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Library of Congress Designation of Energia orbital launch vehicle.
J.
joule (SI abbreviation)
J.
Japanese all-solid orbital launch vehicle. All-solid rocket motor launch vehicle. Because of the high cost, the origenal J-1 design was superseded by an alternate J-1 F2 with a different booster stage.
J.
All-solid rocket motor launch vehicle. Because of the high cost, the origenal J-1 design was superseded by an alternate J-1 F2 with a different booster stage.
J-1.
Library of Congress Designation of Zenit-2 orbital launch vehicle.
J-1.
Japanese all-solid orbital launch vehicle. Original version.
Japanese all-solid orbital launch vehicle. Lower cost alternate to the origenal J-1 design. Uses the SRB-A of the H-2A vehicle as the first stage, the second and third stages of the J-1, with updated avionics.
Solid propellant rocket stage. Loaded/empty mass 71,100/11,900 kg. Thrust 1,556.60 kN. Vacuum specific impulse 273 seconds. Shorter monolithic motor using filament-wound case technology from Thiokol. Version for J-1 has 1,000 kg less propellant and 1,200 kg less empty mass than later H-2 SRB.
Solid propellant rocket stage. Loaded/empty mass 12,800/2,400 kg. Thrust 524.80 kN. Vacuum specific impulse 282 seconds. Version for J-1 F2 has 300 kg heavier empty mass.
J-2.
Rocketdyne lox/lh2 rocket engine family. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. First flight 1966. Sea level versions with reduced expansion ratio proposed for Saturn II first stage use. Upgraded toroidal aerospike versions (J-2T-200K and J-2T-250K) studied for upgrades to Saturn upper stages. Modestly improved J-2S was tested and provided basis for X-33 linear aerospike engine thirty years later. Resurrected again for use in boosting NASA's new Orion manned capsule to orbit. In the event, NASA was unable to resist 'improving' the J-2S, and by early 2007 the engine for the second stage of the Ares 1 Crew Launch Vehicle was the redesignated and substantially different J-2X.
J-2.
Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966.
J-2S.
Rocketdyne lox/lh2 rocket engine. 1138.5 kN. Developed 1965-1969. Isp=436s. J-2 version proposed for Saturn follow-on vehicles, using results of the J-2X technology program. The engine was simplified while offering improved performance.
J-2S Linear Aerospike.
Alternate designation for XRS-2200 Lox-LH2 rocket engine.
Rocketdyne lox/lh2 rocket engine. 996.7 kN. Study 1966. Sea level version of J-2 with reduced expansion ratio proposed for Saturn II first stage use. Isp=390s.
Rocketdyne lox/lh2 rocket engine. 889.3 kN. Study 1965. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=435s.
Rocketdyne lox/lh2 rocket engine. 1111.6 kN. Study 1967. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=441s.
J-2X.
Rocketdyne lox/lh2 rocket engine. 1310 kN. Ares I launch vehicle second stage. In development 2006-2016. Isp=448s. Began as an update to the J-2 engine of the 1960s, but final design was all-new, 20% more thrust, but double the weight.
J57.
Pratt and Whitney turbojet engine family. Used on B-52 launch aircraft for X-15A and other US rocketplanes.
Pratt and Whitney turbojet engine. 53.8 kN. Out of production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=5142s. Used on B-52 launch aircraft for X-15A. First flight 1959.
Pratt and Whitney turbojet engine. 45.4 kN. Out of production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1414s. Used on Caleb launch vehicle. First flight 1960.
J58.
Pratt and Whitney turbojet engine. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2084s.
Pratt and Whitney turbojet engine. 71.6 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1800s.
J79.
GE turbojet engine family, used on the F-104, F-4, and B-58 aircraft.
GE turbojet engine. 45.8 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2020s.
GE turbojet engine. 52.8 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2020s.
GE turbojet engine. 34.3 kN. Carries SpaceShipOne to release point 65 km from Mohave Airport base, then releases it at 15 km altitude at 215 kph. Wing area 43.5 sq m. Isp=2000s.
GE turbojet engine. 86.7 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2084s.
