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seconds (SI abbreviation); or S-, NASA Science experiments prefix
S.
Rocket stage used on S launch vehicle.
S.
Alternate designation for Tu-121 intermediate range cruise missile.
S.
Series of Japanese single-stage sounding rockets designed for low-cost observations of the ionosphere.
S.
Series of Japanese single-stage sounding rockets designed for low-cost observations of the ionosphere.
S A Kosberg.
First Owner of Kosberg
S P Izotov.
First Owner of Izotov
S/C.
Spacecraft
Isayev Nitric acid/Amine rocket engine. 88 kN. V-300/V-303 (S-25 system). Out of Production.
S09.29.0B.
Manufacturer's designation of S09.29 Nitric acid-Amine rocket engine.
Isayev Nitric acid/Amine rocket engine. R-101 SAM. Developed 1949-50. Launch thrust 78.4 kN. Four chamber engine designed for use in the R-101 (derivative of German Wasserfall). Abandoned by 1950 in favour of single-chamber engine.
S1.
Lox/UDMH propellant rocket stage. Loaded/empty mass 8,595/840 kg. Thrust 105.51 kN. Vacuum specific impulse 352 seconds.
S-1.
American earth magnetosphere satellite. 2 launches, 1959.07.16 (Explorer) to 1959.10.13 (Explorer 7). Magnetic field, solar flare data.
Korolev Lox/Kerosene rocket engine. 30 kN. R-7 verniers. Out of Production. Thrust variable 2.5-3.1 tf
Korolev Lox/Kerosene rocket engine family. Designed by Korolev; passed to Isayev for production. Began a series of engines leading through the 8D726 for GR-1 to the Block D for the N1 and Proton.
Korolev Lox/Kerosene rocket engine. 66.7 kN for Molniya 8K78 Stage 3. Flew 1960-1965. Isp=340s. Designed by Korolev; passed to Isayev for production. Began a series of engines leading through the 8D726 for GR-1 to the Block D for the N1 and Proton.
Korolev Lox/Kerosene rocket engine. 67.3 kN. Molniya 8K78M-3. Isp=342s. First flight 1964.
American pressure suit, operational 1965. Pressure suit which introduced many modifications from the early MC-3A capstan suits.
Solid rocket stage. 27.00 kN (6,070 lbf) thrust. Mass 30 kg (66 lb).
American pressure suit, operational 1968. A special variant of the S901, designated the S1010 PPA, was developed specifically for use in the U-2R aircraft in the mid-1960s.
Solid rocket stage. 4.20 kN (944 lbf) thrust. Mass 30 kg (66 lb).
S1024.
Manufacturer's designation for A-P22S-6 space suit.
S1024B.
Manufacturer's designation for A-P22S-6A space suit.
American pressure suit, tested 1965. Developmental bladder type partial pressure suit.
American pressure suit, operational 1970. Upgraded SR-71 full pressure suit, link net with integrated subsystems.
S1030A.
Manufacturer's designation for EES space suit.
American pressure suit, operational 1980. The S1010 and several S1010 dash variants were later replaced by a further advanced model, the S1031 PPA. The S1031 special projects full pressure suit came in 12 sizes and was used in the TR-1 and U-2R.
S1032.
Manufacturer's designation for Shuttle LES space suit.
American pressure suit, operational 1991.
S1035.
Manufacturer's designation for ACES space suit.
S1035X.
Manufacturer's designation for D-1 space suit.
S-125
S-15.
American solar satellite. One launch, 1961.04.27, Explorer 11. Gamma ray data.
Dushkin rocket engine. 39 kN. E-50. Developed 1955-56. Thrust variable 2000 - 4000 kgf.
S160.
Alternate designation for S-160-1 rocket stage.
Japanese sounding rocket. Single stage vehicle.
ISAS solid rocket engine.
Solid propellant rocket stage. Loaded mass 100 kg.
S-2.
American earth magnetosphere satellite. One launch, 1959.08.07, Explorer 6. First Earth photo; radiation data.
American pressure suit, operational 1953. The S-2 was a modified capstan partial pressure suit evolved from the T-1 with no anti-G and no chest bladder. It was produced in 12 sizes for bomber aircraft.
Isayev rocket engine. V-1000. Out of Production. OKB-2 transferred work on the S2.1100 to OKB-117 in 1958-59. OKB-117 completed development.
Isayev Nitric acid/Amine rocket engine. 671.2 kN. Burya booster. Out of production. Isp=250s. First flight 1957. Engines developed from R-11 S2.253 engine.
Isayev rocket engine. Developed 1950s middle. OKB-2 transferred work on the S2.1200 to OKB-154 in 1957. The latter used the designation RO-1 for the engine.
Isayev rocket engine. 88 kN. Developed 1950s early.
Isayev Nitric acid/Kerosene rocket engine family. R-11 (Scud B) .
Isayev Nitric acid/Kerosene rocket engine. 93.3 kN. R-11 (Scud B) 8A61. Thrust 8300 kgf at sea level. Fuel Kerosene T-1, chemical ignition by TG-02. Isp=251s. First flight 1953.
Isayev Lox/Kerosene rocket engine. 93.2 kN. EKR (experimental winged missile). Study 1953. Derivative of S2.253 was proposed for use in EKR Stage 1 (project for an experimental winged missile). Isp=250s.
Isayev Nitric acid/Kerosene rocket engine. 93 kN. R-11FM. Out of Production. Used in R-11FM submarine version of Scud B. Fuel Kerosene T-1, chemical ignition by TG-02. Mixture ratio derived from tank content. 81 kN sea-level.
Isayev Nitric acid/Amine rocket engine. 252.2 kN. R-13 (SS-N-4). Out of Production. First engine to employ gas generator on main propellants. One main and four vernier thrusters. (Mixture derived ratio from tank content.)
Isayev Nitric acid/Amine rocket engine. 34.3 kN. Engine for SAM-missile V-755. Out of Production. Pump-fed engine. Used in engine unit of a special apparatus. Pump-fed engine. 20,4 kN sea level.
Isayev Nitric acid/Amine rocket engine. 11.8 kN. KSR. Developed 1956-.
SKB-30 Nitric acid/Amine rocket engine. 103 kN.
S-20.
Solid rocket stage. 36.00 kN (8,093 lbf) thrust. Mass 300 kg (661 lb).
S-20.
Avibras solid rocket engine. 36 kN.
S-200.
Russian surface-to-air missile. Enormous surface-to-air missile developed by Grushin after the failure of the Dal project. Deployed in limited numbers and exported to countries in the mideast to defend against American high-altitude, high-speed SR-71 reconnaissance aircraft.
Enormous surface-to-air missile developed by Grushin after the failure of the Dal project. Deployed in limited numbers and exported to countries in the mideast to defend against American high-altitude, high-speed SR-71 reconnaissance aircraft.
S-200D.
Complex of V-880M surface-to-air missile.
S-200M.
Complex of V-880 surface-to-air missile.
S-200V.
Complex of V-860PV surface-to-air missile.
S210.
Alternate designation for S-210-1 rocket stage.
ISAS solid rocket engine family.
Japanese sounding rocket. Single stage ionospheric sounding rocket used for research from Japan's Antarctic base.
ISAS solid rocket engine.
Solid propellant rocket stage. Loaded mass 200 kg.
Russian anti-ballistic missile. Anti-ballistic missile system developed in parallel with the A-35, but not put into production.
S-23.
Avibrassolid rocket engine. 18 kN.
S-23.
Solid rocket stage. 18.00 kN (4,047 lbf) thrust. Mass 200 kg (441 lb).
S-25.
Complex of 207A surface-to-air missile.
S-25.
S-25.
Russian surface-to-air missile. First surface-to-air missile deployed by the Soviet Union. Under a crash program ordered by Stalin, development began in 1951, first guided launch was in 1953, and by 1956, 2,640 launchers were deployed in defence of Moscow. The system was upgraded with improved missiles and ground systems into the 1960's.
S-25.
First surface-to-air missile deployed by the Soviet Union. Under a crash program ordered by Stalin, development began in 1951, first guided launch was in 1953, and by 1956, 2,640 launchers were deployed in defence of Moscow. The system was upgraded with improved missiles and ground systems into the 1960's.
Japanese sounding rocket. Single stage vehicle.
Solid propellant rocket stage. Loaded mass 200 kg.
S-25MA.
Complex of 217 surface-to-air missile.
S-25MAM.
Complex of 217M surface-to-air missile.
S-25Mr.
Complex of 218 surface-to-air missile.
S3.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 20,135/1,435 kg. Thrust 156.00 kN. Vacuum specific impulse 303 seconds. Launch count 411 orbital and ca. 300 suborbital to end 1994. Failures based on proration of failures to orbit.
S-3.
Rocketdyne Lox/Kerosene rocket engine family. Jupiter, Juno II, Saturn A-2 studies of 1959.
S-3.
Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Juno II, Saturn A-2 studies of 1959. Isp=282s. First flight 1958.
Sevruk rocket engine. 166 kN. 217. Out of Production.
S-30.
American earth ionosphere satellite. One launch, 1960.11.03, Explorer 8. Ionospheric research.
S-30.
IAE solid rocket engine. 20.490 kN. Development ended 1997. Isp=275s.
S-30.
Solid rocket stage. 102.00 kN (22,931 lbf) thrust. Mass 1,200 kg (2,646 lb).
S300.
Alternate designation for S-300-1 rocket stage.
Third generation family of surface-to-air missiles developed in the 1970's based on new principles. The same launch system could use either 5V55 or 48N6 series missiles, of both mid- and long-range types.
Russian surface-to-air missile. Third generation family of surface-to-air missiles developed in the 1970's based on new principles. The same launch system could use either 5V55 or 48N6 series missiles, of both mid- and long-range types.
ISAS solid rocket engine.
Japanese sounding rocket. The the S-300, was developed for observations in Antarctica, in parallel with the S-210.
Solid propellant rocket stage. Loaded mass 500 kg.
Russian surface-to-air missile. Naval version of the S-300 system using the 5V55RM missile. Maximum target speed 4680 kph.
Russian surface-to-air missile. Naval version of the S-300 system using the 48N6Ye missile. Maximum target speed 10,000 kph.
Russian surface-to-air missile. Original version of the S-300 system for the PVO Air Defence Force using the 5V55R missile
S-300PMU-1.
Launch System of S-300PMU-1 48N6E, S-300PMU-1 5V55U, S-300PMU-1 9M96, S-300PMU-1 9M96E, and S-300PMU-1 9M96E2 surface-to-air missiles.
Russian surface-to-air missile. Version of the S-300 system for the land forces and export using the advanced 48N6E missile, which doubled the range and greatly increased the effectiveness of the system. Alternatively any of the earlier model 5V55 or 48N6 series missiles could be loaded.
Russian surface-to-air missile. Version of the S-300PMU system for export using the 5V55U missile.
Russian surface-to-air missile. New version of S-300PMU with 9M96E and 9M96E2 rockets. The system could also fire earlier-model 5V55 or 48N6 series rockets.
Russian surface-to-air missile. Shorter range version of 9M96.
Russian surface-to-air missile. Longer range version of 9M96.
Russian surface-to-air missile. Version of the S-300 system for export using the advanced 48N6E2 missile, capable of shooting down tactical ballistic missiles.
S-300V.
Launch System of Antey-2500, 9M82, and 9M83 surface-to-air missiles.
Mobile, multiple-target, universal integrated surface-to-air missile. The S-300V system can fire either of two versions of the containerised missiles loaded: long range and medium range. These missiles are given different NATO designations. However any mix of the two missiles can be loaded as needed in the vertical launcher cells.
Russian surface-to-air missile. Mobile, multiple-target, universal integrated surface-to-air missile. The S-300V system can fire either of two versions of the containerised missiles loaded: long range and medium range. These missiles are given different NATO designations. However any mix of the two missiles can be loaded as needed in the vertical launcher cells.
S-31.
IAE solid rocket engine. 240 kN.
S-31.
Solid rocket stage. 240.00 kN (53,954 lbf) thrust. Mass 900 kg (1,984 lb).
S310.
ISAS solid rocket engine family.
Japanese sounding rocket. The S-310 was a mid-sized single-stage sounding rocket designed to reach an altitude of 200 km.
ISAS solid rocket engine.
Solid propellant rocket stage. Loaded mass 600 kg.
Dushkin Nitric acid/Kerosene rocket engine. U-21. Developed -1959. Launch thrust 29.4 kN.
S-3D.
Rocketdyne Lox/Kerosene rocket engine. Launch thrust 600.1 kN. Jupiter Booster. Gas generator, pump-fed. Thrust later 150,000 lbs. Thrust and specific impulse values are at sea level. First flight 1957.
S-4.
American pressure suit, operational 1955. The S-4 was a modified S-2 partial pressure suit, no anti-G, chest bladder incorporated for ease of breathing.
S-4.
Rocketdyne Lox/Kerosene rocket engine. 412.8 kN. Design ca. 1957. Version of Atlas sustainer tailored to Redstone Arsenal upper-stage requirements. Paper study only. Used on Super Jupiter launch vehicle.
S-400.
Russian surface-to-air missile. Fourth generation surface-to-air missile system that replaced the Army's S-300V (SA-12) and the Air Defence Force's S-300PMU (SA-10). The system would feature twice the engagement area of the S-300PMU. Initial service was by the end of 2007.
Fourth generation surface-to-air missile system that replaced the Army's S-300V (SA-12) and the Air Defence Force's S-300PMU (SA-10). The system would feature twice the engagement area of the S-300PMU. Initial service was by the end of 2007.
IAE solid rocket engine. 208.4 kN. Isp=272s. Used on VLS launch vehicle. First flight 1985.
Solid propellant rocket stage. Loaded/empty mass 5,664/1,212 kg. Thrust 208.39 kN. Vacuum specific impulse 275 seconds.
S-43.
IAE solid rocket engine family. Used on VLS launch vehicle.
S-43.
IAE solid rocket engine. 303 kN. Isp=265s. Used on VLS launch vehicle. First flight 1985.
S-43.
Solid propellant rocket stage. Loaded/empty mass 8,550/1,328 kg. Thrust 303.00 kN. Vacuum specific impulse 260 seconds.
IAE solid rocket engine. 321.7 kN. Isp=276s. Used on VLS launch vehicle. First flight 1985.
Solid propellant rocket stage. Loaded/empty mass 8,720/1,536 kg. Thrust 320.60 kN. Vacuum specific impulse 277 seconds.
S-44.
IAE solid rocket engine. 33.2 kN. Isp=282s. Used on VLS launch vehicle. First flight 1985.
S-44.
Solid propellant rocket stage. Loaded/empty mass 1,025/190 kg. Thrust 33.24 kN. Vacuum specific impulse 282 seconds.
S-46.
American earth magnetosphere satellite. One launch, 1960.03.23, Explorer.
S5.1.
Isayev Nitric acid/Amine rocket engine. 167 kN. SAM-missiles 217M and 218. Out of Production. Designation unknown.
S5.19.
Alternate designation for KDU-414 Nitric acid-UDMH rocket engine.
S5.23.
Alternate designation for 11D49 Nitric acid-UDMH rocket engine.
