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Aircraft designation (T-38 - trainer-38); also technical experiments prefix
t/Space.
T-1.
T-1.
American pressure suit, operational 1948. David Clark Company developed Dr. Henry's original capstan partial pressure suit.
T-1.
Original conceptual design for ICBM. Final design was R-7 due to unachievability of mass ratio for this single stage design. Data from chart at Russian Space Agency HQ.
Pratt and Whitney electric rocket engine. 3 kW Hall thruster
Pratt and Whitney / Keldysh Research Center electric rocket engine. Development began in 1997 of this 10 kW Hall thruster Program concluded in 2000 following a 1000 hour erosion characterization.
T2K.
Alternate designation for LK manned lunar lander.
T-38.
Jet trainer used by NASA astronauts to maintain flight proficiency and to shuttle themselves around the country.
T-4.
Mach 3 rocket carrier. Loaded/empty mass 114,400/55,600 kg. Thrust 633.50 kN. Specific impulse 1980 seconds. Sukhoi experimental interceptor - delta wing with forward canards. A modification to be used as first stage in Sukhoi proposal for Spiral manned spaceplane project. Maximum release conditions: 25,000 kg at 3,000 kph at 20,000 m altitude
T-40.
Thiokol solid rocket engine. 13.3 kN.
T-55.
Thiokol solid rocket engine. 21 kN.
T-5E.
Alternate Designation of R-70 tactical ballistic rocket.
T-7.
Chinese sounding rocket. China's first sounding rocket and first indigenously-built sounding rocket, launched from 1960-1965. The basic vehicle consisted of a single liquid propellant stage. This was later augmented with solid propellant booster stages. Later versions dispensed with the liquid propellant stage.
T-7.
China's first sounding rocket and first indigenously-built sounding rocket, launched from 1960-1965. The basic vehicle consisted of a single liquid propellant stage. This was later augmented with solid propellant booster stages. Later versions dispensed with the liquid propellant stage.
SIMED/Shanghai solid rocket engine.
SIMED/Shanghai solid rocket engine.
Chinese sounding rocket. Three stage vehicle consisting of T-7A + GF-01A
Solid propellant rocket stage. Loaded mass 1,000 kg.
T-7A.
Chinese sounding rocket. Boosted version of China's first indigenously-built sounding rocket. Included solid propellant booster. The upper stage and payload were recovered by parachute and reused. Launches began in 1965. Consisted of a solid propellant booster mated to the basic liquid propellant T-7. Flown from 1965 to the end of the 1960's.
Fourth Academy solid rocket engine. 46 kN. T-7 sounding rocket. Out of Production. Isp=209s. China's first flight solid rocket. First flight 1965. Polysulfide binder with aluminium binder fuel in case of high strength steel with a graphite throat insert.
Chinese sounding rocket. 2 stage vehicle
Chinese sounding rocket. 2 stage vehicle
Solid propellant rocket stage. Loaded mass 1,000 kg.
T-7B.
Alternate Designation of R-11M submarine-launched ballistic missile.
T-7M.
Chinese sounding rocket. 2 stage test vehicle for T-7.
TA.
Triacetine
Tabakov, Gleb Mikhailovich (1912-1993) Russian government official. Director of NII-229 1958-1963. Deputy Minister of General Machine Building 1965-1981.
What has been identified by Sean O'Connor as Iran's first IRBM field is located 10 kilometers southwest of Tabriz. As of 2008 site consisted of the silo field, an administrative and support area, missile storage bunkers, and an unoccupied HQ-2 surface-to-air missile site. The latter was used as a staging area for mobile Shahab missile transport-erector launchers. The two silos seemed to include blast vents, indicating a hot-launch design.
TAC.
Tactical Air Command
Taccino, Roberto Maria (1955-) Italian physician payload specialist astronaut, 1990-1993. Professor. Selected by the Italian Space Agency (ASI) as one of the five Italian astronaut candidates for a European Space Agency (ESA) astronaut selection.
French sounding rocket. Single stage sounding rocket using a single Stromboli SEPR 739-2 stage with 'Plastoline' propellant. Stabilisation was by four fins and a nitrogen cold-gas spin thrusters.
TACS.
Thruster Attitude Control System.
American communications technology satellite. First launch 1969.02.09. TACSAT was designed to experimentally test and develop tactical communications concepts for all US military services.
American military surveillance satellite. First launch, 2006.12.16. The Tactical Satellite / Operationally Responsive Satellite program's objective was to demonstrate techniques to dramatically shorten the development time for small satellites.
Category of missiles.
Category of missiles.
Nitric acid/UDMH rocket stage. 570.00 kN (128,141 lbf) thrust. Mass 25,600 kg (56,438 lb).
North Korean long-range ballistic missile and satellite launch vehicle consisted of a No-Dong 1 IRBM as the first stage, and a derivative of the Scud-C SRBM as the second stage.
North Korean long-range ballitic missile and satellite launch vehicle consisted of a No-Dong 1 IRBM as the first stage, and a derivative of the Scud-C SRBM as the second stage.
North Korean orbital launch vehicle. The third stage for the satellite launch version was probably a small solid rocket engine. It failed to reach orbit in the 1998 launch attempt, and later such tests are believed to have used a different design.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 25,649/3,733 kg. Thrust 577.34 kN. Vacuum specific impulse 255 seconds.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 7,505/1,456 kg. Thrust 144.33 kN. Vacuum specific impulse 255 seconds. Included 100 kg spin table for spin-up of third stage prior to release. Burn time is 33.7 seconds at full thrust, 142.3 seconds at half thrust.
Solid propellant rocket stage. Loaded/empty mass 252/50 kg. Thrust 18.33 kN. Vacuum specific impulse 250 seconds.
North Korean intermediate range ballistic missile. Two-stage ballistic missile. First stage is 18 m long, second is 14 m long.
Nitric acid/UDMH rocket stage. 1000.00 kN (224,809 lbf) thrust. Mass 60,000 kg (132,277 lb).
Taifun.
Launch System of 3M65 missile.
German surface-to-air barrage rocket, tested during World War II, but never operational. Copied in the USA as the Loki and in the USSR as the R-103. The name translates as 'Typhoon'.
Ukrainian military target satellite. 25 launches, 1974.06.18 (Cosmos 660) to 1994.09.27 (Cosmos 2292). From 1969 KB Yuzhnoye built the Lira targets for exercise and test of PVO air defense and space tracking systems.
Ukrainian military target satellite. 13 launches, 1979.12.05 (Cosmos 1146) to 1996.04.24 (Cosmos 2332). The Taifun-1Yu, a modification of the basic design with smooth calibration surfaces, was to be in service by 1980.
Ukrainian military target satellite. 31 launches, 1976.04.28 (Cosmos 816) to 1995.03.02 (Cosmos 2306). In 1969 KB Yuzhnoye introduced targets for exercise and test of PVO air defense and space tracking systems.
Russian military target satellite. 2 launches, 1988.12.23 (Cosmos 1985) to 1989.12.27 (Cosmos 2053). Specifications for a third generation Taifun-3 system were developed in 1980 with flight trials to have started in 1984.
Person trained for spaceflight in China.
Taiwan.
First name of NSPO
Taiwan
Taiwan-NSPO.
China's launch site for launch of polar orbiting satellites, also known as Wuzhai. Taiyuan Satellite Launch Center (TSLC) is situated in Kelan County, the northwest part of Shanxi Province, 280 km by road from Taiyuan City.
CZ launch complex. Pad 1
Tajikistan
TAL.
Transatlantic Abort Landing (Shuttle abort plan)
TsNIIMASH electric/xenon rocket engine. 34 mN. Development. Isp=1450s. Hall effect thruster with anode layer. Export version of D-100-I thruster developed under NASA/BMDO contract. Taken to engineering model stage.
TsNIIMASH electric/xenon rocket engine. 8 mN. Development. Isp=2500s. Hall effect thruster with anode layer. Export version of D-38, developed under NASA contract for satellite station-keeping and attitude control. Taken to engineering model stage.
Tall Afar
American Navy long-range ramjet-powered surface-to-air missile. In service 1959-1979.
American Navy long-range ramjet-powered surface-to-air missile family.
Talos AAW.
Popular Name of RIM-8G surface-to-air missile.
Talos ARM.
Popular Name of RGM-8H tactical cruise missile.
American sounding rocket. Two stage sounding rocket consisting of 1 x Talos booster + 1 x Castor
Hercules solid rocket engine. 516 kN. Talos motor fitted with a conical adapter for mating to the second stage.
American sounding rocket. Three stage sounding rocket consisting of 1 x Talos booster + 1 x Sergeant + 1 x Hydac
Solid propellant rocket stage. Loaded mass 300 kg. Thrust 58.70 kN.
Solid propellant rocket stage. Loaded mass 1,500 kg. Thrust 516.00 kN. The Talos motor was fitted with a conical adapter for mating to the second stage. Differential drag forces caused separation. Four fins were arranged at the aft end in a cruciform configuration and drove the vehicle to approximately one revolution per second burnout roll rate.
TsNIIMASH electric/xenon rocket engine. 12 mN. Isp=1350s. Hall effect thruster with anode layer. Export version of D-55 thruster developed under NASA/BMDO contract for flight test under RHETT-II program. Used for satellite orbital altitude maintenance.
Tamayo-Mendez, Arnaldo 'Guasso' (1942-) African-Cuban pilot cosmonaut. Flew on Salyut 6 EP-8. First Cuban astronaut. First person of African descent to fly in space. Graduated from Air Force Academy Pilot, Cuban Air Force. Director of the Organization for Civil Defense in Cuba.
The story of the making of the 1972 Soviet film that took viewers inside the life of Sergei Korolev and the Baikonur cosmonaut -- they thought! As of August 2011 this movie could be viewed on youtube at ????????? ???? / 1972.
Iraqi space launch vehicle/ICBM based on clustering of Scud tactical missiles. Canadian rocket scientist Gerald Bull was allegedly killed by Israeli agents not for his work on the supergun, but rather for his much more damaging assistance to the Iraqis in doing the dynamic calculations for the Tamouz.
American test vehicle. Two stage vehicle consisting of 2 x Deacon + 2 x Deacon
Japan's main launch site for he larger N and H launch vehicles. In use for sounding rockets from 1967 and orbital launches from 1975. As of 2007 over 140 major launches had been made from the site.
J, Delta launch complex. N Launch Complex
Mu launch complex. Q Launch Complex
TR-1, S, MT-135, Lambda launch complex. Takesaki Launch Site
H-2 launch complex. Yoshinobu Launch Complex
H-2 launch complex. Completed in 2000, for H-IIIB launches.
Tani.
Tani, Daniel Michio (1961-) Japanese-American engineer mission specialist astronaut. Flew on STS-108, ISS EO-16-1.
Tani, I (-1943) Japanese Professor. Japanese airplane technical designer.
Tanner, Joseph Richard 'Joe' (1950-) American engineer mission specialist astronaut. Flew on STS-66, STS-82, STS-97, STS-115.
Tannhaeuser, Rosemarie (1919-) German manager. Member of the German Rocket Team in the Soviet Union after WW2. Secretary who worked on rocket engine development in Glushko's design bureau from 1947 to 1952. Worked as Secretary in Dept. 61/Shop 55.
Japanese technology satellite. 5 launches, 1971.02.16 (Tansei 1) to 1985.01.07 (SS-10 Sagikake). Series of spacecraft of varying configurations built for engineering tests of scientific satellite equipment.
Tansuo-1.
Code name for Shiyan civilian surveillance satellite.
TAOS.
American military strategic defense satellite. One launch, 1994.03.13, USA 101. TAOS was a technology demonstration satellite whose purpose was to demonstrate autonomous space navigation systems to reduce satellite ground support needs.
Russian anti-ballistic missile. Anti-ballistic missile design that was part of the basic capability of the UR-100. Studied in 1962-1964 but abandoned.
French study of vertical takeoff / horizontal landing, two stage to orbit launch vehicle with expendable orbiter fuel tanks.
Tarelkin, Yevgeni Igorevich (1974-) Russian engineer cosmonaut, 2003-on.
Category of missiles.
Sounding rocket launch location known to have been used for 16 launches in 1966, reaching up to 90 kilometers altitude.
TAS.
Heavy Automated Station (Russian abbreviation)
TASS.
Telegraph Agency of the Soviet Union (Soviet news agency) (Russian abbreviation)
American test vehicle. Three stage vehicle consisting of 1 x Talos + 1 x Terrier + 1 x Recruit
Headquarters of an RVSN Division, 1964-present. Base for units deployed with 110 light ICBM silos (UR-100/UR-100N) and later ten RT-23 mobile ICBM launchers. A single live launch was known to have been made from here in 1987, reaching 1000 km altitude.
Tattletale.
Code name for GRAB military naval signals reconnaisance satellite.
TAU.
Thousand Astronomical Unit (mission)
Base for units deployed with R-12 missile.
American all-solid orbital launch vehicle. Pad-launched launch vehicle using Pegasus upper stages and Castor-120 first stage. First launch used slightly larger Peacekeeper ICBM first stage instead of Castor-120. Under a 2002 contract from Boeing, Orbital developed a three-stage version of Taurus to serve as the interceptor boost vehicles for the US government's missile intercept system. The firm portion of the company's contract, awarded in early 2002, was valued at $450 million and extended through 2007.
Pad-launched launch vehicle using Pegasus upper stages and Castor-120 first stage.
Hercules solid rocket engine. 457 kN.
American all-solid orbital launch vehicle.
American all-solid orbital launch vehicle.
American all-solid orbital launch vehicle.
American all-solid orbital launch vehicle.
American orbital launch vehicle. Pad-launched launch vehicle using Pegasus upper stages and a first stage combining a Ukrainian Zenit lower stage fitted with 30-year old surplus Russian N1 moon program rocket engines.
Solid rocket stage. 457.00 kN (102,738 lbf) thrust. Mass 1,363 kg (3,005 lb).
