Alternate designation for Tu-133 intercontinental cruise missile.
D.
Library of Congress designation of UR-500 missile.
D.
French earth geodetic satellite. 8 launches, 1966.02.17 (Diapason) to 1975.09.27 (Aura). Small French science and technology satellites used on early Diamant launch vehicle tests.
D-.
Department of Defense experiments prefix
D D Sevruk.
First Owner of Sevruk
D-1.
Launch System of R-11FM submarine-launched ballistic missile.
D-1.
Library of Congress Designation of Proton-K orbital launch vehicle.
D-1.
American space suit, operational 1998. The D-1 (S1035X) space suit assembly was developed to provide a functional all-soft suit technology demonstrator prototype model to be used for mobility system testing and evaluation.
D-1.
Russian tactical ballistic missile. Korolev design for a 'long range' rocket prior to orders to copy the V-2. The 1000 kg rocket would have a range of 32 km. Wingspan 1.0 m; 370 kg propellants; minimum range 12..8 km; maximum velocity 854 m/s; maximum altitude 12.5 km.
D-1.
Kosberg isopropylnitrate monopropellant rocket engine. 39 kN. Developed 1955-56. Second thrust level at 50%. Explosion of D-1 on test bench in 1956 forced stop of work with mono-propellant OT-152. Sea level thrust 39 kN.
TsNIIMASH electric/xenon rocket engine. 65 mN. Development. Isp=1600s. Hall effect thruster with anode layer, designed for satellite orbital raising. Taken to engineering model stage.
D-11.
Launch System of R-31 submarine launched ballistic missile.
Lotarev turbofan engine. 229.4 kN. Used on An-225 launch aircraft for Interim HOTOL, MAKS concepts. Development ended 1988. Isp=9000s.
D-19 Rif.
Launch System of 3M20 submarine-launched ballistic missile.
D-19M.
Launch System of Bulava intercontinental ballistic missile.
D-19UTH Grom.
Launch System of R-39M submarine-launched ballistic missile.
D-1e.
Library of Congress Designation of Proton-K-D, Proton-K-D-1, Proton-K-D-2, Proton-K-DM, Proton-K-DM-2, Proton-K-DM-2M, and Proton-K-17S40 orbital launch vehicles.
D-2.
Launch System of R-13 missile.
D-2.
Russian tactical ballistic missile. Korolev design for a 'long range' rocket prior to orders to copy the V-2. Extended-range winged version of the D-1. The 1200 kg rocket would have a range of 76 km. Wingspan 1.5 m; 370 kg propellants; minimum range 20 km; maximum velocity 628 m/s; maximum altitude 10.7 km.
D-2.
Polyarniy Lox/Kerosene rocket engine. 1373 kN. R-3. Out of Production. Competing engine for 3000 km range IRBM design to study problems of long-range rockets. Developed from April 1947 until cancellation. Isp=288s.
D-20.
TsNIIMASH electric/xenon rocket engine. 1.5 mN. Development. Isp=1400s. Hall effect thruster with anode layer, designed for satellite station-keeping and attitude control. Taken to engineering model stage.
D-21.
American air-launched drone. Project 'Tagboard', Project 'Senior Bowl'. Mach 3.5 ramjet recoverable reconnaisance drone air-launched from back of A-12 or with booster rocket from B-52.
D-3.
Launch System of R-15 submarine-launched ballistic missile.
D-38.
Manufacturer's designation of TAL-38 Electric-Xenon rocket engine.
D-4.
Launch System of R-21 submarine-launched ballistic missile.
D-5.
Launch System of R-27 submarine-launched ballistic missile.
D50.
Yuzhnoye electric/xenon rocket engine. 48 mN. Development. Isp=1700s. Hall engine electric jet propulsion system intended for use by spacecraft for inter-orbital transfer, orbit correction, and stabilization.
D-50G1.
Manufacturer's designation of LR39 Lox-Alcohol rocket engine.
Lockheed solid rocket engine.
Lockheed solid rocket engine.
D-54.
Manufacturer's designation of RD-54 Lox-LH2 rocket engine.
D-55.
Manufacturer's designation of TAL-WSF Electric-Xenon rocket engine.
American manned high-speed research aircraft. Flown 1947-1953. The D-558-I "Skystreaks" were among the early transonic research airplanes like the X-1, X-4, X-5, and XF-92A.
American manned rocketplane. Flown from 1949. Research airplane Douglas D-558. Airplane had both jet and rocket engines and was flown from ground takeoff. The D-558-II Skyrocket exceeded the speed of sound at Edwards AFB, Calif.
American manned rocketplane. Flown 1954. The D-558-3 was a US Navy/Douglas counterpart to the X-15, which would have kept the Navy in the 'space race' and Douglas in the running for future manned spaceplanes.
D-57.
Alternate designation for RD-57 Lox-LH2 rocket engine.
D-6.
First Soviet solid propellant submarine launched ballistic missile. Development began in 1958, but the system was cancelled in 1961 in favour of the D-7 naval version of the RT-15 IRBM (itself in turn cancelled).
D-6.
Russian submarine-launched ballistic missile. First Soviet solid propellant submarine launched ballistic missile. Development began in 1958, but the system was cancelled in 1961 in favour of the D-7 naval version of the RT-15 IRBM (itself in turn cancelled).
D-68.
Alternate designation for RD-68 Nitric acid-UDMH rocket engine.
D-68M.
Alternate designation for RD-68M N2O4-UDMH rocket engine.
D-68M.
Alternate designation for RD-855 N2O4-UDMH rocket engine.
D-69.
Alternate designation for RD-69 Nitric acid-UDMH rocket engine.
D-69M.
D-7.
Launch System of RT-15M submarine-launched ballistic missile.
D-7.
Kosberg isopropylnitrate monopropellant rocket engine. 11.8 kN. Missile by Toropov. Out of Production. Intended for air-air missile by I I Toropov. Uncooled thrust chamber. Sea level thrust 11.8 kN.
D-8.
Launch System of R-29, R-29D, and UR-100M SLBM submarine-launched ballistic missiles.
D-9.
D-9RM Shtil.
Launch System of R-29RM submarine-launched ballistic missile.
DA.
Deployment Assembly.
Canadian manufacturer of spacecraft. Da Vinci Project, Canada.
DAC.
Data Acquisition Camera.
American nuclear-powered orbital launch vehicle. Douglas/Bono 1963 concept for a chemical-boosted / nuclear upper stage launch vehicle, designed as alternatives to the Convair/Ehricke Helios. The baseline version used a nuclear, recoverable upper stage boosted above the atmosphere by a minimum chemical stage.