S5.23, D-25.
Alternate designation for RD-861 N2O4-UDMH rocket engine.
S5.3.
Isayev Nitric acid/Amine rocket engine family. R-21 (SS-N-5). First engine to start underwater.
S5.3.
Isayev Nitric acid/Amine rocket engine. 392 kN. R-21 (SS-N-5). Out of Production. First engine to start underwater. 392 kN sea-level.
S5.35 + S5.60.
Alternate designation for KTDU-35 Nitric acid-UDMH rocket engine.
Isayev Nitric acid/Amine rocket engine. 396.7 kN. R-9 (SS-8) missile stage 1. Out of Production. Proposed for R-9 missile stage 1. Four engines per stage. 396,7 kN sea-level.
S5.4.
Isayev Nitric acid/Amine rocket engine. 15.830 kN. Vostok/Voskhod retorfire engine; spacecraft maneuvering engine. . Out of Production. Includes 4 small lateral steering nozzles. Isp=266s.
Isayev Nitric acid/Amine rocket engine. 177 kN. SAM-missile 5Ya24. Out of Production. Could be throttled. 177-49 kN sea-level. Area ratio 118 - 44.
Isayev Nitric acid/UDMH rocket engine. 1961 kN. correction engine for Zond-1, Venera-2-8, and others. Out of Production. Pressure-fed engine. Used as correction engine for spacecraft Zond-1, Vernera-8, and others. Isp=267s.
S5.5, S5.5A.
Alternate designation for KTDU-5A Nitric acid-Amine rocket engine.
Isayev N2O4/UDMH rocket engine. 33.196 kN. Hardware 1969. Isp=314s. Complex engine used to maneuver the LOK to a rendezvous with the LK lander in lunar orbit, then propel the LOK out of lunar orbit. Verniers included for midcourse corrections.
S5.53.
Alternate designation for KTDU-53 Nitric acid-UDMH rocket engine.
S5.61.
Alternate designation for KRD-61 N2O4-UDMH rocket engine.
S5.66.
Alternate designation for KTDU-66 Nitric acid-UDMH rocket engine.
S5.79.
Alternate designation for KRD-79 N2O4-UDMH rocket engine.
S5.80.
Alternate designation for KTDU-80 N2O4-UDMH rocket engine.
Isayev Lox/Kerosene rocket engine. 2.940 kN. Soyuz-2 Blok LM. Developed 1990s. Thrust chamber from KTDU-80 / S5.80 converted to burn Lox/Kerosene.
Isayev N2O4/UDMH rocket engine. 19.6 kN. Phobos propulsion module, later adapted as Fregat upper stage. In production. Isp=327s. Gas generator cycle. Nominal and low-thrust thrust levels.
Isayev N2O4/UDMH rocket engine. 19.62 kN. Used on Briz and Briz-M upper stages. Isp=325s. Engine system consists of: main engine (2000 kgf, Isp=325.5s) + 4x11D458 (40 kgf, Isp=252s) + 12x17D58E (1.36 kgf, Isp=247s). 8 restarts. First flight 1990.
S-500.
Launch System of R-500 surface-to-air missile.
New anti-aircraft, anti-missile system design in competitive development with Antey's S-400 to produce a Russian equivalent to THAAD.
Japanese sounding rocket. The S-520 was a larger single-stage rocket which could be equipped with a three-axis attitude control and a recovery system. It had the capability of launching a 100 kg payload above 300 km and provided more than five minutes of micro-gravity flight for experiments.
ISAS solid rocket engine. 143.1 kN.
S-55.
American earth micrometeoroid satellite. 4 launches, 1961.06.30 (Explorer (13) S 55) to 1964.11.06 (Explorer 23). Micrometeoroid research.
S-56.
American earth atmosphere satellite. 2 launches, 1960.12.04 (Explorer (9) S 56) to 1961.02.16 (Explorer 9). 12 foot diameter. balloon; atmospheric density studies.
American military target satellite. One launch, 1974.04.10.
S-75.
Known in the west as the SA-2 Guideline, this weapon was responsible for the downing of more American aircraft than any missile in history. It was deployed worldwide beginning in 1957, and improvements and updates, many by third parties, continued into the 21st Century.
S-75.
Russian surface-to-air missile. Known in the west as the SA-2 Guideline, this weapon was responsible for the downing of more American aircraft than any missile in history. It was deployed worldwide beginning in 1957, and improvements and updates, many by third parties, continued into the 21st Century.
Russian surface-to-air missile. Last production version. Fakel-designed missile; Almaz upgrade offered.
French communications technology satellite. Study 1992. Experimental communications satellite.
American pressure suit, operational 1962. A-12, F-12A and SR-71 full pressure suit; integrated subsystems, parachute harness, automatic flotation system, urine collection device, redundant pressure control and breathing system, thermal protective garment.
American space suit, cancelled 1962. Full Pressure Suit for the X-20A Dyna-Soar program.
SA.
Spectrum Astro, Gilbert, Arizona, USA; or Re-entry capsule (Russian abbreviation)
S-A.
Japanese sounding rocket. Single stage vehicle.
S-A.
Mitsubishi solid rocket engine.
Solid propellant rocket stage. Loaded mass 100 kg.
SA-1.
Department of Defence designation of S-25 missile.
SA-10.
Department of Defence Designation of S-300P and S-300PMU-1 5V55U surface-to-air missiles.
SA-12.
Department of Defence designation of S-300V missile.
SA-12a.
SA-12b.
The Spectrum Astro SA-200 satellite bus provided a flexible platform for satellites launched by the Pegasus booster. 4 launches, 2000.07.19 (Mightysat 2.1) to 2009.05.05.
SA-200HP.
Manufacturer's bus designation for Deep Space 1 asteroid probe and Coriolis earth sea satellite.
SA-200LL.
Manufacturer's designation for Swift gamma ray astronomy satellite.
SA-200S.
Manufacturer's designation for HESSI solar satellite.
SA-21.
Department of Defence designation of S-500 missile.
SA-2A,B.
Department of Defence Designation of S-75 surface-to-air missile.
SA-2C,D,E,F.
Department of Defence Designation of S-75M surface-to-air missile.
SA-4.
Department of Defence Designation of Krug surface-to-air missile.
SA-5.
SA-5A.
SA-5B.
Department of Defence Designation of V-860PV surface-to-air missile.
SA-5C.
SA-6.
Department of Defence Designation of Kub surface-to-air missile.
SAA.
South Atlantic Anomaly
Saab.
Swedish manufacturer. Saab Dynamics AB, Sweden.
German manufacturer of rockets. Saar Roechling, Germany.
Saber.
ASCC Reporting Name of 15Zh45, 15Zh45UTTKh, and 15Zh53 intermediate range ballistic missiles.
Rolls Royce air augmented rocket engine. Used Air/Lox/LH2. Developed -1995. Isp=700s. In development for Skylon launch vehicl; descendent of RB545 developed for abandoned HOTOL space launcher.
American manned spaceplane. Study 2004. X-Prize suborbital spaceplane concept of Panaero, Fairfax, Virginia. It envisioned conversion of a Sabre-40 business jet to rocket power.
SAC.
SAC (Satélite de Aplicaciones Científicas) was a series of Argentine satellites devoted to proving and developing Argentinan space technology.
Argentinan technology satellite. One launch, 1998.10.29. The Scientific Applications Satellite-S (SAC-A) was a small, ejectable, low cost Argentinean satellite that was launched during the STS-88 Space Shuttle Endeavour mission.
Argentinan solar satellite. One launch, 1996.11.04. SAC-B, an Argentine / US mission, was designed to study solar physics and astrophysics through the examination of solar flares, gamma-ray burst sources and the diffuse soft X-ray cosmic background.
Argentinan earth land resources satellite. One launch, 2000.11.21. The SAC-C Satelite de Aplicaciones Cientificas C was developed by the Argentine space agency CONAE and built by the Argentine company INVAP.
Sacco, Dr Albert Jr 'Al' (1949-) American chemical engineer payload specialist astronaut. Flew on STS-73.
SACI.
Brazilian technology satellite. 2 launches, 1999.10.14 (SACI 1) and 1999.12.11 (SACI-2). INPE experimental scientific satellites; carried a magnetometer, particle detectors and an atmospheric experiment.
Saddler.
German sled-launched intercontinental boost-glide missile. Saenger-Bredt antipodal bomber - sled launched, boosted to suborbital velocity, 'skips' off upper atmosphere to deliver bombload on target, recovery back at launch site. Fascinated Stalin, led to US Dynasoar project.
Saenger, Eugen Albert (1905-1964) German-Austrian rocket pioneer; designer of Silverbird space bomber. Worked at Trauen for Luftwaffe 1936-1944 on rocket and ramjet development; for the French 1946-1954. Research in Germany 1954-1963 included winged shuttle designs.
German manufacturer of rockets, spacecraft, and rocket engines. Saenger, Germany.
German winged orbital launch vehicle. Final version of the Saenger spaceplane, as conceived by Eugen Saenger during his lifetime. A rocket propelled sled would be used for horizontal launch of delta-winged, rocket-propelled first and second stages.
German manned spaceplane. Study 1964. MBB design for a vertical-launch, horizontal landing two-stage winged launch vehicle.
Proposed two stage to orbit vehicle. Air-breathing hypersonic first stage and delta wing second stage. The German Hypersonics Programme and its Saenger II reference vehicle received most of the domestic funding for spaceplane development in the late 1980s and early 1990s.
European manned space station. Study 2020. The ATV could evolve towards an unmanned free-flying laboratory providing a better microgravity level than the ISS.
American anti-ballistic missile. Safeguard ABM system consisted of Sprint and Spartan missiles
German civilian store-dump communications satellite. One launch, 1998.07.10. Relay satellite built by OHB System of Bremen.
Iranian technology satellite. Study 2005. Minimum satellite equipped like the first Sputnik with only a transmitter to confirm that it achieved orbit. Planned for launch by the Iranian Shahab-3 launcher in early 2005.
Iran's first orbital launch vehicle, based on the Shahab 3 intermediate range ballistic missile with upper stages.
SAGA.
Solar Array Gain Augmentation (for HST)
Sagdeyev, Roald Z (1932-) Russian astronomer, involved in virtually every lunar and planetary probe launched by the Soviet Union.
SAGE.
American earth atmosphere satellite. One launch, 1979.02.18. Studied dust, liquid droplets in upper atmosphere.
SAIC.
American manufacturer of spacecraft. Science Applications International Corporation, USA.
Japanese sounding rocket. Single stage vehicle.
Mitsubishi solid rocket engine.
Solid rocket stage.
American military anti-satellite system. Cancelled 1963.
American manned combat spacecraft. Cancelled 1961. At the beginning of the 1960's, the USAF examined a number of approaches to a manned spacecraft designed to rendezvous with, inspect, and then, if necessary, destroy enemy satellites.
Saint-Jacques, David (1970-) Canadian physicist mission specialist astronaut, 2009-on.
Sakr.
Egyptian manufacturer. Sakr Factory, Egypt.
SAL.
Scientific Airlock.
Saley, Yevgeni Vladimirovich (1950-) Russian pilot cosmonaut, 1976-1987.
American manned spaceplane. Study 1965. 1965 concept for a manned spaceplane equipped with drop tanks, which would be air-launched from a C-5
Sallwey, Hans German expert in rocket turbopumps during World War II. As of January 1947, working at Langen/Frankfurt.
SALT.
Strategic Arms Limitation Treaty; preceded by Strategic Arms Limitation Talks
Salter, Robert M (1920-) American physicist, at North American, 1946-1948; Rand, 1948-1954; Lockheed, 1954-1959. Responsible for much of the early studies of earth satellites, especially reconnaisance satellites.
Salto di Quirra, in southeast Sardinia near the town of Perdas de Fogu, is an inter-service missile test center operated by the Italian Air Force. It also supports sounding rocket launches and test of larger rockets in support of Italy's abandoned ballistic missile and on-and-of satellite launcher programs.
Scout launch complex. San Lorenzo pad
The world's first space station, developed in one year by the Soviet Union on the basis of Chelomei's Almaz station, in an attempt to upstage the American Skylab after the loss of the moon landing race to the Americans.
Russian manned space station. 2 launches, 1971.04.19 (Salyut 1) and 1972.07.29 (Zarya s/n 122). Salyut 1 was the first DOS long duration orbital station.
Russian manned space station. 2 launches, 1973.05.11 (Cosmos 557) to 1974.12.26 (Salyut 4). Four of the initial DOS-1 versions of a civilian Soviet space station were built using converted Almaz military stations.
Mishin was authorised in December 1973 to build an improved design DOS-5 version of the Salyut station using Almaz facilities. Mishin's bureau borrowed the two docking port configuration of Chelomei's Almaz OPS-2 This station's second docking port would allow rotation of crews and resupply/refueling using unmanned Progress spacecraft.
Russian manned space station. One launch, 1977.09.29. The Salyut 6 space station was the most successful of the DOS series prior to Mir. It was aloft for four years and ten months, completing 27,785 orbits of the earth.
Crew: Grechko, Romanenko. Record flight duration. First mission to receive visiting crews launched aboard another spacecraft, and to be resupplied by a logistics spacecraft. First Soviet EVA since Voskhod 2. First Main Expedition aboard Salyut 6. Backup crew: Ivanchenkov, Kovalyonok.
Crew: Ivanchenkov, Kovalyonok. Record flight duration. Manned two crew. Docked with Salyut 6. First transfer of a Soyuz from the aft port to the front port of a space station. Backup crew: Lyakhov, Ryumin.
Crew: Lyakhov, Ryumin. Record flight duration. Manned two crew. Docked with Salyut 6. Repaired the propulsion system, which had sprung leaks. Backup crew: Lebedev, Popov.
Crew: Popov, Ryumin. Record flight duration. Manned two crew. Docked with Salyut 6. Backup crew: Andreyev, Zudov.
Crew: Kizim, Makarov, Strekalov. Manned three crew. Docked with Salyut 6. Tested the improved Soyuz T; carried out repair and preventive maintenance work and some scientific and technical investigation and experiments. Backup crew: Kovalyonok, Polyakov, Savinykh.
Crew: Kovalyonok, Savinykh. Manned two crew. Docked with Salyut 6. Carried out repair and preventive maintenance work and some scientific and technical investigation and experiments. Backup crew: Andreyev, Zudov.
Crew: Dzhanibekov, Makarov. First docking to a space station of two manned spacecraft at one time. First station 'lifeboat' swap. First crew to visit another already aboard a space station. Backup crew: Ivanchenkov, Kovalyonok.
Crew: Popov, Prunariu. First Rumanian astronaut. Manned two crew. Docked with Salyut 6. Mission to swap Soyuz lifeboats docked to station. Backup crew: Dediu, Romanenko.
Crew: Gubarev, Remek. First Czech astronaut. Mission to swap Soyuz lifeboats docked to station. Backup crew: Pelczak, Rukavishnikov.
Crew: Hermaszewski, Klimuk. First Polish astronaut. Manned two crew. Docked with Salyut 6. Mission to swap Soyuz lifeboats docked to station. Backup crew: Jankowski, Kubasov.
