 25 - . 13:10 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: Chang Zheng 2F.
  • BX-1 - . Mass: 40 kg (88 lb). Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Flight: Shenzhou 7. Spacecraft Bus: Ban Xing. Spacecraft: Ban Xing. Decay Date: 2009-10-29 . USAF Sat Cat: 33392 . COSPAR: 2008-047G. Apogee: 331 km (205 mi). Perigee: 321 km (199 mi). Inclination: 42.4000 deg. Period: 91.00 min. BanXing (companion satellite) subsatellite released by Shenzhou 7. If maneuvered away and back to the Shenzhou orbital module after the mission..

2008 September 28 - . Launch Site: Kwajalein. Launch Complex: Kwajalein OM. LV Family: Falcon. Launch Vehicle: Falcon 1.
  • Ratsat - . Nation: USA. Agency: SpaceX. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Ratsat. Spacecraft: Ratsat. USAF Sat Cat: 33393 . COSPAR: 2008-048A. Apogee: 643 km (399 mi). Perigee: 622 km (386 mi). Inclination: 9.3000 deg. Period: 97.40 min. First successful launch of low-cost Falcon launch vehicle. The second stage demonstrated restart. The payload was a dummy mass which remained attached to the stage..

2008 November 5 - . 00:15 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: Chang Zheng 2D.
  • Chuangxin-1-02 - . Mass: 90 kg (198 lb). Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: CX-1. Spacecraft: CX-1. USAF Sat Cat: 33433 . COSPAR: 2008-056A. Apogee: 805 km (500 mi). Perigee: 785 km (487 mi). Inclination: 98.5000 deg. Period: 100.80 min. Microsat built by the Shanghai Institute of Microsystems and Information Technology) and the Shanghai Academy of Space Technology. The satellite was designed to collect and relay hydrological and meteorological data and data for disaster relief..
  • Shiyan Weixing 3 - . Payload: CAST1000C. Mass: 204 kg (449 lb). Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: CAST1000. Spacecraft: CAST1000. USAF Sat Cat: 33434 . COSPAR: 2008-056B. Apogee: 806 km (500 mi). Perigee: 785 km (487 mi). Inclination: 98.5000 deg. Period: 100.80 min. Built by the Harbin Institute of Technology and the DFH Satellite Company for 'experiments on new technologies in atmospheric exploration'..

2008 November 12 - . 05:55 GMT - . Launch Site: Balasore. LV Family: K-15. Launch Vehicle: Shourya.
2008 November 13 - . 09:06 GMT - . Launch Site: Biscarosse. LV Family: MSBS M51. Launch Vehicle: MSBS M51.
2008 November 26 - . 13:20 GMT - . Launch Site: Plesetsk. LV Family: Topol. Launch Vehicle: Yars.
2008 November 28 - . Launch Site: Barents Sea Launch Area. Launch Platform: TK-208. LV Family: Topol. Launch Vehicle: Bulava.
2008 December 23 - . 03:00 GMT - . Launch Site: Barents Sea Launch Area. Launch Platform: TK-208. LV Family: Topol. Launch Vehicle: Bulava.
  • RV-1 - . Nation: Russia. Agency: VMF. Class: Technology. Type: Technology satellite. Apogee: 100 km (60 mi).

2009 January 23 - . 03:54 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • SDS-1 - . Mass: 100 kg (220 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: JAXA SDS. Spacecraft: JAXA SDS. USAF Sat Cat: 33494 . COSPAR: 2009-002C. Apogee: 668 km (415 mi). Perigee: 663 km (411 mi). Inclination: 98.0000 deg. Period: 98.00 min. JAXA Small Demonstration Satellite, a microsatellite with a camera, GPS receiver and sun sensor..
  • Kagayaki - . Mass: 28 kg (61 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Kagayaki. Spacecraft: Kagayaki. USAF Sat Cat: 33497 . COSPAR: 2009-002F. Apogee: 670 km (410 mi). Perigee: 668 km (415 mi). Inclination: 98.0000 deg. Period: 98.10 min. Technology satellite built by Sorun Corporation, Tokyo, with several technology payloads..
  • Kukai - . Mass: 5.00 kg (11.00 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Kukai. Spacecraft: Kukai. USAF Sat Cat: 33498 . COSPAR: 2009-002G. Apogee: 667 km (414 mi). Perigee: 647 km (402 mi). Inclination: 98.0000 deg. Period: 97.90 min. Also named STARS, a Kagawa University picosatellite demonstrating a tethered space robot. It consisted of two tethered box-shaped packages, dubbed Ku and Kai..

2009 February 2 - . Launch Site: Semnan. LV Family: Nodong 1. Launch Vehicle: Safir.
  • Omid - . Mass: 25 kg (55 lb). Nation: Iran. Agency: IRSA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Omid. Spacecraft: Omid. Decay Date: 2009-04-25 . USAF Sat Cat: 33506 . COSPAR: 2009-004A. Apogee: 373 km (231 mi). Perigee: 245 km (152 mi). Inclination: 55.5500 deg. Period: 90.70 min. First Iranian satellite launched by an Iranian launch vehicle..

2009 April 5 - . 02:30 GMT - . LV Family: Unha. Launch Vehicle: Unha-2. FAILURE: Third stage failure..
  • Kwangmyongsong 2 - . Nation: Korea North. Agency: Choson. Class: Technology. Type: Technology satellite. Second North Korean satellite launch attempt. Fell in Pacific..

2009 May 18 - . 23:55 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA0B. LV Family: Minuteman. Launch Vehicle: Minotaur 1.
  • Aerocube 3 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2011-08-11 . USAF Sat Cat: 35005 . COSPAR: 2009-028E. Apogee: 464 km (288 mi). Perigee: 427 km (265 mi). Inclination: 40.5000 deg. Period: 93.50 min. 10-cm 1U cubesat for Aerospace Corporation..
  • Tacsat 3 - . Mass: 400 kg (880 lb). Nation: USA. Agency: USAF. Program: Tacsat. Class: Technology. Type: Surveillance jtechnology satellite. Spacecraft Bus: Tacsat ORS. Spacecraft: Tacsat ORS. Decay Date: 2012-04-30 . USAF Sat Cat: 35001 . COSPAR: 2009-028A. Apogee: 465 km (288 mi). Perigee: 433 km (269 mi). Inclination: 40.5000 deg. Period: 93.60 min. USAF experimental imaging satellite..
  • Pharmasat - . Mass: 3.00 kg (6.60 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2012-08-14 . USAF Sat Cat: 35002 . COSPAR: 2009-028B. Apogee: 465 km (288 mi). Perigee: 429 km (266 mi). Inclination: 40.5000 deg. Period: 93.50 min. 3U cubesat for NASA Ames Research Center, Santa Clara University, UTMB. Measured the effect of antifungal countermeasures on yeast strains in microgravity. 96 hour experiment was successful..
  • Hawksat 1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2011-10-06 . USAF Sat Cat: 35003 . COSPAR: 2009-028C. Apogee: 464 km (288 mi). Perigee: 428 km (265 mi). Inclination: 40.5000 deg. Period: 93.50 min. 10-cm 1U cubesat for Hawk Institute for Space Sciences..
  • CP6 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2011-09-04 . USAF Sat Cat: 35004 . COSPAR: 2009-028D. Apogee: 463 km (287 mi). Perigee: 427 km (265 mi). Inclination: 40.5000 deg. Period: 93.50 min. 10-cm 1U cubesat for California Polytechnic..

2009 July 15 - . 22:03 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • Dragonsat - . Mass: 3.00 kg (6.60 lb). Nation: USA. Agency: Clemson. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2010-03-17 . USAF Sat Cat: 35690 . COSPAR: 2009-038B. Apogee: 332 km (206 mi). Perigee: 326 km (202 mi). Inclination: 51.6000 deg. Period: 91.10 min.

    Ejected from the Endeavour on 30 July at 12:34 GMT. Dragonsat consisted of two 1.5 kg cubesats, BEVO-1 from the University of Texas at Austin and Aggiesat 2 from Texas A&M University. The two satellites were ejected attached to each other, but failed to separate as planned.


2009 July 29 - . 18:46 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. LV Family: R-36M. Launch Vehicle: Dnepr.
  • Nanosat 1B - . Mass: 22 kg (48 lb). Nation: Spain. Agency: Makeyev Design Bureau. Class: Technology. Type: Technology satellite. Spacecraft Bus: Nanosat. Spacecraft: Nanosat. USAF Sat Cat: 35685 . COSPAR: 2009-041E. Apogee: 677 km (420 mi). Perigee: 587 km (364 mi). Inclination: 98.1000 deg. Period: 97.30 min. INTA, Spain..

2009 August 25 - . 08:00 GMT - . Launch Site: Goheung. LV Family: Angara. Launch Vehicle: Naro-1. FAILURE: First and second stages operated correctly, but half of payload fairing failed to separate. Extra mass prevented the second stage and payload from reaching orbital velocity, and the satellite reentered over New Guinea..
2009 September 17 - . 15:55 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz-2-1B.
  • IRIS - . Nation: Russia. Agency: RKA. Class: Technology. Type: Technology satellite. USAF Sat Cat: 35867 . COSPAR: 2009-049C. Apogee: 502 km (311 mi). Perigee: 490 km (300 mi). Inclination: 97.3000 deg. Period: 94.50 min. Inflatable structure technology test - two inflatable masts carrying dummy solar arrays mounted on the Fregat upper stage and inflated after all payloads had been deployed..
  • Sumbandila - . Mass: 81 kg (178 lb). Nation: Russia. Agency: RKA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Sumbandila . Spacecraft: Sumbandila. USAF Sat Cat: 35870 . COSPAR: 2009-049F. Apogee: 505 km (313 mi). Perigee: 501 km (311 mi). Inclination: 97.3000 deg. Period: 94.70 min. South African imaging satellite with a ground resolution of 6.25 m..

2009 September 23 - . 06:21 GMT - . Launch Site: Sriharikota. LV Family: PSLV. Launch Vehicle: PSLV.
  • BEESAT - . Mass: 1.00 kg (2.20 lb). Nation: India. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 35933 . COSPAR: 2009-051C. Apogee: 710 km (440 mi). Perigee: 703 km (436 mi). Inclination: 98.4300 deg. Period: 98.92 min. Cubesat from Technische Universitat Berlin, Germany..
  • UWE-2 - . Mass: 1.00 kg (2.20 lb). Nation: India. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 35934 . COSPAR: 2009-051D. Apogee: 712 km (442 mi). Perigee: 704 km (437 mi). Inclination: 98.4200 deg. Period: 98.95 min. 1U cubesat from Julius-Maximilians-Universitat Wurzburg, Germany. ADCS technology demonstrator. Successful..
  • ITU-p-SAT 1 - . Mass: 1.00 kg (2.20 lb). Nation: India. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 35935 . COSPAR: 2009-051E. Apogee: 715 km (444 mi). Perigee: 704 km (437 mi). Inclination: 98.4400 deg. Period: 98.97 min. Cubesat from Istanbul Teknik Universitesi..

2009 November 2 - . 01:51 GMT - . Launch Site: Plesetsk. LV Family: UR-100N. Launch Vehicle: Rokot.
  • PROBA-2 - . Mass: 130 kg (280 lb). Nation: Europe. Agency: KVR. Class: Technology. Type: Technology satellite. Spacecraft Bus: MiniSil. Spacecraft: MiniSil. USAF Sat Cat: 36037 . COSPAR: 2009-059B. Apogee: 729 km (452 mi). Perigee: 709 km (440 mi). Inclination: 98.3000 deg. Period: 99.20 min. Project for On-Board Autonomy technology satellite for demonstration of technologies allowing operational autonomy. Also carried sun observation and space environment instruments..

2010 May 20 - . 21:58 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • Hayato - . Payload: K-SAT. Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2010-06-28 . USAF Sat Cat: 36573 . COSPAR: 2010-020A. Apogee: 172 km (106 mi). Perigee: 166 km (103 mi). Inclination: 30.0000 deg. Period: 87.90 min. 1U cubesat for Kagoshima University, released in parking orbit. Failed..
  • Ikaros - . Mass: 1,000 kg (2,200 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Solar sail technology satellite. Spacecraft Bus: Ikaros. Spacecraft: Ikaros. USAF Sat Cat: 36577 . COSPAR: 2010-020E.