American sounding rocket. 2 stage vehicle composed of 1 x Taurus (Honest John motor) + 1 x Orion. Payload 68 kg to 260 km or 227 kg to 140 km.
Solid rocket stage. 13.00 kN (2,923 lbf) thrust. Mass 400 kg (882 lb).
American tactical ballistic missile to provide US Navy ships with a long range surface-to-surface capability. Development began 1961; cancelled 1965.
American sounding rocket.
Interim long-range cruise missile considered by the US Navy in 1946-1948, an unmanned version of the AJ-1 Savage carrier-based bomber.
German manufacturer. Taurus Systems GmbH, Germany.
American sounding rocket. NASA two stage sounding rocket. Payload 27 kg to 590 km or 59 kg to 490 km.
Three stage vehicle consisting of 1 x Taurus (Honest John motor) + 1 x Nike + 1 x Tomahawk. Payload 32 kg to 700 km or 125 kg to 400 km.
American all-solid propellant orbital launch vehicle.
Solid propellant rocket stage. Loaded/empty mass 48,960/4,300 kg. Thrust 2,204.50 kN. Vacuum specific impulse 282 seconds. ICBM MX Peacekeeper ICBM 1st stage. Used for only first Taurus launch
Solid propellant rocket stage. Loaded/empty mass 13,242/1,088 kg. Thrust 484.91 kN. Vacuum specific impulse 285 seconds. Pegasus stage 1 without the wings and stabilisers.
Taurus-Lite.
Manufacturer's designation for OBV anti-ballistic missile.
Taurus-Lite.
Alternate designation for Orion 50SG rocket stage.
Tausend Fussler.
Alternate designation for V-3 gun-launched missile.
TAV.
American manned spaceplane. Developed in the 1980s but halted in favor of the X-30. USAF program of the 1980's that reached the test hardware stage and was leading to a single-stage-to-orbit, rocket-powered, winged manned vehicle.
TAV.
American winged rocketplane. USAF program of the 1980's that reached the test hardware stage and was leading to a single-stage-to-orbit, rocket-powered, winged manned vehicle. Halted in favour of the X-30 National Aerospace Plane.
TAVE.
American technology satellite. One launch, 1962.09.29. Thor Agena Vibration Experiment
Libyan rocket test range, 600 km south of Tripoli. Site of tests of Otrag's low cost launch vehicle from 1981 to 1982, reaching up to 150 kilometers altitude.
Taylor, James Martin (1930-1970) American test pilot astronaut, 1965-1969.
Taylor, Brian (1940-) British Astrophysicist. Brian Taylor joined ESA (then ESRO) in 1967 as a staff scientist. In 1971, he became head of the high energy astrophysics division and in 1984, he became head of the astrophysics division.
TCA.
Thrust chamber assembly
TCI.
American agency. Telcom, Indonesia, USA.
TCS.
Thermal Control System
TD-174.
Manufacturer's designation of LR44 rocket engine.
TD-187.
Manufacturer's designation of LR58 rocket engine.
European technology satellite. One launch, 1972.03.12. Sixth satellite of ESRO.
TD-2.
CMIK Nitric acid/UDMH rocket engine. 1000 kN.
TD-232.
Manufacturer's designation of LR62 rocket engine.
TDA.
Target docking adapter
TDF.
French direct broadcasting communications satellite network
TDI.
Toluene-2,4-diisocyanate
TdM.
Telecommunicaciones de Mexico, Mexico
TDRS.
American military communications satellite. 7 launches, 1983.04.04 (TDRS 1) to 1995.07.13 (TDRS 7). Satellite communications network, for use by Shuttle and US military satellites.
Tracking and Data Relay Satellite System
TDU.
Retrofire Engine Unit (Russian abbreviation)
TDU-1.
Manufacturer's designation of S5.4 Nitric acid-Amine rocket engine.
Thiokol solid rocket engine. 21 kN.
Thiokol solid rocket engine. 24.4 kN.
Thiokol solid rocket engine. 53 kN.
Thiokol solid rocket engine. 90 kN.
TEA.
Torque Equilibrium Attitude
Category of persons.
Technical University of Berlin Satellite.
Alternate designation for Tubsat communications technology satellite.
Israeli manufacturer of spacecraft. Technion Institute of Technology, Haifa, Israel.
Category of spacecraft.
Technology for Autonomous Operational Survivability.
Alternate designation for TAOS military strategic defense satellite.
Category of spacecraft.
Techstar.
Manufacturer's designation for GFO earth resources radar satellite.
Israeli military surveillance radar satellite. First launch 2008.01.21. Israeli military radar/optical surveillance satellite using synthetic aperture x-band radar, with estimated 10 cm radar and 1 m optical ground resolution.
Teflon was introduced in the late 1990's as the solid fuel heated electrically to provide a completely solid-state rocket system for spacecraft orientation with no moving parts.
Triethylene glycol dinitrate
Teichmann, A German expert in aerodynamics during World War II. As of January 1947, working at Berliln.
Headquarters of an RVSN Division, 1961-present, operating a peak of 90 light ICBM (UR-100/UR-100N) silos. By 1993 the number of operational silos had declined to 26.
Russian materials science satellite. Study 1990. In 1990 KB Salyut proposed an unmanned derivative of the TKS to conduct zero-gravity materials production experiments.
Russian materials science satellite. In 1991 Lavochkin NPO proposed this recoverable earth orbital spacecraft design, derived from their Venera planetary spacecraft, for materials and microgravity research missions.
TELE.
Television, business communications satellite networ for Nordic countries. High power telecommunications satellites provided both direct TV broadcasting and data communications.
Brazilian agency. Tele Mex, Brazil.
Brazilian agency. Telebras, Brazil.
Communications satellite network
American communications satellite. One launch, 1998.02.26. The Teledesic system was announced in 2004, and was to have provided global communication links via a constellation of 288 LEO spacecraft.
American agency overseeing development of spacecraft. Teledesic Corp. , USA
American manufacturer. Teledyne Ryan, USA.
Teleglobe.
Norwegian agency. Telenor, Oslo, Norway.
Canadian agency overseeing development of spacecraft. Telesat Canada, Canada.
Nuova Telespazio, Italy
Italian agency overseeing development of spacecraft. Telespazio, Italy.
Telespazio Micro Satellite.
Alternate designation for Temisat communications technology satellite.
Television Infrared Observation Satellite.
Alternate designation for TIROS earth weather satellite.
PT Telkom, Jakarta, Indonesia
Teller, Edward (1908-2003) Jewish Hungarian-American physicist, American Father of the H-Bomb. A dedicated cold warrior. Founded Livermore laboratory, convinced Reagan to proceed with 'Star Wars' using nuclear-bomb-pumped x-ray laser.
Russian earth land resources satellite. Study 1990. In 1990 KB Salyut proposed an unmanned derivative of the TKS manned ferry to conduct earth resources experiments.
American communications satellite. 2 launches, 1962.07.10 (Telstar 1) and 1963.05.07 (Telstar 2).
Network of communications satellites, operated by AT&T Skynet, later Loral Skynet, Bedminster.
TE-M-184-3.
Manufacturer's designation of Star 25 Solid rocket engine.
TE-M-186-2.
Manufacturer's designation of Star 40 Solid rocket engine.
TE-M-195.
Manufacturer's designation of Star 10 Solid rocket engine.
TE-M-236.
Manufacturer's designation of Star 12 Solid rocket engine.
TE-M-236-3.
Manufacturer's designation of Star 12A Solid rocket engine.
TE-M-251.
Manufacturer's designation of Star 20 Spherical Solid rocket engine.
TE-M-344-15.
Manufacturer's designation of Star 5C-CB Solid rocket engine.
TE-M-344-16.
Manufacturer's designation of Star 5C Solid rocket engine.
TE-M-345-11/12.
Manufacturer's designation of Star 13C Solid rocket engine.
TE-M-364-1.
Manufacturer's designation of Star 37 Solid rocket engine.
TE-M-364-11.
Manufacturer's designation of Star 37G Solid rocket engine.
TE-M-364-14.
Manufacturer's designation of Star 37N Solid rocket engine.
TE-M-364-15.
Manufacturer's designation of Star 37S Solid rocket engine.
TE-M-364-18.
Manufacturer's designation of Star 37C Solid rocket engine.
TE-M-364-19.
Manufacturer's designation of Star 37F Solid rocket engine.
TE-M-364-2.
Manufacturer's designation of Star 37B Solid rocket engine.
TE-M-364-3.
Manufacturer's designation of Star 37D Solid rocket engine.
TE-M-364-4.
Manufacturer's designation of Star 37E Solid rocket engine.
TE-M-375.
Manufacturer's designation of Star 13D Solid rocket engine.
TE-M-385.
Manufacturer's designation of Star 13E Solid rocket engine.
TE-M-442.
Manufacturer's designation of Star 26 Solid rocket engine.
TE-M-442-1.
Manufacturer's designation of Star 26B Solid rocket engine.
TE-M-442-2.
Manufacturer's designation of Star 26C Solid rocket engine.
TE-M-444.
Manufacturer's designation of Star 13F Solid rocket engine.
TE-M-456-2.
Manufacturer's designation of Star 15 Solid rocket engine.
TE-M-458.
Manufacturer's designation of Star 13 Solid rocket engine.
TE-M-479.
Manufacturer's designation of Star 17 Solid rocket engine.
TE-M-500.
Manufacturer's designation of Star 5 Solid rocket engine.
TE-M-516.
Manufacturer's designation of Star 13A Solid rocket engine.
TE-M-521-5.
Manufacturer's designation of Star 17A Solid rocket engine.
TE-M-541-3.
Manufacturer's designation of Star 6 Solid rocket engine.
TE-M-542-3.
Manufacturer's designation of Star 6A Solid rocket engine.
TE-M-604.
Manufacturer's designation of Star 24 Solid rocket engine.
TE-M-604-2.
Manufacturer's designation of Star 24A Solid rocket engine.
TE-M-604-3.
Manufacturer's designation of Star 24B Solid rocket engine.
TE-M-604-4.
Manufacturer's designation of Star 20B Solid rocket engine.
TE-M-616.
Manufacturer's designation of Star 27 Solid rocket engine.
TE-M-616-1.
Manufacturer's designation of Star 27A Solid rocket engine.
TE-M-616-4.
Manufacturer's designation of Star 27B Solid rocket engine.
TE-M-616-5.
Manufacturer's designation of Star 27C Solid rocket engine.
TE-M-616-8.
Manufacturer's designation of Star 27D Solid rocket engine.
TE-M-616-9.
Manufacturer's designation of Star 27E Solid rocket engine.
TE-M-640.
Manufacturer's designation of FW-4S TEM640 Solid rocket engine.
TE-M-640-1.
Manufacturer's designation of Star 20 Solid rocket engine.
TE-M-640-3.
Manufacturer's designation of Star 20A Solid rocket engine.
TE-M-700-18.
Manufacturer's designation of Star 30C Solid rocket engine.
TE-M-700-19.
Manufacturer's designation of Star 30E Solid rocket engine.
TE-M-700-2.
Manufacturer's designation of Star 30 Solid rocket engine.
TE-M-700-20.
Manufacturer's designation of Star 30BP Solid rocket engine.
TE-M-700-4.
Manufacturer's designation of Star 30A Solid rocket engine.
TE-M-700-5.
Manufacturer's designation of Star 30B Solid rocket engine.
TE-M-711-17.
Manufacturer's designation of Star 48B s Solid rocket engine.
TE-M-711-17.
Alternate designation for PAM-S rocket stage.
TE-M-711-18.
Manufacturer's designation of Star 48B l Solid rocket engine.
TE-M-711-18.
Alternate designation for PAM-D rocket stage.
TE-M-711-3.
Manufacturer's designation of Star 48 Solid rocket engine.
TE-M-711-8.
Manufacturer's designation of Star 48 8 Solid rocket engine.
TE-M-714-1.
Manufacturer's designation of Star 37X Solid rocket engine.
TE-M-714-16/17.
Manufacturer's designation of Star 37XFP Solid rocket engine.
TE-M-714-2.
Manufacturer's designation of Star 37Y Solid rocket engine.
TE-M-714-6.
Manufacturer's designation of Star 37XF Solid rocket engine.
TE-M-714-8.
Manufacturer's designation of Star 37XF 8 Solid rocket engine.
TE-M-731.
Manufacturer's designation of Star 62 Solid rocket engine.
TE-M-762.
Manufacturer's designation of Star 31 Solid rocket engine.
TE-M-763.
Manufacturer's designation of Star 13B Solid rocket engine.
TE-M-775-1.
Manufacturer's designation of Star 75 Solid rocket engine.
TE-M-783.
Manufacturer's designation of Star 37FM Solid rocket engine.
TE-M-790-1.
Manufacturer's designation of Star 6B Solid rocket engine.
TE-M-799.
Manufacturer's designation of Star 48B Solid rocket engine.
TE-M-799-1.
Manufacturer's designation of Star 48A s Solid rocket engine.
TE-M-863-1.
Manufacturer's designation of Star 5A Solid rocket engine.
TE-M-940-1.
Manufacturer's designation of Star 48V Solid rocket engine.
TE-M-963.
Manufacturer's designation of Star 63F Solid rocket engine.
American manufacturer. Temco, USA.
Italian communications technology satellite. One launch, 1993.08.31. Temisat's primary mission was demonstration of a data relay system.
Russian intercontinental ballistic missile. World's first operational mobile ICBM. Deployed in greaty secrecy in 1976-1987 contrary to the terms of the SALT-2 Treaty.
Solid propellant rocket stage. Loaded mass 26,600 kg.
Solid rocket stage. 245.00 kN (55,078 lbf) thrust. Mass 8,700 kg (19,180 lb).
Geosynchronous communications satellite network
Temp-S.
Launch System of 9K76 intermediate range ballistic missile.