Crew: Bykovsky, Jaehn. First German astronaut. Manned two crew. Docked with Salyut 6. Mission to swap Soyuz lifeboats docked to station. Backup crew: Gorbatko, Koellner.
Crew: Farkas, Kubasov. First Hungarian astronaut. Mission to swap Soyuz lifeboats docked to station. Backup crew: Dzhanibekov, Magyari.
Crew: Ivanov Georgi, Rukavishnikov. First Bulgarian astronaut. Manned two crew. Mission to swap Soyuz lifeboats docked to station. Backup crew: Aleksandrov Aleksandr, Romanenko.
Crew: Aksyonov, Malyshev. Test flight of new Soyuz T spacecraft; docked with Salyut 6. Backup crew: Kizim, Makarov.
Crew: Gorbatko, Tuan. First Vietnamese astronaut. Mission to swap Soyuz lifeboats docked to station. Backup crew: Bykovsky, Liem.
Crew: Romanenko, Tamayo-Mendez. First Cuban astronaut. Mission to swap Soyuz lifeboats docked to station. Backup crew: Khrunov, Lopez-Falcon.
Crew: Dzhanibekov, Gurragcha. First Mongolian astronaut. Manned two crew. Docked with Salyut 6. Mission to swap Soyuz lifeboats docked to station. Backup crew: Ganzorig, Lyakhov.
Russian manned space station. One launch, 1982.04.19. Salyut 7 was the back-up article for Salyut 6 and very similar in equipment and capabilities.
Due to cancellation of the Almaz military station, and delays in the Mir project, the decision was taken in the late 1970's to fly the back-up to DOS-5 / Salyut 6. This was launched as Salyut 7 in 1982. The opportunity was still taken to fly 'guest cosmonauts' from friendly countries on short visits to the stations, although emphasis was placed on military experiments. Salyut 7 was able to conduct significant military experiments thanks to the greatly increased volume and payload of the TKS modules diverted from the Almaz programme that docked with the station.
Crew: Berezovoi, Lebedev. Record flight duration. Ejected a 28-kg amateur radio satellite from a Salyut 7 trash airlock; called this the first launch of a communications satellite from a manned space vehicle. Backup crew: Strekalov, Titov Vladimir.
Crew: Aleksandrov, Lyakhov. Manned two crew. Docked with Salyut 7. Unloaded cargo from Cosmos 1443; loaded 350 kg of payload into it for return to earth. Backup crew: Strekalov, Titov Vladimir.
Crew: Atkov, Kizim, Solovyov Vladimir. Record flight duration. Crew entered the failed darkened station carrying flashlights. Reactivated station, attempted propellant system repairs. After their departure the unoccupied space station abruptly ceased communicating. Backup crew: Polyakov, Savinykh, Vasyutin.
Crew: Savinykh. First manned operations in a second space station module. The three-man EO-4 TKS-3 crew conducted military experiments with the Cosmos-1686 module. Mission was cut short due to an incapacitating psychological condition developed by Vasyutin. Backup crew: Aleksandrov, Popov.
Crew: Dzhanibekov. First docking with and repair of dead-in-space station. Crew carried out emergency repairs. Backup crew: Aleksandrov, Popov.
Crew: Vasyutin, Volkov Aleksandr. First manned operations in a second space station module. The three-man EO-4 TKS-3 crew conducted military experiments with the Cosmos-1686 module. Mission was cut short due to an incapacitating psychological condition developed by Vasyutin. Backup crew: Saley, Strekalov, Viktorenko.
Crew: Chretien, Dzhanibekov, Ivanchenkov. First French astronaut. Manned three crew. Mission to swap Soyuz lifeboats docked to station. Backup crew: Baudry, Kizim, Solovyov Vladimir.
Crew: Popov, Savitskaya, Serebrov. Second woman in space, launched for propaganda purposes ahead of first flight of NASA female astronauts aboard the shutle. Mission to swap Soyuz lifeboats docked to station. Backup crew: Pronina, Romanenko, Savinykh.
Crew: Malyshev, Sharma, Strekalov. First Indian astronaut. Mission to swap Soyuz lifeboats docked to station. Backup crew: Berezovoi, Grechko, Malhotra.
Crew: Dzhanibekov, Savitskaya, Volk. First woman to walk in space, accomplished for propaganda purposes ahead of plans for NASA female astronaut EVA. Mission to swap Soyuz lifeboats docked to station. Backup crew: Ivanova, Savinykh, Vasyutin.
Crew: Grechko. Mission to swap Soyuz lifeboats docked to station and conduct an inspection of the repairs conducted the the Soyuz T-13 crew. Backup crew: Saley, Strekalov, Viktorenko.
Crew: Glazkov, Makrushin, Stepanov Eduard. Planned TKS manned mission to Salyut 7 station. Cancelled December 1981; TKS-2 flew unmanned to Salyut 7 as Cosmos 1443. Backup crew: Artyukhin, Yuyukov, Berezovoi.
Crew: Sarafanov, Romanov, Preobrazhensky. Planned second manned flight of TKS ferry to the Salyut 7 space station. The crews were assigned in September/October 1979. Cancelled December 1981. Flew unmanned to Salyut 7 as Cosmos 1686. Backup crew: Artyukhin, Yuyukov, Berezovoi.
SAM-A-18 / M3.
Alternate Designation of MIM-23A surface-to-air missile.
SAM-A-19.
Department of Defence Designation of Plato anti-ballistic missile.
SAM-A-25.
Alternate designation of Nike Hercules missile.
SAM-A-7 / M1.
Alternate Designation of Nike Ajax surface-to-air missile.
SAM-D.
Alternate designation for MIM-104A missile.
Sammeck, Albert German designer for rockets during World War II. As of January 1947, living at Munich, Gladbach.
SAM-N-2.
Department of Defence Designation of Lark surface-to-air missile.
SAM-N-4.
Alternate Designation of Lark surface-to-air missile.
SAM-N-6.
Alternate designation of Talos missile.
SAM-N-6B.
Alternate Designation of RIM-8A surface-to-air missile.
SAM-N-6B1.
Alternate Designation of RIM-8C surface-to-air missile.
SAM-N-6B1-CW.
Alternate Designation of RIM-8G surface-to-air missile.
SAM-N-6BW.
Alternate Designation of RIM-8B surface-to-air missile.
SAM-N-6BW1.
Alternate Designation of RIM-8D surface-to-air missile.
SAM-N-6C1.
Alternate Designation of RIM-8E surface-to-air missile.
SAM-N-7.
Alternate Designation of RIM-2A surface-to-air missile.
Samokutyayev, Aleksandr Mikhailovich (1970-) Russian pilot cosmonaut, 2003-on. Flew on ISS EO-27.
Russian manned rocketplane. Cancelled 1949. Bisnovat was assigned the project to develop an all-Soviet equivalent to the 346 supersonic rocketplane being developed by the German Roessing team in OKB-2.
Samonov, Vladimir Ivanovich (1924-) Russian officer. Major General, Chief Engineer of GUKOS 1970-1980. In 1955 assigned to Baikonur, where participated in launch of first Sputnik, Vostok, and planetary probes. Responsible for completion of Zenit reconnaissance satellite.
American military surveillance satellite. 17 launches, 1960.10.11 (Samos 1) to 1962.11.11 (Samos 11). First generation photo surveillance; return of camera and film by capsule; program still partially classified, evidently due to embarrassment.
American earth magnetosphere satellite. One launch, 1992.07.03.
Space and Missile Systems Organization
Samsung.
Military facility on the California Channel Islands, used for rocket launches in support of other missile tests from Vandenberg or Point Mugu. In use from 1957. Known to have been used for 10 launches from 1958 to 1984, reaching up to 672 kilometers altitude. Later plans were made for an off-shore launch platform here for the Starstruck vehicle.
Dolphin launch complex.
Italian earth atmosphere satellite. 5 launches, 1964.12.15 (San Marco 1) to 1988.03.25 (San Marco D/L). Atmospheric density studies.
In 1962 NASA signed an agreement with the Centro Ricerche Aerospaziali at the University of Rome creating the San Marco program. The purpose of the program was to place an Italian satellite in orbit and to create an Italian equatorial launch site for the Scout rocket. Permission was obtained from Kenya to emplace two modified oil platforms off their coast, on the equator. The Santa Rita platform would serve as a launch control center and would also be used for launch of sounding rockets. The San Marco platform would be dedicated to launch of Scout rockets to orbit.
Apache launch complex. Santa Rita Platform
Military facility on the California Channel Islands, used for rocket launches in support of other missile tests from Vandenberg or Point Mugu. Known to have been used for 35 launches from 1957 to 2004, reaching up to 443 kilometers altitude.
SA-N-2.
Department of Defence Designation of V-753 surface-to-air missile.
SA-N-6.
Sandal.
Sandal; SS-4; 8K63; R-12; 63; 11K63.
Alternate designation for Kosmos A-1 rocket stage.
The Sandhawk motor was developed for Sandia primarily for use in multi-stage rockets launched in support of Atomic Energy Agency activities. It was however flown as a single-stage vehicle in initial tests of the motor and some subsequent scientific mission.s
American sounding rocket. The Sandhawk motor was developed for Sandia primarily for use in multi-stage rockets launched in support of Atomic Energy Agency activities. It was however flown as a single-stage vehicle in initial tests of the motor and some subsequent scientific mission.s
American sounding rocket. Two stage vehicle consisting of 1 x Sandhawk + 1 x Tomahawk
Solid rocket stage. 90.00 kN (20,233 lbf) thrust. Mass 700 kg (1,543 lb).
American manufacturer of rockets and spacecraft. Sandia Laboratories, Albequerque, USA.
Sandys, Duncan British Politician. British politician.
Steam propellant rocket sled. Propelled the first and second stages on a 3-km track to a release velocity of 900 kph
Lox/LH2 propellant rocket stage. Loaded/empty mass 79,000/10,000 kg. Thrust 885.00 kN. Vacuum specific impulse 430 seconds. The first stage took the second stage to 50 km altitude and 4000 m/s separation conditions. The first stage would then land 500 km from the launch point. Takeoff speed was 300 m/s; and landing speed 80 m/s. A two-man crew piloted the booster.
Lox/LH2 propellant rocket stage. Loaded/empty mass 21,000/5,000 kg. Thrust 295.00 kN. Vacuum specific impulse 430 seconds. The second stage would reach a 300 km earth orbit and a top speed of 8000 m/s. The glider had a landing speed of 90 m/s. Aside from the two-man crew, a five tonne payload could be delivered into orbit.
Mach 6.6 rocket launch aircraft. Winged scramjet using LH2 propellant. Loaded/empty mass 254,000/156,000 kg. Thrust 1,500.00 kN. Specific impulse 1200 seconds. Releases Horus @M 6.6 @ 37 km altitude @ 3100 km range
Lox/LH2 propellant rocket stage. Loaded/empty mass 112,000/32,600 kg. Thrust 1,280.00 kN. Vacuum specific impulse 490 seconds. 6000 kg to LEO
Lox/Alcohol propellant rocket stage. Loaded/empty mass 34,000/6,800 kg. Thrust 6,860.00 kN. Vacuum specific impulse 245 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 99,773/19,955 kg. Thrust 1,428.80 kN. Vacuum specific impulse 306 seconds.
Notional Lox/Kerosene rocket engine. 1428.8 kN. Study 1943. Used in Sanger-Bredt. Isp=306s.
Saenger Lox/Alcohol rocket engine. 1144.1 kN. Study 1943. Isp=245s. Used on Sanger launch vehicle.
Chinese manufacturer of rocket engines and rockets. Sanjiang Space Group, Xiaogan, China.
Air-launched rocket drop zone known to have been used for 6 launches in 1958, reaching up to 12 kilometers altitude.
American manufacturer of spacecraft. Santa Clara, USA.
Sounding rocket launch location known to have been used for 1 launch in 1991, reaching up to 90 kilometers altitude.
Santonico, Stefano (1948-) Italian engineer cosmonaut, 1990-1993.
SAO.
Smithsonian Astrophysical Observatory
French orbital launch vehicle. Saphir was the penultimate step in the 'precious stones' series. The variants of the two-stage vehicle were designed to allow testing of radio-controlled guidance (VE231P), inertial guidance (VE231G), and warhead separation and re-entry of an ablative RV (VE231R). Addition of a third stage would transform Saphir into the Diamant satellite launcher.
Saphir VE231.
Alternate designation for Saphir orbital launch vehicle.
Universita degli Studi "la Sapienza", Roma, Italy
American technology satellite. One launch, 2001.09.30. SAPPHIRE (a US DoD-funded microsatellite) was built by Stanford University students and carried experimental infrared horizon sensors, a voice synthesizer and a digital camera.
Sapwood.
ASCC Reporting Name of R-7 intercontinental ballistic missile.
Egyptian tactical ballistic missile.
SAR.
Synthetic Aperture Radar; or Search And Rescue; or Spacecraft acceptance review
SARA.
French radio astronomy satellite. One launch, 1991.07.17. Radioastronomy.
Sarafanov, Gennadi Vassilyevich (1942-2005) Russian pilot cosmonaut. Flew on Soyuz 15.
Shuttle Amateur Radio Experiment
Sark.
ASCC Reporting Name of R-13 missile.
German military surveillance radar satellite. 5 launches, 2006.12.19 (SAR-Lupe 1) to 2008.07.22 (SAR-Lupe 5). Germany's first satellite-based radar reconnaissance system. It consisted of five identical small satellites and a ground segment.
Search and rescue satellite
Chinese manufacturer of spacecraft. Shanghai Aerospace Research Tech. Inst. , Shangai, China
SARV Retro MK I.
Government designation of Star 10 Solid rocket engine.
SARV Retro, MK IV.
Government designation of Star 12 Solid rocket engine.
Primary Soviet anti-ballistic missile test site. Known to have been used for 85 launches from 1958 to 2007, reaching up to 300 kilometers altitude. The actual number of missile tests ran into the thousands.
Launch Complex A
Launch Complex B
A-35, V-1000 launch complex.
Headquarters of an RVSN Division, 1965-on. Perhaps operated R-12 missiles.
SAS.
Space Adaptation Syndrome, or space sickness. Over half of all astronauts experience nausea leading to vomiting when they are first in zero-G, beginning with Gherman Titov on the second manned orbital flight. It normally passes after a day or two.
SAS.
Italian solar satellite. 3 launches, 1970.12.12 (Explorer 42) to 1975.05.07 (Explorer 53).
Sasin.
ASCC Reporting Name of R-9 missile.
Lox/LH2 propellant rocket stage. Loaded/empty mass 97,976/6,668 kg. Thrust 1,558.10 kN. Vacuum specific impulse 464 seconds. Recoverable S-IVB with plug nozzle engine. 36 x plug-nozzle engines (102 atm chamber pressure, 6:1 mixture ratio)
American SSTO VTOVL orbital launch vehicle. Bono proposal for first step toward VTOVL SSTO vehicle - heavily modified Saturn IVB with plug nozzle engine.
SAST.
Third name of SISE
SAST.
First name of Shanghai
SAST.
Shanghai Academy of Spaceflight Technology, Shangai, China.
SAT.