    Solar sail test vehicle. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg. Deployed sail by 11 June, and acceleration due to the pressure of the light from the sun was as expected. Flyby of Venus at 80,000 km distance at 07:39 GMT on 8 December 2010 returned images of sail with crescent Vensu in the background.

  • Unitec-1 - . Payload: Shinen. Mass: 16 kg (35 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Technology satellite. Spacecraft Bus: Unitec. Spacecraft: Unitec. USAF Sat Cat: 36578 . COSPAR: 2010-020F. Space qualification of university-built computers. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg..

2010 June 2 - . 01:58 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Servis 2 - . Mass: 900 kg (1,980 lb). Nation: Japan. Agency: KVR. Class: Technology. Type: Technology satellite. Spacecraft Bus: SERVIS. Spacecraft: Servis. USAF Sat Cat: 36588 . COSPAR: 2010-023A. Apogee: 1,212 km (753 mi). Perigee: 1,185 km (736 mi). Inclination: 100.4000 deg. Period: 109.40 min. Space Environment Reliability Verification Integrated System to test usability of off-the-shelf commercial components in place of space-qualified hardware..

2010 June 10 - . 18:01 GMT - . Launch Site: Goheung. LV Family: Angara. Launch Vehicle: Naro-1. FAILURE: First stage failure..
  • STSAT-2B - . Mass: 99 kg (218 lb). Nation: Korea South. Agency: KARI. Class: Technology. Type: Technology satellite. Spacecraft Bus: STSat. Spacecraft: STSAT. Science and Technology Satellite with Lyman-alpha imaging solar telescope and laser altimeter..

2010 June 15 - . 14:42 GMT - . Launch Site: Dombarovskiy. LV Family: R-36M. Launch Vehicle: Dnepr.
  • Prisma - . Mass: 140 kg (300 lb). Nation: Sweden. Agency: Makeyev Design Bureau. Class: Technology. Type: Technology satellite. Spacecraft Bus: Prisma. Spacecraft: Prisma. USAF Sat Cat: 36599 . COSPAR: 2010-028B. Apogee: 787 km (489 mi). Perigee: 724 km (449 mi). Inclination: 98.3000 deg. Period: 99.90 min. Prototype Research Instruments and Space Mission technology Advancement satellite to test space rendezvous and formation-flight technologies. Consisted of 140 kg primary satellite and 40 kg target..

2010 July 12 - . 03:52 GMT - . Launch Site: Sriharikota. LV Family: PSLV. Launch Vehicle: PSLV.
  • Studsat - . Mass: 1.00 kg (2.20 lb). Nation: India. Agency: ISRO. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 36796 . COSPAR: 2010-035B. Apogee: 640 km (390 mi). Perigee: 621 km (385 mi). Inclination: 98.2000 deg. Period: 97.30 min. ISRO-sponsored Indian student-designed 1U cubesat. First Indian picosatellite..
  • Tisat 1 - . Mass: 1.00 kg (2.20 lb). Nation: Switzerland. Agency: ISRO. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 36799 . COSPAR: 2010-035E. Apogee: 639 km (397 mi). Perigee: 619 km (384 mi). Inclination: 98.2000 deg. Period: 97.30 min. Swiss student 1U cubesat for SUPSI. Successful..

2010 July 31 - . LV Family: R-36M. Launch Vehicle: Dnepr.
  • Prisma Tango - . Payload: Tango. Mass: 40 kg (88 lb). Nation: Sweden. Agency: Makeyev Design Bureau. Class: Technology. Type: Rendezvous technology satellite. Spacecraft Bus: Prisma. Spacecraft: Prisma. USAF Sat Cat: 36827 . COSPAR: 2010-028F. Apogee: 786 km (488 mi). Perigee: 725 km (450 mi). Inclination: 98.3000 deg. Period: 99.90 min. Tango subsatellite separated from the main Prisma satellite Mango on 11 August 2010 at 17:51 GMT to begin formation flying experiments..

2010 September 26 - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: Chang Zheng 2D.
  • Zheda Pixing 1B - . Mass: 3.00 kg (6.60 lb). Nation: China. Agency: SISE. Class: Technology. Type: Technology satellite. Spacecraft Bus: Zheda Pixing. Spacecraft: Zheda Pixing. USAF Sat Cat: 37166 . COSPAR: 2010-047B. Apogee: 657 km (408 mi). Perigee: 622 km (386 mi). Inclination: 98.0000 deg. Period: 97.50 min. Picosatellite testing various systems for later operational satellites..
  • Zheda Pixing 1C - . Mass: 3.00 kg (6.60 lb). Nation: China. Agency: SISE. Class: Technology. Type: Technology satellite. Spacecraft Bus: Zheda Pixing. Spacecraft: Zheda Pixing. USAF Sat Cat: 37167 . COSPAR: 2010-047C. Apogee: 657 km (408 mi). Perigee: 623 km (387 mi). Inclination: 98.0000 deg. Period: 97.50 min. Picosatellite testing various systems for later operational satellites..

2010 November 20 - . 01:25 GMT - . Launch Site: Kodiak. LV Family: Peacekeeper. Launch Vehicle: Minotaur IV.
  • USA 217 - . Payload: STPSat-2 SIV. Mass: 135 kg (297 lb). Nation: USA. Manufacturer: AeroAstro. Class: Technology. Type: Technology satellite. Spacecraft Bus: Astro-200. Spacecraft: Astro-200. USAF Sat Cat: 37222 . COSPAR: 2010-062A. Technology experiments. Lead satellite of USAF Space Test Program mission S26..
  • USA 220 - . Payload: Fastsat-HSV. Mass: 140 kg (300 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Fastsat. Spacecraft: Fastsat. USAF Sat Cat: 37225 . COSPAR: 2010-062D. Developed by NASA-Marshall and subcontractors in Huntsville; carried ionospheric and atmospheric experiments, a USAF experiment, and the Nanosail-D2 solar sail..
  • USA 221 - . Payload: Falconsat-5. Mass: 161 kg (354 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: FalconSat. Spacecraft: Falconsat. USAF Sat Cat: 37226 . COSPAR: 2010-062E. US Air Force Academy satellite with experiments to study plasma and the ionosphere..
  • USA 222 - . Payload: Fastrac 1. Mass: 30 kg (66 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Fastrac satellite. Spacecraft: Fastrac satellite. USAF Sat Cat: 37227 . COSPAR: 2010-062F. Developed by University of Texas at Austin with USAF funding for formation flying experiments..
  • USA 228 - . Payload: Fastrac 2. Mass: 30 kg (66 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Fastrac satellite. Spacecraft: Fastrac satellite. USAF Sat Cat: 37380 . COSPAR: 2010-062M. Developed by University of Texas at Austin with USAF funding for formation flying experiments..
  • Ballast A - . Payload: S26 Ballast A. Nation: USA. Class: Technology. Type: Technology satellite. USAF Sat Cat: 37230 . COSPAR: 2010-062J.
  • Ballast B - . Payload: S26 Ballast B. Nation: USA. Class: Technology. Type: Technology satellite. USAF Sat Cat: 37231 . COSPAR: 2010-062K.
  • Nanosail-D - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 37361 . COSPAR: 2010-062L. 3U cubesat for NASA with 3-m span solar sail; ejected from USA 220 on 18 January 2011 unexpectedly after earlier ejection efforts failed..

2010 December 8 - . 15:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • QBX2 - . Payload: QbX-2. Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2011-12-31 . USAF Sat Cat: 37245 . COSPAR: 2010-066B. Apogee: 187 km (116 mi). Perigee: 173 km (107 mi). Inclination: 34.5000 deg. Period: 88.10 min. 3U cubesat built by Pumpkin Inc of San Francisco for the National Reconaissance Office's Colony-1 technology development project. Successful..
  • SMDC One - . Payload: SMDC-One. Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2011-12-31 . USAF Sat Cat: 37246 . COSPAR: 2010-066C. Apogee: 184 km (114 mi). Perigee: 173 km (107 mi). Inclination: 34.5000 deg. Period: 88.10 min. Operational Nanosatellite Experiment for the US Army Space and Missile Defense Center.
  • Perseus 003 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2010-01-06 . USAF Sat Cat: 37247 . COSPAR: 2010-066D. Apogee: 190 km (110 mi). Perigee: 179 km (111 mi). Inclination: 34.5000 deg. Period: 88.20 min. Los Alamos National Laboratory cubesat, perhaps for ionospheric monitoring..
  • Perseus 001 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2010-12-30 . USAF Sat Cat: 37248 . COSPAR: 2010-066E. Apogee: 183 km (113 mi). Perigee: 176 km (109 mi). Inclination: 34.5000 deg. Period: 88.10 min. Los Alamos National Laboratory cubesat, perhaps for ionospheric monitoring..
  • QBX1 - . Payload: QbX-1. Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2011-12-30 . USAF Sat Cat: 37249 . COSPAR: 2010-066F. Apogee: 197 km (122 mi). Perigee: 185 km (114 mi). Inclination: 34.5000 deg. Period: 88.30 min. 3U cubesat satellite built by Pumpkin Inc of San Francisco for the National Reconaissance Office's Colony-1 technology development project. Successful..
  • Perseus 002 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2010-12-22 . USAF Sat Cat: 37250 . COSPAR: 2010-066G. Apogee: 193 km (119 mi). Perigee: 183 km (113 mi). Inclination: 34.5000 deg. Period: 88.20 min. Los Alamos National Laboratory cubesat, perhaps for ionospheric monitoring..
  • Perseus 000 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2010-12-30 . USAF Sat Cat: 37251 . COSPAR: 2010-066H. Apogee: 190 km (110 mi). Perigee: 180 km (110 mi). Inclination: 34.5000 deg. Period: 88.20 min. Los Alamos National Laboratory cubesat, perhaps for ionospheric monitoring..
  • Mayflower - . Payload: Caerus/Mayflower. Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2010-12-22 . USAF Sat Cat: 37252 . COSPAR: 2010-066J. Apogee: 194 km (120 mi). Perigee: 179 km (111 mi). Inclination: 34.5000 deg. Period: 88.20 min.

    Experiment for Northrop Grumman NovaWorks and the University of Southern California. 3U cubesat with deployable solar panels composed of a Northrop Grumman's 2-unit Mayflower Next Generation Technology Nanosat and University of Southern California's 1-unit cubesat.


2011 February 6 - . 12:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC8. LV Family: Minuteman. Launch Vehicle: Minotaur 1.
  • USA 225 - . Payload: RPP. Mass: 235 kg (518 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: RPP. Spacecraft: RPP. USAF Sat Cat: 37364 . COSPAR: 2011-006A. National Reconnaissance Office Rapid Pathfinder Program technology satellite, probably placed in polar orbit. Built in less than two years for under $20 million to test classified sensors..

2011 March 4 - . 10:09 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Taurus. Launch Vehicle: Taurus 3110. FAILURE: Fairing failed to separate..
  • Hermes - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. 1U cubesat for University of Colorado at Boulder..
  • KySat-1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. University of Kentucky Cubesat..

2011 July 8 - . 07:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Shuttle. Launch Vehicle: Space Shuttle.
  • PSSC-2 - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: PSSC. Spacecraft: PSSC. Decay Date: 2011-12-08 . USAF Sat Cat: 37752 . COSPAR: 2011-031B. Apogee: 338 km (210 mi). Perigee: 307 km (190 mi). Inclination: 51.6000 deg. Period: 91.00 min. Picosatellite Solar Cell Testbed 2. Ejected from STS-135 prior to re-entry..