The Temp-S was the first solid propellant tactical guided missile deployed in the USSR. It was designed by A D Nadiradze at NII-1 and formed the basis of subsequent designs leading to current modern Russian ICBM's.
The Temp-S was the first solid propellant tactical guided missile deployed in the USSR. It was designed by A D Nadiradze at NII-1 and formed the basis of subsequent designs leading to current modern Russian ICBM's.
Russian intercontinental ballistic missile. The Temp-S.2M was the first strategic rocket designed by A D Nadiradze at NII-1. The design was abandoned when weight growth made it too heavy for the planned mobile transport.
American military target satellite. 2 launches, 1965.08.13 (Tempsat 1) and 1969.09.30 (Tempsat 2). Surveillance Calibration; black 14 inch diameter. sphere.
Temp-SM.
Launch System of 9K76B intermediate range ballistic missile.
Tennessee.
Tepper, Morris (1916-) American meteorologist, served in key earth observation posts at NASA 1959-1979.
Tereshkova, Valentina Vladimirovna (1937-) Russian cosmonaut. First woman in space, aboard Vostok 6. But the flight was propaganda and future spaceflight opportunities did not develop. Was married to cosmonaut Andrian Nikolayev. Later a leading Communist politician.
Terilen.
Code name for Yantar-4KS1 military surveillance satellite.
American earth land resources satellite. One launch, 1999.12.18. NASA's Terra satellite (originally known as Earth Observing System EOS AM-1) was the first spacecraft in the EOS program.
Russian military anti-satellite system. Study 1984. OKB Vympel was the systems integrator for ground-based laser systems.
American test vehicle. Terrapin sounding rockets were two-stage vehicles launched from Wallops Island. The Terrapin sounding rocket was developed by Republic Aviation under a National Security Agency contract for a University of Maryland project that allowed graduate students to study the upper atmosphere. The two-stage rocket used a Deacon motor with a slow-burn grain for the lower stage, and a TSI upper stage. The upper stage was equipped with low-drag swept stabilising fins.
German civilian surveillance radar satellite. First launch 2007.06.15. Scientific / commercial surveillance satellite, equipped with an X-band synthetic aperture radar with 1 meter resolution
Standard US Navy surface-to-air missile developed during the 1950's. Modified single stage Navy Terrier missiles were used as sounding rockets, sometimes supplemented with upper stages.
Standard US Navy solid propellant two-stage extended-range surface-to-air missile. Developed in the 1950's, in service until replaced by the Standard ER in the 1980's. Modified Terrier missiles were used as sounding rockets, sometimes supplemented with upper stages.
Solid propellant rocket stage. Loaded/empty mass 800/322 kg. Thrust 257.50 kN. The Terrier MK 12 Mod 1 rocket motor was typically equipped with four 0.22 square meter fin panels arranged in a cruciform configuration.
Terrier 3.
Alternate designation for RIM-2C surface-to-air missile.
Terrier 3A.
Alternate designation for RIM-2D surface-to-air missile.
American sounding rocket.
Solid propellant rocket stage. Loaded mass 100 kg. Thrust 7.00 kN.
American sounding rocket. Two stage vehicle consisting of 1 x Terrier + 1 x Asp
American sounding rocket. Two stage vehicle consisting of 1 x Terrier + 1 x Asp IV
American sounding rocket. Three stage vehicle consisting of 1 x Terrier + 1 x ASROC + 1 x Cajun
Solid rocket stage. Mass 400 kg (882 lb).
Terrier BT-3.
Popular Name of RIM-2C surface-to-air missile.
Terrier BT-3A.
Popular Name of RIM-2D surface-to-air missile.
Terrier BW-0.
Popular Name of RIM-2A surface-to-air missile.
Terrier BW-1.
Popular Name of RIM-2B surface-to-air missile.
Terrier HT-3.
Popular Name of RIM-2F surface-to-air missile.
American sounding rocket.
American anti-ballistic missile. Three stage vehicle consisting of 1 x Terrier Mk 70 + 1 x Mk 30 + 1 x ASAS
American sounding rocket. Two stage vehicle consisting of 1 x Terrier + 1 x Lynx
Solid propellant rocket stage. Loaded mass 300 kg.
American sounding rocket. The Terrier-Malemute launch vehicle was a high performance two-stage vehicle used for payloads weighing less than 180 kg, generally used for relatively lightweight plasma physics payloads. Payload 90 kg to 650 km or 180 kg to 420 km.
Solid rocket stage. 55.10 kN (12,387 lbf) thrust. Mass 600 kg (1,323 lb).
Solid propellant rocket stage. Loaded/empty mass 1,038/290 kg. Thrust kN. The basic Terrier mk70 motor was 3.94 m long with a principal diameter of 46 cm. There was a 7.6-cm interstage adapter which allowed for drag separation at Terrier burnout. Typically, the Terrier booster would utilize two spin motors to reduce dispersion and also serve as drag plates. Each Terrier fin was 0.43 square meters in area. Normally, the fins were canted to provide two revolutions per second spin rate at Terrier burnout.
Naval Prop Plant solid rocket engine. 257.5 kN. The Terrier MK 12 Mod 1 rocket motor was typically equipped with four 0.22 square meter fin panels arranged in a cruciform configuration.
Hercules solid rocket engine. 257.5 kN.
American sounding rocket.
American sounding rocket. SPACEHAB's Astrotech Space Operations developed the Oriole sounding rocket in the late 1990s to provide launch services for commercial and scientific payloads. Oriole was both the first privately developed sounding rocket in the United States and the first new U.S. sounding rocket in 25 years.
American sounding rocket.
Solid rocket stage.
American two-stage, spin-stabilized sounding rocket. It used a Terrier Mk 12 Mod 1 engine for its first stage and an improved Orion motor for its second stage. The Terrier-Orion could loft payloads weighing up to 290 kilograms to altitudes up to 190 kilometers.
Two stage vehicle consisting of 1 x Terrier + 1 x Improved Orion
American sounding rocket.
American sounding rocket. Two stage vehicle consisting of 1 x Terrier + 1 x Sandhawk
American surface-to-air missile. Modified single stage Navy Terrier missiles with cameras were used as sounding rockets. They were launched to an altitude of 140 km from Wallops Island, providing a 1,600 km composite photograph of a frontal cloud formation.
American sounding rocket. Two stage vehicle consisting of 1 x Terrier + 1 x Tomahawk
American sounding rocket. Two stage vehicle consisting of 1 x Terrier + 1 x NOTS 551
Solid rocket stage. Mass 400 kg (882 lb).
American earth ionosphere satellite. One launch, 1999.05.18.
TES.
Thermal Emission Spectrometer (on Mars Observer)
TES.
Indian military surveillance satellite. One launch, 2001.10.22. TES was an imaging satellite equipped with cameras and instruments to test military reconnaissance satellite technology.
Tessmann, Bernhard (1912-1998) Austrian-German engineer, leading engine test at Peenemuende from 1936. In 1943 evacuated to Koelpinsee; designed V-2 mobile launcher and planned Zement facility at Ebensee. In US from 1945, worked as von Braun's Deputy Director for Testing.
Test and Training Satellite.
Alternate designation for TTS tracking network technology satellite.
Category of persons.
Category of persons.
Category of persons.
Category of persons.
Category of persons.
Test Pilot (Scaled Composites).
Pilots for SpaceShipOne, the first private manned spacecraft (with two additional seats for passengers)
Category of persons.
Category of persons.
Category of missiles.
Tether Physics and Survivability.
Alternate designation for TiPS tether technology satellite.
Category of spacecraft.
Tethered Satellite System.
Alternate designation for TSS tether technology satellite.
American agency. Tethers, USA.
TETR.
American tracking network technology satellite. 2 launches, 1969.08.27 (TETR C) and 1971.09.29 (TETR 3). Test satellite for NASA's Manned Space Flight Network.
TETS.
Thursday Evening Tanking Society
TEX.
Code name for Stacksat P87-2 technology satellite.
American manufacturer of rocket engines. Texas Instruments, USA.
TFX.
American pressure suit, tested 1965. Prototype bladder type partial pressure suit with a separate Anti-G suit valve. APL program with Navy and ILC Dover.
TG-1.
TGKS.
Topographic / Geodetic Space System (Russian abbreviation)
TGR.
Russian military surveillance satellite. Study 1963. Two new directions were pursued in the Soviet Union for space optical reconnaissance systems in the mid-1960's: automated systems with television transmission of pictures, and manned systems.
TGU.
Third Chief Directorate (Russian abbreviation)
American manufacturer of spacecraft. TGV Rockets, USA.
American anti-ballistic missile. Theatre High-Altitude Air Defence. SDIO/BMDO project. Single stage vehicle.
Lockheed solid rocket engine.
Solid propellant rocket stage. Loaded mass 600 kg.
Thagard, Dr Norman Earl 'Norm' (1943-) American physician mission specialist astronaut. Flew on STS-7, STS-51-B, STS-30, STS-42, Mir EO-18. First American to fly aboard a Russian spacecraft. Grew up in Jacksonville, Florida.
Thai commercial communications satellite network operated by the Shinawatra Satellite Public Company.
Thailand
Thalau German expert in guided missiles during World War II. As of January 1947, last known to be working at Kassel.
Thales Alenia Space.
Third Owner of Alenia
American manufacturer of spacecraft. Thangavelu, USA.
Poem: Rockets shake the earth, the needle rises...
American manufacturer. The Boeing Co. , USA
Poem: the Great Ocean, two shores, two realms...
The Foundations of the Space Age.
The life and work of Tsiolkovskiy, by Vladimir V. Lytkin, Tsiolkovskiy Museum, Kaluga.
British manned spacecraft. Study 2004. X-Prize suborbital ballistic spacecraft concept of Flight Exploration of London, England.
One third of manned spaceflights suffer major problems that threaten completion of the mission and the life of the astronauts. Five crews - 2% of missions - have perished in their spacecraft....SPACEFLIGHT IS NOT 'ROUTINE'.
Poem: Give the museum your hourglass...
James Oberg's classic account of the greatest disaster in space history.
What was the secret configuration of the L1 spacecraft?
How the Soviet Union fooled the world into believing it wasn't in the moon race.
A curious marriage of pre-war German filmmaking and 1950's low-rent kiddie show syndicated quickies…
American manned spaceplane. Study 2004. X-Prize suborbital flying saucer concept of Discraft Corporation of Portland, Oregon.
American manned spacecraft. Study 2004. X-Prize suborbital ballistic spacecraft concept of American Astronautics Corporation, Oceanside, California.
Poem: Gully Foyle is my name...
Poem: On a sun-singed steppe, Sergei stood, said -...
The Woman from the Krasny Perekop Textile Mill.
Poem: traditionalists always fear women who fly...
The Wrong Stuff - A Catalogue of Launch Vehicle Failures.
The hard road to space...
It's got to get worse before it can get better...
It got better...
Space rebounds!
American earth magnetosphere satellite. 5 launched, 2007.02.17.
French winged orbital launch vehicle. Themis was a planned ESA booster stage demonstrator, to validate integrated propellant tank technology necessary for a reusable Ariane 5 successor. The demonstrator engine would be derived from the Vulcain of the Ariane 5. Estimated cost was up to 2.5 billion dollars. THEMIS would carry 33 tonnes of propellant, enough to reach Mach 11. Expendable boosters might permit orbital flight.
ATEF solid rocket engine.
German manufacturer of rocket engines. Thiel, Germany.
Thiel, Adolf Karl (1915-2001) German-American engineer in WW2, member of the Rocket Team in the United States thereafter. German expert in guided missiles during WW2. As of January 1947, working at Fort Bliss, Texas. Died at Palos Verdes Estates, California.
Thiel, Walter (-1943) German engineer, talented designer at Peenemuende, in charge of development of the engine for the V-2. Killed in the air raid in August 1943, a setback to the project.
Thiele, Gerhard Julius Paul (1953-) German physicist mission specialist astronaut. Flew on STS-99. DARA.
American manufacturer of rocket engines and rockets. Thiokol Corporation, Ogden, UT, USA.
Thiokol solid rocket engine. 14,746.1 kN. Developed to 1966. Isp=263s.
Solid propellant rocket stage. Loaded/empty mass 385,554/68,038 kg. Thrust 14,746.42 kN. Vacuum specific impulse 263 seconds.
Thiokol Chemical Copr (1929).
First Owner of Thiokol
Thiokol Corporation (1989).
Third Owner of Thiokol
Third Generation Soviet Space Systems.
Third Generation Soviet Space Systems
Chinese manufacturer. Third Research Academy, China.
Thirsk, Dr Robert Brent (1953-) Canadian physician mission specialist astronaut. Flew on STS-78,ISS EO-20.
Find out what happened on this day in space history...
Thomas, Dr Donald Alan 'Don' (1955-) American materials scientist mission specialist astronaut. Flew on STS-65, STS-70, STS-83, STS-94.
Thomas, Dr Andrew Sydney Withiel (1951-) Australian-American engineer mission specialist astronaut. Flew on STS-77, Mir NASA-6, STS-102, STS-114.
Thompson, Milton Orville 'Milt' (1926-1993) American test pilot astronaut, 1962-1963. Flew lifting bodies, X-15, assigned as X-20 spaceplane astronaut.
Thompson, William David (1956-) American engineer military spaceflight engineer astronaut, 1982-1985. Retired from the USAF in 1987. Later President Spectrum Technology, Los Angeles.
Thompson, Floyd L (1898-1976) American engineer, at NASA 1927-1968, chief of flight research and then headed Langley.
Thompson, James R 'JR' American engineer, at NASA 1963-1991, deputy administrator 1989-1991; headed development test of the J-2 and SSME engines at NASA.
Thor.
American liquid propellant intermediate range ballistic missile, developed by Douglas in 1956-1958. 60 deployed to Britain in 1958-1962. The basis for a family of Thor and Delta space launch vehicles, remaining in production into the 2010's.
American orbital launch vehicle. Thor with Able stage derived from Vanguard second stage.