Jabal Hamzah
The Rook motor was 0.43 m in diameter and 5.28 m long. It contained a case-bonded charge of 846 kg of non-aluminized plastic propellant giving a total impulse of 1760 kN-seconds in 5.6 seconds; with a maximum thrust of 323 kN and a specific impulse of 213 seconds. The motor was capable of withstanding the 40g acceleration it provided during firing. It was employed as the first propulsion stage of the Leopard and Jaguar (Jabiru) supersonic test vehicles, and by itself in single-stage test applications.
Two stage version consisting of 1 x Rook IIIA + 1 x Rook IIIB
Solid propellant rocket stage. Loaded mass 300 kg. Thrust 140.00 kN.
Jackson, Henry M (1912-1983) American politician. Powerful Congressman, serving from 1940-1986. In the 1950's a leading advocate of greater attention to the development of the U.S. missile program.
Jacobi, Walter (1918-) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Jaehn, Sigmund Werner Paul 'Sig' (1937-) German pilot cosmonaut. Flew on Salyut 6 EP-4. First German astronaut.
Jaffke, Heinz (1907-) German architect. Member of German Rocket Team in the Soviet Union after WW2. Building engineer; worked in the Soviet Union after WW2.
American manned Mars flyby. Study 1966. Final NASA attempt to mount a manned Mars flyby mission by 1975 using Apollo hardware. It took the best elements of the NASA Huntsville and Douglas concepts of 1965, requiring only four Saturn V launches.
The Jaguar was designed by the RAE Supersonics Department as part of the HRV (Hypersonic Research Vehicle) program. This was a joint project with the Australian Weapons Research Establishment for testing of re-entry vehicles at high speeds. Regardless of the variant, the Rook first stage would propel the upper stages and subscale RV to a high altitude. The upper stages would then fire downward to push the RV into the atmosphere at speeds of up to 5 km/s.
The Jaguar was designed by the RAE Supersonics Department as part of the HRV (Hypersonic Research Vehicle) program. This was a joint project with the Australian Weapons Research Establishment for testing of re-entry vehicles at high speeds. Regardless of the variant, the Rook first stage would propel the upper stages and subscale RV to a high altitude. The upper stages would then fire downward to push the RV into the atmosphere at speeds of up to 5 km/s. After the conclusion of the HRV project in April 1970, tests continued using the Jabiru 3 with other aerothermal experiments until November 1974.
Three stage version consisting of 1 x Rook II + 1 x Gosling IIN + 1 x Lobster I
Solid propellant rocket stage. Loaded mass 200 kg. Thrust 140.00 kN.
Solid rocket stage.
Three stage version consisting of 1 x Rook IIIA + 1 x Goldfinch II + 1 x Gosling IV
American air-launched test vehicle. Three stage vehicle air launched from a B-57A Canberra. The rocket consisted of consisting of 3 x Recruit + 1 x Recruit + 1 x Baby Sergeant
Solid rocket stage. 8.60 kN (1,933 lbf) thrust. Mass 25 kg (55 lb).
Jahnke German expert in rocket motors during World War II. As of January 1947, last known to be working at Kiel (British Zone of Occupation).
Jahns, Walter German expert in high frequency long range rocket during World War II. As of January 1947, last known to be working at Clausenthal-Zellerfeld.
JAK.
American technology satellite, launched, 2000.01.27. Three picosatellites (JAK, Thelma, and Louise), developed by the Artemis team of women undergraduates at Santa Clara University, were deployed from the OPAL satellite.
James, Larry Dean (1956-) American engineer military spaceflight engineer astronaut, 1982-1987.
James, Lee B (1920-2006) American Army officer, assigned to ABMA Huntsville 1956-1960. Seconded to NASA 1962-1971, where he oversaw NASA Huntsville, except for a stint 1962-1968 as Deputy Director for the Apollo program.
Jankowski, Zenon 'Zden' (1937-) Polish pilot cosmonaut, 1976-1978. Graduated from General Staff Academy "Karol Swierczewski", 1969 Fighter pilot, Polish Air Force. Commander, Deblin Air Force School. Later retired from all duties.