2011 August 17 - . 07:12 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC2. LV Family: R-36M. Launch Vehicle: Dnepr.
  • EDUSAT - . Mass: 10 kg (22 lb). Nation: Italy. Class: Technology. Type: Technology satellite. Spacecraft Bus: EDUSAT. Spacecraft: EDUSAT. USAF Sat Cat: 37788 . COSPAR: 2011-044A. Apogee: 698 km (433 mi). Perigee: 639 km (397 mi). Inclination: 98.2000 deg. Period: 98.10 min. Technology satellite built by the Universita di Roma la Sapienza..
  • Nigeriasat X - . Mass: 86 kg (189 lb). Nation: Nigeria. Agency: NSRDA. Manufacturer: Surrey. Class: Technology. Type: Technology satellite. Spacecraft Bus: MicroSat-100. Spacecraft: MicroSat-100. USAF Sat Cat: 37790 . COSPAR: 2011-044C. Apogee: 699 km (434 mi). Perigee: 656 km (407 mi). Inclination: 98.2000 deg. Period: 98.30 min. Technology demonstration satellite built by Surrey Satellite with participation by Nigerian engineers..
  • BPA-2/SL-24 - . Nation: Russia. Class: Technology. Type: Technology satellite. USAF Sat Cat: 37795 . COSPAR: 2011-044H. Apogee: 1,296 km (805 mi). Perigee: 692 km (429 mi). Inclination: 98.2000 deg. Period: 105.00 min.

    Yuzhnoye launch vehicle engineering payload which remained attached to the post-boost maneuvering upper stage after deployment of the other six satellites on the launch. 16 minutes after launch, at an altitude of 700 km, the upper stage dispensed the six satellites at two-minute intervals, then maneuvered into itself into a higher orbit.


2011 October 12 - . 05:31 GMT - . Launch Site: Sriharikota. LV Family: PSLV. Launch Vehicle: PSLV.
  • JUGNU - . Mass: 10 kg (22 lb). Nation: India. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 37839 . COSPAR: 2011-058B. Apogee: 866 km (538 mi). Perigee: 839 km (521 mi). Inclination: 20.0000 deg. Period: 102.00 min. 3U cubesat for the Indian Institute of Technology in Kanpur. Micro-imaging system, near infrared camera to observe vegetation, and GPS Receiver to aid tracking. Successful..
  • Vesselsat 1 - . Mass: 29 kg (63 lb). Nation: Luxembourg. Class: Technology. Type: Technology satellite. Spacecraft Bus: Vesselsat. Spacecraft: Vesselsat. USAF Sat Cat: 37840 . COSPAR: 2011-058C. Apogee: 868 km (539 mi). Perigee: 847 km (526 mi). Inclination: 20.0000 deg. Period: 102.10 min. OHB LuxSpace of Luxembourg satllite to provide AIS (ship tracking) services for Orbcomm..

2011 October 28 - . 09:48 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.
  • AubieSat-1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 37854 . COSPAR: 2011-061E. Apogee: 817 km (507 mi). Perigee: 457 km (283 mi). Inclination: 101.7000 deg. Period: 97.50 min. Auburn University, Alabama 1U cubesat. First CubeSat from Auburn University. Successful..
  • M-Cubed - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 37855 . COSPAR: 2011-061F. Apogee: 815 km (506 mi). Perigee: 457 km (283 mi). Inclination: 101.7000 deg. Period: 97.40 min. University of Michigan 1U cubesat. Michigan Multipurpose Mission. Objective was to obtain a mid-resolution image of the earth covering at least 60% land mass and a maximum of 20% cloud coverage from a single CubeSat platform..

2011 November 9 - . 03:21 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.
  • Tianxun 1 - . Mass: 58 kg (127 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: Tianxun. Spacecraft: Tianxun. USAF Sat Cat: 37874 . COSPAR: 2011-066A. Apogee: 489 km (303 mi). Perigee: 477 km (296 mi). Inclination: 97.4000 deg. Period: 94.30 min. Technology satellite built by the Nanjing University of Aeronautics and Astronautics with a small Earth observing CCD camera..

2011 November 20 - . 00:15 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: Chang Zheng 2D.
  • Chuangxin 1-03 - . Mass: 88 kg (194 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: CX-1. Spacecraft: CX-1. USAF Sat Cat: 37930 . COSPAR: 2011-068A. Apogee: 805 km (500 mi). Perigee: 784 km (487 mi). Inclination: 98.5000 deg. Period: 100.80 min. Store-dump communications satellite developed by China Academy of Science, Shanghai Academy of Space Technology, and Shanghai Telecomm..

2012 February 13 - . 10:00 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELV. LV Family: Vega. Launch Vehicle: Vega.
  • Almasat - . Mass: 12 kg (26 lb). Nation: Italy. Class: Technology. Type: Technology satellite. Spacecraft Bus: Almasat. Spacecraft: Almasat. USAF Sat Cat: 38078 . COSPAR: 2012-006B. Apogee: 1,415 km (879 mi). Perigee: 312 km (193 mi). Inclination: 69.5000 deg. Period: 102.20 min. Student satellite from the University of Bologna, testing a cold gas microthruster system and the platform for a future Earth observing satellite..
  • UNICubeSat-GG - . Mass: 1.00 kg (2.20 lb). Nation: Italy. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 38078 . COSPAR: 2012-006B. Apogee: 1,415 km (879 mi). Perigee: 312 km (193 mi). Inclination: 69.5000 deg. Period: 102.20 min. Student 1U cubesat from the GAUSS team-Universita Roma La Sapienza with a gravity gradient experiment. First Italian CubeSat..
  • MaSat-1 - . Mass: 1.00 kg (2.20 lb). Nation: Hungary. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-01-16 . USAF Sat Cat: 38079 . COSPAR: 2012-006C. Apogee: 1,385 km (860 mi). Perigee: 305 km (189 mi). Inclination: 69.5000 deg. Period: 101.80 min. Student 1U cubesat from the Budapest University of Technology and Economics. Technological demonstration. Successful. First Hungarian satellite.
  • PWSat-1 - . Mass: 1.00 kg (2.20 lb). Nation: Poland. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-12-31 . USAF Sat Cat: 38080 . COSPAR: 2012-006D. Apogee: 1,384 km (859 mi). Perigee: 306 km (190 mi). Inclination: 69.5000 deg. Period: 101.80 min. 1U cubesat student satellite from the Warsaw Institute of Technology..
  • Goliat - . Mass: 1.00 kg (2.20 lb). Nation: Romania. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-01-09 . USAF Sat Cat: 38081 . COSPAR: 2012-006E. Apogee: 1,386 km (861 mi). Perigee: 305 km (189 mi). Inclination: 69.5000 deg. Period: 101.80 min. Student 1U cubesat from the University of Bucharest. Earth imaging and space environment measuring. First Romanian satellite..
  • e-st@r - . Mass: 1.00 kg (2.20 lb). Nation: Italy. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-08-31 . USAF Sat Cat: 38082 . COSPAR: 2012-006F. Apogee: 1,376 km (855 mi). Perigee: 305 km (189 mi). Inclination: 69.5000 deg. Period: 101.70 min. Student satellite from the Politecnico di Torino..
  • ROBUSTA - . Mass: 1.00 kg (2.20 lb). Nation: France. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-10-28 . USAF Sat Cat: 38083 . COSPAR: 2012-006G. Apogee: 1,379 km (856 mi). Perigee: 306 km (190 mi). Inclination: 69.5000 deg. Period: 101.80 min. Student 1U cubesat from the Universite' de Montpellier. Mission: Radiation effects on bipolar-transistor-based circuits. Status: Failed. First French CubeSat.
  • XaTcobeo - . Mass: 1.00 kg (2.20 lb). Nation: Spain. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-01-28 . USAF Sat Cat: 38084 . COSPAR: 2012-006H. Apogee: 1,390 km (860 mi). Perigee: 305 km (189 mi). Inclination: 69.5000 deg. Period: 101.90 min. Student satellite from the University of Vigo..
  • LARES Support System - . Mass: 300 kg (660 lb). Nation: Europe. Class: Technology. Type: Technology satellite. Spacecraft Bus: LARES Support System. Spacecraft: LARES Support System. USAF Sat Cat: 38086 . COSPAR: 2012-006K. Apogee: 1,394 km (866 mi). Perigee: 270 km (160 mi). Inclination: 69.5000 deg. Period: 101.50 min. Remained attached to the AVUM upper stage. Included extensive instrumentation to monitor the launch vehicle during ascent. It also deployed seven 1U Cubesats from three P-POD deployers.

2012 April 12 - . 22:39 GMT - . Launch Site: Tongchang-ri. LV Family: Unha. Launch Vehicle: Unha-3. FAILURE: Failed at second stage separation..
  • Kwangmyongsong-3 - . Mass: 100 kg (220 lb). Nation: Korea North. Class: Technology. Type: Technology satellite. Spacecraft Bus: Kwangmyongsong. Spacecraft: Kwangmyongsong.

    Third North Korean satellite launch attempt, conducted despite international protests (that attempted to connect it with the country's missile program). Launched from a new site on the west coast of Korea on a southwest trajectory, to achieve a polar orbit and also avoid overflying Japan. Failed at first stage separation. Unusually North Korea provided the western press access to the launch site prior to the attempt, and admitted the launch failure after the fact.


2012 May 10 - . 07:06 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.
  • Tiantuo 1 - . Mass: 2,500 kg (5,500 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: Tiantuo. Spacecraft: Tiantuo. Decay Date: 2014-11-03 . USAF Sat Cat: 38258 . COSPAR: 2012-021B. Apogee: 472 km (293 mi). Perigee: 466 km (289 mi). Inclination: 97.2000 deg. Period: 94.00 min. Technology satellite for the National University of Defense Technology; carried an imager, an atomic oxygen sensor, and an AIS (maritime tracking) receiver..

2012 May 17 - . 16:39 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • SDS-4 - . Mass: 50 kg (110 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: JAXA SDS. Spacecraft: JAXA SDS. USAF Sat Cat: 38339 . COSPAR: 2012-025C. Apogee: 673 km (418 mi). Perigee: 662 km (411 mi). Inclination: 98.2000 deg. Period: 98.10 min. Small Demonstration Satellite; carried four technology experiments including a space-based AIS (ship tracking) payload..
  • Horyu-2 - . Mass: 7.00 kg (15.40 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: Horyu. Spacecraft: Horyu. USAF Sat Cat: 38340 . COSPAR: 2012-025D. Apogee: 671 km (416 mi). Perigee: 652 km (405 mi). Inclination: 98.2000 deg. Period: 98.00 min. Kyushu Institute of Technology satellite to study spacecraft charging effects and test a camera payload for Surrey Satellite (which observed the second stage after payload deployment to support development of improved propellant insulation)..

2012 July 22 - . 06:41 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz-FG.
  • TET-1 - . Mass: 120 kg (260 lb). Nation: Germany. Class: Technology. Type: Technology satellite. Spacecraft Bus: TET. Spacecraft: TET. USAF Sat Cat: 38710 . COSPAR: 2012-039D. Apogee: 506 km (314 mi). Perigee: 504 km (313 mi). Inclination: 97.5000 deg. Period: 94.70 min. DLR Technologieerprobungsträger 1, as part of their On-Orbit Verification Program. Tested new space components; carried an imaging payload..

2012 September 9 - . 04:23 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. Launch Pad: LP1. LV Family: PSLV. Launch Vehicle: PSLV.
  • Proiteres - . Mass: 15 kg (33 lb). Nation: Japan. Class: Technology. Type: Ion engine technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 38756 . COSPAR: 2012-047B. Apogee: 657 km (408 mi). Perigee: 640 km (390 mi). Inclination: 98.3000 deg. Period: 97.70 min. 15 kg pulsed plasma thruster experiment: 'Project of Osaka Institute of Technology Electric Rocket Engine aboard small Spaceship'..