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 1/AJ10-41 + 1 x Altair
American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 2/AJ10-42
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 2/AJ10-42 + 1 x Altair
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 3/AJ10 + 1 x Altair
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x AJ10 + 1 x Altair
American orbital launch vehicle. As Thor Able but with enlarged Ablestar second stage with 2 1/2 x greater burn time.
American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DSV-2A + 1 x Able-Star/AJ10-104D
American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Agena A
American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-21 + 1 x Agena B
Two stage vehicle consisting of 1 x Thor DSV-2A + 1 x Agena B
Thor Agena B upgraded with addition of three Castor 1 strap-on motors.
American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-21 + 1 x Agena D
Two stage vehicle consisting of 1 x Thor DSV-2A + 1 x Agena D
Thor Agena upgraded with addition of three Castor 1 strap-on motors.
American orbital launch vehicle. Thor DM-18A with 'Burner' upper stage solid rocket packages used for launch of classified payloads.
American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x FW4S
American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Star 37B
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Star 37B + 1 x Star 26B
The Thor communication satellites are orbited by Telenor of Norway and provide television services to Scandinavia. Thor 1 satellite was originally orbited by British Satellite Broadcasting as Marcopolo 2. It was purchased on orbit in 1992 from BSB.
American orbital launch vehicle. Commercial name for the military's Thor-Delta. The name of the Delta second stage eventually was applied to subsequent commercial follow-ons.
Thor Delta A.
Alternate designation for Delta A orbital launch vehicle.
Thor Delta B.
Alternate designation for Delta B orbital launch vehicle.
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DSV-2A + 1 x Delta D + 1 x Altair 2
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DSV-2A + 1 x Delta D + 1 x FW4D
Thor Delta D.
Alternate designation for Delta D orbital launch vehicle.
Thor Delta G.
Alternate designation for Delta G orbital launch vehicle.
Thor Delta J.
Alternate designation for Delta J orbital launch vehicle.
Thor Delta L.
Alternate designation for Delta L orbital launch vehicle.
American orbital launch vehicle. Single stage vehicle adapted from Thor IRBM with no upper stage.
American orbital launch vehicle. Single stage vehicle
American orbital launch vehicle. Single stage vehicle
Lox/Kerosene propellant rocket stage. Loaded/empty mass 49,340/3,125 kg. Thrust 758.71 kN. Vacuum specific impulse 282 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 48,354/2,948 kg. Thrust 760.64 kN. Vacuum specific impulse 285 seconds.
American orbital launch vehicle. Single stage vehicle.
American orbital launch vehicle. Single stage vehicle.
American orbital launch vehicle. Single stage vehicle.
American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x AJ10-118
American anti-ballistic missile. Single stage vehicle.
American orbital launch vehicle. Single stage vehicle.
American orbital launch vehicle. Thor with Hydra liquid oxygen/hydrogen pressure-fed upper stage. Never went beyond initial hardware testing. However such a stage would have vastly increased Thor-Ablestar performance, from 150 kg to over 1000 kg in a medium polar orbit.
American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x MG-18
Thor Agena upgraded with Long Tank Thor stage. Variant with straight tank from Delta was Thorad (Long Tank Augmented Thrust Thor Delta)
Thor Agena upgraded with Extended Length Tank Thor stage. 3 stage vehicle.
Thor-Delta.
Alternate designation for Thor Delta orbital launch vehicle.
Thorne, Steven Douglas (1953-1986) German test pilot mission specialist astronaut, 1985-1986. Died in an airplane crash.
Thornton, Dr Kathryn Ryan Cordell 'Kathy' (1952-) American physicist mission specialist astronaut. Flew on STS-33, STS-49, STS-61, STS-73.
Thornton, Dr William Edgar 'Bill' (1929-) American physician mission specialist astronaut. Flew on STS-8, STS-51-B.
Three-Corner Sat.
Alternate designation for 3CSat technology satellite.
Three-Magnum Mars Mission.
Alternate designation for Combo Lander Mission manned mars expedition.
Thrust Augmented Thor.
Thrust Augmented Thor.
Alternate designation for Delta Thor TA rocket stage.
Air Force base used for a series of geomagnetic pole sounding rocket launches from 1970 to 1976. Also known to have been used for 988 launches from 1964 to 1980, reaching up to 122 kilometers altitude.
Loki launch complex. Thule/Camp Tuto (Geopole Station)
Sounding rocket launch location known to have been used for 1385 launches from 1963 to 2004, reaching up to 400 kilometers altitude.
Sounding rocket launcher
Sounding rocket launcher
Sounding rocket launcher
Sounding rocket launcher
RH launch complex.
Thunderbird.
Alternate designation for Starchaser 5 manned spacecraft.
Thuot, Pierre Joseph (1945-) American test pilot mission specialist astronaut. Flew on STS-36, STS-49, STS-62.
Thuraya was founded in the UAE in 1997 by a consortium of leading national telecommunications operators and international investment houses. The concept was to offer cost-effective satellite-based mobile telephone services to Europe, the Middle East, North and Central Africa, and Central and South Asia. The new aspect was the use of dynamic dual mode handsets.
Emiratan agency. Thuraya Satellite, UAE.
Chinese manned spaceplane. Study 1988. The Tian Jiao 1 (Pre-eminent in Space 1) manned spaceplane was proposed by the First Academy (now the China Academy of Launch Technology) in 1988.
Chinese manned spaceplane. Study 2006. What appeared to be an evolved version of 1988's Tian Jiao 1 manned spaceplane concept was proposed by the China Academy of Launch Technology in 2006. A 2020 operational date was mentioned.
Chinese man-tended space laboratory. Operational, first launch planned September 2011. A series of three of these laboratories will be visited by a series of Shenzhou manned spacecraft between 2011 and 2018. The 8.5-ton design will then be extended to a 13-ton cargo carrier for resupply of the Chinese multi-module space station after 2020.
French test vehicle. Tibere was an atmospheric re-entry test vehicle derived from the earlier Berenice. Development was authorized in 1965 to support the Electre re-entry experiment program. The first two stages were Stromboli motors of identical length. The third stage was the P.064 motor developed for the Diamant orbital launcher.
Solid rocket stage.
Solid rocket stage. 170.00 kN (38,218 lbf) thrust. Mass 1,700 kg (3,748 lb).
Tier 1.
Alternate designation for SpaceShipOne manned spaceplane.
Tier 1b.
Alternate designation for SpaceShipTwo manned spaceplane.
Tier 2.
Alternate designation for Tier Two manned spacecraft.
American winged rocketplane. Burt Rutan's Tier One was the second manned reusable suborbital launch system (after the B-52/X-15). But it was developed privately at a small fraction of the cost.
American manned spacecraft. Study 2005. After the successful win of the X-Prize for the first suborbital flight by Burt Rutan's Tier One / SpaceShipOne, the designer hinted a follow-on orbital spacecraft was being designed.
Russian manufacturer of rockets. Tikhomirov Design Bureau, Zhukovsky, Russia.
Tikhonov, Nikolai Vladimirovich Russian engineer cosmonaut, 2006-on. Graduated MAI, 2005.
Tikhonravov, Mikhail Klavdiyevich (1900-1974) Pioneering Soviet engineer and space visionary. Designer at Nll-4 and Korolev design bureau. Leader in development of Sputnik and Vostok spacecraft. Also performed early ICBM work and was pioneering rocketeer at GIRD and Nll-3.
Tilford, Shelby G American NASA geophysicist, from the late 1980's Director of Earth Sciences in the Office of Space Science. In 1992 he was appointed acting Associate Administrator for Mission to Planet Earth and served until 1994.
Wing-recovered compressed powder rockets that set altitude records in Germany before being surpassed by liquid propellant designs.
Tiling, Reinhold (1893-1933) German rocket pioneer, developed wing-recovered powder rockets. Inspired by Oberth lecture in 1924. By 1931 demonstrated stable flight to 7 km, first rocket launch from airplane 1932. Killed 1933 in an explosion.
Military testing range, known to have been used for 7 launches from 1998 to 2006, reaching up to 150 kilometers altitude.
Tiller, Werner (1914-1974) German engineer in WW2, member of the Rocket Team in the United States thereafter.
American navigation technology satellite. 2 launches, 1967.05.31 (Timation 1) and 1969.09.30 (Timation 2).
American nuclear-powered orbital launch vehicle. DARPA project. Nuclear fission engine using pebble bed reactor with spherical fuel elements.
DARPA project. Nuclear fission engine using pebble bed reactor with spherical fuel elements.
Nuclear/LH2 propellant rocket stage. Loaded/empty mass 170,000/45,000 kg. Thrust 2,450.00 kN. Vacuum specific impulse 1000 seconds.
DoE nuclear/lh2 rocket engine. 2451.6 kN. Development ended 1992. Isp=1000s. Used on Timberwind launch vehicle.
DoE nuclear/lh2 rocket engine. 441.3 kN. Development ended 1992. Isp=1000s. Used on Timberwind Centaur launch vehicle.
Nuclear/LH2 propellant rocket stage. Loaded/empty mass 28,000/7,500 kg. Thrust 441.00 kN. Vacuum specific impulse 1000 seconds.
DoE nuclear/lh2 rocket engine. 735.5 kN. Development ended 1992. Isp=1000s. Used on Timberwind Titan launch vehicle.
Nuclear/LH2 propellant rocket stage. Loaded/empty mass 110,000/28,500 kg. Thrust 2,206.00 kN. Vacuum specific impulse 1000 seconds.
American nuclear-powered orbital launch vehicle.
American nuclear-powered orbital launch vehicle.
American solar satellite. One launch, 2001.12.07. TIMED was the first NASA Solar Terrestrial Probe, operated by Johns Hopkins Applied Physics Lab to study the thermosphere, mesosphere and lower ionosphere.
Timmons, Kenneth P (1919-1994) American engineer. Headed the Skylab Multiple Docking Adapter and External Tank projects.
Timofei.
Alternate designation for Kristall manned space station.
Tingle, Scott David (1965-) American test pilot astronaut, 2009-on.
Naval Prop Plant solid rocket engine. 220 kN.
TIP.
American navigation satellite. 6 launches, 1972.09.02 (Triad 1) to 1988.06.16 (Nova 2).
TiPS.
American tether technology satellite. 3 launches, 1996.05.12 (USA 123) to 1998.10.03 (USA 141). 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.
Kayser N2O4/MMH rocket engine. 1 N. Satellite orientation. Isp=303s. Tangential Injection and Rotational Combustion, the world's smallest thruster burning monomethylhydrazine and nitrogen tetroxide.
TIROS spacecraft were the beginning of a long series of polar-orbiting meteorological satellites. TIROS was followed by the TOS (TIROS Operational System) series, and then the ITOS (Improved TIROS) series, and later the NOAA series. TIROS spacecraft were developed by GSFC and managed by ESSA (Environmental Science Services Administration). The objective was to establish a global weather satellite system.
American earth weather satellite. 12 launches, 1960.04.01 (Tiros 1) to 1966.02.28 (ESSA 2). TIROS spacecraft were the beginning of a long series of polar-orbiting meteorological satellites.
American earth weather satellite. 6 launches, 1978.10.13 (Tiros N) to 2002.06.24 (NOAA 17). Tiros N was part of the ongoing US series of polar-orbiting weather satellites. These were preceded by the TIROS series and the ITOS (Improved TIROS) series.
TIROS Operational System.
Alternate designation for TOS earth weather satellite.
TIT.
Japanese manufacturer of spacecraft. Tokyo Insitute of Technology, Tokyo, Japan.
The Titan launch vehicle family was developed by the United States Air Force to meet its medium lift requirements in the 1960's. The designs finally put into production were derived from the Titan II ICBM. Titan outlived the competing NASA Saturn I launch vehicle and the Space Shuttle for military launches. It was finally replaced by the USAF's EELV boosters, the Atlas V and Delta IV. Although conceived as a low-cost, quick-reaction system, Titan was not successful as a commercial launch vehicle. Air Force requirements growth over the years drove its costs up - the Ariane using similar technology provided lower-cost access to space.
American orbital launch vehicle. The Titan launch vehicle family was developed by the United States Air Force to meet its medium lift requirements in the 1960's. The designs finally put into production were derived from the Titan II ICBM. Titan outlived the competing NASA Saturn I launch vehicle and the Space Shuttle for military launches. It was finally replaced by the USAF's EELV boosters, the Atlas V and Delta IV. Although conceived as a low-cost, quick-reaction system, Titan was not successful as a commercial launch vehicle. Air Force requirements growth over the years drove its costs up - the Ariane using similar technology provided lower-cost access to space.
American intercontinental ballistic missile. ICBM, built as back-up to Atlas, using two stages instead of one and a half, and conventional tank construction in lieu of balloon tanks. It was also to have been used for suborbital tests of the X-20A Dynasoar manned space plane. For unknown reasons never refurbished for use as space launcher and scrapped after being replaced by the Titan II in the missile role in mid-1960's.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 76,203/4,000 kg. Thrust 1,467.91 kN. Vacuum specific impulse 290 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 28,939/1,725 kg. Thrust 355.86 kN. Vacuum specific impulse 308 seconds.
American intercontinental ballistic missile. ICBM, developed also as the launch vehicle for the manned Gemini spacecraft in the early 1960's. When the ICBM's were retired in the 1980's they were refurbished and a new series of launches began.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 117,866/6,736 kg. Thrust 2,172.23 kN. Vacuum specific impulse 296 seconds.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 28,939/2,404 kg. Thrust 444.82 kN. Vacuum specific impulse 316 seconds.
American orbital launch vehicle. Basic Titan 3A core, originally developed for Titan 3C, with Agena D upper stage replacing Transtage. New radio guidance system, 1.5 m diameter fairing atop Agena. Payload remained attached to the Agena.
American orbital launch vehicle. Post-MOL standardisation of Titan 3C, with man-rated systems removed, upgraded first stage engines, digital avionics, blowdown solid rocket motor thrust vector control in place of pressure-regulated system, simplified Transtage attitude control system.