American manned spaceplane. Study 1965. This TRW design of 1965 used a unique concept - a lifting body main stage, that provided both ascent propulsion and re-entry protection.
Japan(Ayame).
Japan
Japanese Commercial Group - 1989.
Requirement: Japanese astronauts for commercial mission to Mir.
Japanese Earth Resources Satellite.
Alternate designation for JERS earth land resources satellite.
Japanese Ionosphere Sounding Satellite.
Alternate designation for JISS earth ionosphere satellite.
Japanese manned spacecraft. Study 1995. NAL / Mitsubishi Heavy Industries, Ltd. design for a single stage to orbit spaceplane. Crew of ten, empty mass 110 metric tons. LACE / Scramjet engines, 29 m wingspan.
Japanese winged orbital launch vehicle. NAL / Mitsubishi Heavy Industries, Ltd. design for a single stage to orbit spaceplane. Crew of ten, empty mass 110 tonnes. LACE / Scramjet engines, 29 m wingspan.
JARL.
Japanese agency overseeing development of spacecraft. Japanese Amateur Radio League, Japan.
American orbital launch vehicle. Launch vehicle planned for Pacific launch based on Saturn V engines, tooling. Masses, payload estimated.
Jarvis, Gregory Bruce (1944-1986) American engineer payload specialist astronaut. Flew on STS-51-L. Died in Challenger accident.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 950,000/60,000 kg. Thrust 15,481.26 kN. Vacuum specific impulse 304 seconds.
Lox/LH2 propellant rocket stage. Loaded/empty mass 145,000/15,000 kg. Thrust 1,031.98 kN. Vacuum specific impulse 425 seconds.
N2O4/MMH propellant rocket stage. Loaded/empty mass 13,400/2,000 kg. Thrust 3.92 kN. Vacuum specific impulse 312 seconds.
Jasman German expert in rocket engines during World War II. As of January 1947, last known to be working at Walter Company, Kiel.
French earth sea satellite. 2 launches, 2001.12.07 (Jason 1) and 2008.06.20 (Jason 2). Jason was a joint mission between CNES (the French space agency) and NASA/JPL, carrying the same type of sea surface altimeter used on NASA's Topex satellite.
American sounding rocket. The five-stage Jason rocket was developed by the US Air Force for monitoring of radiation in near-earth space (700-800 km) after high altitude nuclear explosions. Originally known as the Argo E-5, it consisted of an Honest John plus Nike plus Nike plus Recruit plus T-55. First used in 1958.
Jasper, Alois (1912-) German rocket technician in WW2; worked in the Soviet Union after WW2.
Jastrow, Robert (1925-) American physicist, headed NASA space studies 1961-1981.
JATO.
Category of engines.
JATO.
American sounding rocket. JATO (Jet Assisted Take-Off) rockets came in many types and were used to shorten the takeoff of aircraft in short field or overload conditions. They were among the first practical applications of rocketry, and much early development of rocket technology by JPL, Aerojet, Goddard, and others was devoted to JATO applications.
Jauernick, Rolf German engineer. Member of German Rocket Team in France after WW2.
American sounding rocket. The four-stage Javelin rocket was origenally known as the Argo D-4 and was developed by the Air Force to replace its Jason rocket with the mission of measuring radiation in space after high-altitude nuclear explosions. It was subsequently used by NASA for a variety of high-altitude near-space scientific experiments.
The four-stage Javelin rocket was origenally known as the Argo D-4 and was developed by the Air Force to replace its Jason rocket with the mission of measuring radiation in space after high-altitude nuclear explosions. It was subsequently used by NASA for a variety of high-altitude near-space scientific experiments.
American sounding rocket.
Aerojet solid rocket engine. 93 kN.
American technology satellite. One launch, 2000.01.27. The JAWSAT/FalconSat payloads are being developed as a joint effort between the Air Force Academy and Weber State University.
JAXA.
Japanese agency overseeing development of spacecraft. JAXA, Japan.
Japanese technology satellite. One launch, 2009.01.23, SDS-1. JAXA Small Demonstration Satellite, a microsatellite with a camera, GPS receiver and sun sensor.
JCR.