Douglas/Bono 1963 concept for a chemical-boosted / nuclear upper stage launch vehicle, designed as alternatives to the Convair/Ehricke Helios. The baseline version used a nuclear, recoverable upper stage boosted above the atmosphere by a minimum chemical stage.
American nuclear-powered orbital launch vehicle. As the basic design, but featuring an Improved Specific Impulse chemical stage that used many engines feeding into single large nozzle.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,333,000/120,000 kg. Thrust 49,807.00 kN. Vacuum specific impulse 455 seconds.
Nuclear/LH2 propellant rocket stage. Loaded/empty mass 1,070,000/214,000 kg. Thrust 17,926.00 kN. Vacuum specific impulse 850 seconds.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,660,000/149,000 kg. Thrust 52,926.00 kN. Vacuum specific impulse 410 seconds.
Nuclear/LH2 propellant rocket stage. Loaded/empty mass 1,070,000/214,000 kg. Thrust 17,926.00 kN. Vacuum specific impulse 850 seconds.
American sounding rocket. Single stage vehicle.
Solid rocket stage.
DACO.
DACO.
DAD.
American earth atmosphere satellite. 2 launches, 1975.12.06 (DAD-B) and (DAD-B). Dual Air Density; air density experiments.
Dadieu, Armin German engineer. Worked on German uranium processing in WW2, and for Saenger post-war. By the 1970's on review committees for post-Apollo space programs in US and Europa III LV in Europe. Consultant to West German goverment on OTRAG.
Dahm.
Dahm, Werner Karl (1917-2008) German-American aerodynamicist, worked at Peenemuende on A9/A10, A7, A4b, and Wasserfall winged missiles. Post-war completed studies, joined von Braun team in US as Head of Aerodynamics Analysis Branch, Aeroballistics Division, Huntsville.
Japanese civilian surveillance radar satellite. One launch, 2006.01.24. Advanced Land Observing Satellite, which carried an L-band synthetic aperture radar, an optical 2.
Dailey, John R American USMC officer, associate deputy administrator of NASA 1992-1999 and director of the NASM 2000-2009. He flew 450 missions during two tours in Viet Nam.
Daimler-Benz Aerospace.
Second name of DASA
Daimler-Benz Aerospace.
Third name of MBB
DaimlerChrysler Aerospace.
First Owner of Dornier
DaimlerChrysler Aerospace, Bremen (formerly ERNO).
Fourth Owner of Bremen
DaimlerChrysler Dornier.
Third Owner of Friedrichshafen
Dal.
Russian surface-to-air missile. Trials of this long range surface-to-air missile were conducted in 1960-1963 but the project was cancelled after the system failed to down a single target. V-200 missiles were installed in the Dal installations built around Leningrad for the failed missile. In a bit of disinformation, the V-400 was paraded in Moscow, and US intelligence, thinking it was operational, applied the SA-5 designation. The SA-5 code was transferred to the V-200 after the La-400 was cancelled.
Dal.
Trials of this long range surface-to-air missile were conducted in 1960-1963 but the project was cancelled after the system failed to down a single target. V-200 missiles were installed in the Dal installations built around Leningrad for the failed missile. In a bit of disinformation, the V-400 was paraded in Moscow, and US intelligence, thinking it was operational, applied the SA-5 designation. The SA-5 code was transferred to the V-200 after the La-400 was cancelled.
Russian surface-to-air missile. Planned next generation high performance long-range surface-to-air missile developed 1959-1963. Cancelled together with basic the Dal system at the end of 1963.
Dal-M.
Launch System of Dal-2 surface-to-air missile.
Russian surface-to-air missile. Planned improved version of the Dal high performance long-range surface-to-air missile developed 1959-1963. Cancelled together with basic the Dal system at the end of 1963.
Dana.
Dana, William Harvey 'Bill' (1930-) American test pilot. Flew on X-15 Flight 174, X-15 Flight 197.
Danchik, Robert J (1933-) American engineer. John Hopkins APL 1967-2000. Transit program manager for 16 years.
French test vehicle. Three stage test vehicle for Israel's Jericho consisting of 1 x SPRAN-50 + 1 x MD-620 + 1 x Melanie
Israel and South Africa collaborated closely in rocket technology in the 1970's and 1980's. South Africa provided Israel with the uranium and test facilities it needed for its strategic weapons programmes. In exchange Israel provided aerospace technology. This included the capability of building the ten-tonne solid propellant rocket motors designed for the Israeli Jericho-2 missile. These motors were the basis of two space launchers for an indigenous 'R5b' space programme. It seems that South Africa also planned to use these motors in a series of missiles to provide a nuclear deterrent.
Solid propellant rocket stage. Loaded mass 400 kg.
N2O4/UDMH propellant rocket stage. Loaded mass 2,000 kg.
Danish Technical University, Denmark.
Dannenberg, Konrad (1912-) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Dantscher, Josef German pilot and chief staff engineer.
DARA.
German agency overseeing development of spacecraft. Deutsche Agentur fuer Raumfahrtangelegenheiten (German Space Agency), Germany.
Darevskiy, Sergei Grigoryevich Russian engineer. Chief Designer 1965-1975 of Special OKB of Gromov LII. Designed simulators and cockpit consoles.
American agency overseeing development of rockets and spacecraft. Defense Advanced Research Projects Agency (formerly ARPA), USA.
American low cost orbital launch vehicle. Lockheed Martin all-hybrid propulsion, mobile orbital launch system that could launch from an unimproved site with limited infrastructure on 24 hours notice, placing up to 840 kilograms into LEO
American technology satellite. One launch, 1994.03.13, USA 102. GPS receiver and data processor technology tests.
Dart.
American surface-to-surface anti-tank missile. Development started in 1953 Program cancelled in 1958 in favor of the the French SS.10.
DART.
American rendezvous technology satellite. One launch, 2005.04.15. Autonomous Rendezvous Technology mission, planned to guide itself to within a few meters of a US satellite.
American manufacturer. Dartmouth, USA.
DASA.
German agency. Deutsche Aerospace AG, Bremen, Germany.
Daimler-Benz Aerospace, Bremen (formerly ERNO), Germany
Daimler-Benz Aerospace, Munich (formerly MBB), Germany
Dash.
American military technology satellite. 2 launches, 1963.05.09 (Dash 1) and 1963.07.18 (Dash 2). Space craft engaged in investigation of spaceflight techniques and technology.
Japanese re-entry vehicle technology satellite. One launch, 2002.02.04, DASH. DASH (Demonstrator of Atmospheric Reentry System and Hypervelocity) was a small secondary payload built by ISAS, the scientific space agency which was to merge with NASDA.