Titan 23D.
Manufacturer's designation for Titan 3D orbital launch vehicle.
Titan 23E.
Manufacturer's designation for Titan 3E orbital launch vehicle.
American orbital launch vehicle. Stretched first stage, originally developed for the cancelled MOL program, with Agena D upper stage. Radio guidance system, 1.5 m diameter fairing atop Agena. Payload remained attached to the Agena.
American intercontinental ballistic orbital launch vehicle. Space launch version of Titan 2 ICBM, obtained through minimal modification of ICBM (new wiring and avionics only, and use of existing ICBM re-entry vehicle shroud). Proposed in the late 1980's but never developed.
American intercontinental ballistic orbital launch vehicle. Space launch version, obtained through minimal refurbishment of decommissioned ICBM's.
American intercontinental ballistic orbital launch vehicle. Version of refurbished Titan 2 ICBM with two liquid propellant strap-on stages. Proposed in the late 1980's but never developed.
American intercontinental ballistic orbital launch vehicle. Version of refurbished Titan 2 ICBM with two to eight Castor 4A solid-propellant strap-on stages. Proposed in the late 1980's but never developed.
American orbital launch vehicle. Basic Titan 3A core, except guidance provided by the Agena upper stage. The Agena and its payload were completely enclosed in a new 3.05 m diameter shroud. 'Ascent Agena' seperated after orbital insertion and did not remain attached to the payload.
American orbital launch vehicle. Stretched Titan core, originally developed for Titan 3M MOL, with Agena D upper stage. Guidance provided by the Agena upper stage. The Agena and its payload were completely enclosed in a 3.05 m diameter shroud. 'Ascent Agena' seperated after orbital insertion and did not remain attached to the payload.
American orbital launch vehicle. Stretched Titan core designed for use with 5 1/2 segment solid rocket motors. IUS (Interim/Inertial Upper Stage) solid upper stages, Transtage, or used without upper stages.
American orbital launch vehicle. Version of Titan 34D with IUS upper stages.
American orbital launch vehicle. Version of Titan 34D with Transtage upper stage.
American orbital launch vehicle. Titan with Transtage third stage. Core for Titan 3C.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 116,573/5,443 kg. Thrust 2,339.76 kN. Vacuum specific impulse 302 seconds.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 29,188/2,653 kg. Thrust 453.71 kN. Vacuum specific impulse 316 seconds.
American orbital launch vehicle. Titan core with Agena upper stage. Found to be more cost effective and higher performance than using Transtage.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 139,935/7,000 kg. Thrust 2,413.19 kN. Vacuum specific impulse 302 seconds.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 37,560/2,900 kg. Thrust 460.31 kN. Vacuum specific impulse 316 seconds.
American orbital launch vehicle. Configuration of Titan 3B proposed by Martin in mid-1960's. Titan 3B for deep space missions with Centaur upper stage, Algol strapons for liftoff thrust augmentation. Never flown.
American orbital launch vehicle. Titan 3A with five segment solid motors. Man-rated design originally developed for Dynasoar spaceplane.
American orbital launch vehicle. Variant of Titan 3C with seven segment solid motors. Proposed by Martin for precise delivery of payloads beyond Titan 3C capacity into geosynch orbit. Never flown.
American orbital launch vehicle. Titan 3C without transtage.
American orbital launch vehicle. Titan 3D with Centaur D-1T upper stage. Used by NASA for deep space missions in 1970's.
American orbital launch vehicle. Variant of Titan with 15 foot Large Diameter Core, 2 x 7 segment strap-ons. Man-rated, optimized for delivery of heavy payloads into LEO. Never developed.
American orbital launch vehicle. Variant of Titan with 15 foot Large Diameter Core, 4 x 7 segment strap-ons. Man rated, optimized for delivery of 40,000 pound manned payloads into 250 nm / 50 deg space station orbit.
American orbital launch vehicle. Man-rated launch vehicle designed for MOL and other missions of the 1970's. Malfunction Detection System initiated abort procedures during launch. Also suited for launch of 'bulbous and lifting body payloads'. 7 segment UA1207 motors developed but not used until Titan 4 in 1990's. Cancelled with MOL program in 1969.
American orbital launch vehicle. Developed to handle military payloads designed for launch on Shuttle from Vandenberg before the USAF pulled out of the Shuttle program after the Challenger disaster. Further stretch of core from Titan 34, 7-segment solid rocket motors (developed for MOL but not used until 25 years later). Enlarged Centaur G used as upper stage (variant of stage designed for Shuttle but prohibited for flight safety reasons after Challenger). Completely revised electronics. All the changes resulted in major increase in cost of launch vehicle and launch operations.
American orbital launch vehicle. Version of Titan 4 with IUS upper stages.
American orbital launch vehicle. Version of Titan 4B with IUS upper stage.
American orbital launch vehicle. Version of Titan 4 with no upper stage, configured for launch of lower-mass, higher-orbit Lacrosse, SDS and NOSS-2 payloads from Vandenberg.
American orbital launch vehicle. Version of Titan 4B with no upper stage, configured for launch from Vandenberg.
American orbital launch vehicle. Version of Titan 4 with no upper stage, configured for launch of heavy-weight, low altitude KH-12 and Improved CRYSTAL payloads from Vandenberg.
American orbital launch vehicle. Version of Titan 4B with no upper stage, configured for launch from Vandenberg.
American orbital launch vehicle. Version of Titan 4 with no upper stage, configured for launch of lower-mass, higher-orbit SDS and NOSS-2 payloads from Cape Canaveral.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 163,000/8,000 kg. Thrust 2,428.31 kN. Vacuum specific impulse 302 seconds.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 39,500/4,500 kg. Thrust 459.51 kN. Vacuum specific impulse 316 seconds.
Titan 45D.
Manufacturer's designation for Titan 402A-IUS and Titan 402B-IUS orbital launch vehicles.
Titan 45F.
Manufacturer's designation for Titan 403A and Titan 403B orbital launch vehicles.
Titan 45H.
Manufacturer's designation for Titan 405A orbital launch vehicle.
Titan 45J.
Manufacturer's designation for Titan 404A and Titan 404B orbital launch vehicles.
American orbital launch vehicle. Titan 4 with Upgraded Solid Rocket Motors replacing UA1207. Developed to improve performance for certain missions, and reduce number of field joints in motor after Challenger and Titan 34D explosions involving segmented motors.
American orbital launch vehicle. Proposed Titan upgrade with cryogenic core as replacement for NLS.
Lox/LH2 propellant rocket stage. Loaded/empty mass 500,000/45,000 kg. Thrust 4,457.10 kN. Vacuum specific impulse 425 seconds. Part of launch vehicle proposed by Martin as alternative to NLS. All figures estimated based on 1,000,000 lb thrust single engine.
American orbital launch vehicle. The Titan C, a Titan II booster stage topped by a new liquid oxygen/hydrogen upper stage, was the launch vehicle selected in November 1959 for the DynaSoar orbital flight program. Despite the fact the upper stage engine was secretly tested in 1958-1960, after many political twists and turns, it was cancelled in favor of the Titan 3C in July 1961
Lox/LH2 propellant rocket stage. Loaded/empty mass 57,400/6,000 kg. Thrust 666.00 kN. Vacuum specific impulse 403 seconds. Engine developed 1958-1960, but launch vehicle cancelled 1961.
Version of Titan 4 with Centaur T upper stage.
Version of Titan 4B with Centaur T upper stage.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 150,000/10,000 kg. Thrust 2,940.00 kN. Vacuum specific impulse 130 seconds. Masses estimated (cluster of four Titan I first stages)
Titan I.
Alternate designation for Titan 1 intercontinental ballistic missile.
Titan II.
Alternate designation for Titan 2 intercontinental ballistic missile.
American intercontinental ballistic orbital launch vehicle. Version for launch of Gemini manned spacecraft. Developed in parallel with ICBM version. Differed in having redundancy features in systems and MDS (Malfunction Detection System) installed.
Titan II SLV.
Alternate designation for Titan 2G intercontinental ballistic orbital launch vehicle.
Titan IIIA.
Alternate designation for Titan 3A orbital launch vehicle.
Titan IIIB.
Alternate designation for Titan 3B orbital launch vehicle.
Titan IIIC.
Alternate designation for Titan 3C orbital launch vehicle.
Titan IIID.
Alternate designation for Titan 3D orbital launch vehicle.
Titan IIIE.
Alternate designation for Titan 3E orbital launch vehicle.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 350,000/20,000 kg. Thrust 4,344.46 kN. Vacuum specific impulse 296 seconds. 15 foot diameter core Titan proposed in 1960's for space station logistics. Masses estimated.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 50,000/3,000 kg. Thrust 444.82 kN. Vacuum specific impulse 316 seconds. 15 foot diameter core Titan proposed in 1960's for space station logistics. Masses estimated.
Titan Retro.
Government designation of Star 5C-CB Solid rocket engine.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 12,247/1,950 kg. Thrust 71.17 kN. Vacuum specific impulse 311 seconds.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 15,000/2,200 kg. Thrust 71.17 kN. Vacuum specific impulse 311 seconds. 20% stretch of Transtage to handle geosynch insertion of larger payloads launched by Titan 3C7. Masses estimated.
Solid propellant rocket stage. Loaded/empty mass 226,233/33,798 kg. Thrust 5,849.41 kN. Vacuum specific impulse 263 seconds.
Solid propellant rocket stage. Loaded/empty mass 251,427/40,827 kg. Thrust 6,227.00 kN. Vacuum specific impulse 265 seconds.
Solid propellant rocket stage. Loaded/empty mass 319,330/51,230 kg. Thrust 7,117.00 kN. Vacuum specific impulse 272 seconds.
Solid propellant rocket stage. Loaded/empty mass 357,239/52,040 kg. Thrust 7,560.68 kN. Vacuum specific impulse 286 seconds.
American orbital launch vehicle. The Martin Company proposed to the Department of Defense that the first stage of the Titan I intercontinental ballistic missile be combined with the Vanguard rocket to provide a launch vehicle capable of placing an instrument package into lunar orbit and on the lunar surface. NASA was instead given the mission and used Atlas/Agena and Atlas/Centaur for this purpose instead.
Tito.
Tito, Dennis Anthony (1940-) American engineer cosmonaut. Flew on ISS EP-1. First space tourist. First American to return to earth in a Russian spacecraft.
Titov, Gherman Stepanovich (1935-2000) Russian pilot cosmonaut. Flew on Vostok 2. Second person in orbit. Youngest person in space. Left cosmonaut team for brilliant career in the space forces after deciding his future spaceflight prospects were nil.
Titov, Vladimir Georgiyevich (1947-) Russian test pilot cosmonaut. Flew on Soyuz T-8, Soyuz T-10-1, Mir EO-3, STS-63, STS-86. Survived first pad abort during a manned launch. 387 cumulative days in space. SU Air Force. Call sign: Okean (Ocean).
Titschak German expert in guided missiles during World War II. As of January 1947, living at Eberstadt, Hitlerstr. 164.
Tittle, Theresa Mary Stevens (1960-) American engineer military spaceflight engineer astronaut, 1985-1988. Graduated in operations research from the USAF Academy, 1982. US Air Force operations specialist, stationed in the Pentagon. Later a Shuttle Flight Controller at the JSC.
French sounding rocket. Sounding rocket derived from the first two stages of the Berenice test vehicle. The two stage vehicle consisted of 4 x SEPR P167 stabilisation rockets around a Stromboli 739 first stage, topped by a stretched Stromboli SEPR 740-3 second stage with four fins. The launches were made from Chaco in collaboration with the Argentinian agency CNIE.
Solid rocket stage. 170.00 kN (38,218 lbf) thrust. Mass 1,100 kg (2,425 lb).
TKA.
Transport-Supply Ship (Russian abbreviation)
Tkachev, Fedor Dmitriyevich Russian engineer. Chief Designer of NIEI PDS. Specialised in parachutes. Fired 1968 after Soyuz 1 parachute failure and death of Cosmonaut Komarov.
TKM-O.
Manufacturer's designation for Spektr manned space station.
TKS.
Family of spacecraft.
TKS.
Russian manned spacecraft. 4 launches, 1977.07.17 (Cosmos 929) to 1985.09.27 (Cosmos 1686).
Russian manned spacecraft module. 4 launches, 1977.07.17 (Cosmos 929) to 1985.09.27 (Cosmos 1686). The BSO was equipped with the retro-rocket for deorbit of the VA capsule following separation from the space station. Deorbit Block.
Russian manned spacecraft module. 4 launches, 1977.07.17 (Cosmos 929) to 1985.09.27 (Cosmos 1686). Orbital Living and Service Module.
Russian manned space station. Study 1961. The TKS (Heavy Space Station, also known as TOSZ - Heavy Orbital Station of the Earth) was Korolev's first 1961 project for a large N1-launched military space station.
Russian manned spacecraft module. 4 launches, 1977.07.17 (Cosmos 929) to 1985.09.27 (Cosmos 1686). Emergency escape system.
Russian manned spacecraft module. 13 launches, 1976.12.15 (Cosmos 881) to 1985.09.27 (Cosmos 1686). The VA reentry capsule was similar in configuration to the American Apollo, but 30% smaller. Reusable re-entry capsule.
Planned manned single-orbit flight aboard the TKS space capsule during a series of two-TKS-launched-by-one-Proton flight tests. Flown unmanned due to inability to demonstrate two consecutive failure-free launches.
Crew: Berezovoi, Glazkov, Makrushin. Planned first test manned flight of the TKS large ferry craft. Would have docked with the Almaz OPS 4 military space station. Flight cancelled with the rest of the Almaz program in 1981. Flown later unmanned to Salyut 6 as Cosmos 1267. Backup crew: Kozelsky, Artyukhin, Romanov.