Synthetic Aperture Telescope
Satélite de Aplicaciones Científicas.
Alternate designation for SAC-B solar satellite.
Satan.
ASCC Reporting Name of R-36M, R-36M2 15A18M, and R-36MU 15A18 intercontinental ballistic missiles.
Satcher, Robert Lee Jr 'Bobby' (1965-) African-American chemical engineer mission specialist astronaut, 2004-on.
Series of communications satellites started by RCA Americom in 1975 and continued by GE when it took over RCA.
Brazilian technology satellite.
American agency. Satelife, USA.
Indonesian agency. Satelind, Indonesia.
PT Satelit Palapa Indonesia
Satelite de Aplicaciones/Cientifico-A.
Alternate designation for SAC-A technology satellite.
Satelite de Coleta de Dados.
Alternate designation for SCD communications technology satellite.
SAtellite INTerceptor.
Alternate designation for SAINT military anti-satellite system.
Satellite Italiano Ricerca Industriale Orientata.
Alternate designation for Sirio communications technology satellite.
Satellite Launch Vehicle.
Full name of SLV all-solid orbital launch vehicle.
American orbital launch vehicle. Orbital version. Selected by NASA under the COTS program in January 2008 in place of the cancelled Kistler for post-shuttle ISS resupply missions. Uses half-length shuttle SRB as first stage; proven Castor-120 as second stage; new Castor-30 as third stage; and Oribtal Adjusment Module from Lockheed's cancelled Athena launcher as a fourth stage.
Satellite pour Astronomie Radio Amateur.
Alternate designation for SARA radio astronomy satellite.
Satellite Probatoire d'Observation de la Terre.
Alternate designation for SPOT-1-2-3 earth land resources satellite.
Satish Dhawan Space Centre.
Alternate name for Sriharikota launch site.
Mexican agency. Satellites Mexicanos SA de SV, Mexico City, Mexico.
The South Korean Satrec Initiative built on earlier Kitsat technology to develop 100-kg and 200-kg satellite buses for national and international customers.
Sattarov, Nail Sharipovich (1941-) Tatar-Russian test pilot cosmonaut, 1979-1980.
The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. Numerous designs and variants were studied, but in the end only three models - the Saturn I, IB, and V - were built in the 1960's, and then only used to support NASA's Apollo moon landing program.
Solid propellant rocket stage. Loaded/empty mass 561,100/57,600 kg. Thrust 11,143.20 kN. Vacuum specific impulse 263 seconds. 260 inch solid booster - full length.
American orbital launch vehicle. Projected first version of Saturn I, to be used if necessary before S-IV liquid hydrogen second stage became available. Titan 1 first stage used as second stage, Centaur third stage. Masses, payload estimated.
American orbital launch vehicle. More powerful version of Saturn I with low energy second stage consisting of cluster of four IRBM motors and tankage, Centaur third stage. Masses, payload estimated.
Saturn Application Single Stage to Orbit.
Alternate designation for SASSTO ssto vtovl orbital launch vehicle.
Saturn Applications Single Stage to Orbit.
Alternate designation for SASSTO rocket stage.
American orbital launch vehicle. Most powerful version of Saturn I considered. New low energy second stage with four H-1 engines, S-IV third stage, Centaur fourth stage. Masses, payload estimated.
Saturn C-1.
Manufacturer's designation for Saturn I orbital launch vehicle.
American orbital launch vehicle. Original flight version with dummy upper stages, including dummy Saturn S-V/Centaur (never flown).
American orbital launch vehicle. The launch vehicle initially considered for realizing the Apollo lunar landing at the earliest possible date. 15 launches and rendezvous required to assemble direct landing spacecraft in earth orbit.
The launch vehicle concept considered for a time as the leading contender for the Earth Orbit Rendezvous approach to an American lunar landing.
The launch vehicle concept considered for a time as the leading contender for the Earth Orbit Rendezvous approach to an American lunar landing.
American orbital launch vehicle. Final configurtion of the Saturn C-3 at the time of selection of the Saturn C-5 configuration for the Apollo program in December 1961.
American nuclear orbital launch vehicle. Version of Saturn C-3 considered with small nuclear thermal stage in place of S-IVB oxygen/hydrogen stage.
American orbital launch vehicle. The launch vehicle actually planned for the Lunar Orbit Rendezvous approach to lunar landing. The Saturn C-5 was selected instead to have reserve capacity.
American orbital launch vehicle. Final configurtion of the Saturn C-4 at the time of selection of the Saturn C-5 configuration for the Apollo program in December 1961. Only Saturn configuration with common bulkhead propellant tanks in first stage, resulting in shorter vehicle than less powerful Saturn C-3.
American orbital launch vehicle. Final configuration of Saturn C-5 at the time of selection of this configuration for the Apollo program in December 1961. The actual Saturn V would be derived from this, but with an increased-diameter third stage (6.61 m vs 5.59 m in C-5) and increased propellant load in S-II second stage.
American nuclear orbital launch vehicle. Version of Saturn C-5 considered with small nuclear thermal stage in place of S-IVB oxygen/hydrogen stage.
American orbital launch vehicle. The largest member of the Saturn family ever contemplated. Designed for direct landing of Apollo command module on moon. Configuration used eight F-1 engines in the first stage, eight J-2 engines in the second stage, and one J-2 engine in the third stage. Distinguishable from Nova 8L in use of J-2 engines instead of M-1 engines in second stage.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 432,681/45,267 kg. Thrust 7,582.10 kN. Vacuum specific impulse 289 seconds. Configuration as flown, Saturn I.
Von Braun launch vehicle known as 'Cluster's Last Stand' - 8 Redstone tanks around a Jupiter tank core,powered by eight Jupiter engines. Originally intended as the launch vehicle for Apollo manned circumlunar flights. However it was developed so early, no payloads were available for it.
American orbital launch vehicle. Von Braun launch vehicle known as 'Cluster's Last Stand' - 8 Redstone tanks around a Jupiter tank core,powered by eight Jupiter engines. Originally intended as the launch vehicle for Apollo manned circumlunar flights. However it was developed so early, no payloads were available for it.
American orbital launch vehicle. Second Block of Saturn I, with substantially redesigned first stage and large fins to accomodate Dynasoar payload.
American nuclear orbital launch vehicle. In the first half of the 1960's it was planned to make suborbital tests of nuclear propulsion for upper stages using a Saturn IB first stage to boost a Rover-reactor powered second stage on a suborbital trajectory. The second stage would impact the Atlantic Ocean down range from Cape Canaveral.
American orbital launch vehicle. Improved Saturn I, with uprated first stage and Saturn IVB second stage (common with Saturn V) replacing Saturn IV. Used for earth orbit flight tests of Apollo CSM and LM.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 448,648/41,594 kg. Thrust 8,241.76 kN. Vacuum specific impulse 296 seconds. Configuration as flown, Saturn IB.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 505,953/48,545 kg. Thrust 8,241.76 kN. Vacuum specific impulse 296 seconds. 20 foot stretch of Saturn IB for use with UA1207 7 segment solid rocket strap-on units.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 478,103/45,873 kg. Thrust 8,241.76 kN. Vacuum specific impulse 296 seconds. 10 foot stretch of Saturn IB. Not found useful in any configuration except with Minuteman first-stage strap-ons to augment thrust.
American orbital launch vehicle. Douglas Studies, 1965: S-IB with 225 k lbf H-1's; S-IVB stretched with 350,000 lbs propellants; Centaur third stage.
American orbital launch vehicle. Douglas Studies, 1965: S-IB with 225 k lbf H-1's; S-IVB stretched with 350,000 lbs propellants and HG-3 high performance engine.
American orbital launch vehicle. Douglas Studies, 1965: 4 Minuteman strap-ons; standard S-IB, S-IVB stages.
American orbital launch vehicle. Douglas Studies, 1965: Standard Saturn IB with Centaur upper stage.
American orbital launch vehicle. Douglas Studies, 1965: Standard Saturn IB with Titan UA1205 5-segment strap-on motors.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,286,217/135,218 kg. Thrust 38,703.16 kN. Vacuum specific impulse 304 seconds. Configuration as flown.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,160,787/72,549 kg. Thrust 22,954.80 kN. Vacuum specific impulse 304 seconds. Final first stage design of Saturn C-3 (November 1961).
Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,450,984/90,686 kg. Thrust 30,606.40 kN. Vacuum specific impulse 304 seconds. Final first stage design of Saturn C-3 (November 1961). Unique S-IC design in that fuel and propellant tank shared common bulkhead; stage was actually shorter than C-3B S-IC.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,217,285/131,495 kg. Thrust 38,257.99 kN. Vacuum specific impulse 304 seconds. Final first stage design of Saturn C-5 (November 1961) before selection as Apollo launch vehicle and development in Saturn V.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,278,800/127,000 kg. Thrust 38,717.60 kN. Vacuum specific impulse 304 seconds. Standard S-IC but with reduced length and structural weight through use of 'flat' bulkheads consisting of multiple conical sections.
Lox/LH2 propellant rocket stage. Loaded/empty mass 490,778/39,048 kg. Thrust 5,165.79 kN. Vacuum specific impulse 421 seconds. Configuration as flown.
Lox/LH2 propellant rocket stage. Loaded/empty mass 384,057/31,740 kg. Thrust 4,446.65 kN. Vacuum specific impulse 420 seconds. Final common second stage design for Saturn C-3, C-4 and C-5 (November 1961). Developed into Saturn V second stage.
American manned space station. Study 1964. Wernher von Braun made a rough sketch of a space station based on fitting out of an expended Saturn II stage in orbit on 24 November 1964.
Lox/LH2 propellant rocket stage. Loaded/empty mass 495,000/48,000 kg. Thrust 9,713.40 kN. Vacuum specific impulse 450 seconds. Saturn II modifed with reduced expansion ratio HG-3 high pressure engines for use a first stage (sea level launch).
Lox/LH2 propellant rocket stage. Loaded/empty mass 490,952/44,240 kg. Thrust 5,500.77 kN. Vacuum specific impulse 390 seconds. Saturn II modifed with reduced expansion ratio J-2 engines for use a first stage (sea level launch). Requires solid rocket motor augmentation to get off the ground.
American orbital launch vehicle. NASA Study, 1965: Half length 260 inch solid motor with S-IVB upper stage.
American orbital launch vehicle. UA Study, 1965: Full length 260 inch solid motor with S-IVB upper stage.
American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 4 Titan UA1205 with standard S-IB stage, S-IVB stage, or 4 Titan UA1207 strap-ons with 20-foot stretche S-IB stage, S-IVB stage. S-IB ignition at altitude.
American orbital launch vehicle. Chrysler Studies, 1966: S-IB with only 4 H-1 motors, with 4 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 4 Titan UA1207 strap-ons with 20-foot stretche S-IB stage, S-IVB stage. S-IB ignition at sea level at same time as strap-ons.
American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 2 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 2 Titan UA1207 strap-ons with 20-foot stretche S-IB stage, S-IVB stage. S-IB ignition at sea level at same time as strap-ons.
American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 4 Minuteman motors as strap-ons, with no, 10, or 20-foot stretch S-IB stages, S-IVB stage. S-IB ignition at sea level at same time as strap-ons.
American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 8 Minuteman motors as strap-ons, with no, 10, or 20-foot stretch S-IB stages, S-IVB stage. S-IB ignition at sea level at same time as strap-ons.
American orbital launch vehicle. UA Studies, 1966: S-IVB upper stage with from 2 to 5 Titan UA1205, 1206, or 1207 motors as first stage, clustered around from 1 to 3 of the same motors as a second stage. S-IVB upper stage.
North American study, 1966. Saturn variant with a modified S-II first stage with seven high-performance HG-3 engines; S-IVB second stage. Poor performance and cost-effectiveness and not studied further.
North American study, 1966. Saturn variant with Titan UA1205 or 1207 motors as boosters, Saturn II stage as core, and Saturn IVB upper stage. Various combinations of numbers of strap-ons, propellant loading of the two core stages, and sea-level versus altitude ignition were studied.
North American study, 1966. Saturn variant with 4 to 12 Minuteman motors as boosters, Saturn II stage as core, and Saturn IVB upper stage. Saturn II stage would be fitted with lower expansion ratio engines and would ignite at sea level. Various combinations of numbers of strap-ons, propellant loading of the two core stages were studied.
American orbital launch vehicle. Saturn variant consisting of S-IC first stage and S-IVB second stage. Consideration was given to deleting one or more of the F-1 engines in the first stage.
American orbital launch vehicle. Saturn variant consisting of S-IC first stage and S-II second stage. This essentially flew once to launch Skylab in 1972, although the IU was located atop the Skylab space station (converted S-IVB stage) rather than atop the S-II as in the INT-21 design.
American orbital launch vehicle. UA study, 1965. Saturn variant using various combinations of 156 inch rocket motors as first and second stages, with S-IVB upper stage.
Lox/LH2 propellant rocket stage. Loaded/empty mass 50,576/5,217 kg. Thrust 400.35 kN. Vacuum specific impulse 410 seconds. Configuration as flown.
Lox/LH2 propellant rocket stage. Loaded/empty mass 119,920/13,311 kg. Thrust 1,031.98 kN. Vacuum specific impulse 425 seconds. Configuration as flown on Saturn V.
Lox/LH2 propellant rocket stage. Loaded/empty mass 118,800/12,900 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Saturn IB version of S-IVB stage. Due to lower payload payload, 300 kg saving in structure compared to Saturn V version. Due to deletion of restart requirement, 700 kg saving in propulsion system (primarily reduction in helium for restart).
Lox/LH2 propellant rocket stage. Loaded/empty mass 119,900/13,300 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Saturn V version of S-IVB stage for use with upper stage.
Lox/LH2 propellant rocket stage. Loaded/empty mass 52,144/6,801 kg. Thrust 889.33 kN. Vacuum specific impulse 420 seconds. Final common third stage design for Saturn C-3B (November 1961).
Lox/LH2 propellant rocket stage. Loaded/empty mass 102,249/11,563 kg. Thrust 889.33 kN. Vacuum specific impulse 420 seconds. Final common third stage design for Saturn C-4 and C-5 (November 1961). Developed into Saturn V second stage. After development started, decision taken to boost performance by increasing diameter to 6.61 m and increasing propellant load.
Lox/LH2 propellant rocket stage. Loaded/empty mass 118,800/12,900 kg. Thrust 956.10 kN. Vacuum specific impulse 421 seconds. Douglas Studies, 1965: S-IVB with 215k lbf J-1 (actual final model had 230k J-1)
N2O4/Alumizine propellant rocket stage. Loaded/empty mass 1,542,200/154,200 kg. Thrust 22,563.10 kN. Vacuum specific impulse 280 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/Alumizine Propellant engine, HY-140 Hull
American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/Alumizine Propellant engine, HY-140 Steel Hull.
American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/Alumizine Propellant engine, Ni-250 Steel Hull.