French manufacturer of rockets, spacecraft, and rocket engines. Dassault Aircraft, France.
Data on astronauts, manned flights, rockets, engines, and more!
Military testing range, known to have been used for 3 launches in 1963, reaching up to 50 kilometers altitude.
French sounding rocket. Single stage sounding rocket consisting of a single Stromboli motor.
Daus.
Daus German expert in special vehicles for rocket transportation during World War II. As of January 1947, last known to be working at Hamburg-Harburg.
American manufacturer of spacecraft. David Clark, USA.
Davies, Merton E (1917-2001) American scientist, worked for Douglas 1940-1948 and then RAND. Conceptual work on reconnaisance satellites led to the Corona program. Involved at JPL in early Mars imaging missions, establishing the reference systems for other planets.
Davis, Dr Nancy Jan (1953-) American engineer mission specialist astronaut. Flew on STS-47, STS-60, STS-85. Engineer, was married to astronaut Mark Lee, part of first married couple to fly in space together.
Titan 2 ICBM base. Davis-Monthan, a US military base since 1925, was selected in 1960 as the headquarters for a Titan 2 ICBM wing (the 570th). By the end of 1962 18 silos had been built, at the cost of five lives and many injuries. The missiles remained on alert in their silos for nearly twenty years, until the decision was taken to retire them in October 1981. The missiles were removed for refurbishment and use as space launchers. The silos were demolished with explosives beginning 30 November 1983. One silo was preserved as the Titan Missile Museum.
American tactical ballistic rocket.
American tactical ballistic rocket.
Dawn.
American asteroid probe. One launch, 2007.09.27. Asteroid belt unmanned probe designed to first orbit and survey the asteroid Vesta, and then fly on to the largest asteroid, Ceres. Orbit asteroids Ceres and Vesta.
Dawn-1.
Alternate designation for Shuguang 1 manned spacecraft.
Day.
Day, Melvin Sherman (1923-1986) American engineer. Worked in leadership positions in the area of technical information services at the AEC (1947-1960) and NASA (1960-1970).
American manned lunar rover. Study 1990. The Daylight Rover was a Boeing concept of 1990, which consisted of two separate pressure vessels. The forward served as the driving station, and the rear served as a storm shelter and EVA airlock.
db.
Decibel.
DBP.
Deutsche Bundespost (Germany), Germany
DBP Telekom.
DC.
Delta Clipper
DCA.
Defence Communications Agency, US Department of Defense, USA
DC-I.
Alternate designation for DC-Y ssto vtovl orbital launch vehicle.
DC-I.
Alternate name for DC-Y manned spacecraft.
DC-I.
Lox/LH2 propellant rocket stage. Loaded/empty mass 470,000/36,000 kg. Thrust 6,860.00 kN. Vacuum specific impulse 425 seconds.
DCR.
Design certification review
DCS.
Digital Command System.
DCX.
Delta Clipper eXperimental
DC-X.
The Space Defense Initiative Office's Single Stage Rocket Technology program of 1990-1995 demonstrated technology readiness for an SSTO vehicle. Despite successful test flights of the DC-X technology demonstrator, no development funding was forthcoming, and designs for prototype and production rockets remained on the drawing boards.
DC-X.
American VTOVL test vehicle. The DC-X was an experimental vehicle, 1/3 the size of a planned DC-Y vertical-takeoff/vertical-landing, single stage to orbit prototype. It was not designed as an operational vehicle capable of achieving orbital flight. Its purpose was to test the feasibility of both suborbital and orbital reusable launch vehicles using the VTOVL scheme. The DC-X flew in three test series. The first series ran from August 18 to September 30, 1993, before the initial project funding ran out in late October 1993. Additional funding was provided and a second series was conducted June 1994-July 1995.
DC-X.
Lox/LH2 propellant rocket stage. Loaded/empty mass 16,320/7,200 kg. Thrust 262.80 kN. Vacuum specific impulse 373 seconds.
American SSTO VTOVL orbital launch vehicle. Proposed intermediate 1/2 scale test vehicle between DC-X and DC-Y orbital version. No government agency was willing to fund the $450 million development cost -- and neither were any private investors.
DC-XA.
Alternate designation for DC-X vtovl test vehicle.
American VTOVL test vehicle. After a hard landing in the last flight of this series, the vehicle was rebuilt to the DC-XA configuration. The DC-XA flew from May 1996 until destroyed when it tipped over while landing on its fourth flight on 31 July 1996.
DC-Y.
American manned spacecraft. Study 1995. The ultimate goal of the Delta Clipper program, a prototype reusable single-stage to orbit, vertical takeoff/vertical landing space truck. The DC-I Delta Clipper would be the full production version.
DC-Y.
American SSTO VTOVL orbital launch vehicle. The ultimate goal of the Delta Clipper program, a prototype reusable single-stage to orbit, vertical takeoff/vertical landing space truck. The DC-I Delta Clipper would be the full production version. No government sponsor could be found for the concept and the $ 5 billion development cost was never funded. If it had been funded in 1991, the first DC-Y suborbital flight was predicted for 1995, and a first orbital mission in 1997.
DC-Y.
Lox/LH2 propellant rocket stage. Loaded/empty mass 84,000/6,000 kg. Thrust 1,051.20 kN. Vacuum specific impulse 373 seconds.
DDCU.
DC-to-DC Converter Unit
DDR.
German Democratic Republic (German abbreviation)
DDTE.
Design, Development, Test, and Evaluation
De Beek, Gerd Wilhelm (1904-1989) German engineer in WW2, member of the Rocket Team in the United States thereafter.
de Bergerac, Cyrano (1619-1655) French writer. Writer who's works included two novels involving flight to the moon. Most remembered as the subject of an 1897 novel.
De Winne, Frank (1961-) Belgian physician astronaut. Flew on ISS EP-4, ISS EO-20.
The Deacon was an advanced solid rocket motor design cancelled at the end of World War II. In 1947 NACA began using reworked surplus motors to boost instrumented subscale aircraft models to speeds of up to Mach 4. They became a workhorse for the Agency's aerodynamic research, resulting in new production. Thousands were flown, until, by the end of the 1950's, supersonic wind tunnels took over the job.
American test vehicle. The Deacon was an advanced solid rocket motor design cancelled at the end of World War II. In 1947 NACA began using reworked surplus motors to boost instrumented subscale aircraft models to speeds of up to Mach 4. They became a workhorse for the Agency's aerodynamic research, resulting in new production. Thousands were flown, until, by the end of the 1950's, supersonic wind tunnels took over the job. Data shown is for single-stage version.