Crew: Kozelsky, Artyukhin, Romanov. Second TKS flight that would have docked with the cancelled Almaz OPS 4 military space station. The spacecraft was instead flown unmanned to Salyut 7 as Cosmos 1443. Backup crew: Sarafanov, Preobrazhensky, Yuyukov.
Crew: Sarafanov, Preobrazhensky, Yuyukov. Third TKS flight that would have docked with the cancelled Almaz OPS 4 military space station. The spacecraft was instead flown unmanned to Salyut 7 as Cosmos 1686. Backup crew: Vasyutin, Rozhdestvensky, Grechanik.
TLA.
Three Letter Acronym
TLI.
Translunar injection (insertion into trajectory from low earth orbit towards the moon)
American pressure suit, tested 1982. Tactical Life Support System. Developed by the USAF and Boeing/Gentex to provide get-me-down protection from 18 km.
TM.
Telemetry; or Technical memorandum
TsNIIMASH electric/xenon rocket engine. 250 mN. Development. Isp=3000s. Hall effect thruster with anode layer, designed for satellite orbital raising. Taken to engineering model stage.
TM-61A.
Alternate Designation of Matador intermediate range cruise missile.
TM-61B.
TM-76A.
Alternate designation for CGM-13A intermediate range cruise missile.
TM-76B.
Alternate Designation of CGM-13B intermediate range cruise missile.
TME.
Manufacturer's designation for Teknologia materials science satellite.
Trimethylolethane trinitrate
TMI.
Canadian agency. TMI, Canada.
TMK.
Heavy Interplanetary Spacecraft (Russian abbreviation)
Russian manned Mars flyby. Study 1959. In 1959 a group of enthusiasts in OKB-1 Section 3 under the management of G U Maksimov started engineering design of this first fantastic project for manned interplanetary travel.
TMKB.
Turayevo Machine-Building Design Bureau (Russian abbreviation)
TMKB Soyuz.
Third Owner of Stepanov
Russian manned Mars expedition. Study 1960. Feoktistov felt that the TMK-1 manned Mars flyby design was too limited. His design group proposed in 1960 a complete Mars landing expedition, to be assembled in earth orbit using two or more N1 launches.
TMP.
Manufacturer's designation for Skif-DM sattelite.
TMP.
Russian materials science satellite. Study 1992. The enormous 88 metric ton Engineering Production Module (TMP) was proposed by the Salyut Design Bureau in the early 1990's.
Uosat Microbus-class payload built by Surrey Satellite for the Thai Microsatellite Company of Bangkok. Conducted a dual Earth observation and data communications mission.
TMZ.
Tushino Machine Building Plant (Russian abbreviation)
TN.
Technical note
TN-81.
Standard warhead of ASMP cruise missile.
TNT.
Trinitrotoluene, high explosive.
Tochka.
Tactical short-range ballistic missile, deployed from 1976.
Russian intermediate range ballistic missile. Tactical short-range ballistic missile, deployed from 1976.
Tochka-U.
Launch System of 9K79-1 intermediate range ballistic missile.
Todt.
Todt, Fritz (1891-1942) German Manager. National Socialist politician, Major general, Defence Minister and Director/Manager of organization Todt.
Toebe, Konrad (1913-) German engineer in WW2, member of the Rocket Team in the Soviet Union thereafter. Engineer, German airplane and rocket technician; worked in the Soviet Union.
Toftoy, Holger N (1902-1967) American Army officer, expert in ordnance, responsible for transferring von Braun's rocket technology to the US in 1945. Commanded Huntsville 1954-1956. Held other rockt development posts until retirement in 1960.
Tognini, Michel Ange-Charles (1949-) French test pilot mission specialist astronaut. Flew on Mir Antares, STS-93. Trained for missions under both US and Russian programs.
Tokarev, Valeri Ivanovich (1952-) Russian test pilot cosmonaut. Flew on STS-96, ISS EO-12. Russian Air Force test pilot, flying 44 types of aircraft and helicopters. Selected as Buran test pilot in 1987. From 1994, commander cosmonaut group for aerospace systems.
Japanese agency. University of Tokyo, Tokyo, Japan.
Tokyo Broadcasting.
Tolboyev, Maghomed Omarovich (1951-) Avar (Dagestani)-Russian test pilot cosmonaut, 1983-1994.
Tolmachev, Viktor Grigoryevich Russian engineer. General Director, Votkinsk Factory from 1989. Manufacturers of solid propellant ballistic missiles.
Tolubko, Vladimir Fedorovich (1914-1989) Russian officer. First Deputy Commander-in-Chief of the Strategic Missile Forces 1960-1968. Commander-in-Chief 1972-1985.
Tomahawk.
Popular Name of BGM-110 intermediate range cruise missile.
Test and sounding vehicles developed by Sandia using the TE-416 Tomahawk motor.
American sounding rocket. Test and sounding vehicles developed by Sandia using the TE-416 Tomahawk motor.
Solid rocket stage. 53.00 kN (11,915 lbf) thrust. Mass 200 kg (441 lb).
Russian manufacturer. Tomashevit Design Bureau, Russia.
American pressure suit, tested 1940-43. Project MX-117 full "tomato worm" pressure suits were developed during World War II.
Tommein, W German expert in aerodynamics during World War II. As of January 1947, working at Goettingen (Russian Zone of Occupation).
Tomographic Experiment / Radiative Recombinative Ionospheric EUV & Radio Sources.
Alternate designation for TERRIERS earth ionosphere satellite.
TOMS.
Total Ozone Mapping Spectrometer
American earth atmosphere satellite. One launch, 1996.07.02.
Headquarters of an RVSN Division, 1961-1962. Moved to Gladkaya.
Tonkikh, Fedor Petrovich (1912-1987) Russian officer. 1969-1985, Chief, Dzerzhinskiy Military Academy. Colonel-General, doctor of military science, professor. After WW2 action, service in artillery forces. From 1960 deputy chief commander of the rocket forces for readiness.
Sounding rocket and test vehicle launch site. Conducted launches in support of US nuclear weapons development programs. Known to have been used for 93 launches from 1957 to 1986, reaching up to 270 kilometers altitude.
Tomahawk Sandia launch complex. HAD Launcher No. 4
Malemute launch complex. Universal Launcher No. 3
Topaze.
Alternate designation for Diamant-2 rocket stage.
SEP N2O4/UDMH rocket engine. 120.1 kN. Out of production. Isp=255s. Used on Diamant launch vehicle. First flight 1965.
Topaze was the first guided rocket in the French 'precious stones' series. As such it was the first launched from a pad rather than a ramp. The initial model was the VE111C (short) with the NA802 motor.
N2O4/UDMH propellant rocket stage. Loaded mass 1,500 kg. Thrust 120.00 kN.
French test vehicle. The VE111L (long) used the stretched NA803 motor. The VE111L was successfully demonstrated the thrust vectoring concept over a longer burn period. The last two flights were VE111LG configuration, equipped with all-up inertial navigation systems.
N2O4/UDMH propellant rocket stage. Loaded mass 2,200 kg. Thrust 156.00 kN.
American earth sea satellite. One launch, 1992.08.10. TOPEX/Poseidon was a co-operative mission between the United States and France designed to provide high-accuracy global sea level measurements.
TOPO.
American earth geodetic satellite. One launch, 1970.04.08. US Army topographic / geodesic satellite launched in 1970.
Topol.
Containerised all-solid propellant Nadiradze ICBM designed for launch from mobile and silo launchers. Replaced UR-100/UR-100NU in silos.
Russian containerised all-solid propellant intercontinental ballistic missile designed for launch from mobile and silo launchers. Replaced UR-100/UR-100NU in silos.
Topol'.
Alternate designation for Topol missile.
All-Russian solid propellant ICBM set to replace all older models in the first decade of the 21st Century. Designed for mobile deployment on 8-axis transport-launcher RT-2M2/SS-X-29), or placement in existing UR-100N and R-36M silos (RT-2M1/SS-X-27).
Topol'-M.
Alternate designation for Topol M intercontinental ballistic missile.
Solid rocket stage. 980.00 kN (220,313 lbf) thrust. Mass 26,000 kg (57,320 lb).
Solid rocket stage. 490.00 kN (110,156 lbf) thrust. Mass 13,000 kg (28,660 lb).
Solid rocket stage. 245.00 kN (55,078 lbf) thrust. Mass 6,000 kg (13,228 lb).
TOPS.
Thermoelectric Outer Planets spacecraft; or Toward Other Planetary Systems
Topside sounder satellite
Notional lox/lh2 rocket engine. 20,015 kN. Study 1963. Operational date would have been December 1976. Engines for recoverable stage. Isp=455s. Used on Nova MM T10RR-2 launch vehicle.
Notional lox/lh2 rocket engine. 1778 kN. Study 1967. Isp=447s. Used on Saturn V-3B launch vehicle.
Notional lox/lh2 rocket engine. 2491 kN. Design concept 1990's. Isp=447s.
Canadian agency. Toronto, Toronto, Canada.
Russian manufacturer. Torpov Design Bureau, Russia.
TOS.
Alternate designation for IUS-2 rocket stage.
TOS.
Heavy Orbital Station (Russian abbreviation)
TOS.
American earth weather satellite. 7 launches, 1966.10.02 (ESSA 3) to 1969.02.26 (ESSA 9). TOS spacecraft marked the first operational system of US polar-orbiting meteorological satellites.
TOS.
Solid propellant rocket stage. Loaded/empty mass 10,960/1,130 kg. Thrust 185.10 kN. Vacuum specific impulse 296 seconds. IUS-2 stage with simplified electronics.
Japanese manufacturer of spacecraft. Toshiba Corp. , Tokyo, Tokyo, Japan
Toshiba Corp.
First Owner of NEC
Total Ozone Mapping Spectrometer - Earth Probe.
Alternate designation for TOMS-EP earth atmosphere satellite.
French manufacturer. Toulouse, Toulouse, France.
Townsend, Ronald Dean (1948-) American meteorologist payload specialist astronaut, 1985-1986.
TPI.
Terminal phase initiation
TPS.
Thermal Protection System
TR-1.
Single stage vehicle.
TR-1.
American pressure suit, tested 1980. Prototype full pressure suit developed by ILC Dover for the TR-1 aircraft.
TR-1.
Japanese test vehicle. Single stage vehicle.
TR106.
Manufacturer's designation of TR-106 Lox-LH2 rocket engine.
TRW lox/lh2 rocket engine. 2892 kN. Development. Innovative TRW 650K Low Cost Pintle Engine, test fired at NASA's test center in October 2000.
TRW lox/kerosene rocket engine. 4900 kN. Booster stages. TRW design for NASA's Space Launch Initiative. The engine used duct-cooling of the main combustion chamber and materials that would not interact with kerosene to minimise coking.
Solid rocket stage. 608.00 kN (136,684 lbf) thrust. Mass 10,800 kg (23,810 lb).
NASDA solid rocket engine. 608 kN.
NASDA solid rocket engine. 608 kN.
Japanese test vehicle. Single stage vehicle.
Solid rocket stage. 608.00 kN (136,684 lbf) thrust. Mass 7,500 kg (16,535 lb).
TR-201.
Alternate designation for Delta P rocket stage.
TRW N2O4/Aerozine-50 rocket engine. 41.9 kN. Apollo lunar module ascent stage engines. Surplus engines used on Delta P stage. Isp=301s. First flight 1972.
American technology satellite. One launch, 1961.11.15. Transit Research and Attitude Control.
American solar satellite. One launch, 1998.04.02. TRACE, carried a 30-cm extreme ultraviolet imaging telescope for studies of the sun. Lockheed was the lead contractor while the Smithsonian Astrophysical Observatory made the telescope mirrors.
Tracking and Data Relay Satellite.
Alternate designation for TDRS military communications satellite.
Tracking network technology satellite.
Category of spacecraft.
American manufacturer. Tracor, USA.
American test vehicle. The Trailblazer rockets were designed to conduct experiments in re-entry physics.
The Trailblazer rockets were designed to conduct experiments in re-entry physics.
American technology satellite. Launched 2008.08.03,
American test vehicle. The rocket's first three stages would take the upper stage package to a 260 km apogee. The upper stage package was mounted upside-down in relation to the other stages. When it had reached the peak, the three upper stages fired in sequence, ramming the payload, a 13 cm sphere, into the atmosphere at orbital re-entry speeds.
American test vehicle. NASA rocket designed for high-speed re-entry tests.
Solid rocket stage. 200.00 kN (44,962 lbf) thrust. Mass 900 kg (1,984 lb).
Solid rocket stage. 22.00 kN (4,946 lbf) thrust. Mass 100 kg (220 lb).
Solid rocket stage. 2.30 kN (517 lbf) thrust.
American test vehicle. Five stage version for artificial meteorite launches consisting of 2 x Recruit strap-ons + 1 x Castor first stage + 1 x Skat second stage. The upper stage package consisted of 1 x Altair + 1 x Cygnus 15 + 1 x Cygnus 5
Category of missiles.
SEPR solid rocket engine. 50 kN. Out of production. Isp=220s. Used on Berenice launch vehicle. First flight 1962.
Transfer Orbit Stage.
Alternate designation for TOS rocket stage.
American manned space station module. Cancelled 1998. Cost overruns soon forced NASA to consider other options for the International Space Station's habitation module. The space agency originally intended to use the same 8.
American navigation satellite. 46 launches, 1959.09.17 (Transit 1A) to 1988.08.25 (Transit O-31). The Transit Navigation System began development in 1958.
Spin-stabilized Transit satellites were developed by the US Navy into the first operational navigation satellite system, for use by ballistic missile submarines and surface vessels. Early Transits carried a variety of piggy-back payloads, many still classified. Transit was also known as the Navy Navigation Satellite (NNS). Transit provided continuous navigation satellite service from 1964, initially for Polaris submarines and later for civilian use.
Transportniy Korabl Snabzheniya.
Alternate designation for TKS manned spacecraft.
Transtage.
Alternate designation for Titan Transtage rocket stage.