N2O4/Alumizine propellant rocket stage. Loaded/empty mass 1,270,100/95,300 kg. Thrust 18,873.80 kN. Vacuum specific impulse 280 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/Alumizine Propellant engine, Ni-250 Hull
American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed Lox/RFP-1 engine.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,360,800/108,900 kg. Thrust 20,306.60 kN. Vacuum specific impulse 275 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed Lox/RFP-1 engine
Solid propellant rocket stage. Loaded/empty mass 1,678,300/136,100 kg. Thrust 27,034.90 kN. Vacuum specific impulse 263 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Solid Propellant
American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, 260 inch solid motor, full length.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 1,995,800/199,600 kg. Thrust 28,553.00 kN. Vacuum specific impulse 267 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, HY-140 Hull
American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, HY-140 Steel Hull.
American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, Ni-250 Steel Hull.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 1,451,500/108,900 kg. Thrust 21,232.30 kN. Vacuum specific impulse 267 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, Ni-250 Hull
Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,180,000/80,000 kg. Thrust 15,484.00 kN. Vacuum specific impulse 304 seconds. Liquid strap-on booster studied for improved Saturn V.
American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 41 inches with 1.0 million pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine.
American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Variant of MLV-V-1 with toroidal J-2T-200K engines replacing standard J-2 engines in upper stages.
American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Variant of MLV-V-1 with toroidal J-2T-250K engines replacing standard J-2 engines in upper stages.
American orbital launch vehicle. MSFC study, 1965. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 6 F-1 engines; S-II stretched 156 inches with 1.2 million pounds propellant and 7 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.
American orbital launch vehicle. MSFC study, 1965. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 41 inches with 1.0 million pounds propellant and 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine.
American orbital launch vehicle. MSFC study, 1965. Ultimate core for improved Saturn V configurations studied under contract NAS8-11359. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 156 inches with 1.2 million pounds propellant and 5 HG-3 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine.
American orbital launch vehicle. MSFC study, 1965. Saturn V core, strengthened but not stretched, with 4 Titan UA1205 strap-on solid rocket boosters.
American orbital launch vehicle. MSFC study, 1965. 4 Titan UA1205 solid rocket boosters; Saturn IC stretched 337 inches with 6.0 million pounds propellant and 5 F-1 engines; S-II with 970,000 pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine.
American orbital launch vehicle. Boeing study, 1967. Configuration of improved Saturn 5 with Titan UA1207 120 inch solid rocket boosters. Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1 engines; Saturn II and Saturn IVB stages strengthened but not stretched. Empty mass of stages increased by 13.9% (S-IC), 8.6% (S-II) and 11.8% (S-IVB). Studied again by Boeing in 1967 as Saturn V-4(S)B.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,721,600/181,400 kg. Thrust 38,717.60 kN. Vacuum specific impulse 304 seconds. Standard length S-IC but with feed of propellant from fuel and propellant tanks housed above strap-on solid rocket motors
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,694,703/169,719 kg. Thrust 45,948.75 kN. Vacuum specific impulse 310 seconds. Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,694,700/160,600 kg. Thrust 46,443.30 kN. Vacuum specific impulse 304 seconds. Basic Saturn IC stretched 240 inches with 6 F-1 engines.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,694,000/169,000 kg. Thrust 38,703.16 kN. Vacuum specific impulse 304 seconds. Basic Saturn IC stretched 240 inches with standard F-1 engines.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 3,223,800/211,900 kg. Thrust 45,925.50 kN. Vacuum specific impulse 304 seconds. S-IC with 41.5 foot stretch, 6,640,0000 lbs propellant, uprated F-1 engines.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,718,800/178,700 kg. Thrust 45,925.50 kN. Vacuum specific impulse 304 seconds. S-IC with 20 foot stretch, 1.8 million lb thrust F-1's, 5.6 million pounds propellant capacity (fuel offloaded to 4.99 million for LEO or 4.80 million lbs for LOR mission).
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,875,500/154,000 kg. Thrust 38,717.60 kN. Vacuum specific impulse 304 seconds. S-IC with 336 inch stretch, 6,000,0000 lbs propellant, structural strength increased from 56% to 65% depending on station, resulting in 13.9% increase in empty weight.
Lox/LH2 propellant rocket stage. Loaded/empty mass 521,447/49,877 kg. Thrust 5,165.79 kN. Vacuum specific impulse 425 seconds. Basic Saturn II with 41 inch stretch of hydrogen tank.
Lox/LH2 propellant rocket stage. Loaded/empty mass 600,800/60,000 kg. Thrust 6,380.94 kN. Vacuum specific impulse 421 seconds. Basic Saturn II with 187 inch stretch of propellant tanks, 1.2 million pound propellant capacity, and 7 J-2 engines.
Lox/LH2 propellant rocket stage. Loaded/empty mass 521,447/49,877 kg. Thrust 4,446.65 kN. Vacuum specific impulse 435 seconds. Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 200k engines with 10 second increase in specific impulse.
Lox/LH2 propellant rocket stage. Loaded/empty mass 521,447/49,877 kg. Thrust 5,558.31 kN. Vacuum specific impulse 441 seconds. Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 250k engines with 25% improvement in thrust and 16 second increase in specific impulse.
Lox/LH2 propellant rocket stage. Loaded/empty mass 600,788/59,844 kg. Thrust 7,003.48 kN. Vacuum specific impulse 451 seconds. Basic Saturn II with 187 inch stretch of propellant tanks and high chamber pressure SSME-type engines with 65% increase in thrust and 26 second improvement in specific impulse.
Lox/LH2 propellant rocket stage. Loaded/empty mass 643,200/53,500 kg. Thrust 12,455.40 kN. Vacuum specific impulse 447 seconds. S-II with 15.5 foot stretch, 1.29 million pounds propellant, 7 x 400,000 lb thrust toroidal engines.
Lox/LH2 propellant rocket stage. Loaded/empty mass 494,100/42,300 kg. Thrust 5,169.00 kN. Vacuum specific impulse 421 seconds. Standard S-II but with structural strength increased from 86% to 502% depending on station, resulting in 8.6% increase in empty weight.
American space tug. Study 1965. Upper stage / space tug - Marshall studies, 1965. Launched by Saturn V. S-IVB structurally strengthened to handle larger payloads, otherwise unchanged
Lox/LH2 propellant rocket stage. Loaded/empty mass 120,500/13,900 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Marshall studies, 1965: S-IVB structurally strengthened to handle larger payloads, otherwise unchanged
Lox/LH2 propellant rocket stage. Loaded/empty mass 179,200/20,400 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine.
American space tug. Study 1966. Upper stage / space tug - Boeing study 1967. Launched by Saturn V. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine.
American space tug. Study 1965. Upper stage / space tug - Douglas study, 1965. Launched by Saturn V. S-IVB with 315 k high pressure 3000 psia engine, 350,000 pounds propellant
Lox/LH2 propellant rocket stage. Loaded/empty mass 176,600/17,800 kg. Thrust 1,401.30 kN. Vacuum specific impulse 447 seconds. Douglas Studies, 1965: S-IVB with 315 k high pressure 3000 psia engine, 350,000 pounds propellant
Lox/LH2 propellant rocket stage. Loaded/empty mass 179,200/20,400 kg. Thrust 1,778.90 kN. Vacuum specific impulse 447 seconds. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, 1 400,000 pound thrust toroidal engine.
American space tug. Study 1967. Upper stage / space tug - Boeing study, 1967. Launched by Saturn V. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, 1 x 400,000 pound thrust toroidal engine.
Lox/LH2 propellant rocket stage. Loaded/empty mass 118,400/14,100 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Standard S-IVB but with structural strength increased from 78% to 217% depending on station, resulting in 11.8% increase in empty weight.
American space tug. Study 1967. Upper stage / space tug - studied by Boeing in 1967. Standard S-IVB but with structural strength increased from 78% to 217% depending on station, resulting in 11.8% increase in empty weight.
Lox/LH2 propellant rocket stage. Loaded/empty mass 195,000/36,300 kg. Thrust 912.00 kN. Vacuum specific impulse 421 seconds. Marshall studies, 1965: S-IVB structurally strengthened to handle larger payloads, otherwise unchanged
American space tug. Study 1965. Upper stage / space tug - studied by NASA Marshall in 1965. Launched by Saturn V. S-IVB structurally strengthened to handle larger payloads, otherwise unchanged
Lox/Kerosene propellant rocket stage. Loaded/empty mass 874,100/18,100 kg. Thrust 15,486.60 kN. Vacuum specific impulse 304 seconds. Liquid rocket booster strap-ons using 2 F-1's.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 2,057,400/205,400 kg. Thrust 28,553.00 kN. Vacuum specific impulse 267 seconds. NASA, Saturn Alternative Booster Studies, 1969 (trade study of 120, 156, 260 inch solid, and Storable liquid boosters for S-IVB. Reached opposite conclusion from Boeing study, that Pressure Fed Liquid Booster would be 6.5% more expensive than solid). Pre
Lox/Kerosene propellant rocket stage. Loaded/empty mass 444,700/37,600 kg. Thrust 4,120.70 kN. Vacuum specific impulse 296 seconds. Chrysler Studies, 1966: S-1B with 4 H-1's for use with Titan UA1205 strap-ons
American orbital launch vehicle. A winged recoverable Saturn IC stage was considered instead of solid rocket boosters after the final shuttle design was selected.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 725,491/68,014 kg. Thrust 13,339.96 kN. Vacuum specific impulse 304 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,813,729/108,823 kg. Thrust 30,962.53 kN. Vacuum specific impulse 304 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 448,600/41,600 kg. Thrust 9,045.60 kN. Vacuum specific impulse 296 seconds. Douglas Studies, 1965: S-1B with 225 k lbf H-1's
Lox/Kerosene propellant rocket stage. Loaded/empty mass 3,627,500/181,400 kg. Thrust 61,925.00 kN. Vacuum specific impulse 304 seconds.
American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): S-IC Technology Liquid Booster: 260 inch liquid booster with 2 x F-1 engines, recoverable/reusable
Lox/Kerosene propellant rocket stage. Loaded/empty mass 952,500/68,000 kg. Thrust 15,532.70 kN. Vacuum specific impulse 304 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): S-IC Technology Liquid Booster: 260 inch liquid booster with 2 x F-1 engines, recoverable/reusable
Lox/Kerosene propellant rocket stage. Loaded/empty mass 67,100/67,100 kg. Thrust 30,962.50 kN. Vacuum specific impulse 304 seconds. Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage recoverable. Mass estimated based on double mass of four F-1's (based on Atlas example).
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,219,100/68,100 kg. Thrust 7,740.30 kN. Vacuum specific impulse 304 seconds. Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage burns 124 seconds in this configuration.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,627,600/84,400 kg. Thrust 7,740.30 kN. Vacuum specific impulse 304 seconds. Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas; 20 foot stretch of sustainer stage. Booster stage burn 154 seconds in this configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 100,000/14,000 kg. Thrust 3,557.31 kN. Vacuum specific impulse 420 seconds. Early design version for use with Saturn I first stage.
Lox/LH2 propellant rocket stage. Loaded/empty mass 294,731/24,938 kg. Thrust 3,557.31 kN. Vacuum specific impulse 420 seconds. Version for Saturn C-4.
Lox/LH2 propellant rocket stage. Loaded/empty mass 770,835/63,480 kg. Thrust 8,265.26 kN. Vacuum specific impulse 425 seconds. Version for Saturn C-8.
Lox/LH2 propellant rocket stage. Loaded/empty mass 204,044/24,938 kg. Thrust 3,557.31 kN. Vacuum specific impulse 420 seconds. Version for Saturn C-3.
Lox/LH2 propellant rocket stage. Loaded/empty mass 204,044/22,671 kg. Thrust 1,031.98 kN. Vacuum specific impulse 425 seconds.
Nuclear/LH2 propellant rocket stage. Loaded/empty mass 32,470/7,708 kg. Thrust 266.80 kN. Vacuum specific impulse 800 seconds. Nuclear upper stage considered in lieu of S-IVB in final Saturn C-3B study in November 1961.
American space tug. Study 1961. Upper stage / space tug - Study 1961. Launched by Saturn C-5N-3. Nuclear upper stage considered in lieu of S-IVB in final Saturn C-3B study in November 1961.
Nuclear/LH2 propellant rocket stage. Loaded/empty mass 53,694/10,429 kg. Thrust 266.80 kN. Vacuum specific impulse 800 seconds. Nuclear upper stage considered in lieu of S-IVB in final Saturn C-5 study in November 1961.
American space tug. Study 1961. Upper stage / space tug - Study 1961. Launched by Saturn C-5N-3. Nuclear upper stage considered in lieu of S-IVB in final Saturn C-5 study in November 1961.
Nuclear/LH2 propellant rocket stage. Loaded/empty mass 245,760/71,190 kg. Thrust 889.33 kN. Vacuum specific impulse 825 seconds. Version of Nerva studied by Boeing for manned Mars expedition.
American space tug. Study 1968. Upper stage / space tug - study 1969. Launched by Saturn V-25(S)U. Version of Nerva studied by Boeing for manned Mars expedition.
American orbital launch vehicle. America's booster for the Apollo manned lunar landing. The design was frozen before a landing mode was selected; the Saturn V could be used for either Earth-Orbit-Rendezvous or Lunar-Orbit-Rendezvous methods. The vehicle ended up with the same payload capability as the 'too large' Nova. The basic diameter was dictated by the ceiling height at the Michoud factory selected for first stage manufacture.
America's booster for the Apollo manned lunar landing. The design was frozen before a landing mode was selected; the Saturn V could be used for either Earth-Orbit-Rendezvous or Lunar-Orbit-Rendezvous methods. The vehicle ended up with the same payload capability as the 'too large' Nova. The basic diameter was dictated by the ceiling height at the Michoud factory selected for first stage manufacture. Despite the study of innumerable variants, production was ended after only 12 were built and America spent the next fifty years in a pointless slow-motion withdrawal from manned space exploration.
American orbital launch vehicle. Two stage version of Saturn V, consisting of 1 x Saturn S-IC + 1 x Saturn S-II, used to launch Skylab.
American orbital launch vehicle. Boeing study, 1967-1968. Use of full length 260 inch solid rocket boosters with stretched Saturn IC stages presented problems, since the top of the motors came about half way up the liquid oxygen tank of the stage, making transmission of loads from the motors to the core vehicle complex and adding a great deal of weight to the S-IC. Boeing's solution was to retain the standard length Saturn IC, with the 260 inch motors ending half way up the S-IC/S-II interstage, but to provide additional propellant for the S-IC by putting propellant tanks above the 260 inch boosters. These would be drained first and jettisoned with the boosters. This added to the plumbing complexity but solved the loads problem.
American orbital launch vehicle. Boeing study, 1967. 4 260 inch liquid propellant boosters (each with 2 F-1's!).; Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1 engines; S-II strengthened but with standard 930,000 pounds propellant and 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.
American orbital launch vehicle. Boeing study, 1967. 4 260 inch liquid propellant boosters (each with 2 F-1A).; Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1A engines; S-II stretched 156 inches with 1.2 million pounds propellant and 5 HG-3 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine. Not studied in detail since vehicle height of 600 feet with payload exceeded study limit of 410 feet.
American orbital launch vehicle. Boeing study, 1967. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.