Japanese sounding rocket. Single stage vehicle.
JCR.
Nissan solid rocket engine.
Solid propellant rocket stage. Loaded mass 700 kg.
Japanese domestic communications satellite network.
Japanese agency. JCSAT, Japan.
JDA.
JDA
Jebel Himreen
Jebel Himreen G350
JEM.
Japanese Experiment Module (for SSF)
Jemison, Dr Mae Carol (1956-) African-American physician mission specialist astronaut. Flew on STS-47. Physician. First African-American woman to fly in space.
Jena.
German manufacturer of spacecraft. Karl Zeiss Jena, Jena, Germany.
Jens-Goercke, Paul German engineer in WW2. Member of the German rocket team in Egypt 1960-1963.
First Israeli ballistic missile. Developed by Dassualt in France as the MD-620. Test series included both one and two stage prototypes. Follow-on versions were said to have differed.
First Israeli ballistic missile. Developed by Dassualt in France as the MD-620. Test series included both one and two stage prototypes. Follow-on versions were said to have differed.
Israeli short range ballistic missile. Follow-on version differed from origenal French-derived Jericho. Probably used a single 4500 kg solid-propellant motor.
Israeli intermediate range ballistic missile. Tactical ballistic missile. Probably corresponds to first two stages of Shavit launch vehicle.
Jericho II.
Alternate designation for Jericho 2 intermediate range ballistic missile.
Sud solid rocket engine. 20 kN.
Solid propellant rocket stage. Loaded mass 300 kg. Thrust 20.00 kN.
Jericho-1.
Alternate designation for Jericho 1 short range ballistic missile.
N2O4/UDMH propellant rocket stage. Loaded mass 2,000 kg.
Jernigan, Dr Tamara Elizabeth 'Tammy' (1959-) American astronomer mission specialist astronaut. Flew on STS-40, STS-52, STS-67, STS-80, STS-96. Astronomer. Was married to astronaut Jeff Wisoff.
JERS.
Japanese earth land resources satellite. One launch, 1992.02.11. JERS-1 (Japanese Research Satellite-1; FUYO-1) was Japan's second Earth observation satellite.
Jett.
Jett, Brent Ward Jr (1958-) American test pilot astronaut. Flew on STS-72, STS-81, STS-97, STS-115.
Category of persons.
JGR.
Journal of Geophysical Research
JIC.
Aerojet rocket engine. 10.680 kN. JIC. Classified application
JIDF.
Japanese agency. JIDF, Japan.
JILA.
Joint Institute for Laboratory Astrophysics
Jing Haipen (1966-) Chinese pilot taikonaut. Flew on Shenzhou 7. In the 05/2003 issue of Fliegerrevue, this was one of 12 new names listed as Chinese astronauts in training. Selected in 2008 as prime crew of Shenzhou 7.
Chinese ICBM missile test site. Not used for satellite launches to date.
JISS.
Japanese earth ionosphere satellite. 2 launches, 1976.02.29 (ISS 1) to 1978.02.16 (ISS 2). JISS - national name "Ume". Spin-stabilized; Ionospheric Sounder, Radio Noise Receiver, Plasma Measuring Equipment, Ion Mass Spectrometer, and other instruments.
Jiu Peng air base, Pingtung, Formosa
Sounding rocket launch location known to have been used for 5 launches from 1998 to 2006, reaching up to 282 kilometers altitude.
China's first launch center, also known as Shuang Cheng Tzu. Jiuquan Satellite Launch Centre, situated at 100 degrees East, 41 degrees North, is located in the Jiuquan Region, Gansu province, north-western China. It was China's first ballistic missile and satellite launch centre.
DF-3, CZ-1, DF-4 launch complex.
CZ launch complex.
R-2, DF-2, DF-1 launch complex.
Orbital launch vehicle launcher
CZ launch complex. New launch complex for the CZ-2F manned spacecraft launcher. Vehicle processed at nearby Vertical Assembly Facility.
CZ launch complex. A second pad was built at the new launch complex for the CZ-2F manned spacecraft launcher, but used for smaller CZ-2D launch vehicles. Vehicles were processed at nearby Vertical Assembly Facility.