2012 September 13 - . 21:39 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3E. LV Family: Atlas V. Launch Vehicle: Atlas V 401.
  • SMDC One 1.2 - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Climate technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 38759 . COSPAR: 2012-048B. 3U cubesat operational Nanosatellite Effect communications experiment for US Army Space and Missile Defence Command, Huntsville, Alabama..
  • Aeneas - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 38760 . COSPAR: 2012-048C. Cubesat with a cargo container tracking experiment by the University of Southern California, Los Angeles for the Department of Homeland Security.
  • CP5 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Solar sail technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 38763 . COSPAR: 2012-048F. California Polytechnic State University San Luis Obispo solar sail deorbit technology experiment..
  • SMDC One 1.1 - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 38766 . COSPAR: 2012-048J. 3U cubesat operational Nanosatellite Effect communications experiment for US Army Space and Missile Defence Command, Huntsville, Alabama..
  • Aerocube 4.5A - . Payload: Aerocube-4.5A. Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 38767 . COSPAR: 2012-048K. Cubesat for Aerospace Corporation, El Segundo, California..
  • Aerocube 4.5B - . Payload: Aerocube-4.5B. Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 38768 . COSPAR: 2012-048L. Cubesat for Aerospace Corporation, El Segundo, California..
  • Aerocube 4 - . Payload: Aerocube-4. Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 38769 . COSPAR: 2012-048M. Cubesat for Aerospace Corporation, El Segundo, California..

2012 October 4 - . 14:37 GMT - . Launch Site: ISS. LV Family: Proton. Launch Vehicle: Proton-K.
  • RAIKO - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2013-08-06 . USAF Sat Cat: 38852 . COSPAR: 1998-067CN. Apogee: 414 km (257 mi). Perigee: 390 km (240 mi). Inclination: 51.6000 deg. Period: 92.60 min. Released from the J-SSOD cubesat deployer outside the ISS Kibo module's equipment airlock by the JEM-RMS robot arm..
  • We Wish - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2013-03-11 . USAF Sat Cat: 38856 . COSPAR: 1998-067CS. Apogee: 400 km (240 mi). Perigee: 375 km (233 mi). Inclination: 51.6000 deg. Period: 92.30 min. Released from ISS Kibo module..
  • Niwaka - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2013-07-04 . USAF Sat Cat: 38853 . COSPAR: 1998-067CP. Apogee: 410 km (250 mi). Perigee: 390 km (240 mi). Inclination: 51.6000 deg. Period: 92.60 min. Released from ISS Kibo module..
  • TechEdSat - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2013-05-05 . USAF Sat Cat: 38854 . COSPAR: 1998-067CQ. Apogee: 406 km (252 mi). Perigee: 385 km (239 mi). Inclination: 51.6000 deg. Period: 92.50 min. Released from ISS Kibo module. 1U cubesat for San Jose State University. Mission: SPA hardware and software, inter-satellite communication link analysis ..
  • F-1 - . Mass: 1.00 kg (2.20 lb). Nation: Vietnam. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2013-05-09 . USAF Sat Cat: 38855 . COSPAR: 1998-067CR. Apogee: 407 km (252 mi). Perigee: 386 km (239 mi). Inclination: 51.6000 deg. Period: 92.50 min. Released from ISS Kibo module..

2012 October 14 - . 00:00 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: Chang Zheng 2C.
  • Shi Jian 9 A - . Payload: CAST1000C. Mass: 200 kg (440 lb). Nation: China. Class: Technology. Type: Rendezvous technology satellite. Spacecraft Bus: CAST1000. Spacecraft: CAST1000. USAF Sat Cat: 38860 . COSPAR: 2012-056A. Apogee: 651 km (404 mi). Perigee: 622 km (386 mi). Inclination: 98.0000 deg. Period: 97.40 min.

    The pair of SJ-9 satellites carried technical experiments and to perform orbital rendezvous, intercept, and formation flying exercises under the control of the China Resources Satellite Applications Center. On 19 October SJ-9A began maneuvers, lowering its orbit to 619 km x 644 km and then returning to a 623 km x 650 km orbit on October 22-23.

  • Shi Jian 9 B - . Payload: CAST1000C. Mass: 200 kg (440 lb). Nation: China. Class: Technology. Type: Rendezvous technology satellite. Spacecraft Bus: CAST1000. Spacecraft: CAST1000. USAF Sat Cat: 38861 . COSPAR: 2012-056B. Apogee: 650 km (400 mi). Perigee: 623 km (387 mi). Inclination: 98.0000 deg. Period: 97.50 min.

2012 October 23 - . Launch Site: Semnan. LV Family: Unha. Launch Vehicle: Unha-3. FAILURE: Launch vehicle exploded on pad, causing extensive damage..
  • Fajr - . Nation: Iran. Class: Technology. Type: Technology satellite. Payload of the failed launch was a 50 kg satellite built by Iran Electronics Industry, with an imaging sensor and a small thruster..

2012 November 18 - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: Chang Zheng 2C.
  • Feng Niao 1 (FN-1) - . Mass: 800 kg (1,760 lb). Nation: China. Class: Technology. Type: Rendezvous technology satellite. Spacecraft Bus: CAST2000. Spacecraft: CAST2000. USAF Sat Cat: 38998 . COSPAR: 2012-064B. Apogee: 500 km (310 mi). Perigee: 488 km (303 mi). Inclination: 97.3000 deg. Period: 94.50 min. Demonstration of new CAST mini- and micro-satellite buses. FN-1 (Hummersat) was to release the 30 kg FN-1A for formation flying and interorbital communications experiments..
  • Xin Yan 1 (XY-1) - . Mass: 140 kg (300 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: XY-1. Spacecraft: XY-1. USAF Sat Cat: 38999 . COSPAR: 2012-064C. Apogee: 501 km (311 mi). Perigee: 489 km (303 mi). Inclination: 97.3000 deg. Period: 94.50 min. Technology mission..

2012 December 12 - . 00:49 GMT - . Launch Site: Tongchang-ri. LV Family: Unha. Launch Vehicle: Unha-3.
  • Kwangmyongsong-3F2 - . Mass: 100 kg (220 lb). Nation: Korea North. Class: Technology. Type: Technology satellite. Spacecraft Bus: Kwangmyongsong. Spacecraft: Kwangmyongsong. USAF Sat Cat: 39026 . COSPAR: 2012-072A. Apogee: 581 km (361 mi). Perigee: 498 km (309 mi). Inclination: 97.4000 deg. Period: 95.40 min.

    First successful North Korean satellite launch. Amateur observations showed the satellite to be tumbling, and no signals were picked up at the announced 470 MHZ frequency - it was assumed the spacecraft never functioned or failed shortly after orbital insertion.


2013 February 25 - . 12:31 GMT - . Launch Site: Sriharikota. LV Family: PSLV. Launch Vehicle: PSLV.
  • STRaND-1 - . Mass: 4.00 kg (8.80 lb). Nation: UK. Agency: Surrey. Manufacturer: Surrey. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39090 . COSPAR: 2013-009E. Apogee: 783 km (486 mi). Perigee: 771 km (479 mi). Inclination: 98.6300 deg. Period: 100.40 min. 3U cubesat, a technical test project of Surrey Satellite and the Surrey Space Centre. Carried a Google Nexus One smartphone as its main avionics, and featured plasma thrusters and a water-alcohol thruster. Successful; first in STRaND Program..

2013 April 21 - . 21:00 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LP0A. LV Family: Antares LV. Launch Vehicle: Antares 110.
  • Dove-1 - . Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2013-04-27 . USAF Sat Cat: 39143 . COSPAR: 2013-016B. Apogee: 169 km (105 mi). Perigee: 160 km (90 mi). Inclination: 51.6200 deg. Period: 87.78 min. 3U cubesat, a demonstration satellite for Cosmogia, designed to return on-board system health data and validate the design for future Dove satellites, which will carry remote sensing payloads..
  • Alexander - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2013-04-27 . USAF Sat Cat: 39144 . COSPAR: 2013-016C. Apogee: 152 km (94 mi). Perigee: 134 km (83 mi). Inclination: 51.6000 deg. Period: 87.35 min. 1U cubesat from NASA's Ames Research Center, designed to demonstrate use of a commercial Nexus S mobile phone as a spacecraft avionics/computer system, together with an S-band radio, solar panels, GPS receiver, magnetorquers and reaction wheels..
  • Bell - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2013-05-10 . USAF Sat Cat: 39145 . COSPAR: 2013-016D. Apogee: 150 km (90 mi). Perigee: 144 km (89 mi). Inclination: 51.6100 deg. Period: 87.42 min. 1U cubesat from NASA's Ames Research Center, designed to demonstrate use of a commercial Nexus One Android-based mobile phone as a spacecraft avionics/computer system..
  • Graham - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2013-04-26 . USAF Sat Cat: 39146 . COSPAR: 2013-016E. Apogee: 175 km (108 mi). Perigee: 161 km (100 mi). Inclination: 51.6200 deg. Period: 87.85 min. 1U cubesat from NASA's Ames Research Center, designed to demonstrate use of a commercial Nexus One Android-based mobile phone as a spacecraft avionics/computer system..

2013 April 26 - . 04:13 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: Chang Zheng 2D.
  • NEE-01 Pegaso - . Mass: 1.00 kg (2.20 lb). Nation: Ecuador. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39151 . COSPAR: 2013-018B. Apogee: 654 km (406 mi). Perigee: 627 km (389 mi). Inclination: 98.0700 deg. Period: 97.53 min. 1U cubesat for the Ecuadorian space agency EXA..
  • Turksat-3USAT - . Mass: 3.00 kg (6.60 lb). Nation: Turkey. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39152 . COSPAR: 2013-018C. Apogee: 654 km (406 mi). Perigee: 628 km (390 mi). Inclination: 98.0500 deg. Period: 97.54 min. 3U cubesat from Istanbul Technical University..
  • CubeBug-1 - . Mass: 2.00 kg (4.40 lb). Nation: Argentina. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39153 . COSPAR: 2013-018D. Apogee: 654 km (406 mi). Perigee: 627 km (389 mi). Inclination: 98.0700 deg. Period: 97.53 min. 2U cubesat from Argentina..

2013 May 7 - . 02:06 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELV. LV Family: Vega. Launch Vehicle: Vega.
  • ESTCube-1 - . Mass: 1.00 kg (2.20 lb). Nation: Estonia. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39161 . COSPAR: 2013-021C. Apogee: 672 km (417 mi). Perigee: 656 km (407 mi). Inclination: 98.1300 deg. Period: 98.03 min. 1U cubesat by the Estonian Student Satellite Program led by the University of Tartu. Space test of the electric solar wind sail. Successful. First Estonian satellite.

2013 July 19 - . 23:37 GMT - . Launch Site: Taiyuan. Launch Pad: xxx. LV Family: CZ. Launch Vehicle: Chang Zheng 4C.
  • Chuangxin 3 - . Mass: 40 kg (88 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: Ban Xing. Spacecraft: Ban Xing. USAF Sat Cat: 39209 . COSPAR: 2013-037B. Apogee: 673 km (418 mi). Perigee: 665 km (413 mi). Inclination: 98.0400 deg. Period: 98.12 min. Served as target for the Shiyan 7 satellite inspector / robotic arm test vehicle..
  • SJ-15 - . Mass: 2,700 kg (5,900 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: SJ-6. Spacecraft: SJ-6. USAF Sat Cat: 39210 . COSPAR: 2013-037C. Apogee: 608 km (377 mi). Perigee: 563 km (349 mi). Inclination: 97.6800 deg. Period: 96.39 min.

    Thought to be carrying out observations of space debris. Made a slight orbit adjustment of 1 km on 15 October to a 660 km x 675 km orbit, then released a new object, 2013-037J, with which it maintained stationkeeping within 2 km. The new object was perhaps a target subsatellite, possibly passive, for experiments with proximity operations.


2013 September 29 - . 16:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • CUSat - . Mass: 23 kg (50 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: CUSat. Spacecraft: CUSat. USAF Sat Cat: 39266 . COSPAR: 2013-055B. Apogee: 1,426 km (886 mi). Perigee: 323 km (200 mi). Inclination: 80.9900 deg. Period: 102.45 min.

    Cornell University satellite; carried a differential GPS navigation system and pulsed plasma thrusters. The defunct-before-launch CUSAT 2/Top satellite remained attached to the Falcon 9 second stage. CUSAT (formerly CUSAT 1/Bottom) was launched attached to CUSAT 2 and separated from it after orbit insertion.