American orbital launch vehicle. Boeing study, 1968. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines. This vehicle would place Nerva nuclear third stage into low earth orbit, where five such stages would be assembled together with the spacecraft for a manned Mars expedition.
American orbital launch vehicle. Boeing study, 1967. Variation on MSFC 1965 study Saturn MLV-V-3 but with toroidal engines. Saturn IC stretched 240 inches with 5.6 million pounds propellant (but only 4.99 million pounds usable without solid rocket boosters) and 5 F-1A engines; S-II stretched 186 inches with 1.29 million lbs propellant and 5 J-2T-400 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2T-400 engine.
American orbital launch vehicle. Boeing study, 1968. Four core vehicles from Saturn V-25(S) study lashed together to obtain million-pound payload using existing hardware. First stage consisted of 4 Saturn IC's stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; second stage 4 Saturn II standard length stages with 5 J-2 engines
American orbital launch vehicle. MSFC study, 1968. Essentially identical to Saturn INT-20; standard Saturn IC stage together with Saturn IVB second stage, with Centaur third stage for deep space missions.
American orbital launch vehicle. MSFC study, 1968. Intriguing stage-and-a-half to orbit design using Saturn S-ID stage. The S-ID would be the same length and engines as the standard Saturn IC, but the four outer engines and their boost structure would be jettisoned once 70% of the propellant was consumed, as in the Atlas ICBM. This booster engine assembly would be recovered and reused. The center engine would be gimbaled and serve as a sustainer engine to put the rest of the vehicle and its 50,000 pound payload into orbit. At very minimal cost (36 months leadtime and $ 150 million) the United States could have attained a payload capability and level of reusability similar to that of the space shuttle.
American orbital launch vehicle. MSFC study, 1968. S-ID stage-and-a-half first stage and Saturn IVB second stage. Centaur available as third stage for deep space missions. 30% performance improvement over Saturn V-A/Saturn INT-20 with standard Saturn IC first stage.
American orbital launch vehicle. MSFC study, 1968. S-ID stage-and-a-half first stage and Saturn IVB second stage. Centaur available as third stage for deep space missions. 30% performance improvement over Saturn V-A/Saturn INT-20 with standard Saturn IC first stage.
American orbital launch vehicle. MSFC study, 1968. Rehashed the Boeing 1967 studies, covering a variety of stage stretches and 120, 156, or 260 inch solid rocket boosters, but with S-ID stage-and-a-half first stage.
American orbital launch vehicle. NASA study, 1966. No-height-limitation stretched Saturn with Titan UA1207 motors for thrust augmentation.
Saudi Arabia
Saudi Institute for Space Research.
Saudi manufacturer of spacecraft. Saudi Institute for Space Research, Saudi Arabia.
Saudi military communications satellite. 5 launched, 2007.04.17.
Saudi amateur radio communications satellite. 7 launches, 2000.09.26 (SaudiSat 1A) to 2007.04.17 (Saudisat 2).
Saul.
Saul, Aldo German expert in guided missiles during World War II. As of January 1947, working "c/o Klinger", British Zone.
British manufacturer of rocket engines and rockets. Saunders-Roe, UK.
von Saurma, Friedrich und Hans German-American rocket engine designer, worked at Huntsville with von Braun. Ranking Prussian aristrocrat of the German rocket team. His wife was von Braun's personal secretary.
Saus.
Saus, Valentin Andreyeich (1932-) Russian officer. Deputy Chief GNITs KS Space Tracking Centre for Space Communications and Television 1977-1991.
Savage.
American manned rescue spacecraft. Study 1966. The Rockwell SAVER concept provided return of a single crew member in his ejection seat. A nosecap only the size of the seat absorbed most of the re-entry heat.
Savin, Anatoli Ivanovich (1920-) Russian chief designer. General Designer from 1962 of KB-1 and TsNII Kometa. Specialised in the hardware for the Soviet RORSAT. EORSAT, and ASAT programs.
Savinykh, Viktor Petrovich (1940-) Russian engineer cosmonaut. Flew on Salyut 6 EO-6, Salyut 7 EO-4-1a, Mir EP-2.
Savitskaya, Svetlana Yevgenyevna (1948-) Russian test pilot cosmonaut. Flew on Salyut 7 EP-2, Salyut 7 EP-4. Test pilot, engineer, second woman in space. First woman to walk in space.
Sawatzki, Albin (-1945) German engineer, head of productionisation of the A4 missile, and technical director at Mittelwerk. His family believes that he was captured by the U.S. Army near the end of the war, perhaps tortured, and died in custody.
Sawfly.
SAX.
Italian x-ray astronomy satellite. One launch, 1996.04.30, Beppo SAX. Satellite per Astronomia a raggi X; X-ray celestial observatory
SB.
Solar panel (Russian abbreviation)
S-B.
Japanese sounding rocket. Single stage vehicle.
S-B.
Mitsubishi solid rocket engine.
Solid propellant rocket stage. Loaded mass 100 kg.
SB-1.
First Owner of Almaz
ISAS solid rocket engine. 95 kN.
SB-735.
Alternate designation for Mu-3S-0 rocket stage.
Family of launch vehicles.
Japanese sounding rocket.
Nissan solid rocket engine. 327.8 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969.
A range of frequencies used in radar and communications that extends from 1,550 to 5,200 megahertz (wavelength region from 0.06 m to 0.2 m).
SBD.
American technology satellite. One launch, 2001.09.21. SBD, the Orbital Corporation Special Bus Design, was a 73 kg test version of an enlarged Microstar bus.
SpaceDev N2O/Solid hybrid rocket engine. 1100 kN. First stage. Upper-stage hybrid propulsion system, part of 2004 Phase 2 of SBIR contract from AFRL for a hybrid rocket motor-based small launch vehicle project.
Sbracyvaemiy oporniy konus.
Alternate designation for Soyuz 7K-L1 SOK manned spacecraft module.
SBS.
Satellite Business Systems communications network.
SBS.
American agency. SBS, USA.
S-C.
Japanese sounding rocket. Single stage vehicle.
S-C.
Mitsubishi solid rocket engine.
Solid propellant rocket stage. Loaded mass 100 kg.
SCA.
Shuttle Carrier Aircraft
SCAD.
Popular Name of AGM-86A air-to-surface missile.
Scaleboard.
American manufacturer of rockets and spacecraft. Scaled Composites, USA.
Scalpel.
ASCC Reporting Name of RT-23 15Zh44, RT-23 15Zh52, RT-23U 15Zh60, and RT-23U 15Zh61 intercontinental ballistic missiles.
Scamp.
Alternate designation for RT-15 intermediate range ballistic missile.
American sounding rocket. Four stage vehicle consisting of 2 x Recruit + 1 x Aerojet Jr + 1 x Lance + 1 x Altair
Horizon definition experiment (sounding rocket)
Rocket stage used on Astrobee 1500 sounding rocket.
Scapegoat (Scamp).
ASCC Reporting Name of RT-15 intermediate range ballistic missile.
Scarab-A.
ASCC Reporting Name of 9K79 intermediate range ballistic missile.
Scarab-B.
ASCC Reporting Name of 9K79-1 intermediate range ballistic missile.
Scarp.
ASCC Reporting Name of R-36 8K67P intercontinental ballistic missile.
American communications technology satellite. One launch, 1979.01.30.
SCC.
Japanese agency. Space Communications Corporation, Tokyo, Japan.
SCCJ.
Space Communications Corp, Japan
SCD.
Specification control drawing
SCD.
Brazilian communications technology satellite. 3 launches, 1993.02.09 (SCD-1) to 1998.10.23 (SCD-2). Environmental data relay.
SCE.
Article Number of Stacksat P87-2 technology satellite.
SCEL.
US Army Signal Corps Engineering Laboratories
Schabert German rocket technician in WW2; later worked in France at LRBA in the chemistry group from 1947-1950.
Schaefer, Wilhelm German expert in guided missiles during World War II. As of January 1947, last known to be working at Steinlager, Allendorf.
American manufacturer of spacecraft. Schafer, USA.
Schaper, Otto Friedrich (1892-1967) German expert in guided missiles during World War II. Arrived in America under Project Paperclip on 1945.11.16 aboard the Argentina. Worked at Port Washington, Long Island, New York, USA, until his death in 1967.
Scheidt, Karl German engineer. Member of German Rocket Team in France after WW2.
Schellinger
Scheufelen, Klaus Eduard (1913-2008) German engineer, V-2 test leader. At end of war headed development of Taifun unguided antiaircraft rocket, characterised as a 'desperation project'. As of January 1947, working at Fort Bliss, Texas. Living in Lenningen, Germany in 2004.
Schiaparelli, Giovanni (1835-1910) Italian astronomer, made observations in the 1860's of Martian canals; believed them to be artificial constructions and indicating intelligent life. Tremendously influenced the public and science fiction writers. Later shown to be an optical i
Schierhorn, Walter (1907-) German welding 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 Manufacturing; Shop 55.
Schilling, Martin (1911-2002) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Atlas F (SMS 550) ICBM base.
Schilling AFB Missile Site 01.
Schilling AFB Missile Site 02.
Schilling AFB Missile Site 03.
Schilling AFB Missile Site 06.
Schilling AFB Missile Site 07.
Schilling AFB Missile Site 09.
Schilling AFB Missile Site 10.
Schilling AFB Missile Site 11.
Schilling AFB Missile Site 12.
Schindler, William 'Bill' American manager. NASA Delta launch vehicle program manager, the single individual most responsible for developing the light launch vehicle into a medium lift workhorse
Schirra, Walter Marty Jr 'Wally' (1923-2007) American test pilot astronaut. Flew on Mercury MA-8, Gemini 6, Apollo 7. Member of first crew to rendezvous in space, and commander of first manned Apollo mission. Remembered both for practical jokes and uncompromising attention to detail. Flew 90 combat missions in the Korean War.
Schlechter, Peter German expert in guided missiles during World War II. As of January 1947, living at Niederbeerbach bei Darmstadt, Obergasse 2 (American Zone of Occupation).
Schlegel, Hans Wilhelm (1951-) German physicist mission specialist astronaut. Flew on STS-55, STS-122.
Schlesinger, James R (1929-) American manager, chair of the Atomic Energy Commission, 1971-1973, Secretary of Defense, 1973-1975.
Schlidt, Rudolf Karl Hans (1914-) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Schlitt, Helmut Wilhelm Emil (1912-2005) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Schlotzer German rocket engineer in WW2; later worked in France as head of the armature group for LRBA from 1947 until retirement in 1970.
German surface-to-air missile which completed development at the beginning of 1945. However it was never produced in appreciable quantities. The name translates as 'Butterfly'.
Schmidt, Helmut Heinrich 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.
Schmidt, C German rocket engineer in WW2. Later worked in France at LRBA in the instrumentation group of the flight mechanics and control department from 1947-1952.
Schmidt, Johannes German expert in rocket engines during World War II, working at the Walter Werke, Kiel. Moved by the British to Saenger's facility in Trauen in early 1946 to conduct rocket engine tests, which were completed on 16 June 1946.
Schmidt, Paul (1898-) German engineer, physicist and expert in jet propulsion at Peenemuende during World War II. As of January 1947, working at Munich, Allach.
Schmidt, W German rocket engineer in WW2; later worked in France at LRBA on electronic homing systems in the target tracking department 1947-1952.
Schmieder, Curt Otto German expert in guided missiles during World War II. As of January 1947, last known to be working at Darmstadt.
Friedrich Schmiedl used powder rockets to make regular rocket mail service between two Austrian towns from 1931 to 1933.
Schmiedl, Friedrich (1902-1994) Austrian rocket pioneer, tested recoverable solid propellant rockets from 1924-1934 for use as stratospheric probes and mail delivery. Refused to participate in development of military rockets, either for the Nazis or the Americans.
Austrian manufacturer of rockets. Schmiedl, Austria.
Schmitt, Dr Harrison Hagan 'Jack' (1935-) American geologist astronaut. Flew on Apollo 17. Twelvth person and only geologist to walk on the moon.
Schmoll German rocket technician and engineer in WW2; later worked in France at LRBA as part of the armature group from 1947-1951 before returning to Germany.
Schnapper German rocket engineer in WW2. Later worked in France at LRBA in the doppler tracking group of the flight mechanics and control department from 1947-1952.
Schnarowski, Heinz Ludwig (1910-2005) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Schneider, William C American engineer, at NASA 1963-1980. Mission director for seven Gemini missions; Apollo mission director 1967-1968; Skylab Program director 1968-1974.
Schneider, Hans (1909-1990) German expert in jet propulsion at Peenemuende during World War II. As of January 1947, working at Munich. Later became head of ERNO.
Scholz, Walter (1907-) German measurement technician in WW2, worked in the Soviet Union thereafter. One of the group that fired V-2 rockets at Kapustin Yar in 1946.
Schomburg, August (1908-1972) American US Army US Army Officer. August Schomburg was a career Army officer who rose to the rank of lieutenant general. From 1960 to 1962 he was commander of the Army missile ordnance command at Redstone Arsenal.
Schongs, Bernhard German expert in guided missiles during World War II. As of January 1947, working "c/o Klinger", British Zone.
Schossig German rocket engineer in WW2; later worked in France at LRBA on gyroscopes and antennae in the automated control loop department 1947-1952.
Schrader, Leopold German expert in missile a-4 during World War II. As of January 1947, living at Ahrweiler, Grafschafterstr. "with Schmitz". (French Zone of Occupation).
Schriever, Bernard A (1910-2005) Key German-American military manager of development of the Thor, Atlas, Titan, and Minuteman ballistic missiles.
Schubert German rocket guidance engineer; later worked in France at LRBA as head of the automated control loop department 1946-1952.
Schuesseln, Leo K German expert in guided missiles during World War II. As of January 1947, living at Stuttgart, Gaenseheidestr. 15.
Schuetz, Wilhelm (1900-) German professor. Member of German Rocket Team in the Soviet Union after WW2. Measurement technician; worked in the Soviet Union after WW2.
Schuler, Albert E (1915-1998) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Schulz German staff officer and commander of V-2 units.
Schulze, August Wilhelm (1905-2001) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Schumann, Erich German expert in biological warfare during World War II. As of January 1947, last known to be working at Berlin.
Schuminszky, Nandor Hungarian historian. Space archivist; since 1964 collected over 10,000 photos and slides related to spaceflight and space research.
Schuran German engineer in WW2. Worked at LRBA from 1947 to 1958 as leader of the ground support equipment group. Returned to Germany thereafter.
Schwab German expert in guided missiles during World War II. As of January 1947, living at Berlin Schmargendorf Cranerstr. 3.
US base in the 1980's for 36 Pershing 2 IRBM's. The launchers and missiles were withdrawn and destroyed under the INF Treaty with the Soviet Union.
Schwarz, Friedrich Wilhelm (1909-1961) 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 Phoenix, Arizona.
Schwarz, Robert (1896-) German engineer in WW2, member of the Rocket Team in the Soviet Union thereafter.
Schwarz, Willi (1910-) German test engineer in WW2, worked on rocket engine development in Glushko's design bureau from 1947 to 1952. Worked as Deputy to the Test Bench Chief; Laboratory Department.