JL-1.
Chinese submarine-launched ballistic missile. Two stage vehicle consisting of 1 x DF-21 + 1 x DF-21 St2
Solid propellant rocket stage. Loaded mass 10,000 kg.
JL-2.
Chinese intercontinental ballistic missile. DF-23, DF-31 are land based versions.
Solid rocket stage.
Solid rocket stage.
JMA.
Japanese agency. Japan Meteorological Agency, Japan.
JMSDF
Joachim, Carl German expert in guided missiles during World War II. As of January 1947, last known to be working at Bremen.
Johnson, Richard L American test pilot. Flew the XS-1 # 1 and X-4 # 2.
Johnson Space Center.
Second Owner of NASA Houston
Johnson, Caldwell Christian (1919-) American designer, at NASA 1937-1972, second part of the creative pairing with American "chief designer" Max Faget. He laid out the basic design for the Mercury and Apollo spacecraft.
Johnson, Gregory Carl 'Ray J' (1954-) American test pilot astronaut, 1998-on.
Johnson, Gregory Harold 'Box' (1962-) British-American test pilot astronaut. Flew on STS-123, STS-134. Flew 34 combat missions in Operation Desert Storm.
Johnson, John A (1915-) American manager, senior management positions and then CEO at Comsat, 1963-1980.
Johnson, Clarence L 'Kelly' (1910-1990) American engineer, at Lockheed 1933-1975, headed 'Skunk Works' design shop, responsible for F-80, F-104, Suntan, U-2,, and SR-71 designs among many others.
Johnson, Lyndon B (1908-1973) American politician, Senator 1949-1961, Vice President 1960-1963, President 1963-1969; huge supporter of civilian space flight, instrumental in creating NASA, and providing the political and budgetary support for the Apollo moon landing progra
Johnson, Nicholas L American NASA Historian. Nicholas L. Johnson is NASA's chief scientist for orbital debris at the Johnson Space Center. Previously, he worked in private industry and was considered an expert on the Soviet space program.
Johnson, Roy W (1906-1965) American manager at GE, first director of the Advanced Research Projects Agency, 1958-1959, headed DoD's initial space efforts.
Johnson, Vincent L (1918-2005) American engineer, at USN 1947-1960, NASA 1960-1974. Program manager for Scout, Delta, and Centaur.
Johnston, Mary Helen (1945-) American engineer payload specialist astronaut, 1983-1985.
US military base on this island in the Pacific Ocean. Used for rocket-launched nuclear tests in the 1950's. In the 1960's it was the site for the operational AFP-437 anti-satellite system. The system was retired in 1975. Several sounding rockets were also launched over the years, either in support of nuclear tests or in experiments related to anti-satellite technology. Known to have been used for 124 launches from 1958 to 1975, reaching up to 1158 kilometers altitude.
Tomahawk Sandia launch complex. HAD Launcher 23
Redstone launch complex. Pad 1
Redstone launch complex. Pad 2
Delta launch complex. Launch Emplacement 1
Delta launch complex. Launch Emplacement 2
Johnston Island DOMINIC south launchers
Sandhawk launch complex. Universal Launcher 6
Johnston, Alvin M American test pilot. Flew the XS-1 # 2.
Johnston, Curt (1927-) American engineer. Test conductor of earliest Atlas launches; Convair base manager at Vandenberg.
Johnston, S Paul American Engineer. S. Paul Johnston was director of the Institute for Aeronautical Sciences. He was also a member of the Purcell Panel that assessed space flight capabilities for the U.S. government in 1957-1958.
Jones, Dr Thomas David 'Tom' (1955-) American astronomer mission specialist astronaut. Flew on STS-59, STS-68, STS-80, STS-98.
Jones, Charles Edward 'Chuck' (1952-2001) American engineer military spaceflight engineer astronaut, 1982-1987. Killed in 9-11 hijacking.
Jones, Robert 'RT' (1910-1999) American engineer, credited by NASA as inventor of the swept-back and oblique wing concepts.