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x Arrow II
Solid propellant rocket stage. Loaded mass 100 kg. Thrust 10.00 kN.
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x Deacon
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x HVAR
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x Judi III
American sounding rocket. The Rockoon concept involved release of a 12 m diameter balloon from a ship, which took a Deacon sounding rocket to 9 to 27 km altitude in 80 minutes. The rocket was ignited at a preset time or altitude or by remote control, and then boosted an 18 kg payload to a 50 to 100 km altitude. The Deacon was painted black and wrapped in plastic to protect it against the cold, and fitted with larger fins for stability at high altitude.
Two stage version of Rockoon balloon-launched soundinr coekt consisting of a Deacon first stage and Loki second stage.
Rocket stage used on Deacon Rockoon sounding rocket.
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x HPAG
DeArmond, Frank Maxton (1954-) American engineer military spaceflight engineer astronaut, 1985-1988.
A velocity control engine burn to allow a spacecraft to decelerate and go into orbit around a planetary body, or to leave an orbit and descend to a landing on that body.
Debus, Kurt Heinrich (1908-1983) German-American engineer. At Peenemuende from 1940, designed and operated V-2 test launch facility. In US from 1945, headed design, build, and operation of launch facilities for the V-2, Redstone, Jupiter, and Saturn rockets for Apollo.
Japanese communications technology satellite. One launch, 1990.02.07. Boom, umbrella test. DEBUT "Orizuru". Experiment of extending and contracting boom; experiment of expanding and contracting aerodynamic brake. Launching organization NASDA.
The decibel is a ratio of two numbers, equal to the tenth root of ten or about 1.259. It is mostly used as the ratio of two power levels. If a radio receiver, playing at a certain "volume" level. is turned up until the acoustic power output has increased by 25.9%, its new level is one decibel above the original level.
Dediu, Dumitru (1942-) Romanian pilot cosmonaut, 1978-1981. Rumanian Air Force. Served in the Rumanian Army as Lieutenant Colonel, stationed in Bucharest.
Dedkov, Anatoli Ivanovich (1944-) Belarusian pilot cosmonaut, 1970-1983.
American comet probe. One launch, 2005.01.12. Studied interior composition of Comet Tempel 1. The flyby spacecraft carried a smaller impactor which it released, allowing it to study the plume from the collision with the comet on 2005.07.04.
American asteroid probe. One launch, 1998.10.24. Deep Space 1 (DS1) was a primarily a technology demonstration probe powered by an ion engine, although the spacecraft also flew by asteroid and cometary targets.
Defender.
Alternate designation for Bambi military anti-ballistic missile satellite.
Defense Meteorological Satellite Program.
Alternate designation for DMSP Block 4A earth weather satellite.
Defense Research Agency.
Second name of Farnborough
Defense Research Agency.
Third name of Farnborough
Defense Satellite Communications System.
Alternate designation for DSCS II military communications satellite.
Defense Support Program.
Alternate designation for DSP military early warning satellite.
Defense System.
American manufacturer of spacecraft. Defense Systems Inc, USA.
DeFrance, Smith J (1896-1985) American engineer. Designer and director of research for wind tunnels at Langley, 1922-1940, and Ames, 1940-1965. His work in the 1950's established blunt-body shapes for re-entry vehicles.
Diethylene glycol dinitrate
Degenkolb, Gerd German Phantom cosmonaut. Leader of the Special Group for the A4 and supervisor of manufacturing for the 'war locomotive'.
Degrees Kelvin. A degree of temperature on the Kelvin scale also called '`absolute scale." The Kelvin zero point is approximately -273.1° Centigrade. A degree Kelvin is equal in magnitude to a degree on the Centigrade scale.
Degtyarov, Dr Vladimir Aleksandrovich (1932-) Russian physician cosmonaut, 1965-1966.
DEI.
Design (development) engineering inspection
Air-launched rocket drop zone known to have been used for 62 launches from 1962 to 1968, reaching up to 95 kilometers altitude.
Runway
Dutch technology satellite. One launch, 2008.04.28. Technical University of Delft nanosat.
Dellmeier German Engineer. Engineer at Peenemuende.
American orbital launch vehicle. The Delta launch vehicle was America's longest-lived, most reliable, and lowest-cost space launch vehicle. Delta began as Thor, a crash December 1955 program to produce an intermediate range ballistic missile using existing components, which flew thirteen months after go-ahead. Fifteen months after that, a space launch version flew, using an existing upper stage. The addition of solid rocket boosters allowed the Thor core and Able/Delta upper stages to be stretched. Costs were kept down by using first and second-stage rocket engines surplus to the Apollo program in the 1970's. Continuous introduction of new 'existing' technology over the years resulted in an incredible evolution - the payload into a geosynchronous transfer orbit increasing from 68 kg in 1962 to 3810 kg by 2002. Delta survived innumerable attempts to kill the program and replace it with 'more rationale' alternatives. By 2008 nearly 1,000 boosters had flown over a fifty-year career, and cancellation was again announced.
The Delta launch vehicle was America's longest-lived, most reliable, and lowest-cost space launch vehicle. Development began in 1955 and it continued in service in the 21st Century despite numerous candidate replacements.
American orbital launch vehicle. The military Thor-Delta vehicles were developed into the first of a series of commercial satellite launch vehicles. The Delta 0100 series featured Castor 2 solid propellant strap-ons and a Long Tank Thor core with MB-3 engine.
American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x DSV-3N-4
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x DSV-3N-4
American orbital launch vehicle. The Delta 1000 series used Castor 2 strap-ons and the Extended Long Tank core with MB-3 engine.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 4,472/590 kg. Thrust 35.10 kN. Vacuum specific impulse 278 seconds.
American orbital launch vehicle. Three stage vehicle consisting of 4 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201
American orbital launch vehicle. Four stage vehicle consisting of 6 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta F + 1 x Star 37C
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta F
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201 + 1 x Star 37D
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201 + 1 x Star 37C
American orbital launch vehicle. The Delta 6000 series used the Castor 4A strap-ons with the ultimate Extra Extended Long Tank core with RS-27 engine.
American orbital launch vehicle. The Delta 7000 series used GEM-40 strap-ons with the Extra Extended Long Tank core, further upgraded with the RS-27A engine.
American orbital launch vehicle. The Delta 2000 series used Castor 2 strap-ons together with an Extended Long Tank core equipped with the more powerful RS-27 engine. This engine was derived from surplus H-1 engines intended for the Saturn IB booster of the Apollo programme. The Delta P upper stage was built by Douglas and used surplus Apollo lunar module engines from TRW.