Schweickart, Russel Luis 'Rusty' (1935-) American pilot astronaut. Flew on Apollo 9.
Schwidetzky, Walter Hans (1910-) 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. Living in San Diego, California in 2004.
Category of spacecraft.
Science and Applications Manned Space Platform.
American manned space station. Study 1980. While NASA/Johnson was studying the Space Operations Center concept, the Marshall Space Flight Center was lobbying for its own station -- the Science and Applications Manned Space Platform (SAMSP).
Science and Technology Satellite.
Alternate designation for STSat technology satellite.
Scientific and Industrial Research Organization.
Iranian manufacturer of spacecraft. Scientific and Industrial Research Organization, Iran.
Category of persons.
A flash of light produced in a phosphor by an ionizing particle or photon.
Canadian earth atmosphere satellite. One launch, 2003.08.13.
Scobee, Francis Richard 'Dick' (1939-1986) American test pilot astronaut. Flew on STS-41-C, STS-51-L. Died in Challenger accident.
American communications technology satellite. One launch, 1958.12.18. Signal Communication by Orbiting Relay Equipment; first communications satellite; transmitted taped messages for 13 days.
American low cost orbital launch vehicle. Family of sounding rockets and launch vehicles based on combining liquid oxygen/kerosene pressure-fed engine modules. Modest government funding and over a decade of development had still not resulted in a production contract as of 2006.
Scott, David Randolph 'Dave' (1932-) American test pilot astronaut. Flew on Gemini 8, Apollo 9, Apollo 15. Seventh person to walk on the moon. First to drive a lunar wheeled vehicle. Member of first crew to dock in space.
Scott, Winston Elliott (1950-) African-American test pilot mission specialist astronaut. Flew on STS-72, STS-87.
American all-solid orbital launch vehicle. Solid-fuel, light payload, lower-cost launch vehicle developed by the Air Force and NASA in the late 1950's and used in a variety of configurations over thirty years. Launched from Cape Canaveral, Vandenberg, Wallops Island, and from Italy's equatorial San Marco platform off Kenya. Italy studied but did not develop subsequent upgraded versions.
Solid-fuel, light payload, lower-cost launch vehicle developed by the Air Force and NASA in the late 1950's and used in a variety of configurations over thirty years. Launched from Cape Canaveral, Vandenberg, Wallops Island, and from Italy's equatorial San Marco platform off Kenya. Italy studied but did not develop subsequent upgraded versions.
Scout 2.
Alternate Designation of Advanced Scout all-solid orbital launch vehicle.
American all-solid orbital launch vehicle. All-solid low cost lightweight launch vehicle.
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2C + 1 x Castor 2 + 1 x Antares 2 + 1 x Altair 2
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2B + 1 x Castor 2 + 1 x Antares 2 + 1 x FW4S
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2A + 1 x Castor 2 + 1 x Antares 2 + 1 x FW4S
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2C + 1 x Castor 2 + 1 x Antares 2 + 1 x Star 20
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2C + 1 x Castor 2 + 1 x Antares 2 + 1 x FW4S
American all-solid orbital launch vehicle.
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 3A + 1 x Castor 2 + 1 x Antares 2 + 1 x Star 20
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 3A + 1 x Castor 2 + 1 x Antares 2 + 1 x FW4S
American all-solid orbital launch vehicle. Five stage vehicle consisting of 1 x Algol 3A + 1 x Castor 2 + 1 x Antares 2 + 1 x FW4S + 1 x BE-3
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 3A + 1 x Castor 2 + 1 x Antares 2B + 1 x Star 20
Scout F-1.
Alternate designation for Scout F all-solid orbital launch vehicle.
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 3A + 1 x Castor 2 + 1 x Antares 3 + 1 x Star 20
Scout G-1.
Alternate designation for Scout G all-solid orbital launch vehicle.
American test vehicle. Single stage vehicle.
Solid rocket stage. 590.00 kN (132,637 lbf) thrust. Mass 17,300 kg (38,140 lb).
American suborbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1A + 1 x Castor + 1 x Antares + 1 x Altair
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1B + 1 x Castor + 1 x Antares + 1 x Altair
American all-solid orbital launch vehicle. Five stage vehicle consisting of 1 x Algol 1B + 1 x Castor + 1 x Antares + 1 x Altair + 1 x Cetus
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1D + 1 x Castor + 1 x Antares 2 + 1 x Altair
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1C + 1 x Castor + 1 x Antares 2 + 1 x Altair
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1D + 1 x Castor + 1 x Antares 2 + 1 x Altair 2
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1D + 1 x Castor + 1 x Antares 2 + 1 x MG-18
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair
American all-solid orbital launch vehicle. Five stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair + 1 x Cetus
American all-solid orbital launch vehicle. Three stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x MG-18
Solid propellant rocket stage. Loaded mass 300 kg.
American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair 2
American all-solid orbital launch vehicle. Five stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair 2 + 1 x Cetus
American suborbital launch vehicle. Three stage vehicle consisting of 1 x Algol 2B + 1 x Castor 2 + 1 x Antares 2
Scout X-5C.
Alternate designation for Scout X-5 suborbital launch vehicle.
Scrag.
ASCC Reporting Name of GR-1 intercontinental ballistic missile.
Supersonic combustion ramjet engine
Scramjet engine for X-30 SSTO. 1372.9 kN. Development ended 1992. Thrust is maximum sea level thrust; specific impulse is average during ascent. Isp=1550s. Propellant Slush LH2.
American agency overseeing development of spacecraft. SCREEM, USA.
Scrooge.
SCS.
Stabilization and control system
SCT.
Schmidt-Cassegrain Telescope
SCU.
Santa Clara University, USA
Scud A.
ASCC Reporting Name of R-11 tactical ballistic missile.
Scud B.
ASCC Reporting Name of R-17 mobile short-range liquid-propellant ballistic missile. Later used to designate North Korean Hwasong 5 copy of the R-17 with a range of 340 km and the Iranian Shahab-1 license-built version of the Korean missile.
Mobile Iraqi Scud batteries were known to have been used for 59 wartime launches from 1990 to 1991, reaching up to 100 kilometers altitude, en route to targets in Israel and Saudi Arabia.
Scud C.
ASCC Reporting Name of a longer-range version of the R-17 mobile ballistic missile, tested in the 1960's but not put into production in the Soviet Union. Later applied to the North Korean Hwasong 6 development of the R-17 with a range of 500 km and the Iranian Shahab-2 version of the same missile.
Scud D.
ASCC Reporting Name of a precision-guidance version of the R-17 mobile short-range liquid-propellant ballistic missile. Tested but not put into production due to the collapse of the Soviet Union. Later used to designate North Korean Hwasong 7 copy of the R-17 with a range of 500 km.
Scully-Power, Paul Desmond (1944-) Australian-American geophysicist payload specialist astronaut. Flew on STS-41-G.
Scunner.
ASCC Reporting Name of R-1 missile.
SDC.
US Army Strategic Defense Command
SDI.
American military strategic defense satellite. 18 launches, 1986.09.05 (USA 19) to 1989.03.24 (USA 36). SDIO sensor tests.
SDI.
Strategic Defense Initiative
SDIO.
Precursor organization to BMDO
SDIO.
American agency overseeing development of spacecraft. Strategic Defense Initiative Organization (renamed the BMDO), USA.
SDO.
NASA's Solar Dynamics Observatory mission was to observe the Sun for a five year period from an inclined geosynchronous orbit. From there the satellite could constantly download data to the White Sands ground station, while minimizing the time spent in Earth's shadow. The satellite's three instruments measured the extreme ultraviolet radiation output, returning up to 150 million bits of data per second. Launched 2010.02.11,
SDS.
American military communications satellite. 7 launches, 1976.06.02 (SDS no. 1) to 1987.02.12 (USA 21). SDS satellites, put into Molniya-type orbits, provided data relay services for optical reconnaissance and other military spacecraft.
American military communications satellite. 4 launches, 1989.08.08 (USA 40) to 1996.07.03 (USA 125).
American military communications satellite, provided data relay services for optical reconnaissance and other military spacecraft. Operational, first launch 2000.12.06.
SDS-C.
Manufacturer's designation for CAPRICORN military communications satellite.
SE.
Solar Explorer satellite
French post-war surface-to-air missile based on the German Hs.117.
French post-war surface-to-air missile based on the German Rheintochter.
French post-war surface-to-air missile based on the German Enzian.
French surface-to-air missile. SNCASE missile design using a Stromboli booster and two ramjet sustainers.
SE-1.
Manufacturer's designation of SE-1, 1-1, -2, and -4 Series N2O4-UDMH rocket engine.
Rocketdyne N2O4/UDMH rocket engine. SE-1, 1-1, -2, and -4 Series. Spacecraft Reaction Control. Pressure-fed. Multiple thrust levels. First flight 1959.
Rocketdyne N2O4/Aerozine-50 rocket engine. 46.670 kN. Lunar Module Descent. Pressure-fed. Thrust throttleable 1050-10,500 lbs vac. Isp=305s. First flight 1968.
Solid propellant rocket stage. Loaded mass 1,500 kg. Thrust 200.00 kN.
SE-5-2.
Manufacturer's designation of SE-5-2--3 N2O4-UDMH rocket engine.
Rocketdyne N2O4/UDMH rocket engine. 0.205 kN. SE-5-2/-3. Agena Auxiliary. Pressure-fed. SE-5-2 four engines in satellite system. SE-5-3 two engines for Agena auxiliary propuslion. Isp=272s. First flight 1963.
SE-6.
Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Gemini Re-entry Control System. Pressure-fed. Isp=277s. First flight 1964.
SE-7.
Rocketdyne N2O4/MMH rocket engine family. Developed for Gemini Orbit Attitude and Maneuvering System; later satellite applications.
Rocketdyne N2O4/MMH rocket engine. 0.313 kN. S-IVB Stage APS Ullage Control Engine (propellant settling). Pressure-fed. Isp=274s. First flight 1966.
Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Gemini Orbit Attitude and Maneuvering System (100 Ib thrust). Pressure-fed. Isp=296s. First flight 1964.
Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Gemini Orbit Attitude and Maneuvering System (25 Ib thrust). Pressure-fed. Isp=277s. First flight 1964.
Rocketdyne N2O4/MMH rocket engine. 0.372 kN. Gemini Orbit Attitude and Maneuvering System (85 Ib thrust). Pressure-fed. Isp=295s. First flight 1964.
SE-8.
Rocketdyne N2O4/MMH rocket engine. 0.411 kN. Apollo Command Module Reaction Control. Pressure-fed. Isp=274s. First flight 1966.
SE-9.
Rocketdyne N2O4/Aerozine-50 rocket engine family. Titan III Transtage.
Rocketdyne N2O4/Aerozine-50 rocket engine. 0.107 kN. Titan III Transtage. Pressure-fed. System included two modules of three engines plus two additional SE-9-5 separate engines, tanks, and a pressuirzation system. Isp=295s. First flight 1964.
Rocketdyne N2O4/Aerozine-50 rocket engine. 0.196 kN. Titan III Transtage. Pressure-fed. System included two modules of three engines plus two additional SE-9-5 separate engines, tanks, and a pressuirzation system. Isp=300s. First flight 1964.
American sea-launched test vehicle. Seabee was a brief proof of principle program to validate the sea-launch concept for Sea Dragon. A surplus Aerobee rocket was modified so that it could be fired underwater. The rocket worked properly the first time in restrained mode. Later tests were made with various approaches to readying the unit for repeat firings. This proved to be so simple that the cost of turn-around was found to be about 7% of the cost of a new unit.
American sea-launched heavy-lift orbital launch vehicle. Sea Dragon was an immense, sea-launched, two-stage launch vehicle designed by Robert Truax for Aerojet in 1962. It was to be capable of putting 1.2 million pounds (550 tonnes) into low Earth orbit. The concept was to achieve minimum launch costs through lower development and production costs. This meant accepting a larger booster with a lower performance propulsion system and higher stage dead weight then traditional NASA and USAF designs.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 11,600,000/1,300,000 kg. Thrust 356,900.00 kN. Vacuum specific impulse 290 seconds. Sea level thrust shown. Thrust, chamber pressure varies during ascent. Vacuum thrust at cut-off 40 million kgf. Total mass, specific impulse estimated from booster performance figures.
Aerojet Lox/Kerosene rocket engine. 356,9 kN. Design, 1962. Isp=290s. Truax pressure fed design. Thrust, chamber pressure varied during ascent.
Lox/LH2 propellant rocket stage. Loaded/empty mass 5,900,000/530,000 kg. Thrust 62,270.00 kN. Vacuum specific impulse 320 seconds. Length with extendible nozzle deployed 87 m. Diameter of extended nozzle 30 m. Total mass, specific impulse estimated from booster performance figures.
Aerojet lox/lh2 rocket engine. 62,270 kN. Design, 1962. Truax pressure fed design. Diameter of extended nozzle 30 m. Specific impulse estimated from booster performance figures. Isp=320s.
American sea-launched test vehicle. The second phase of Sea Launch was to demonstrate the concept on a larger scale, with a rocket with a complex set of guidance and control systems. Sea Horse used one of 39 surplus Corporal missiles that Truax obtained from the Army and successfully demonstrated ignition in the ocean of a rocket stage.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 40,000/5,000 kg. Thrust 755.00 kN. Vacuum specific impulse 285 seconds.
Lox/LH2 propellant rocket stage. Loaded/empty mass 15,000/2,000 kg. Thrust 147.00 kN. Vacuum specific impulse 425 seconds.
Sea Lance.
Popular Name of XMGM-52B short range ballistic missile.
Sea Launch.
Alternate name for Kiritimati launch site.
Category of launch sites.
Sea of Okhotsk Launch Area
British surface-to-air missile.
British surface-to-air missile.
American sea-launched orbital launch vehicle. Sea-launched microsatellite orbital launch vehicle for payloads up to 13 kilograms and a testbed for the planned larger Neptune orbital launch vehicle.
Seaborg, Glenn T (1912-1999) American physicist, chair of the Atomic Energy Commission 1961-1971.
American sounding rocket. Single stage vehicle.
Solid rocket stage.
American manufacturer of spacecraft. Seal Beach, USA.
American sea-launched orbital launch vehicle. SEALAR (SEA LAunched Rocket) was yet another attempt by Truax Engineering to get the amphibious-launch concept off the ground. The project received some Navy Research Laboratory funding in the early 1990's, with a planned first launch date of 1996. A production model would have been able to achieve orbit at an estimated cost of $ 10 million per launch. As with the earlier Truax projects, it did not achieve flight test status.
American agency. SeaLaunch, USA.
Sounding rocket launched from a naval vessel at an undocumented location. 2001 launches from 1956 to 2008, reaching up to 35,820 kilometers altitude, fall into this category.
Category of launch vehicles.
Seamans, Robert C (1918-2008) American engineer. Key leadership positions at NASA 1960-1968 during the Apollo program.
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Searfoss, Richard Alan 'Rick' (1956-) American test pilot astronaut. Flew on STS-58, STS-76, STS-90.
American earth resources radar satellite. One launch, 1978.06.27. Seasat was the first satellite designed for remote sensing of the Earth's oceans with synthetic aperture radar (SAR).