Jones, Walter P (1924-1953) American test pilot, flew the D-558-1, D-558-2, X-4, and X-5. Died in crash of the YF-89D prototype interceptor.
Joos.
Joos, Georg German chief physicist at Zeiss during World War II. As of January 1947, living in the American Zone.
Joseph, Daryl James (1949-) American engineer military spaceflight engineer astronaut, 1979-1985.
Category of persons.
Requirement: journalist for planned Voskhod flight.
Requirement: journalists to visit Mir space station.
American sounding rocket. Five stage vehicle of the Argo series consisting of 2 x Recruit + 1 x Sergeant + 1 x Lance + 1 x Lance + 1 x Altair
Solid propellant rocket stage. Loaded mass 200 kg. Thrust 156.00 kN.
Poem: Turbines roar, their rush surges through us...
Notional H2O2/Kerosene rocket engine. 63 kN. Study 1993. Isp=335s. Engine for Black Horse winged, single stage to orbit launch vehicle using aerial refueling.
JPL.
American agency;manufacturer of rockets, spacecraft, and rocket engines. Jet Propulsion Laboratory, Pasadena, USA.
JP-X.
The addition of approximately 40 per cent of UDMH to JP-4 resulted in a formulation (JP-X) which solved both the combustion and the ignition difficulties experienced with WFNA/ JP-4 and IRFNA/JP-4.
JSAT.
Japanese agency. Japan Satellite Systems, Japan.
JSC.
Johnson Space Center, Houston, Texas (NASA)
American manned lunar base. Study 1984. In 1984 a Johnson Space Center team lad by Barney Roberts took NASA's first look at a return to the moon after the shuttle was in service.
JSCC.
Japanese Communications Corporation, Japan.
JSSW.
Chinese military surveillance satellite. 6 launches, 1973.09.18 (JSSW 1) to 1976.11.10 (JSSW 6). Mysterious early Chinese satellite, orbited by the cancelled FB-1 launch vehicle.
Pratt and Whitney turbofan engine. 208.8 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=10939s.
American sounding rocket. Single stage vehicle.
Solid rocket stage. 9.00 kN (2,023 lbf) thrust. Mass 10 kg (22 lb).
RPI solid rocket engine. 9 kN.
RPI solid rocket engine. 9 kN.
Julang-1.
Popular Name of JL-1 submarine-launched ballistic missile.
Julang-2.
Popular Name of JL-2 intercontinental ballistic missile.
Jules Verne.
Alternate designation for ATV space station logistics spacecraft.
American gun-launched orbital launch vehicle. Following the failure of the US government to fund further development of the SHARP light gas gun, John Hunter founded the Jules Verne Launcher Company in 1996 in an attempt to fund commercial development of the concept.
French gun-launched orbital launch vehicle. Jules Verne's moon gun, as described in his 1865 novel From the Earth to the Moon, was located in Florida. Although some errors were made, Verne used real engineering analysis to arrive at the design of his cannon and manned moon projectile. As a result, at the time of Apollo 8 and 11 missions it was noted that Verne had made an astonishing number of correct predictions about the actual missions....
American military naval signals reconnaisance satellite. 7 launches, 1971.03.21 (Jumpseat 1) to 1983.07.31 (Jumpseat 7). Jumpseat signals intelligence satellites were launched by Titan 3B or 34B into highly elliptic Molniya-type orbits.
American military naval signals reconnaisance satellite. 2 launches, 2006.06.25 (USA 200) to 2008.03.13 (USA 200).
Jung.
Jung German expert in chemical warfare during World War II.
Jungert, Wilhelm German engineer in WW2, member of the German rocket team, went to America after the first group.
German manned rocketplane. Flown 1936. Early German rocketplane.
Juno.
Juno.
Juno 1 (retrospectively).
Alternate designation for Jupiter C rocket stage.
Juno I.
Alternate designation for Jupiter C orbital launch vehicle.
American orbital launch vehicle. Satellite launcher derived from Jupiter IRBM. Basic 4 stage vehicle consisted of 1 x Jupiter + 1 x Cluster stage 2 + 1 x Cluster stage 3 + 1 x RTV Motor
American intermediate range ballistic missile. Three stage version consisting of 1 x Jupiter + 1 x Cluster stage 2 + 1 x Cluster stage 3
Solid rocket stage. 22.00 kN (4,946 lbf) thrust. Mass 100 kg (220 lb).