American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201
American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37D
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37D
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37E
American orbital launch vehicle. Delta 3 was an attempt by the manufacturer to provide the ultimate development of the original Delta booster. The core vehicle was beefed-up to accomodate much larger solid rocket boosters and a new cryogenic upper stage. However problems were incurred during development, resulting in the first two launches being failures. Meanwhile the satellite launch market crashed and the new vehicle was left without customers. The venerable Delta 7925 soldiered on for NASA, and the new Delta 4 series captured the USAF EELV requirement.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 104,377/6,822 kg. Thrust 1,085.79 kN. Vacuum specific impulse 302 seconds. The first stage of the Delta III is powered by a Rocketdyne RS-27A main engine which has a 12:1 expansion ratio and employs a turbine/turbopump, a regeneratively cooled thrust chamber and nozzle, and a hydraulically gimbaled thrust chamber and nozzle that provides pitch and yaw control.
American orbital launch vehicle. The Delta 3000 series upgraded the boosters to Castor 4 solid propellant strap-ons, while retaining the Extended Long Tank core with RS-27 engine. The 3910 series used the TRW Lunar Module engine in the second stage, while the 3920 series reintroduced the Aerojet AJ110 Delta engine.
Lox/LH2 propellant rocket stage. Loaded/empty mass 19,300/2,476 kg. Thrust 110.03 kN. Vacuum specific impulse 462 seconds. The upgraded cryogenic second-stage Pratt & Whitney RL10B-2 engine is based on the 30-year heritage of the reliable RL10 engine. It incorporates an extendable exit cone for increased specific impulse (Isp) and payload capability.
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P + 1 x Star 48B
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37N
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37E
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K + 1 x Star 48B
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K + 1 x Star 37E
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K + 1 x Star 48B
American space tug. One launch, , 2002. Upper stage / space tug - in production. Delta 3 second stage with hydrogen tank stretch.
Lox/LH2 propellant rocket stage. Loaded/empty mass 24,170/2,850 kg. Thrust 110.05 kN. Vacuum specific impulse 462 seconds. Delta 3 second stage with hydrogen tank stretch.
American orbital launch vehicle. The Delta 4000 series used more powerful Castor 4A strap-ons, but the old Extended Long Tank core with MB-3 engine. Only two of these were launched.
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor /MB-3 + 1 x Delta K + 1 x Star 48B with 2.4 m (8 foot) diameter fairing)
Delta 4H.
Alternate designation for Delta IV Heavy orbital launch vehicle.
Lox/LH2 propellant rocket stage. Loaded/empty mass 30,710/3,490 kg. Thrust 110.05 kN. Vacuum specific impulse 462 seconds. Delta 4 second stage with hydrogen tank increased to 5.1 m diameter.
American space tug. Study 2001. Upper stage / space tug - in production. Delta 4 second stage with hydrogen tank increased to 5.1 m diameter.
Delta 4M.
Alternate designation for Delta IV Medium orbital launch vehicle.
Delta 4M+(4,2).
Alternate designation for Delta IV Medium+ (4.2) orbital launch vehicle.
American orbital launch vehicle. The Delta 5000 series used the more powerful Castor 4A strap-ons but with the Extended Long Tank core with RS-27 engine. Only one was launched.
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K with 2.4 m (8 foot) diameter fairing)
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K with 2.4 m (8 foot) diameter fairing)
Three stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K with 3.05 m (10 foot) diameter fairing
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K + 1 x Star 48B
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K + 1 x Star 48B with 2.4 m (8 foot) diameter fairing)
American orbital launch vehicle. Three stage vehicle consisting of 3 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K
American orbital launch vehicle.
American orbital launch vehicle. Four stage vehicle consisting of 3 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 37FM with 2.9 m (9.5 foot) diameter fairing)
American orbital launch vehicle.
Three stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter composite fairing
American orbital launch vehicle. Four stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 3.05 m (10 foot) diameter fairing
American orbital launch vehicle. Four stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 2.9 m (9.5 foot) diameter fairing)
American orbital launch vehicle. Four stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 37FM with 2.9 m (9.5 foot) diameter fairing)
American orbital launch vehicle. Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter long fairing
American orbital launch vehicle. Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 2.4 m (8 foot) diameter fairing)
American orbital launch vehicle. Version of Delta 7000 using much larger GEM 46 solid rocket motors originally developed for the Delta 3.
Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter fairing
Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter composite fairing
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 3.05 m (10 foot) diameter fairing
American orbital launch vehicle.
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 2.4 m (8 foot) diameter fairing)
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 2.9 m (9.5 foot) diameter fairing)
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-46 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B
Delta 8930.
Alternate designation for Delta 3 orbital launch vehicle.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 2,164/694 kg. Thrust 33.80 kN. Vacuum specific impulse 271 seconds. Able was only the first of many engine and application programs that flowed from the Vanguard experience base. These included Able, Ablestar, Delta, Fat Delta, the Japanese N II, and applications or offshoots such as Hydra, Saint (Satellite Intercept), and other classified programs.
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-21 + 1 x AJ10-118 + 1 x Altair
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-21 + 1 x AJ10-118A + 1 x Altair
American orbital launch vehicle. Unaugmented Thor with Delta D and solid propellant upper stages.
Delta Clipper.
Manufacturer's designation for DC-Y ssto vtovl orbital launch vehicle.
Delta Clipper.
Manufacturer's designation for DC-Y manned spacecraft.
Delta Clipper Experimental.
Manufacturer's designation for DC-X vtovl test vehicle.
Delta Clipper-Experimental.
Alternate designation for DC-X vtovl test vehicle.
Delta Clipper-Prototype.
Alternate designation for DC-X2 ssto vtovl orbital launch vehicle.
American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta D + 1 x Altair 2
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 2,693/545 kg. Thrust 33.70 kN. Vacuum specific impulse 278 seconds.
American orbital launch vehicle. Thor augmented with 3 x Castor 2 motors with Delta E and Altair 2 upper stage.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 6,009/785 kg. Thrust 35.10 kN. Vacuum specific impulse 278 seconds.
American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E + 1 x FW4D
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 5,629/784 kg. Thrust 41.36 kN. Vacuum specific impulse 280 seconds.
American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E
Delta III.
Alternate designation for Delta 3 orbital launch vehicle.
The Delta IV was the world's first all-Lox/LH2 launch vehicle and represented the only all-new-technology launch vehicle developed in the United States since the 1970's. It was the winner of the bulk of the USAF EELV orders and was based on the all-new RS-68-powered Lox/LH2 cryogenic Common Booster Core (CBC). This could be used with new Delta cryogenic upper stages powered by the RL10 engine but unrelated to previous Centaur upper stages.