2013 October 25 - . 03:50 GMT - . Launch Site: Jiuquan. Launch Pad: xxx. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.
  • SJ-16 - . Payload: SJ-16. Mass: 2,700 kg (5,900 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: SJ-6. Spacecraft: SJ-6. USAF Sat Cat: 39358 . COSPAR: 2013-057A. Apogee: 614 km (381 mi). Perigee: 599 km (372 mi). Inclination: 74.9800 deg. Period: 96.82 min. The mission of SJ-16 is unknown; the orbit represents a new profile for the series. The SJ ('practice') series satellites carry a mix of technology development and military payloads..

2013 November 19 - . 12:18 GMT - . Launch Site: ISS. LV Family: Proton. Launch Vehicle: Proton-K.
  • PicoDragon - . Mass: 1.00 kg (2.20 lb). Nation: Vietnam. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-04-16 . USAF Sat Cat: 39412 . COSPAR: 1998-067DA. Apogee: 188 km (116 mi). Perigee: 180 km (110 mi). Inclination: 51.6300 deg. Period: 88.17 min. On 19 November a J-SSOD cubesat deployer was retrieved from the Kibo module airlock by the JEM RMS arm and moved to a deployment position; at 12:18 GMT it ejected three 1U cubesats, including PicoDragon for Vietnam..
  • Ardusat-1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-02-28 . USAF Sat Cat: 39413 . COSPAR: 1998-067DB. Apogee: 165 km (102 mi). Perigee: 121 km (75 mi). Inclination: 51.7300 deg. Period: 87.35 min.

    On 19 November a J-SSOD cubesat deployer was retrieved from the Kibo module airlock by the JEM RMS arm and moved to a deployment position; at 12:18 GMT it ejected three 1U cubesats, including two Ardusats for a demonstration of spaceborne Arduino processors for the US company NanoSatisfi.


2013 November 20 - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA0B. LV Family: Minuteman. Launch Vehicle: Minotaur 1.
  • ORS Tech 1 - . Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-03-23 . USAF Sat Cat: 39387 . COSPAR: 2013-064H. Apogee: 473 km (293 mi). Perigee: 457 km (283 mi). Inclination: 40.5200 deg. Period: 93.90 min. Cubesat; 3U technology demonstration satellites for USAF Operationally Responsive Space office developed by APL..
  • ORS Tech 2 - . Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-04-03 . USAF Sat Cat: 39396 . COSPAR: 2013-064S. Apogee: 474 km (294 mi). Perigee: 458 km (284 mi). Inclination: 40.5200 deg. Period: 93.92 min. Cubesat; 3U technology demonstration satellites for USAF Operationally Responsive Space office developed by APL..
  • STPSAT-3 - . Mass: 180 kg (390 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Astro-200. Spacecraft: Astro-200. USAF Sat Cat: 39380 . COSPAR: 2013-064A. Apogee: 498 km (309 mi). Perigee: 493 km (306 mi). Inclination: 40.5200 deg. Period: 94.52 min.

    Carried technology and space weather experiments, including a Total Solar Irradiance sensor, TCTE, to provide data lost when the Glory launch failed. Also on the launch vehicle were two CubeStack wafers which eject a record total of 28 cubesats. The upper wafer carried four 6U Cubesat dispensers for NRO missions, and the lower wafer carried eight 3U P-POD cubesat dispensers for various payloads including NASA's ELANA IV cubesat cluster.

  • ChargerSat 1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39405 . COSPAR: 2013-064AB. Apogee: 484 km (300 mi). Perigee: 476 km (295 mi). Inclination: 40.5000 deg. Period: 94.21 min. Cubesat from University of Alabama-Huntsville..
  • PhoneSat-2.4 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39381 . COSPAR: 2013-064B. Apogee: 487 km (302 mi). Perigee: 480 km (290 mi). Inclination: 40.5000 deg. Period: 94.28 min. Cubesat from NASA-Ames, with systems based on a Nexus/Android cellphone..
  • CAPE 2 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-10-23 . USAF Sat Cat: 39382 . COSPAR: 2013-064C. Apogee: 445 km (276 mi). Perigee: 417 km (259 mi). Inclination: 40.4900 deg. Period: 93.20 min. Cubesat from University of Louisiana-Lafayette..
  • Vermont Lunar Cubesat - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39407 . COSPAR: 2013-064AD. Apogee: 482 km (299 mi). Perigee: 473 km (293 mi). Inclination: 40.5300 deg. Period: 94.15 min. 1U cubesat from Vermont Technical College, testing equipment for a proposed future lunar mission. Testing navigation components to be used in a follow up 3U ion drive CubeSat to the Moon. Successful. First university satellite from New England..
  • DragonSat - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39383 . COSPAR: 2013-064D. Apogee: 487 km (302 mi). Perigee: 478 km (297 mi). Inclination: 40.5100 deg. Period: 94.26 min. Cubesat from Drexel University, Penn. and the US Naval Academy, Annapolis..
  • KySat-2 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-02-12 . USAF Sat Cat: 39384 . COSPAR: 2013-064E. Apogee: 470 km (290 mi). Perigee: 452 km (280 mi). Inclination: 40.5000 deg. Period: 93.81 min. Cubesat from Kentucky Space, Lexington, Kentucky..
  • TJ3Sat - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-09-17 . USAF Sat Cat: 39385 . COSPAR: 2013-064F. Apogee: 481 km (298 mi). Perigee: 469 km (291 mi). Inclination: 40.5300 deg. Period: 94.10 min. Cubesat from Thomas Jefferson High School, Virginia..
  • ORS-3 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: ORS-3. Spacecraft: ORS-3. Decay Date: 2015-09-17 . USAF Sat Cat: 39385 . COSPAR: 2013-064F. Apogee: 481 km (298 mi). Perigee: 469 km (291 mi). Inclination: 40.5300 deg. Period: 94.10 min. The ORS-3 Minotaur final stage carried an experimental launch tracking system and a drag device to reduce the amount of time it spent in orbit..
  • NPS-SCAT - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-10-28 . USAF Sat Cat: 39389 . COSPAR: 2013-064K. Apogee: 482 km (299 mi). Perigee: 471 km (292 mi). Inclination: 40.5000 deg. Period: 94.13 min. Cubesat for the US Navy Postgraduate School, with a solar cell exposure experiment..
  • COPPER - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39395 . COSPAR: 2013-064R. Apogee: 484 km (300 mi). Perigee: 475 km (295 mi). Inclination: 40.5000 deg. Period: 94.19 min. Cubesat from Saint Louis University, Missouri..
  • Black Knight 1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-07-16 . USAF Sat Cat: 39398 . COSPAR: 2013-064U. Apogee: 479 km (297 mi). Perigee: 467 km (290 mi). Inclination: 40.5300 deg. Period: 94.06 min. Cubesat for the US Military Academy at West Point, New York..
  • Trailblazer - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39400 . COSPAR: 2013-064W. Apogee: 485 km (301 mi). Perigee: 477 km (296 mi). Inclination: 40.5100 deg. Period: 94.23 min. Cubesat from University of New Mexico-Albequerque..
  • SwampSat - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39402 . COSPAR: 2013-064Y. Apogee: 483 km (300 mi). Perigee: 473 km (293 mi). Inclination: 40.5000 deg. Period: 94.17 min. Cubesat from University of Florida-Gainesville..

2013 November 20 - . 07:58 GMT - . Launch Site: ISS. LV Family: Proton. Launch Vehicle: Proton-K.
  • TechEdSat-3p - . Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-01-16 . USAF Sat Cat: 39415 . COSPAR: 1998-067DD. Apogee: 227 km (141 mi). Perigee: 205 km (127 mi). Inclination: 51.6200 deg. Period: 88.81 min.

    On 19 November a J-SSOD cubesat deployer was retrieved from the Kibo module airlock by the JEM RMS arm and moved to a deployment position. On 20 November it released this 3U cubesat from NASA-Ames and San Jose State University, which deployed an 0.6m `Exobrake' sail to test a way to increase the cubesat's drag and make it reenter quickly.


2013 November 21 - . 07:10 GMT - . Launch Site: Dombarovskiy. Launch Pad: xxx. LV Family: R-36M. Launch Vehicle: Dnepr.
  • HINCube-1 - . Mass: 1.00 kg (2.20 lb). Nation: South Africa. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39417 . COSPAR: 2013-066B. Apogee: 678 km (421 mi). Perigee: 592 km (367 mi). Inclination: 97.7800 deg. Period: 97.42 min. 1U cubesat from French South African Institute of Technology at the Cape Peninsula University of Technology. Mission: Space weather, technology demonstration, education and human capital development.. Successful. First South African CubeSat..
  • OPTOS - . Mass: 4.00 kg (8.80 lb). Nation: Spain. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39420 . COSPAR: 2013-066E. Apogee: 793 km (492 mi). Perigee: 594 km (369 mi). Inclination: 97.7600 deg. Period: 98.63 min. 3U cubesat from INTA of Spain..
  • Unisat-5 - . Mass: 19 kg (41 lb). Nation: Italy. Class: Technology. Type: Technology satellite. Spacecraft Bus: UniSat. Spacecraft: Unisat. USAF Sat Cat: 39421 . COSPAR: 2013-066F. Apogee: 636 km (395 mi). Perigee: 592 km (367 mi). Inclination: 97.7800 deg. Period: 96.97 min.

    Technology satellite for the University of Rome. It carried a further eight tiny satellites within it, and one of those (PUCP-Sat) carried a further nested satellite, Pocket-PUCP. Most of the subsatellites were ejected from Unisat-5 between 08:10 and 08:25 GMT on November 21.