American space tug. Flown 1968-1982 on Titan 3A and 3C boosters. Transtage mass remaining after insertion of Dynasoar and Abort Stage into orbit. Transtage had its own RCS. Maneuver in earth orbit.
Aerojet N2O4/MMH rocket engine. 16.7 kN. Development completed 1987. Isp=328s. Upper stage engine using injectors, chamber, and nozzle derived from the Shuttle OMS system, but pump-fed for increased chamber pressure and Isp. Tested; no production.
Traub German expert in biological warfare during World War II.
The text of the ABM Anti-Ballistic Missile Treaty, which limited deployment of anti-ballistic missile systems to two sites in each country.
The text of the Intermediate Nuclear Forces Treaty, which banned intermediate-range nuclear weapons in Europe.
The text of the Outer Space Treaty, which prohibited deployment of nuclear weapons in space.
The text of the SALT-1 Strategic Arms Limitation Treaty, which stopped the growth in US/Soviet intercontinental-range nuclear weapons arsenals
The second part of the text of the SALT-2 Strategic Arms Limitation Treaty, which cut back the US/Soviet intercontinental-range nuclear weapons arsenals
The second part of the text of the START-1 Strategic Arms Reduction Treaty, which further cut back the US/Soviet intercontinental-range nuclear weapons arsenals
The text of the START-2 Strategic Arms Reduction Treaty, which further cut back the US/Soviet intercontinental-range nuclear weapons arsenals
Tregub, Yakov Isayevich Russian engineer. Deputy Chief Designer 1964-1973 of Korolev design bureau for flight controls for piloted flights.
Treshchev, Sergey Yevgenyevich (1958-) Russian engineer cosmonaut. Flew on ISS EO-5. Civilian Engineer, Energiya NPO
Tresvyatski, Sergei Nikolayevich (1954-) Russian test pilot cosmonaut, 1985-1996.
Triad.
Alternate designation for TIP navigation satellite.
American winged orbital launch vehicle. The General Dynamics proposed an ingenious "Triamese" concept for the US Air Force "Integral Launch & Re-entry Vehicle" program. This system (originally developed in 1965 for a classified USAF SAMSO study) would have utilised three virtually identical reusable booster/orbiter element vehicles rather than develop two different booster and orbiter spaceplanes. General Dynamics estimated that the Triamese only would cost $1-2 billion to develop (=$4.5-9B at 1999 economic conditions) and be operational by 1976.
Three stage vehicle consisting of 3 x Deacon + 1 x Deacon + 1 x HPAG
US Navy submarine-launched ballistic missiles, which superseded the Polaris.
American submarine-launched ballistic missile. US Navy submarine-launched ballistic missiles, which superseded the Polaris.
Trident 1.
Alternate designation for Trident C-4 intercontinental ballistic missile.
Trident 2.
Alternate designation for Trident D-5 intercontinental ballistic missile.
American intercontinental ballistic missile. 3 stages, inertial guided, warhead: nuclear MIRV. Could replace Poseidon in existing submarine launch tubes.
Solid propellant rocket stage. Loaded mass 23,000 kg.
Solid propellant rocket stage. Loaded mass 8,000 kg.
Solid rocket stage. Mass 2,000 kg (4,409 lb).
American intercontinental range, submarine-launched ballistic missile. Deployed March 1990 aboard the new Ohio-class submarines. 336 remain in service in the 2010's as America's seaborne nuclear deterrent.
Solid rocket stage. Mass 39,100 kg (86,201 lb).
Solid rocket stage. Mass 11,800 kg (26,015 lb).
Solid rocket stage. Mass 2,200 kg (4,850 lb).
Philco-Ford solid rocket engine. 35 kN.
CSD solid rocket engine.
Trifanov, Yuri Nikolayevich Russian engineer. Deputy Chief Designer of Chelomei design bureau Filial 1. Later management positions at NPO Energia and NPO Lavochkin.
Trinh, Dr Eugene Huu-Chau 'Gene' (1950-) Vietnamese-American physicist payload specialist astronaut. Flew on STS-50.
American test vehicle. Single stage vehicle.
American test vehicle. Two stage vehicle consisting of 3 x Deacon + 1 x HPAG
Tripoli
Tritko, Karl Ivanovich Russian engineer. Chief of SKB of NII-88 1946-1949. Led work on early missiles.
US Navy ship- and sub-to-surface cruise ramjet-powered supersonic missile. Development started in 1946. Program cancelled in 1957.
Triumf.
TRMM.
American earth atmosphere satellite. One launch, 1997.11.27. TRMM was an international mission dedicated to measuring tropical and subtropical rainfall.
Tropical Rainfall Measuring Mission.
Alternate designation for TRMM earth atmosphere satellite.
James Oberg's prescient account of the beginning of the end - or the end of the beginning - of the Soviet space industry
TRS.
Tele-operated Reboost System
TRS.
American technology satellite. 5 launches, 1963.05.09 (TRS 2) to 1964.07.17 (TRS 6). TRS satellites undertook a range of engineering experiments related to radiation-hardening of solar cells and spacecraft electronics.
American test vehicle. The US Navy's R. C. Truax, at Annapolis, Md., developed a number of pioneering early rockets.
Truax, Robert C American USN rocket pioneer, developed missiles USN 1940-1959. Loaned to USAF to run Thor program 1955-1958. At Aerojet 1958-1967. Proponent and inventor of ultra-low-cost rocket engine and vehicle concepts.
American manufacturer of rockets. Truax, USA.
Aerojet lox/lh2 rocket engine. 147.1 kN. Test 1962. Used in Sea Horse-2. Isp=425s.
Truax Volksrocket..
Alternate designation for Sea Horse sea-launched test vehicle.
Trubachev, Pavel Yefimovich (1911-1981) Russian officer. Major General, Chief of Directorate of GURVO 1963-1970. In 1945-1946 part of team recovering rocket technology in Germany. After that worked in NII-88.
Truhill, Geraldine 'Jerri' (1927-) American pilot, one of the Mercury 13 female astroauts proposed in 1961, but never entered training.
Truly, Richard Harrison 'Dick' (1937-) American pilot astronaut. Flew on STS-2, STS-8.
American military naval signals reconnaisance satellite. 3 launches, 1994.05.03 (USA 103) to 1997.11.08 (USA 136).
TRW.
First name of Chantilly
TRW.
First name of Redondo Beach
TRW.
American manufacturer of rockets, spacecraft, and rocket engines. TRW Corporation, Redondo Beach, CA, USA.
American manned Mars expedition. Study 1963. In 1963 TRW designed a Mars expedition using aerobraking at both Mars and Earth, and a swingby of Venus on return.
TRW Space & Electronics.
First Owner of TRW
American manufacturer. TRW-IAI, USA.
Tryggvason, Bjarni Valdimar (1945-) Icelandic-Canadian engineer mission specialist astronaut. Flew on STS-85. CSA; Alternate Payload Specialist to MacLean for STS-52 Mission LAGEOS-2 and Test of the Canadian Space Vision System.
Ts-1.
Alternate designation for LL manned rocketplane.
TS-1.
Article Number of Shiyan civilian surveillance satellite.
Central Aerohydrodynamics Institute (Russian abbreviation)
Israeli agency. Tsahal, Israel.
Tsander, Friedrich Arturovich (1887-1933) Soviet chief theoretician. Rocket pioneer Russian-Soviet rocket pioneer.
TsAO.
Russian agency. Central Aerology Observatory, Russia.
Russian agency. Central Bank of the Russian Federation.
Central Bank of the Russian Federation, Moskva, Russia
Tschechner, Robert (1899-) German specialist engineer in WW2, member of the Rocket Team in the Soviet Union, worked on rocket engine development in Glushko's design bureau from 1947 to 1952. Worked in Manufacture; Laboratory Department.
Tschinkel, Johann G (1907-2004) German-Austrian rocket technician, arrived in the United States under Project Paperclip on 1945.11.16 aboard the Argentina from La Havre. Fluent in English prior to arrival in the United States. Died in Tallahassee, Florida.
TSCJ.
Japanese agency overseeing development of spacecraft. TSCJ, Japan.
Russian ELINT satellite network
Ukrainian military naval signals reconnaisance satellite. 25 launches, 1984.09.28 (Cosmos 1603) to 2007.06.29 (Cosmos 2406).
Ukrainian intercontinental ballistic missile. Development of the Tselina-2 road transport for a heavy ICBM can be traced back to the late 1960's. By the 1970's two versions had been designed, the 12-axle MAZ-7906 and 8-axle MAZ-7907. They could transport loads of up to 140 tonnes, much greater than the single-warhead RT-23 and its container. Although trials of prototypes were conducted in the 1980's, the road mobile version of the RT-23 was never put into service.
Ukrainian military naval signals reconnaisance satellite. Cancelled in the early 1990s. The Tselina-3 third generation two-tier ELINT satellite system was developed in parallel with Tselina-2.
Ukrainian military naval signals reconnaisance satellite. 77 launches, 1970.12.18 (Cosmos 389) to 1994.05.25 (Tselina-D). The Tselina D was the detailed observation portion of the two-satellite Tselina ELINT satellite system.
Ukrainian military naval signals reconnaisance satellite. 42 launches, 1967.06.26 (Tselina-O GVM) to 1982.03.31 (Cosmos 1345). From 1965 to 1967 two dedicated ELINT systems were tested by the Soviet Union: Tselina and US. Both were routinely operated.
Ukrainian military naval signals reconnaisance satellite. Study 1970. Improved version of Tselina-O. Either not put into production or later launches listed as Tselina-O were actually of Tselina-OM model.
Tsibliyev, Vasili Vasilyevich (1954-) Russian pilot cosmonaut. Flew on Mir EO-14, Mir EO-23. 381 cumulative days in space. Call sign: Sirius (Sirius).
Tsien Hsue-shen (1911-) Father of Chinese spaceflight. Leading rocket theoretician, expelled from USA as Red in 1955. Created China's space industry from scratch, results: China's first ballistic missiles, 1960s; first satellite, 1970; and first astronaut, 2003.
Chinese manufacturer of rockets. Tsien, China.
American winged rocketplane. In 1949 Tsien Hsue-shen, the leading expert in high-speed aerodynamics working in America, applied the knowledge learned from German rocket developments to the design of a practical intercontinental rocket transport.
American manned spaceplane. Study 1949. Intercontinental rocket transport, 5,000 km range, single stage winged design clearly derived from V-2 aerodynamics.
Chinese manned spaceplane. Study late 1970s. Tsien Hsue-shen's manned spacecraft design proposed in the late 1970's was a winged spaceplane, launched by a CZ-2 core booster with two large strap-on boosters.
Russian navigation satellite. 20 launches, 1976.12.15 (Cosmos 883) to 1995.07.05 (Cosmos 2315). Tsikada was a complementary civilian version of the Parus military naval navigation satellite system for the Soviet Merchant Marine and Academy of Sciences.
Tsikada-M.
Alternate designation for Parus navigation satellite.
Ukrainian intercontinental ballistic missile. The R-36 ICBM was the largest ever built and the bogeyman of the Pentagon throughout the Cold War. Dubbed the 'city buster', the 308 silos built were constantly held up by the US Air Force as an awesome threat that justified a new round of American missile or anti-missile systems. On the other hand, the Americans were never motivated to build and deploy corresponding numbers of their equivalent, the liquid propellant Titan 2. Derivatives of the R-36 included the R-36-O orbital bombing system, the Tsiklon-2 and -3 medium orbital launch vehicles, and the replacement R-36M missiles. With the collapse of the Soviet Union, the design and manufacturing facility ended up in independent Ukraine. Accordingly the missile was finally retired in the 1990's, conveniently in accordance with arms reduction agreements with the Americans.
Russian navigation satellite. 31 launches, 1967.05.15 (Cosmos 158) to 1978.07.27 (Cosmos 1027).
The R-36 ICBM was the largest ever built and the bogeyman of the Pentagon throughout the Cold War. Dubbed the 'city buster', the 308 silos built were constantly held up by the US Air Force as an awesome threat that justified a new round of American missile or anti-missile systems. On the other hand, the Americans were never motivated to build and deploy corresponding numbers of their equivalent, the liquid propellant Titan 2. Derivatives of the R-36 included the R-36-O orbital bombing system, the Tsiklon-2 and -3 medium orbital launch vehicles, and the replacement R-36M missiles. With the collapse of the Soviet Union, the design and manufacturing facility ended up in independent Ukraine. Accordingly the missile was finally retired in the 1990's, conveniently in accordance with arms reduction agreements with the Americans.
Tsiklon-1.
Alternate designation for 64S5 intercontinental ballistic missile.
Ukrainian orbital launch vehicle. A government decree of 24 August 1965 ordered development by Yangel of a version of his R-36 rocket to orbit Chelomei's IS (Istrebitel Sputnik) ASAT and US (Upravlenniye Sputnik) naval intelligence satellites. The Tyklon 2 definitive operational version replaced the 11K67 launch vehicle from 1969 and was an adaptation of the 8K69 (SS-9) two stage ICBM. The IS and US Raketoplan-derived payloads had their own engines for insertion into final orbit.
Ukrainian orbital launch vehicle. Minimal modification of the R-36 ICBM used in replacement of Chelomei's cancelled UR-200 booster for initial launches of the IS ASAT and US naval radarsat. Development was authorized in late 1965 and first launch was made before the end of 1967. It flew only eight times before being replaced by the definitive Tsyklon-2 space launch vehicle.
Ukrainian orbital launch vehicle. The Tsyklon 3 was developed in 1970-1977 as a part of a program to reduce the number of Soviet booster types. The first two stages were derived from the 8K68 version of the R-36 ICBM, while the restartable third stage was derived from that of the R-36-O. Compared to the Tsyklon 2, the launch vehicle increased payload to 4 metric tons, provided for completely automated launch operations, and had increased orbital injection accuracy.