American orbital launch vehicle. The Delta IV was the world's first all-Lox/LH2 launch vehicle and represented the only all-new-technology launch vehicle developed in the United States since the 1970's. It was the winner of the bulk of the USAF EELV orders and was based on the all-new RS-68-powered Lox/LH2 cryogenic Common Booster Core (CBC). This could be used with new Delta cryogenic upper stages powered by the RL10 engine but unrelated to previous Centaur upper stages. It could be flown without augmentation, or use 2-4 large GEM-60 solid rocket boosters. The heavy lift version used two core vehicles as a first stage, flanking the single core vehicle second stage.
American orbital launch vehicle. Heavy lift all-cryogenic launch vehicle using two Delta-4 core vehicles as first stage flanking a single core vehicle as second stage. A heavy upper stage is carried with a 5 m diameter payload fairing.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding RS-68B upgraded engines to the core vehicles and an AUS-60 upper stage powered by 2 MB-45 or RL-45 20 tonne thrust Lox/LH2 engines. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters, RS-68 Regen upgraded engines with regeneratively-cooled nozzles to the core vehicles, and cryogenic propellant densification. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding new RS-800 engines to the core vehicles, an AUS-60 upper stage powered by 2 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters, RS-68 Regen upgraded engines with regeneratively-cooled nozzles to the core vehicles, cryogenic propellant densification, and an AUS-60 upper stage powered by 1 MB-60 or RL-60 27 tonne thrust Lox/LH2 engine. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 6 GEM-60 solid rocket boosters, RS-68B upgraded engines to the core vehicles, and an AUS-60 upper stage powered by 1 MB-60 or RL-60 27 tonne thrust Lox/LH2 engine. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters, RS-68 Regen upgraded engines with regeneratively-cooled nozzles to the core vehicles, cryogenic propellant densification, and cryogenic propellant cross-feed between the strap-ons and core. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering five common booster modules, using an AUS-60 upper stage powered by 2 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, and using an AUS-60 upper stage powered by 2 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines. A payload fairing over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using an AUS-60 upper stage powered by 3 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines. A payload fairing over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using an AUS-60 upper stage powered by 3 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using a new RS-800K engine in the booster stages, and an AUS-60 27 tonne thrust Lox/LH2 upper stage. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using a new RS-800K engine in the booster stages, an AUS-60 upper stage powered by 4 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Basic Delta-4 vehicle with no strap-ons, the core vehicle, and RL10B-1 upper stage with a 4 m diameter payload fairing. World's first all-cryogenic launch vehicle.
American orbital launch vehicle. As Delta 4 medium but with 2 x GEM-60 solid rocket boosters and a 4 m diameter payload fairing.
American orbital launch vehicle. As Delta 4 medium but with 2 x GEM-60 solid rocket boosters and a 5 m diameter payload fairing.
American orbital launch vehicle. As Delta 4 medium but with 4 x GEM-60 solid rocket boosters and a 5 m diameter payload fairing.
American orbital launch vehicle. Light launch vehicle using the Delta-4 core with the traditional Delta K and PAM-D upper stages. 2 m diameter payload fairing. Not flown as of 2008 but cancellation of the Delta II could lead to its eventual use.
American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E + 1 x Star 37D
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 6,954/950 kg. Thrust 43.63 kN. Vacuum specific impulse 319 seconds.
American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor DSV-2L-1B + 1 x Delta E + 1 x FW4D
American orbital launch vehicle. Long Tank Thor augmented with 3 Castor 2 boosters and Delta E / Burner 2 (Star 37D) upper stages.
American orbital launch vehicle. Four stage vehicle consisting of 6 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x Delta E + 1 x Star 37D
American orbital launch vehicle. Long Tank Thor augmented with 3 Castor 2 boosters and Delta E upper stage.
American orbital launch vehicle. Three stage vehicle consisting of 6 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x Delta E
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 5,434/820 kg. Thrust 41.92 kN. Vacuum specific impulse 301 seconds.
Lox/LH2 propellant rocket stage. Loaded/empty mass 226,400/26,760 kg. Thrust 3,312.76 kN. Vacuum specific impulse 420 seconds. Low cost expendable stage using lower performance engine. Used in Delta 4, Boeing EELV. Engine can be throttled to 60%.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 84,067/4,059 kg. Thrust 1,030.21 kN. Vacuum specific impulse 296 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 70,354/3,715 kg. Thrust 866.71 kN. Vacuum specific impulse 290 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 84,368/4,360 kg. Thrust 1,030.22 kN. Vacuum specific impulse 296 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 49,442/3,175 kg. Thrust 866.71 kN. Vacuum specific impulse 290 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 101,700/5,690 kg. Thrust 1,032.00 kN. Vacuum specific impulse 295 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 101,900/5,900 kg. Thrust 1,054.20 kN. Vacuum specific impulse 302 seconds.
European manufacturer of spacecraft. Delta Utec, Europe.
A change in velocity.
DeLucas, Dr Lawrence James 'Larry' (1950-) American physiologist payload specialist astronaut. Flew on STS-50.
Dementiev, Petr Vasilyevich (1907-1977) Russian politician. Minister of Aviation Industry 1953-1977. Supporter of Chelomei.
French earth seismology satellite. One launch, 2004.06.29. Demeter studied disturbances of the ionosphere due to seismo electromagnetic effects and human activities (power lines, VLF transmitters, HF broadcasting stations).
Demin, Lev Stepanovich (1926-1998) Russian engineer cosmonaut. Flew on Soyuz 15.
WRE solid rocket engine.
Dempsey, James Raymon (1921-) American engineer. Headed development of the Atlas missile at Convair.
Demyanenko, Anatoly Pavlovich (1942-1971) Russian engineer cosmonaut, 1969-1971. Engineer at the Scientific Research Institute of Automatics and Instrument Engineering. On 11 September 1969 selected as a cosmonaut, but the selection was not confirmed by the government commission.
South African manufacturer of spacecraft. Denel, South Africa.
Deng Qingming Chinese pilot taikonaut, 1998-on. PLAAF pilot. Selected in the first Chinese cosmonaut detachment.
Denmark
Denner German Wehrmacht Officer; expert in biological warfare during World War II.
Denver, John (1943-1997) American pop singer who sought to fly into space before his death in an air crash.
DEP.
Diethylphtalate (solid fuel plasticizer)
Deppe, Hans German-American expert in guided missiles during WW2. Member of the German rocket team, arrived in America under Project Paperclip on 1945.11.16 aboard the Argentina from La Havre. As of January 1947, working at Fort Bliss, Texas.