  • Delfi-3nXt - . Mass: 5.00 kg (11.00 lb). Nation: Netherlands. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39428 . COSPAR: 2013-066N. Apogee: 773 km (480 mi). Perigee: 593 km (368 mi). Inclination: 97.7600 deg. Period: 98.41 min. 3U cubesat from Delft University of Technology..
  • ICUBE-1 - . Mass: 2.00 kg (4.40 lb). Nation: Pakistan. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39432 . COSPAR: 2013-066S. Apogee: 634 km (393 mi). Perigee: 587 km (364 mi). Inclination: 97.7800 deg. Period: 96.90 min. 2U cubesat from Unisat-5 for Institute of Space Technology, Islamabad. Successful. First Pakistani cubesat..
  • HUMSAT-D - . Mass: 1.00 kg (2.20 lb). Nation: Spain. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39433 . COSPAR: 2013-066T. Apogee: 632 km (392 mi). Perigee: 586 km (364 mi). Inclination: 97.7800 deg. Period: 96.88 min. Deployed from Unisat-5 for University of Vigo, Spain..
  • WREN - . Mass: 0 kg (0 lb). Nation: Germany. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39435 . COSPAR: 2013-066V. Apogee: 638 km (396 mi). Perigee: 594 km (369 mi). Inclination: 97.8000 deg. Period: 97.02 min. PocketQube cubesat from StaDoKo (spinoff company of the University of Aachen)..
  • 50SAT - . Mass: 0 kg (0 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39436 . COSPAR: 2013-066W. Apogee: 615 km (382 mi). Perigee: 580 km (360 mi). Inclination: 97.7800 deg. Period: 96.63 min. AKA Eagle-2, 50DollarSat; from Morehead State University. First PocketQube cubesat; 1P size was 0.15 kg, 5 x 5 x 5cm cubes.
  • BeakerSat-1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39437 . COSPAR: 2013-066X. Apogee: 619 km (384 mi). Perigee: 583 km (362 mi). Inclination: 97.7900 deg. Period: 96.71 min. 2.5P PocketQube, AKA Eagle-1, from Morehead State University..
  • VELOX-P2 - . Mass: 1.00 kg (2.20 lb). Nation: Singapore. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39438 . COSPAR: 2013-066Y. Apogee: 695 km (431 mi). Perigee: 593 km (368 mi). Inclination: 97.7700 deg. Period: 97.60 min. Cubesat from Nanyang Tech University..
  • First-Move - . Mass: 1.00 kg (2.20 lb). Nation: Germany. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39439 . COSPAR: 2013-066Z. Apogee: 691 km (429 mi). Perigee: 591 km (367 mi). Inclination: 97.7700 deg. Period: 97.54 min. Cubesat from Technical University of Munich..
  • Manolito - . Payload: CUBEBUG 2. Mass: 2.00 kg (4.40 lb). Nation: Argentina. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39440 . COSPAR: 2013-066AA. Apogee: 710 km (440 mi). Perigee: 593 km (368 mi). Inclination: 97.7700 deg. Period: 97.76 min. 2U cubesat from Argentina..
  • Krysaor - . Payload: NEE-2. Mass: 1.00 kg (2.20 lb). Nation: Ecuador. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39441 . COSPAR: 2013-066AB. Apogee: 711 km (441 mi). Perigee: 593 km (368 mi). Inclination: 97.7700 deg. Period: 97.77 min. Cubesat from Ecuadorian Space Agency..
  • PUCPSat-1 - . Mass: 1.00 kg (2.20 lb). Nation: Peru. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39442 . COSPAR: 2013-066AC. Apogee: 633 km (393 mi). Perigee: 587 km (364 mi). Inclination: 97.7800 deg. Period: 96.90 min. 1U cubesat deployed from Unisat-5 for Pontifica Universidad Catolica del Peru, Lima..
  • QBScout-1 - . Mass: 0 kg (0 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39443 . COSPAR: 2013-066AD. Apogee: 630 km (390 mi). Perigee: 591 km (367 mi). Inclination: 97.7800 deg. Period: 96.90 min. 2.5P PocketQube from University of Maryland/Baltimore County..
  • FUNcube-1 - . Mass: 1.00 kg (2.20 lb). Nation: UK. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39444 . COSPAR: 2013-066AE. Apogee: 677 km (420 mi). Perigee: 592 km (367 mi). Inclination: 97.7700 deg. Period: 97.41 min. Cubesat for AMSAT-UK..
  • Tshepiso - . Payload: ZACUBE. Mass: 1.00 kg (2.20 lb). Nation: Norway. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39445 . COSPAR: 2013-066AF. Apogee: 677 km (420 mi). Perigee: 592 km (367 mi). Inclination: 97.7700 deg. Period: 97.41 min. Cubesat from South Africa's Cape Peninsula University of Tech (CPUT)..
  • UWE-3 - . Mass: 1.00 kg (2.20 lb). Nation: Germany. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39446 . COSPAR: 2013-066AG. Apogee: 694 km (431 mi). Perigee: 593 km (368 mi). Inclination: 97.7700 deg. Period: 97.59 min. Cubesat from University of Wurzburg..
  • BPA-3 - . Payload: SL-24. Nation: Russia. Class: Technology. Type: Technology satellite. USAF Sat Cat: 39448 . COSPAR: 2013-066AJ. Apogee: 1,610 km (1,000 mi). Perigee: 591 km (367 mi). Inclination: 97.6700 deg. Period: 107.27 min. Yuzhnoye experiment attached to final stage of rocket..
  • Pocket-PUCP - . Mass: 0 kg (0 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. COSPAR: 2013-066x. Apogee: 616 km (382 mi). Perigee: 579 km (359 mi). Inclination: 97.7800 deg. Period: 96.64 min. PocketQube cubesat ejected from PUCPSat-1..

2013 November 25 - . 02:12 GMT - . Launch Site: Jiuquan. Launch Pad: xxx. LV Family: CZ. Launch Vehicle: Chang Zheng 2D.
  • Shiyan 5 Weixing - . Payload: SY-5. Mass: 800 kg (1,760 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: CAST2000. Spacecraft: CAST2000. USAF Sat Cat: 39455 . COSPAR: 2013-068A. Apogee: 755 km (469 mi). Perigee: 739 km (459 mi). Inclination: 97.9600 deg. Period: 99.76 min. Experiment Satellite No 5..

2013 December 6 - . 07:14 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3E. LV Family: Atlas V. Launch Vehicle: Atlas V 501.
  • Aerocube 5a - . Mass: 10 kg (22 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39465 . COSPAR: 2013-072D. Apogee: 883 km (548 mi). Perigee: 467 km (290 mi). Inclination: 120.5000 deg. 5U technology cubesat for the Aerospace Corporation..
  • Aerocube 5b - . Mass: 10 kg (22 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39466 . COSPAR: 2013-072E. Apogee: 883 km (548 mi). Perigee: 467 km (290 mi). Inclination: 120.5000 deg. 5U technology cubesat for the Aerospace Corporation..
  • ALICE - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39467 . COSPAR: 2013-072F. Apogee: 883 km (548 mi). Perigee: 467 km (290 mi). Inclination: 120.5000 deg. 1U cubesat from the Air Force Institute of Technology carrying technology experiments..
  • SNAP-3 - . Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39468 . COSPAR: 2013-072G. Apogee: 883 km (548 mi). Perigee: 467 km (290 mi). Inclination: 120.5000 deg. 3U cubesat for the SMDC Nanosatellite Program, with an unknown mission..
  • MCubed-2 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39469 . COSPAR: 2013-072H. Apogee: 883 km (548 mi). Perigee: 467 km (290 mi). Inclination: 120.5000 deg. 1U cubesat from the University of Michigan with technology experiments, including a low resolution imager..
  • IPEX - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39471 . COSPAR: 2013-072K. Apogee: 883 km (548 mi). Perigee: 467 km (290 mi). Inclination: 120.5000 deg. 1U cubesat built by Cal Poly to test systems and algorithms for JPL..
  • Tacsat 6 - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 39473 . COSPAR: 2013-072M. Apogee: 883 km (548 mi). Perigee: 467 km (290 mi). Inclination: 120.5000 deg. 3U cubesat for SMDC with an unknown mission, probably tactical communications or imaging..

2014 February 27 - . 18:37 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • Ginrei - . Payload: SHINDAISAT. Mass: 33 kg (72 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: Ginrei. Spacecraft: Ginrei. Decay Date: 2014-11-24 . USAF Sat Cat: 39572 . COSPAR: 2014-009A. Apogee: 371 km (230 mi). Perigee: 348 km (216 mi). Inclination: 65.0100 deg. Period: 91.73 min. Microsatellite from Shinshu University to study use of LED's for long-distance communication..
  • Hayato-2 - . Payload: ITF 1. Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-06-29 . USAF Sat Cat: 39573 . COSPAR: 2014-009B. Apogee: 256 km (159 mi). Perigee: 233 km (144 mi). Inclination: 65.0000 deg. Period: 89.40 min. Cubesat from Tsukuba University..
  • OPUSat - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-07-24 . USAF Sat Cat: 39575 . COSPAR: 2014-009D. Apogee: 310 km (190 mi). Perigee: 288 km (178 mi). Inclination: 65.0000 deg. Period: 90.50 min. 1U cubesat from Osaka Prefectural University. Technology mission..
  • Invader - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-09-02 . USAF Sat Cat: 39577 . COSPAR: 2014-009F. Apogee: 336 km (208 mi). Perigee: 315 km (195 mi). Inclination: 65.0100 deg. Period: 91.04 min. Cubesat from Tama Art University..
  • STARS-2 - . Mass: 22 kg (48 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: STARS-2. Spacecraft: STARS-2. Decay Date: 2014-05-18 . USAF Sat Cat: 39578 . COSPAR: 2014-009G. Apogee: 178 km (110 mi). Perigee: 164 km (101 mi). Inclination: 64.9700 deg. Period: 87.91 min. Microsatellite from Kagawa University. Composed of two sections and a tether, deployed length 300 metres. Believed to have succeeded based on later orbital decay rate..
  • Yui - . Payload: K-SAT2. Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Education satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-04-26 . USAF Sat Cat: 39579 . COSPAR: 2014-009H. Apogee: 162 km (100 mi). Perigee: 145 km (90 mi). Inclination: 64.9900 deg. Period: 87.56 min. Cubesat from Kagoshima University..

2014 February 28 - . 07:30 GMT - . Launch Site: ISS. LV Family: Proton. Launch Vehicle: Proton-K.
  • Ardusat-2 - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-11-08 . USAF Sat Cat: 39567 . COSPAR: 1998-067EL. Apogee: 376 km (233 mi). Perigee: 373 km (231 mi). Inclination: 51.6400 deg. Period: 92.04 min. Cubesat from Nanosatisfi Inc., San Francisco, with an Arduino processor..
  • UAP-SAT - . Mass: 2.00 kg (4.40 lb). Nation: Peru. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-05-22 . USAF Sat Cat: 39568 . COSPAR: 1998-067EM. Apogee: 196 km (121 mi). Perigee: 183 km (113 mi). Inclination: 51.6200 deg. Period: 88.28 min. Cubesat from Universidad Alas Peruanas, Lima..
  • Litsat 1 - . Mass: 2.00 kg (4.40 lb). Nation: Lithuania. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-05-23 . USAF Sat Cat: 39570 . COSPAR: 1998-067EP. Apogee: 180 km (110 mi). Perigee: 168 km (104 mi). Inclination: 51.5900 deg. Period: 87.97 min. Cubesat from the Lithuanian Space Association, Vilnius, Lithuania..
  • LituanicaSat-1 - . Mass: 2.00 kg (4.40 lb). Nation: Lithuania. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-07-01 . USAF Sat Cat: 39571 . COSPAR: 1998-067EQ. Apogee: 291 km (180 mi). Perigee: 281 km (174 mi). Inclination: 51.6400 deg. Period: 90.23 min. Cubesat from Kaunas Tech Univ. in Kaunas, Lithuania..

2014 April 18 - . 19:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • TSat - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-05-28 . USAF Sat Cat: 39682 . COSPAR: 2014-022C. Apogee: 167 km (103 mi). Perigee: 153 km (95 mi). Inclination: 51.6100 deg. Period: 87.68 min. Cubesat for Taylor University. Released from Falcon second stage..
  • PhoneSat-2.5 - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-05-15 . USAF Sat Cat: 39684 . COSPAR: 2014-022E. Apogee: 119 km (73 mi). Perigee: 109 km (67 mi). Inclination: 51.5400 deg. Period: 86.76 min. Cubesat for NASA Ames. Released from Falcon second stage..
  • Kicksat - . Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2014-05-14 . USAF Sat Cat: 39685 . COSPAR: 2014-022F. Apogee: 175 km (108 mi). Perigee: 160 km (90 mi). Inclination: 51.6500 deg. Period: 87.83 min.

    Cubesat for Cornell University's Space Systems Design Stuido. The satellite had a mass of 2.68 kg, of which 0.52 kg was to have been ejected on May 4 in the form of 104 tiny 5-gram Sprites, circuit boards which acted as independent satellites with small transmitters able to send a simple message to ground stations. A timer problem on Kicksat meant that the deployment of the Sprite subsatellites was reset to May 16. However, Kicksat, and its undeployed Sprites, were destroyed when it reentered on May 14.


2014 May 23 - . 05:28 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Cosmos 2499 - . Payload: OBJECT E. Mass: 45 kg (99 lb). Nation: Russia. Class: Technology. Type: Technology satellite. Spacecraft Bus: SKRL. Spacecraft: SKRL. USAF Sat Cat: 39765 . COSPAR: 2014-028E. Apogee: 1,509 km (937 mi). Perigee: 1,480 km (910 mi). Inclination: 82.4500 deg. Period: 115.86 min. Additional small military payload, eventually given the cover name Cosmos-2499. It was probably built by the Reshetnev company and may have had a mass of around 45 kg..

2014 May 24 - . 03:05 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • SPROUT - . Mass: 7.00 kg (15.40 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft Bus: SPROUT. Spacecraft: SPROUT. USAF Sat Cat: 39770 . COSPAR: 2014-029E. Apogee: 627 km (389 mi). Perigee: 615 km (382 mi). Inclination: 97.8700 deg. Period: 97.13 min. Microsatellite with a Nihon University experiment to deploy a 1.5m inflatable triangular membrane..