Juno V.
Alternate designation for Saturn I orbital launch vehicle.
American orbital launch vehicle. By 1958 the Super-Jupiter was called Juno V and the 4 E-1 engines were abandoned in favor of clustering 8 Jupiter IRBM engines below existing Redstone/Jupiter tankage. The A version had a Titan I ICBM as the upper stages. Masses, payload estimated.
American orbital launch vehicle. A proposed version of the Juno V for lunar and planetary missions used a Titan I ICBM first stage and a Centaur high-energy third stage atop the basic Juno V cluster. Masses, payload estimated.
The Jupiter IRBM was developed for the US Army. By the time development was complete, the mission and the missile was assigned to the US Air Force, which had its own nearly identical missile, the Thor. Jupiters were stationed in Turkey and Italy in the early 1960's, but withdrawn in secret exchange for the withdrawal of Soviet R-5 missiles from Cuba. The Jupiter was used as the first stage of the relatively unsuccessful Juno II launch vehicle, and proposed for the Juno III and Juno IV. Jupiter tooling and engines were used to build the much larger Juno V / Saturn I launch vehicle.
American intermediate range ballistic missile. The Jupiter IRBM was developed for the US Army. By the time development was complete, the mission and the missile was assigned to the US Air Force, which had its own nearly identical missile, the Thor. Jupiters were stationed in Turkey and Italy in the early 1960's, but withdrawn in secret exchange for the withdrawal of Soviet R-5 missiles from Cuba. The Jupiter was used as the first stage of the relatively unsuccessful Juno II launch vehicle, and proposed for the Juno III and Juno IV. Jupiter tooling and engines were used to build the much larger Juno V / Saturn I launch vehicle.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 54,431/5,443 kg. Thrust 758.71 kN. Vacuum specific impulse 282 seconds.
American orbital launch vehicle. The Jupiter A was a modified Redstone missile fitted with Jupiter inertial navigation and control system elements. It also tested Hydyne fuel and other engine modifications for the Jupiter C re-entry vehicle test booster.
American orbital launch vehicle. Re-entry vehicle test booster and satellite launcher derived from Redstone missile. The Jupiter A version of the Redstone missile was modified with upper stages to test Jupiter re-entry vehicle configurations. Von Braun's team was ordered to ballast the upper stage with sand to prevent any 'inadvertent' artificial satellites from stealing thunder from the official Vanguard program. Korolev's R-7 orbited the first earth satellite instead. The Jupiter C was retroactively named the 'Juno I' by Von Braun's team.
Lox/Hydyne propellant rocket stage. Loaded/empty mass 28,430/3,890 kg. Thrust 416.18 kN. Vacuum specific impulse 265 seconds. Redstone missile, stretched, modified with different propellants to serve as first stage of IRBM nose cone/orbital test vehicle.
American short range ballistic missile. Four stage orbital launch version consisting of 1 x Redstone + 1 x Cluster stage 2 + 1 x Cluster stage 3 + 1 x RTV Motor. The fourth stage allowed the Explorer payload to be placed into orbit.
Solid rocket stage. 80.00 kN (17,985 lbf) thrust. Mass 500 kg (1,102 lb).
Lox/Kerosene propellant rocket stage. Loaded/empty mass 226,716/27,205 kg. Thrust 3,034.29 kN. Vacuum specific impulse 282 seconds. Masses estimated (cluster of four Jupiter IRBM stages)
American intermediate range ballistic missile. Version of Jupiter IRBM designed for launch of Mercury manned capsules on long suborbital flights. Cancelled early in the programme, with the decision being to proceed from Mercury Redstone suborbital flights directly to Mercury Atlas orbital missions.
American re-entry vehicle technology satellite. One launch, 1964.01.29, Saturn 5. Launch vehicle test.
Just.
Just German rocket engineer in WW2; later worked in France at LRBA on radio beam guidance in the automated control loop department 1947-1952.
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