DERA.
Defense Eval. and Research Agency, Farnborough, UK
Headquarters of an RVSN Division, 1965-1996. Operated 52 heavy ICBM silos (R-36/R-36M2).
Descent Module.
Alternate designation for MRC DM manned spacecraft module.
Descent Stage.
Alternate designation for Apollo LM DS manned spacecraft module.
Category of launch vehicles.
American manned Mars expedition. Study 1993. The Design Reference Mission 1.0 was the Space Exploration Initiative's last gasp.
American manned Mars expedition. Study 1996. This July 1997 DRM was a subscale version of the original, with a scrub of the original payloads to reduce mass wherever possible.
Design Reference Mission 4 NTR.
American manned Mars expedition. Study 1998. The design reference mission 4.0 took into account all of the changes in payload masses as a result of further study of individual elements.
Design Reference Mission 4 SEP.
American manned Mars expedition. Study 1998. In 1998 NASA Lewis studied a Solar Electric Transfer Vehicle for use in a Mars Expedition. This would never leave earth orbit yet provide most of the delta-V to send a spacecraft toward Mars.
Russian intercontinental ballistic missile. Silo-launched version, silo hardened to 15-30 atmospheres overpressure.
Desna-N.
Alternate Designation of Romashka intercontinental ballistic missile.
Desna-V.
Launch System of Desna intercontinental ballistic missile.
A drying agent.
Detroye, Jeffrey Eliot (1955-) American engineer military spaceflight engineer astronaut, 1979-1985. Bachelor of science in astronautical engineering from USAF Academy, 1977. From 1986 worked as a Shuttle Flight Controller.
Dettmering, Wilhelm Heinrich (1912-) German Professor. Worked at Peenemuende West.
Deucker German rocket technician in WW2; later worked in France at LRBA in the theoretical group of the target acquisition department from 1947-1952.
Deutch, John (1938-) American scientist, served as Deputy Secretary of Defense from 1994-199; Director of Central Intelligence from 1995-1997. Doctorate from MIT and also served as that school's dean of science and provost.
Deutsche Aerospace.
Third name of DASA
Deutsche Aerospace.
Fourth name of MBB
American manufacturer. Developmental Sciences, USA.
Deversoir
Dezhurov, Vladimir Nikolayevich (1962-) Russian pilot cosmonaut. Flew on Mir EO-18, ISS EO-3. Made nine spacewalks, total time 1.58 days.
DF-1.
Chinese version of Soviet R-2.
DF-1.
CALT Liquid oxygen/Alcohol rocket engine. 270 kN.
DF-1 (before 1964).
Alternate designation for DF-3 intermediate range ballistic missile.
Chinese single-stage solid-propellant short range ballistic missile. Export designation M-11, assembled as Ghaznavi in Pakistan.
Sanjiang solid rocket engine. 93.2 kN.
Lox/Alcohol rocket stage. 270.00 kN (60,698 lbf) thrust. Mass 14,000 kg (30,865 lb).
Solid rocket stage. 93.20 kN (20,952 lbf) thrust. Mass 5,400 kg (11,905 lb).
Solid rocket stage. 93.20 kN (20,952 lbf) thrust. Mass 5,400 kg (11,905 lb).
Family of launch vehicles.
Chinese mobile single-stage solid propellant intermediate range ballistic missile.
China ARMT solid rocket engine.
Solid propellant rocket stage. Loaded mass 6,200 kg.
DF-2.
First Chinese IRBM, a single stage missile with the objective of carrying a 1500 kg warhead to Japan. The starting point for the design were R-12 construction drawings and a single exemplar of the missile provided by the Soviet Union prior to the break with Moscow in 1960. Following protracted development the design was accepted by the Chinese military for service in 1970.
DF-2.
First Chinese IRBM, a single stage missile with the objective of carrying a 1500 kg warhead to Japan. The starting point for the design were R-12 construction drawings and a single exemplar of the missile provided by the Soviet Union prior to the break with Moscow in 1960. Following protracted development the design was accepted by the Chinese military for service in 1970.
Family of launch vehicles.
Chinese two-stage solid propellant intermediate range ballistic missile.
Nitric acid/kerosene rocket stage. 300.00 kN (67,443 lbf) thrust. Mass 30,000 kg (66,139 lb).
Shanxi solid rocket engine.
Shanxi solid rocket engine.
Solid propellant rocket stage. Loaded mass 4,000 kg.
Chinese intermediate range ballistic missile. Extended-range version of DF-2. The missile featured reduced thrust, but 20% more range, and used autonomous gyroscopic guidance in place of the DF-2's radio system.
Nitric acid/kerosene rocket stage. 300.00 kN (67,443 lbf) thrust. Mass 30,000 kg (66,139 lb).
DF-3.
The DF-3 project began in 1964 with the objective of developing a nuclear-tipped missile capable of reaching the Philippines (earlier referred to as the DF-1).
DF-3.
Chinese intermediate range ballistic missile. The DF-3 project began in 1964 with the objective of developing a nuclear-tipped missile capable of reaching the Philippines (earlier referred to as the DF-1).
Development of the original DF-3 10,000 km missile was undertaken personally by Tsien Hue Shen, the father of Chinese rocketry, but faced insurmountable technical and management difficulties. It was cancelled and replaced by the DF-4.
Chinese intercontinental ballistic missile. Version of JL-2. Mobile, solid propellant, land-based, medium range, three-stage ballistic missile. Basis for the KT-1 light orbital launch vehicle.
Version of JL-2. Mobile, solid propellant, land-based, medium range, three-stage ballistic missile. Basis for the KT-1 light orbital launch vehicle. The missile was tested on the ground in 1995. Ejection tests from the transport-launch tube began in 1998. The first flight test took place on 1 August 1999. Deployment was not expected until 2005-2010.
Shanxi solid rocket engine.
Shanxi solid rocket engine.
Shanxi solid rocket engine.
Chinese intermediate range ballistic missile.
DF-4.
Chinese intermediate range ballistic missile. Development of the DF-4 began in 1964 with the objective of fielding a ballistic missile capable of hitting Guam. The technical solution was to add a second stage to the DF-3 IRBM.
New Chinese solid propellant, mobile ICBM. The DF-41 is expected to be a longer-range version of the DF-31. It is still in the development stage, with deployment not expected until after 2010.
DF-5.
Development of the the DF-5 began in 1964. The goal was an ICBM capable of reaching the United States. Although deployed in very limited numbers as an ICBM, this rocket became the basis for an entire family of space launch vehicles and the foundation of the Chinese space program.