2014 June 19 - . 19:11 GMT - . Launch Site: Dombarovskiy. LV Family: R-36M. Launch Vehicle: Dnepr.
  • Aerocube 6a - . Mass: 10 kg (22 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40045 . COSPAR: 2014-033AM. Apogee: 700 km (430 mi). Perigee: 613 km (380 mi). Inclination: 97.9700 deg. Period: 97.87 min.
  • Aerocube 6b - . Mass: 10 kg (22 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40046 . COSPAR: 2014-033AN. Apogee: 700 km (430 mi). Perigee: 613 km (380 mi). Inclination: 97.9700 deg. Period: 97.87 min.

2014 October 28 - . 22:20 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA0A. Launch Pad: Wallops MARS 0A. LV Family: Antares LV. Launch Vehicle: Antares 130.
  • Arkyd-3 - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Apogee: 0.10 km (0.06 mi). Perigee: -6,378 km (-6,378 mi). Inclination: 51.6000 deg. 3U cubesat from Planetary Resources. Lost in explosion of booster..

2014 November 28 - . 14:30 GMT - . Launch Site: ISS.
  • SpinSat - . Mass: 50 kg (110 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SpinSat. USAF Sat Cat: 40314 . COSPAR: 1998-067FL. Apogee: 373 km (231 mi). Perigee: 365 km (226 mi). Inclination: 51.6400 deg. Period: 91.92 min.

    The Japanese JEM-RMS robot arm extracted the SSIKLOPS (Cyclops) deployer and its attached SpinSat satellite from the Kibo airlock and positioned it for deployment. The Cyclops then ejected SpinSat into orbit. SpinSat was a Naval Research Lab satellite to test new microthrusters for attitude control.


2014 December 3 - . 04:22 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. Launch Pad: Tanegashima Y1. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • Shin'en-2 - . Mass: 15 kg (33 lb). Nation: Japan. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Shin'en. Spacecraft: Shin'en. USAF Sat Cat: 40320 . COSPAR: 2014-076B. Apogee: -50,912 km (-50,912 mi). Perigee: 245 km (152 mi). Inclination: 29.9000 deg. Communications payload designed to demonstrate deep space communications with a small spacecraft from a 0.915 AU x 1.089 AU x 6.8 deg solar orbit..
  • DESPATCH - . Mass: 32 kg (70 lb). Nation: Japan. Class: Technology. Type: Art satellite. Spacecraft Bus: DESPATCH. Spacecraft: DESPATCH. USAF Sat Cat: 40321 . COSPAR: 2014-076C. Apogee: -50,912 km (-50,912 mi). Perigee: 245 km (152 mi). Inclination: 29.9000 deg.

    Also known as ArtSat-2; from Tama Art University. The yellowish, tapered-helix assembly was intended mainly as a work of art although it also carries an amateur radio communications payload with a limited range. In a 0.915 AU x 1.089 AU x 6.8 deg solar orbit.


2014 December 23 - . 05:57 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk. LV Family: Angara. Launch Vehicle: Angara 5A.
  • IPM - . Nation: Russia. Class: Technology. Type: Re-entry test vehicle. USAF Sat Cat: 40355 . COSPAR: 2014-085A. Apogee: 39,083 km (24,285 mi). Perigee: 36,163 km (22,470 mi). Inclination: 0.9100 deg. Period: 1,530.92 min.

    First launch of the Angara-A5 booster, composed of five standard URM-1 modules and a Briz-M upper stage. Four URM-1's, clustered around a URM-1 in the core, formed the first stage. The core URM-1 was the second stage. The four first stage URM-1's separated at 06:01 GMT at an altitude of 82 km; the core URM-1 shut down and separated at 06:03 GMT at an altitude of 148 km, reentering downrange near Tomsk. The nose fairing was jettisoned 10 seconds later. The third stage was a URM-2, powered by the RD-0124A engine; it reached a marginally suborbital trajectory and, after separating from the upper composite section, reentered in the Philippine Sea at a range of 2320 km from the launch site. Meanwhile, the fourth stage, a standard Briz-M (S/N 88801) propelled the stack into a 250 km, 63 deg parking orbit with a burn starting at 06:11 GMT. After coasting to the equator, two perigee burns at 07:03 and 09:26 GMT boosted the apogee to 5,000 km and then 35,800 km, while reducing inclination to 60.6 deg. The Briz-M's additional propellant tank (DTB), now empty, was jettisoned into a 433 km x 35,808 km x 60.6 deg orbit. The payload on this flight was a dummy satellite called the IPM. The stack coasted to apogee and at 14:44 GMT, began the fourth burn to enter circular geosynchronous orbit. At 14:57 GMT the Briz sent a simulated separation command, but the payload remained attached to the stage as intended. After a few more hours, two burns of the Briz stage's SOZ auxiliary engines moved the stack to a graveyard orbit a few hundred kilometers above GEO. This was the first GEO mission ever launched from Plesetsk.


2015 January 31 - . 14:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10C.
  • GRIFEX - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40379 . COSPAR: 2015-003D. Apogee: 648 km (402 mi). Perigee: 433 km (269 mi). Inclination: 99.1000 deg. Period: 95.45 min. 3U cubesat by Michigan/JPL; technology satellite. Sun synchronous orbit; 0600 GMT local time of the descending node..

2015 February 5 - . 12:50 GMT - . Launch Site: ISS. Launch Complex: ISS Japanese Experiment Module. Launch Pad: ISS Kibo RMS.
  • AESP-14 - . Mass: 1.00 kg (2.20 lb). Nation: Brazil. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-05-11 . USAF Sat Cat: 40389 . COSPAR: 1998-067FM. Apogee: 405 km (251 mi). Perigee: 397 km (246 mi). Inclination: 51.6000 deg. ISS cubesat deploys resumed after a five-month hiatus following deployer problems. Brazil's AESP-14 cubesat was ejected but appeared not to be transmitting..

2015 February 11 - . 13:40 GMT - . Launch Site: Kourou. Launch Complex: Kourou ZLV. LV Family: Vega. Launch Vehicle: Vega.
  • IXV - . Mass: 1,844 kg (4,065 lb). Nation: Europe. Class: Technology. Type: Re-entry test vehicle. Spacecraft Bus: IXV. Spacecraft: IXV. COSPAR: 2015-0U01. Apogee: 416 km (258 mi). Perigee: 76 km (47 mi). Inclination: 5.4000 deg.

    Fourth flight of the Vega booster. The AVUM 4th stage entered a 76 km x 416 km x 5.4 deg orbit at 13:53 GMT. ESA's Intermediate Experimental Vehicle was a reentry vehicle designed to study hypersonic aerothermodynamics. The IXV reentered over the Pacific at 14:44 GMT, with parachute deployment at 15:09 GMT and splashdown at 123 deg W / 3 deg N at about 15:18 GMT.

  • AVUM VV04 - . Nation: Europe. Class: Technology. Type: Technology satellite. COSPAR: 2015-0U01. Apogee: 430 km (260 mi). Perigee: 220 km (130 mi). Inclination: 5.4000 deg.

    The AVUM stage made a second burn at apogee at 14:11 GMT and entered a 220 km x 430 km x 5 deg orbit. A third burn followed at 15:29 GMT as the AVUM passed over Kourou again, to deorbit the stage after one trip around Earth. The AVUM reentered over the Indian Ocean around 16:15 GMT.


2015 March 4 - . 01:20 GMT - . Launch Site: ISS. Launch Complex: ISS Japanese Experiment Module. Launch Pad: ISS Kibo. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1.
  • TechEdSat-4 - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-04-03 . USAF Sat Cat: 40455 . COSPAR: 1998-067FY. Apogee: 402 km (249 mi). Perigee: 393 km (244 mi). Inclination: 51.6000 deg. 3U cubesat of San Jose State University, the University of Idaho, and NASA Ames. Tested Exo-Brake passive de-orbit system..
  • LambdaSat - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Decay Date: 2015-05-16 . USAF Sat Cat: 40458 . COSPAR: 1998-067GB. Apogee: 405 km (251 mi). Perigee: 393 km (244 mi). Inclination: 51.6000 deg. 1U cubesat built by the Lambda Team of San Jose, California..

2015 March 31 - . 13:48 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. Launch Pad: Plesetsk LC133. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Cosmos 2504 - . Mass: 225 kg (496 lb). Nation: Russia. Class: Technology. Type: Technology satellite. Spacecraft Bus: Strela. Spacecraft: Strela-3. USAF Sat Cat: 40555 . COSPAR: 2015-020D. Apogee: 1,506 km (935 mi). Perigee: 1,172 km (728 mi). Inclination: 82.4900 deg. Period: 112.44 min.

    Additional military payload carried on a Gonets launch, evidently to prove orbital rendezvous or anti-satellite technology. For the first time, this payload was ejected from the Briz-KM upper stage after its depletion burn, and ended up in a lower perigee orbit than the Gonets trio. The payload began small orbit maneuvers on 9 April. On 14 April it completed a rendezvous with its Briz-KM rocket stage and appeared to have deliberately or accidentally hit the stage. It made a major orbit change on 3 July around 07:10 GMT, from its 1172 km x 1506 km orbit to a lower 1119 km x 1451 km orbit. To be the first move in a new rendezvous experiment of some kind. The satellite previously


2015 May 20 - . 15:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Atlas V. Launch Vehicle: Atlas V 501.
  • USA 261 - . Payload: X-37B OTV-4. Mass: 5,400 kg (11,900 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: X-37. Spacecraft: X-37. USAF Sat Cat: 40651 . COSPAR: 2015-025A. Apogee: 332 km (206 mi). Perigee: 309 km (192 mi). Inclination: 38.0000 deg.

    Classified mission of the winged, recoverable X-37B Orbital Test Vehicle. Publicly stated to be carrying an AFRL ion engine test and a NASA materials exposure experiment. After releasing the X-37B the Centaur AV-054 rocket stage reignited to reach a 355 km x 700 km x 55-57 deg orbit and at around 17:00 GMT released a set of 9 cubesats. Centaur then made a third burn to deorbit itself over the Indian Ocean.

  • USS Langley - . Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40652 . COSPAR: 2015-025B. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.0000 deg. 3U cubesat from the US Naval Academy (UNSA) testing out an IP link to the satellite's computer which hosts a Unix webserver..
  • BRICSat-P - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40655 . COSPAR: 2015-025E. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.0000 deg. 1.5U cubesat from the US Naval Academy (UNSA), built in collaboration with George Washington University, testing an electric micropropulsion system..
  • Aerocube-8a - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40659 . COSPAR: 2015-025J. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.0000 deg. Aerospace Corporation 1.5U cubesat testing an ion-electrospray propulsion system..
  • Aerocube-8b - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40660 . COSPAR: 2015-025K. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.0000 deg. Aerospace Corporation 1.5U cubesat testing carbon nanotube materials..
  • LightSail-A - . Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40661 . COSPAR: 2015-025L. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.0000 deg.

    Planetary Society's 3U cubesat with a solar sail deployment experiment. The cubesat went into safe mode a few days after launch but rebooted on May 30. Its solar panels were deployed on June 3 and the solar sail was unfurled on June 7 at 19:47 GMT. The satellite reentered on June 14.


2015 July 10 - . 16:28 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. Launch Pad: Sriharikota FLP. LV Family: PSLV. Launch Vehicle: PSLV-XL.
  • DeOrbitSail - . Mass: 3.00 kg (6.60 lb). Nation: UK. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: CubeSat. USAF Sat Cat: 40719 . COSPAR: 2015-032E. Apogee: 657 km (408 mi). Perigee: 634 km (393 mi). Inclination: 98.0400 deg. Period: 97.63 min. 3U cubesat. 22:10 local time longitude of descending node sun synchronous orbit..