Ukrainian orbital launch vehicle. Updated version of Tsyklon 3, announced by the Ukraine in 2005 as being in design. Improved lower stages, new upper stage and a new 4.0-m diameter payload fairing. No production plans.
Tsiklon-B.
Manufacturer's designation for Parus navigation satellite.
Chinese manufacturer of spacecraft. Tsinghua University, Beijing, China.
Tsiolkovskiy, Konstantin E (1857-1935) Chief Soviet theorist of spaceflight, developed mathematics of rocketry and space travel, identifying basic rocket and spacecraft designs. But work little known outside the Soviet Union, did not influence Goddard and Oberth.
Russian orbital launch vehicle. Tsiolkovsky was the first to propose the use of liquid hydrogen and oxygen to propel a rocket, and calculated its performance using the crucial rocket equation V = c ln(Mo/ Me).
Tsirulnikov, Mikhail Yurevich (1907-1990) Russian engineer. First manager of the Perm Mechanical Engineering Design Bureau (later NPO Iskra). Designer of artillery systems, solid propellant missiles, and engine units.
Russian manufacturer of rockets. Tsirulnikov Design Bureau, Russia.
TsK.
Central Committee (Russian abbreviation)
TsKB.
Central Design Bureau (Russian abbreviation)
Russian manufacturer of rocket engines. TsKB-7, Russia.
Central Design Bureau of Experimental Machine Building (Russian abbreviation)
TsKBEM (1965).
Third Owner of Korolev
TsKBEM Kuibyshev Filial.
Second Owner of Kozlov
Central Design Bureau of Machine Building (Russian abbreviation)
Central Command-Measurement Complex (Russian abbreviation)
Central Institute of Aviation Motor Building (Russian abbreviation)
TsM-D 77KSD-17101.
Manufacturer's designation for Kvant-2 manned space station.
TsM-E 37Ke-010.
Manufacturer's designation for Kvant manned space station.
TsM-I 77KSI.
Manufacturer's designation for Priroda manned space station.
TsM-T 77KST-17201.
Manufacturer's designation for Kristall manned space station.
Central Scientific-Research Institute (Russian abbreviation)
Russian manufacturer of rocket engines. Central Scientific-Research Institute for Machine Building, Russia.
TsNPO Vympel.
Third Owner of Vympel
TsPK.
Cosmonaut Training Centre (Russian abbreviation)
TSS.
Targeted Search System
TSS.
Italian tether technology satellite. One launch, 1996.02.22. Test from shuttle of 20 km long tether; satellite unintentionally deployed when tether broke February 25 1996. Re-entered March 19.
Central Specialized Design Bureau (Samara, Russia), Russia
TsSKB (1965).
Third Owner of Kozlov
TSTO.
Two Stage To Orbit (also 2STO)
Central Directorate of Space Assets (Russian abbreviation)
TsUP.
Russian manufacturer.
TsUP.
Flight Control Centre (Russian abbreviation)
Russian manufacturer.
Russian manufacturer of rockets and spacecraft. Tsybin Design Bureau, Russia.
Tsybin, Paver Vladimirovich (1905-1992) Russian Chief Designer OKB-256 1945-1959. Designs: LL rocketplanes, RS Mach 3 ramjet aircraft, PKA spaceplane. Bureau closed, worked for Korolev on Vostok, Soyuz, AMS and Molniya satellites. Deputy Designer of Buran space shuttle, 1974-1992.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 122,300/6,400 kg. Thrust 2,640.00 kN. Vacuum specific impulse 301 seconds. SL-11; 11K68;R-36M
N2O4/UDMH propellant rocket stage. Loaded/empty mass 49,300/3,700 kg. Thrust 940.40 kN. Vacuum specific impulse 317 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 3,200/400 kg. Thrust 77.96 kN. Vacuum specific impulse 317 seconds. Integral portion of payload.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 127,000/8,300 kg. Thrust 3,032.00 kN. Vacuum specific impulse 301 seconds. SL-14;11K69
N2O4/UDMH propellant rocket stage. Loaded/empty mass 53,300/4,800 kg. Thrust 941.00 kN. Vacuum specific impulse 318 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 4,600/1,407 kg. Thrust 78.71 kN. Vacuum specific impulse 317 seconds.
Tsyklon M.
Manufacturer's designation for Tsiklon-2 orbital launch vehicle.
TT-.
Tyuratam. Designation given by US intelligence services to launch complexes observed there; or TT, Technical Translation (US government)
TT&C.
Telemetry Tracking and Command
Japanese sounding rocket. Single stage vehicle.
NASDA solid rocket engine.
Solid propellant rocket stage. Loaded mass 200 kg.
Japanese sounding rocket. Single stage vehicle.
NASDA solid rocket engine.
Solid propellant rocket stage. Loaded mass 200 kg.
NASDA solid rocket engine family.
Japanese sounding rocket. Small, half-meter diameter, two stage suborbital rocket used for tracking system and microgravity tests.
NASDA solid rocket engine. 116 kN.
Solid rocket stage. 116.00 kN (26,078 lbf) thrust. Mass 1,300 kg (2,866 lb).
Solid rocket stage. 61.00 kN (13,713 lbf) thrust. Mass 700 kg (1,543 lb).
Japanese sounding rocket.
NASDA solid rocket engine. 61 kN.
TTS.
American tracking network technology satellite. 2 launches, 1967.12.13 (TTS 1) and 1968.11.08 (TTS 2; TATS 2 (TETR 2)). Tested Apollo tracking network.
TTT.
System requirements (Russian abbreviation)
TTZ.
System specifications (Russian abbreviation)
TU.
Technical University (German)
Tu Shoue Chinese Engineer. Chief Designer of the CZ-2E heavy-lift launch vehicle.
Turbojet powered cruise missile stage. Loaded/empty mass 23,200/7,200 kg. Thrust 98.00 kN. KR-15-300 engine by OKB-300 (now MZ Soyuz), rated for 15 hour endurance.
Russian intermediate range cruise missile. Mach 3 intermediate range cruise missile, tested in 1958-1960 before cancellation.
Russian intercontinental boost-glide missile. Exotic design for an intercontinental missile using a gas core fission reactor for cruise propulsion. Studied circa 1957.
Nuclear/Air propellant rocket stage. Loaded/empty mass 27,000/7,300 kg. Turbojet using mixed propulsion, either burning kerosene or heating air directly with a nuclear reactor.
Tu-123D.
Alternate designation for Tu-133 intercontinental cruise missile.
Tu-123DP.
Alternate designation for Tu-123 intercontinental boost-glide missile.
Russian intercontinental boost-glide missile. Three-stage intercontinental boost-glide missile. Studied 1957-1960.
Russian surface-to-air missile. Tupolev design for a long-range air-breathing surface-to-air missile. Never got beyond the design stage.
Russian intercontinental cruise missile. Mach 3 intercontinental range cruise missile, cancelled in 1960 before flight tests began.
Mach 2 rocket launch aircraft. Loaded/empty mass 205,442/99,773 kg. Thrust 533.67 kN. Specific impulse 1980 seconds. Tupolev Bomber-variable geometry. Maximum release conditions: Belly-mounted, 9,977 kg at 2,451 kph at 18,292 m altitude
Airbreathing Slush LH2 propellant rocket stage. Loaded/empty mass 90,000/40,000 kg. Thrust 882.00 kN. Specific impulse 1550 seconds. Aerospaceplane to compete with American X-30. Single stage to orbit, scramjet air breather. Tupolev assigned to start work in 1993. Mockup built, and some subscale flights to Mach 6 on tactical missiles of scramjet model, but project now dormant due to lack of funds. Wing area 160 square meters, wing sweep 70 degrees. Two crew.
Russian winged orbital launch vehicle. This Soviet equivalent to the US X-30 single-stage-to-orbit scramjet aerospaceplane began development in1986. Three versions were planned: a Mach 6 test vehicle, under construction at cancellation of the program in 1992; a Mach 6 intercontinental bomber; and a single-stage-to-orbit launch vehicle.
Russian manned spaceplane. Study 1986. In reaction to US X-30 project, government decrees of 27 January and 19 July 1986 ordered development of a Soviet equivalent.
TU-289.
Manufacturer's designation of SR49 rocket engine.
Thiokol solid rocket engine. 85 kN.
Thiokol solid rocket engine. 186 kN.
Thiokol solid rocket engine. 55.1 kN.
TU-844.
Manufacturer's designation of SSUS-A Motor Solid rocket engine.
TU-903.
Manufacturer's designation of Peacekeeper 1 Solid rocket engine.
Thiokol solid rocket engine. 1711 kN.
TU-936.
Manufacturer's designation of Star 63D Solid rocket engine.
TUAF.
TUAF
Tuan.
Pham Tuan (1947-) Vietnamese pilot cosmonaut. Flew on Salyut 6 EP-7. First Vietnamese astronaut. Engineer, Air force pilot. Participated in the Vietnam War. Major General of Vietnam Air Force.
TUB.
German manufacturer of spacecraft. Technische Universitaet Berlin, Berlin, Germany.
Turkish agency. Tubitak-Bilten, Turkey.
Small experimental store and forward communications satellite series.
German communications technology satellite. 7 launches, 1991.07.17 (Tubsat-A) to 2007.01.10 (Maroc-Tubsat). Germany's Technical University of Berlin (TUB) built a successful series of 40 kg 'Tubsat' experimental technology satellites.
Tuchkov, Leonid Timofeyevich (1920-) Russian officer. Major General, Deputy Chief of the Mozhaiskiy Military Engineering Institute 1971-1986.
Tucker, Charles American test pilot. Flew the X-5 # 1.
Tug.
Category of spacecraft.
Tumanskiy, Sergei Konstantinovich (1901-1973) Russian chief designer. Chief Designer and General Designer 1955-1973 of OKB-300. Specialised in aircraft turbine engines but also produced spacecraft attitude control engines.
Tumanyan, Gay Lazarevich (1901-1972) Russian officer. Major General, Commander of the political units of the KIK space tracking units 1961-1968.
Tupolev, Andrei Nikolayevich (1888-1972) Russian chief designer. Chief Designer and General Designer 1943-1972 of OKB-156.
Russian manufacturer of rockets and spacecraft. Tupolev Design Bureau, Russia.
Category of engines.
Category of engines.
Turkish Posts and Telecom Ministry, Turkey.
Turkey
Turkish agency.
Communications satellites launched to support Turkish domestic communications and television, orbited by the Ministry of Posts and Communications of the Republic of Turkey.
Turovets, Vladimir Yevgeniyevich (1949-1982) Russian test pilot cosmonaut, 1977-1980. Test pilot, Gromov Flight Research Institute. Selected as a cosmonaut for the Buran program in 1977 by the Gromov Flight Test Center, but the selection was not confirmed by the government commission. Died in the crash of an Mi-8 helicopter.
TV.
Televison
Tveretskiy, Aleksandr Fedorovich (1904-1992) Russian officer. First Commander of Special Purpose Brigade (precursor to the Strategic Missile Forces), 1946-49.
West German communications satellite network
Twining, Nathan F (1897-1982) American USAF officer, chief of staff from 1953 and Chairman of the Joint Chiefs of Staff 1957-1960. During this period key decisions were made regarding ICBM, manned spacecraft, and military satellite development.
TWX.
Teletype message
Thiokol solid rocket engine. 2000 kN.
Thiokol solid rocket engine. 117 kN.
Thiokol solid rocket engine. 85 kN.
Thiokol solid rocket engine. 213 kN.
Thiokol solid rocket engine.
Thiokol solid rocket engine.
Thiokol solid rocket engine. 244 kN.
Thiokol solid rocket engine. 44.5 kN.
Thiokol solid rocket engine. 285 kN.
Thiokol solid rocket engine. 258.9 kN. Used in Scout A; Delta E; H-1-0; Castor 2. License built in Japan for H-1. Isp=262s. First flight 1960.
Thiokol solid rocket engine.
TX-481.
Manufacturer's designation of SR109 rocket engine.
Thiokol solid rocket engine. 2000 kN.
Thiokol solid rocket engine. 168 kN.
TX-526.
Manufacturer's designation of Castor 4 Solid rocket engine.
TX-633.
Manufacturer's designation of SR114 rocket engine.
Thiokol solid rocket engine. Basic Terrier mk70 motor.
Thiokol solid rocket engine. 227 kN.
TX-780.
Manufacturer's designation of Castor 4A Solid rocket engine.
TX-780B.
Manufacturer's designation of Castor 4B rocket engine.
TX-780XL.
Manufacturer's designation of Castor 4AXL Solid rocket engine.
TX-859.
Manufacturer's designation of Castor 4BXL Solid rocket engine.
Type 149.
Standard RV of Variant B submarine-launched ballistic missile.
Type 46.
Standard warhead of P-205 intermediate range cruise missile.
British pressure suit, operational 1965. Full pressure suit designed by R. E. Simpson, and developed by Baxter, Woodhouse and Taylor Ltd. for the Royal Air Force.
Tyulin, Georgi Aleksandrovich (1914-1990) Russian officer. First Deputy Chairman of GKOT 1961-1965. First Deputy Minister of General Machine Building 1965-1976. Chaired many State Commissions.
Russian military anti-satellite system target satellite. Study 1987. ASAT target designed to be released and tracked by sensors in original design of Mir Spektr module. May also have been the ASAT targets carried aboard the Polyus star wars testbed.
Russian communications satellite. By 1994 Lavochkin's Tyulpan system was promoted more heavily than its earlier Nord system.
Headquarters of an RVSN Division, 1961-1964. Base for units deployed with nine R-9 launchers. Moved to Aleisk.
Tyuratam.
Alternate name for Baikonur launch site.
Tyurin, Michael Vladislavovich (1960-) Russian engineer cosmonaut. Flew on ISS EO-3, ISS EO-14. Civilian Engineer, Energiya NPO.
Tyurin, Petr Aleksandrovich (1917-2000) Russian chief designer. Chief Designer 1953-1981 of KB Arsenal. Specialised in L3 components and later performed EORSAT work.