Chinese intercontinental ballistic missile.
Chinese intercontinental ballistic missile. Modernised DF-5 incorporating guidance and propulsion improvements developed for the CZ-series of launch vehicles.
DFBW.
Digital fly-by-wire program
DFH.
Chinese manufacturer of spacecraft. Aerospace Dongfanghong Satellite Ltd, China.
Chinese communications technology satellite. 3 launches, 1969.11.16 (DFH Mao 1) to 1971.03.03 (SJ-1). First Chinese satellite. The initial satellite was flown for purely propaganda purposes, using a tune generator to play the 'East is Red'.
Chinese military communications satellite. 7 launches, 1984.01.29 (STTW-T1) to 1991.12.28 (Zhongxing-4). The DFH-2 was a spin-stabilized, drum-shaped military communications satellite with a despun antenna, a diameter of 2.1 m, and a height of 3.1 m.
Fourth Academy solid rocket engine. 43.460 kN. DFH series apogee kick motor. Out of Production. Isp=287s. First flight 1984. First use in China of glass fibre wound cases, carbon/carbon nozzle throat insert material, contoured divergent nozzle.
Chinese military communications satellite using indigenous technologies. Operational, first launch 1994.02.08.
Large Chinese communications satellite bus using a blend of Chinese and subcontracted European technologies. Operational, first launch on 2006.10.28 (Xinnuo 2).
DFRC.
Dryden Flight Research Center
DFRF.
Dryden Flight Research Facility (was ADFRF, now DFRC)
DFS.
Multipurpose communications.
DFV.
First Owner of DFVLR
German agency overseeing development of spacecraft. Deutsche Forshungs- und Versuchsanstalt für Luft- und Raumfahrt, Germany.
DGA.
French agency overseeing development of spacecraft. Delegation Generale de l'Armament, France.
Indian short-range, sea-based, liquid-propellant ballistic missile thought to be a variant of the Prithvi.
Dhom.
Dhom, Friedrich (1909-1988) 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 Brownsboro, Texas.
French earth geodetic satellite. 2 launches, 1967.02.08 (Diademe 1) and 1967.02.15 (Diademe 2). French geodetic satellites.
French technology satellite. One launch, 1970.03.10. Engineering package; monitored launch vehicle performance.
German technology satellite. One launch, 1970.03.10, DIAL-WIKA.
French orbital launch vehicle. In December 1961 France decided to demonstrate an indigenous satellite-launch capability, using stages in development for its ballistic missile program. Following careful evolutionary development, Diamant was successful on its first attempt in 1965. Improved versions were flown over the next ten years.
In December 1961 France decided to demonstrate an indigenous satellite-launch capability, using stages in development for its ballistic missile program. Following careful evolutionary development, Diamant was successful on its first attempt in 1965. Improved versions were flown over the next ten years.
French orbital launch vehicle. Diamant development could be done relatively quickly using stages and systems being developed for strategic missiles. In May 1962 CNES selected DMA as program manager, with SEREB as the prime contractor. The Diamant orbital launch vehicle was created by replacing the payload of the existing Saphir test vehicle with a new third stage. Prior to any all-up satellite launch attempt the P064 third stage was flight tested on the smaller suborbital Rubis test vehicle. This evolutionary approach paid off.
French orbital launch vehicle. As a follow-on to the Diamant-A, CNES decided to evolve a more capable launch vehicle. The Diamant-B used a new first stage with 50% more propellants and 33% more thrust; the same second stage; and a fatter third stage. Six Diamant-B boosters were ordered. Originally four of these were to be used to test the Europa 2 launch vehicle's Perigee-Apogee System. These tests were cancelled and instead CNES used five of the six boosters for orbital attempts.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 21,500/3,500 kg. Thrust 396.52 kN. Vacuum specific impulse 251 seconds.
Solid propellant rocket stage. Loaded/empty mass 800/120 kg. Thrust 50.00 kN. Vacuum specific impulse 211 seconds.
French orbital launch vehicle. In January 1972 a further evolution, the Diamant BP.4, was authorized. The second stage was replaced with the P4 Rita motor developed for the MSBS SLBM. The larger 1.38 m diameter fairing developed for the British Black Arrow launcher allowed larger payloads to be accommodated. Three launches of the BP.4 in 1975 completed the Diamant saga.
Solid propellant rocket stage. Loaded/empty mass 4,500/1,000 kg. Thrust 176.00 kN. Vacuum specific impulse 273 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 14,685/1,946 kg. Thrust 301.55 kN. Vacuum specific impulse 251 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 2,815/540 kg. Thrust 120.08 kN. Vacuum specific impulse 255 seconds.
Solid propellant rocket stage. Loaded/empty mass 703/68 kg. Thrust 29.40 kN. Vacuum specific impulse 211 seconds.
Boron 'zip' fuels were much in fashion in the late 1950's. They seemed to offer a means of boosting the performance of both aircraft (the B-70 bomber) and rockets. However expense, toxicity, and fouling of engines led to them being abandoned.
The property of a substance to appear in one color by reflected light and in another by transmitted light.
Dietrich, Jan (1926-2008) American pilot, one of the Mercury 13 female astroauts proposed in 1961, but never entered training.
Dietrich, Marion (1926-1974) American pilot, one of the Mercury 13 female pilots declared fit for astronaut duty in 1961, but never entered training.
In an atmosphere, as in any gaseous system, the exchange of fluid parcels between regions, in apparently random motions of a scale too small to be treated by the equations of motion.
Digges, Thomas (1576-1576) British astronomer and mathematician who modified Dante's medieval conceptions of the universe in his Description of the Caelestiall Orbes (1576), adopting a Copernican view that placed the Sun in the centre of the universe.
American agency overseeing development of spacecraft. DigitalGlobe, USA.
Category of persons.
Direct Measurement Explorer.
Alternate designation for DME earth ionosphere satellite.
DirecTV Incorporated began broadcast of satellite-to-home direct television services in mid-1994. Originally a subsidiary of Hughes Communications, the company faced as competitors the similar Primestar and USSB services, as well as older C-band satellite services and cable TV companies. By 2007 it had become the most successful American direct-broadcast television service.
American agency. DirecTV Inc. , USA
Disaster Monitoring Constellation.
Alternate designation for HJ-1 civilian surveillance satellite.
The Discovery program was begun by NASA in the early 1990s as the planetary counterpart to the Explorer program.
American manned spaceplane. 39 launches, 1984.08.30 to 2011.02.24.
American manufacturer of spacecraft. Discraft Corporation, USA.
Disney, Walt (1901-1966) Spanish-American creator of child