2015 July 16 - . 06:41 GMT - . Launch Site: ISS. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • Arkyd-3R - . Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40743 . COSPAR: 1998-067GV. Apogee: 354 km (219 mi). Perigee: 345 km (214 mi). Inclination: 51.6400 deg. Period: 91.53 min. 3U cubesat from Planetary Resources, testing software and systems for future Arkyd satellites..
  • SERPENS - . Mass: 4.00 kg (8.80 lb). Nation: Brazil. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: CubeSat. USAF Sat Cat: 40897 . COSPAR: 1998-067GX. Apogee: 384 km (238 mi). Perigee: 380 km (230 mi). Inclination: 51.6400 deg. Period: 92.19 min. SERPENS 3U cubesat from the University of Brasilia; ejected from the J-SSOD deployer on the Kibo robot arm on 17 September..

2015 September 19 - . 23:01 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC16. LV Family: CZ-NGLV. Launch Vehicle: Chang Zheng 6.
  • Kaituo-1 - . Mass: 130 kg (280 lb). Nation: China. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Kaituo. Spacecraft: Kaituo. USAF Sat Cat: 40899 . COSPAR: 2015-049A. Apogee: 537 km (333 mi). Perigee: 513 km (318 mi). Inclination: 97.4500 deg. Period: 95.13 min. Satellite from Shenzen DFH Company, also called XY 2 (Xinyan-2 or NewTech-2), which tested electric propulsion Hall thrusters. Deployed the DCBB subsatellite..
  • Zhineng hao - . Payload: NUDT-PHONESAT. Mass: 1.00 kg (2.20 lb). Nation: China. Class: Technology. Type: Technology satellite. USAF Sat Cat: 40900 . COSPAR: 2015-049B. Apogee: 536 km (333 mi). Perigee: 511 km (317 mi). Inclination: 97.4500 deg. Period: 95.11 min.

    Zhineng hao shouji weixing (Smart Phone Satellite), a 1 kg satellite also known as NUDT-Phone-Sat, built around the motherboard of an Android smartphone. Deployed four Xingchen 100 gram picosats. The overall experiment was to control a cluster of satellites using intersatellite communications.

  • Zheda Pixing 2A - . Payload: ZDPS 2A. Mass: 12 kg (26 lb). Nation: China. Class: Technology. Type: Technology satellite. USAF Sat Cat: 40901 . COSPAR: 2015-049C. Apogee: 537 km (333 mi). Perigee: 514 km (319 mi). Inclination: 97.4600 deg. Period: 95.14 min. One of a pair of Zhejian University (Hangzhou, Zhejiang) satellites to test MEMS microelectronic technology, including a small deployable truss antenna on top of each satellite..
  • Zheda Pixing 2B - . Payload: ZDPS 2B. Mass: 12 kg (26 lb). Nation: China. Class: Technology. Type: Technology satellite. USAF Sat Cat: 40902 . COSPAR: 2015-049D. Apogee: 537 km (333 mi). Perigee: 514 km (319 mi). Inclination: 97.4500 deg. Period: 95.15 min. One of a pair of Zhejian University (Hangzhou, Zhejiang) satellites to test MEMS microelectronic technology, including a small deployable truss antenna on top of each satellite..
  • Naxing-2 - . Payload: OBJECT G. Mass: 20 kg (44 lb). Nation: China. Class: Technology. Type: Technology satellite. USAF Sat Cat: 40905 . COSPAR: 2015-049G. Apogee: 542 km (336 mi). Perigee: 517 km (321 mi). Inclination: 97.4500 deg. Period: 95.23 min. Tsinghua University (Beijing)'s Naxing-2 (Nanosatellite-2, NS-2) had a mass of 20 kg and tested MEMS microelectronic components and carried small Beidou/GPS receivers. It also deployed the Zijing 1 and 2 picosats..
  • Zidingxiang-2 - . Payload: LILACSAT 2. Mass: 11 kg (24 lb). Nation: China. Class: Technology. Type: Communications technology satellite. USAF Sat Cat: 40908 . COSPAR: 2015-049K. Apogee: 543 km (337 mi). Perigee: 518 km (321 mi). Inclination: 97.4600 deg. Period: 95.25 min. Zidingxiang-2 ("LilacSat-2") was from the Harbin Institute of Technology in Heilongjiang province, in China's far northeast. The 11 kg satellite carries an ADS-B reciever, and an FPGA radiation exposure test..
  • DCBB - . Payload: KAITUO 1B. Mass: 2.00 kg (4.40 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40912 . COSPAR: 2015-049P. Apogee: 536 km (333 mi). Perigee: 510 km (310 mi). Inclination: 97.4600 deg. Period: 95.10 min. 2U cubesat with an amateur radio payload..
  • Xingchen 1 - . Mass: 0 kg (0 lb). Nation: China. Class: Technology. Type: Technology satellite. COSPAR: 2015-049. Apogee: 536 km (333 mi). Perigee: 515 km (320 mi). Inclination: 97.5000 deg. Xingchen ('Starlight') 100 gram picosat, deployed from the Zhineng hao / NUDT-Phone-Sat, measuring only 98 x 98 x 7mm in size..
  • Xingchen 2 - . Mass: 0 kg (0 lb). Nation: China. Class: Technology. Type: Technology satellite. COSPAR: 2015-049. Apogee: 536 km (333 mi). Perigee: 515 km (320 mi). Inclination: 97.5000 deg. Xingchen ('Starlight') 100 gram picosat, deployed from the Zhineng hao / NUDT-Phone-Sat..
  • Xingchen 3 - . Mass: 0 kg (0 lb). Nation: China. Class: Technology. Type: Technology satellite. COSPAR: 2015-049. Apogee: 536 km (333 mi). Perigee: 515 km (320 mi). Inclination: 97.5000 deg. Xingchen ('Starlight') 100 gram picosat, deployed from the Zhineng hao / NUDT-Phone-Sat..
  • Xingchen 4 - . Mass: 0 kg (0 lb). Nation: China. Class: Technology. Type: Technology satellite. COSPAR: 2015-049. Apogee: 536 km (333 mi). Perigee: 515 km (320 mi). Inclination: 97.5000 deg. Xingchen ('Starlight') 100 gram picosat, deployed from the Zhineng hao / NUDT-Phone-Sat..
  • Zijing-1 - . Mass: 0 kg (0 lb). Nation: China. Class: Technology. Type: Technology satellite. COSPAR: 2015-049. Apogee: 541 km (336 mi). Perigee: 519 km (322 mi). Inclination: 97.5000 deg. 234 gram picosat deployed from Naxing-2..
  • Kongjian Shiyan 1 - . Mass: 0 kg (0 lb). Nation: China. Class: Technology. Type: Technology satellite. COSPAR: 2015-049. Apogee: 541 km (336 mi). Perigee: 519 km (322 mi). Inclination: 97.5000 deg. 173 gram picosat, also called Ziging-2, deployed from Naxing-2. Built by the Xi'an University of Electronic Science and Technology (Xidian) in Jiangxi..

2015 September 25 - . 01:41 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS-2. Launch Pad: Jiuquan SLS-E. LV Family: CZ-NGLV. Launch Vehicle: Chang Zheng 11.
  • Pujiang-1 - . Mass: 300 kg (660 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: Pujiang. Spacecraft: Pujiang. USAF Sat Cat: 40925 . COSPAR: 2015-051A. Apogee: 487 km (302 mi). Perigee: 465 km (288 mi). Inclination: 97.3000 deg. Period: 94.13 min.

    First launch of the CZ-11 solid-fuel, four-stage, light launch vehicle, though to be related to the DF-31 and DF-41 ICBMs. Pujiang, the Chinese Technology Experiment Satellite, was designed to promote the construction of smart cities in China, by monitoring urban weather, traffic and population density. It was the first Chinese satellite to use 3D printing for the titanium structure of its antenna. It included a Wi-Fi router providing a communication network between the three Tianwang cubesats released on the same launch.

  • Shangkeda-2 - . Payload: TIANWANG 1C (TW-1C). Mass: 3.00 kg (6.60 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40926 . COSPAR: 2015-051B. Apogee: 485 km (301 mi). Perigee: 460 km (280 mi). Inclination: 97.3000 deg. Period: 94.04 min.

    Part of the Tianwang constallation of three CubeSats for space networking experiments. Codeveloped by the Shanghai Engineering Center for Microsatellites (SECM), the Nanjing University of Science and Technology (NJUST), GomSpace Denmark, Tekever Space Portugal and NanoSpace Sweden.

  • NJUST-2 - . Payload: TIANWANG 1B (TW-1B). Mass: 3.00 kg (6.60 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40927 . COSPAR: 2015-051C. Apogee: 485 km (301 mi). Perigee: 462 km (287 mi). Inclination: 97.3100 deg. Period: 94.07 min.
  • NJFA-1 - . Payload: TIANWANG 1A (TW-1A). Mass: 3.00 kg (6.60 lb). Nation: China. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40928 . COSPAR: 2015-051D. Apogee: 485 km (301 mi). Perigee: 463 km (287 mi). Inclination: 97.2900 deg. Period: 94.08 min.

2015 September 28 - . 04:30 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. Launch Pad: Sriharikota FLP. LV Family: PSLV. Launch Vehicle: PSLV-XL.
  • LAPAN-A2 - . Mass: 68 kg (149 lb). Nation: Indonesia. Class: Technology. Type: Technology satellite. Spacecraft Bus: Tubsat. Spacecraft: Tubsat. USAF Sat Cat: 40931 . COSPAR: 2015-052B. Apogee: 650 km (400 mi). Perigee: 631 km (392 mi). Inclination: 6.0000 deg. Period: 97.54 min. Indonesian microsatellite; carried an AIS (Automatic Identification System) to identify ships in Indonesia waters, a video camera, and a payload for disaster management by amateur radio operators..

2015 October 8 - . 12:49 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3E. LV Family: Atlas V. Launch Vehicle: Atlas V 401.
  • Aerocube-5C - . Mass: 10 kg (22 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40965 . COSPAR: 2015-058B. Apogee: 802 km (498 mi). Perigee: 500 km (310 mi). Inclination: 64.8000 deg. Aerospace Corporation cubesat..
  • Aerocube-7 - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40966 . COSPAR: 2015-058C. Apogee: 802 km (498 mi). Perigee: 500 km (310 mi). Inclination: 64.8000 deg. Aerospace Corporation cubesat..
  • AMSAT-OSCAR-85 - . Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40967 . COSPAR: 2015-058D. Apogee: 802 km (498 mi). Perigee: 500 km (310 mi). Inclination: 64.8000 deg. Also called Fox-1A; amateur radio cubesat from AMSAT-North America..
  • Bisonsat - . Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40968 . COSPAR: 2015-058E. Apogee: 802 km (498 mi). Perigee: 500 km (310 mi). Inclination: 64.8000 deg. Cubesat from Salish Kootenai College in Montana..
  • ARC-1 - . Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40969 . COSPAR: 2015-058F. Apogee: 802 km (498 mi). Perigee: 500 km (310 mi). Inclination: 64.8000 deg. Alaska Research Cubesat 1 from University of Alaska, Fairbanks..
  • LMRST - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40971 . COSPAR: 2015-058H. Apogee: 802 km (498 mi). Perigee: 500 km (310 mi). Inclination: 64.8000 deg. Low Mass Radio Science Transponder experiment cubesat from JPL..
  • SINOD-D 1 - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40974 . COSPAR: 2015-058L. Apogee: 802 km (498 mi). Perigee: 500 km (310 mi). Inclination: 64.8000 deg. One of two SINOD-D cubesats with software-defined radio demonstrations from SRI International..
  • SINOD-D 3 - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. USAF Sat Cat: 40977 . COSPAR: 2015-058P. Apogee: 802 km (498 mi). Perigee: 500 km (310 mi). Inclination: 64.8000 deg. One of two SINOD-D cubesats with software-defined radio demonstrations from SRI International..

2015 November 4 - . 03:45 GMT - . Launch Site: Barking Sands. LV Family: Strypi. Launch Vehicle: Super Strypi.
  • PrintSat - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • Techsat-1 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • EDSN 1 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • EDSN 2 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • EDSN 3 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • EDSN 4 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • EDSN 5 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • EDSN 6 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • EDSN 7 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • EDSN 8 - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..
  • Argus - . Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Cubesat. Cubesat; lost when first stage failed..


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