British surface-to-air missile. Ramjet
Ramjet-powered surface-to-air missile series.
SeaStar; SeaWiFS.
Alternate designation for Orbview-2 civilian surveillance satellite.
SEB.
Source Evaluation Board
Seba Oasis.
Alternate name for Tawiwa launch site.
sec.
second(s)
Sechkin, Aleksey Semenovich (1936-) Russian officer. Major General, Chief Commander of the Mozhaisky School, 1984-1991.
Second Generation Soviet Space Systems.
Second Generation Soviet Space Systems
American earth geodetic satellite. 13 launches, 1962.01.24 (Secor) to 1969.04.14 (SECOR 13).
SECS.
Alternate designation for GLOMR military store-dump communications satellite.
British military communications satellite. Study 1990. United Kingdom military communications satellite; 1 deg W. Owner/operator: UK Ministry of Defense. Expected operational life 10 years.
SECT.
SECT
Seddon, Dr Margaret Rhea (1947-) American physician mission specialist astronaut. Flew on STS-51-D, STS-40, STS-58. Physician. Was married to astronaut Robert Lee (Hoot) Gibson.
Sedov, Leonid Ivanovich (1907-) Russian scientist. Chaired the Commission for Promotion of Interplanetary Flights. Public spokesman for the Soviet space program.
SEDR.
Spacecraft Engineering Design (Development) Report
SEDS.
American tether technology satellite. 4 launches, 1993.03.30 (SEDS 1) to 1994.03.10 (SEDS 2 Deployer).
SEDS.
American manufacturer of spacecraft. Students for the Exploration and Development of Space, USA.
American technology satellite. One launch, 1998.10.24. The SEDSAT micro-satellite was built by the Huntsville, Alabama chapter of SEDS (the Students for the Exploration and Development of Space).
See.
See, Elliot McKay Jr (1927-1966) American test pilot astronaut, 1962-1966. Died in crash of his T-38 trainer into the McDonnell Aircraft plant.
Japanese technology satellite. One launch, 2008.04.28. Nihon University at Tokyo nanosat.
Seeler, H German expert in aero medicine during World War II. As of January 1947, working in Heidelberg (American Zone of Occupation).
Sefchek, Paul Andrew (1946-1997) American engineer military spaceflight engineer astronaut, 1979-1985.
Sega.
Sega, Dr Ronald Michael 'Ron' (1952-) American engineer mission specialist astronaut. Flew on STS-60, STS-76. Was married to astronaut Bonnie Dunbar.
Sego.
SEI.
Space Exploration Initiative
Seidel, Joachim German rocket engineer at BMW document center during World War II. As of January 1947, working at Rosenheim, Bavaria. Later worked in France in the engine group at LRBA from 1947 until retiring in 1977. Remained in France, living in Vernon.
Iranian two-stage solid propellant intermediate range ballistic missile, with a range of 2,000 km.
Family of Iranian launch vehicles.
American manned space station. Study 1963. The first space station designs using the Saturn V launch vehicle involved spinning stations, providing artificial G for the crew.
German sounding rocket. Berthold Seliger's firm designed a modular series of sounding rockets in 1961-1964. One, two, and three stage versions were built, reaching 52, 80, and 120 km altitude.
Berthold Seliger's firm designed a modular series of sounding rockets in 1961-1964. One, two, and three stage versions were built, reaching 52, 80, and 120 km altitude.
Seliger, Berthold (1928-) German engineer, assistant to Saenger, most successful developer of rocketry in Germany 1960-1964. Work was ended by government decision to restrict missile development to established military contractors.
German manufacturer of rocket engines and rockets. Seliger, Germany.
Seliger solid rocket engine. 49 kN.
German sounding rocket.
German sounding rocket.
Seliger solid rocket engine.
German sounding rocket.
Solid propellant rocket stage. Thrust 49.00 kN.
Solid rocket stage.
Sellers, Piers John (1955-) British-American ecologist mission specialist astronaut. Flew on STS-112, STS-121, STS-132.
Matador and MGM-13A Mace operating base, 1955 to 1966.
Semenov, Anatoli Ivanovich (1908-1973) Russian officer. Commander of GURVO 1954-1964.
Semenov, Yuri Pavlovich (1935-) Russian engineer. General Designer of RKK Energia 1989 to 2005
Launch site for Iran's Safir space launch vehicle.
Semyorka.
Alternate designation for R-7A missile.
Sendler, Karl (1914-) Austrian-German engineer in WW2, member of the Rocket Team in the United States thereafter.
Senior.
Alternate designation for Algol 1 rocket stage.
Senior.
Manufacturer's designation of Algol 1 Solid rocket engine.
American intermediate range stealth cruise missile. US Air Force program with test flights in 1978-1981.
Senkevich, Dr Yuri Aleksandrovich (1937-2003) Russian physician cosmonaut, 1965-1966.
American anti-ballistic missile. ABM, BTDS missile
Sep.
Separation
SEP.
First name of SEPR
Aerospatiale solid rocket engine. 900 kN.
Aerospatiale solid rocket engine. 300 kN.
Aerospatiale solid rocket engine. 100 kN.
Sud/SEP solid rocket engine. 440 kN.
Sud/SEP solid rocket engine. 540 kN.
SEP solid rocket engine. 440 kN.
Sud/SEP solid rocket engine. 450 kN.
American space tug. Study 1986. In 1986, Graeme Aston of NASA's Jet Propulsion Laboratory proposed a lunar transportation system based on a solar-electric propulsion (SEP) space tug for ferrying moon base elements and cargo between Earth and lunar orbit.
SEPC.
Space Exploration Program Council
SEPR.
French manufacturer of rocket engines. Société Européene de Propulsion, France.
SEPR rocket engine. 200 kN. AA.10 AAM. First flight 1950.
SEPR rocket engine. 1250 kN. SE 4100 SAM. Used turbopumps SEPR 3 and SEPR 4. First flight 1950.
SEPR 200.
Manufacturer's designation of Tramontane Solid rocket engine.
French post-war missile based on the German 109-510A.
SEPR rocket engine. 4500 kN. Trident/Espadon fighter augmentation.
SEPR rocket engine. 1250 kN. R.04 SAM. First flight 1950.
ONERA solid rocket engine. 33 kN.
ONERA solid rocket engine. 200 kN.
ONERA solid rocket engine. 75 kN.
SEPR 739.
Manufacturer's designation of Stromboli Solid rocket engine.
ONERA solid rocket engine. 170 kN.
SEPR solid rocket engine family.
SEPR solid rocket engine. 91.7 kN. Out of production. Isp=230s. Used on Berenice, Titus. First flight 1962.
ONERA solid rocket engine. 170 kN.
Matra solid rocket engine. 1.4 kN.
SEP solid rocket engine.
Matra solid rocket engine. 14.8 kN.
Sud solid rocket engine. 200 kN.
SEPS.
Hughes, TRW, NASA Cleveland electric/mercury rocket engine. 128 mN Isp=3000s. Solar Electric Propulsion Stage program, started in the early 1970s, a goal to provide a primary ion propulsion system operating at a fixed power for Earth orbital applications.
JPL, Hughes, TRW electric/mercury rocket engine. 88 mN. Isp=3600s. The Solar Electric Propulsion System Technology program of 1960-1980 demonstrated a complete breadboard ion propulsion system that would be applicable to an interplanetary spacecraft.
Serb.
Serbin, Ivan Dmitryevich (1910-1981) Russian government official. Chief of Defence lndustries Department 1958-1981.
French manufacturer of rocket engines and rockets. SEREB, France.
Serebrov, Aleksandr Aleksandrovich (1944-) Russian engineer cosmonaut. Flew on Salyut 7 EP-2, Soyuz T-8, Mir EO-5, Mir EO-14. Ten spacewalks. 372 cumulative days in space. Civilian Engineer, Energia NPO. Civilian Engineer, Energia NPO.
Single-stage solid-propulsion tactical ballistic missile developed for the US Army. Surplus rockets and the Sergeant's rocket motor (known commercially as Castor) became the basis for many sounding rockets.
American single-stage solid-propulsion tactical ballistic missile developed for the US Army in 1956-1962. Surplus rockets and the Sergeant's rocket motor (known commercially as Castor) became the basis for many sounding rockets.
Multiple-source solid rocket engine. 6.660 kN. Out of Production. Used in Jupiter C, Juno 2. Isp=235s. First flight 1956.
Solid propellant rocket stage. Loaded/empty mass 42/21 kg. Thrust 6.66 kN. Vacuum specific impulse 235 seconds.
American test vehicle. Five stage vehicle consisting of 1 x Sergeant + 1 x Lance + 1 x Lance + 1 x Recruit + 1 x T-55
American sounding rocket. Two stage vehicle consisting of 1 x Sergeant + 1 x Hydac
American sounding rocket. Single stage vehicle consisting.
Poem: in the garden of the spacecraft designer, nightingales fly to his trees....
Sergeyev, Vladimir Grigoryevich (1914-) Russian officer. From 1966 General Director and Chief Designer for OKB-692 GKRE (later NPO Elktropribot, Kharkov). Designer of control systems for missiles and space launchers.
Serov, Ivan Aleksandrovich (1905-1990) Russian government official. First Deputy Minister of Internal Affairs. Chaired KGB 1954-1958.
Serov, Mark Vyacheslavovich (1974-) Russian engineer cosmonaut, 2003-on. An engineer at RKK Energia since 1998.
Serova, Elena Olegovna (1976-) Russian engineer cosmonaut, 2006-on.Wife of Mark Serov (2003 selection group) Graduate of MAI. Worked in TsUP Flight Control Center.
SERT.
American ion engine technology satellite. One launch, 1970.02.04. Electric ion engine tests.
NASA Cleveland electric/mercury rocket engine. 28 mN. Flown in 1970. Isp=4200s. The thruster for the Sert-II test consisted of two electron bombardment engines using mercury propellant.
Hughes electric/cesium rocket engine. 5.6 naN. In Development, 1962-1964. Isp=8050s. 8 cm diameter cesium contact ion engine was designed to operate at 0.6 kW.
NASA Cleveland electric/mercury rocket engine. 28 mN. Developed 1962-1964. Isp=4900s. 10 cm diameter mercury electron bombardment ion engine used on the first successful flight test of ion propulsion on a Scout X-4 launch vehicle.
SERV.
American VTOVL orbital launch vehicle. Chrysler ballistic single stage to orbit alternate shuttle proposal of June 1971. This was the most detailed design study ever performed on a VTOVL SSTO launch vehicle. The 2,040 tonne SERV was designed to deliver a 53 tonne payload to orbit in a capacious 7 m x 18 m payload bay.
Japanese technology satellite. First launch 2003.10.30.
SES.
Second name of SES Americom
SES.
Luxembourg agency overseeing development of spacecraft. Societe Europeene des Satellites, Luxembourg.
American agency. Americom, USA.
SESP.
American military technology satellite. 3 launches, 1971.06.08 (SESP 70-1) to 1976.07.08 (SESP 74-2). Space craft engaged in investigation of spaceflight techniques and technology.
SEST.
Swedish ESO Submillimeter Telescope
SETI.
Search for ExtraTerrestrial Intelligence
SEV.
Satellite time synchronisation system (Russian abbreviation)
SEVA.
Surface extravehicular activity (lunar exploration); also standup extravehicular activity
Sevastyanov, Vitali Ivanovich (1935-2010) Russian engineer cosmonaut. Flew on Soyuz 9, Soyuz 18.
Sevastyanov, Nikolai (1944-) Russian engineer. General Designer of RKK Energia 2005 to 2007
Russian manned spacecraft. Study 1959. Sever was the original OKB-1 design for a manned spacecraft to replace the Vostok. It was designed to tackle such problems as maneuvering in orbit, rendezvous and docking, and testing of lifting re-entry vehicles.
Severin, Gay Ilich (1926-2008) Russian engineer. Chief Designer and General Designer from 1961 of OKB Zvezda. Specialised in spacesuits and EVA airlocks.
Severin, Vladimir Gayevich (1956-) Russian engineer cosmonaut, 1990-1995. Son of design bureau chief Gay Ilich Severin.
Russian manufacturer of rocket engines. Sevruk Design Bureau, Russia.
Russian earth geodetic satellite. 18 launches, 1968.02.20 (Cosmos 203) to 1978.12.26 (Cosmos 1067). The Sfera geodetic system covered a broad development for solving problems in geodetics, continental drift, and precise location of cartographic points.
SFOF.
Space Flight Operations Facility
SFU.
Japanese materials science satellite. One launch, 1995.03.18. Carried materials, astronomy, biological experiments; released and later retrieved by space shuttle.
System of Global Space Radio Observation
SH-11.
Alternate Designation of 51T6 anti-ballistic missile.
SH-8.
Alternate designation for 53T6 anti-ballistic missile.
Shaba North.
Alternate name for Kapani Tonneo launch site.
Shabalin, Vladimir Alekseyevich (1920-) Russian officer. Lieutenant General, from 1970 Chief Designer and Director of MNII for Automatic Equipment. From 1954 to 1958 senior scientific specialist in NII-5 GAU. Developed systems for KIK space tracking and control network.
Shabarov, Yevgeni Vasilyevich (1922-) Russian engineer. Deputy Chief Designer at Korolev design bureau. Led the flight testing of piloted spacecraft.
Shaddock-B.
ASCC Reporting Name of P-6 intermediate range cruise missile.
Headquarters of an RVSN Division, 1961-1962. Base for units deployed with R-16 launchers.
Iranian derivatives of North Korean Nodong 1 intermediate range ballistic missile, evolved incrementally with Russian assistance into a longer-range missile and the first stage of an orbital launch vehicle.
Shahab 1.
Iranian designation for their version of the North Korean Hwasong 5 Scud-B short range missile.
Shahab 2.
Iranian designation for their version of the North Korean Hwasong 6 Scud-C short range ballistic missie.
Iranian intermediate range ballistic missile, evolved incrementally with Russian assistance from initial copy of North Korean Nodong 1 into a longer-range missile and the first stage of an orbital launch vehicle. Initial version began flight tests in 1998.
Nitric acid/UDMH rocket stage. 255.00 kN (57,326 lbf) thrust. Mass 15,100 kg (33,290 lb).
Iranian missile said to be derived from Soviet-era R-12 intermediate range ballistic missile and having a 1400 kg payload. Was to have been the basis for an Iranian space launcher, then abandoned in 2003 in favor of development of the Shahab 3 for the role.
Shahab 6.
Alternate designation for Safir-2 orbital launch vehicle.
Shaheen.
Pakistani designation for DF-11 short range ballistic missile.
Pakistani ballistic missile family, starting with license-assembled Chinese DF-15's and progressing to indigenous models.
Pakistani mobile single-stage solid propellant intermediate range ballistic missile, a license-assembled Chinese DF-15. First flown in 1999. Entered service 2003. Project managed by Pakistan Atomic Energy Commission.
Pakistani mobile two-stage solid propellant intermediate range ballistic missile developed by Pakistan, derived from Chinese technology. First flight March 9, 2004. Range extended from 2,500 km to 3,500 km during development.
Nitric acid/UDMH rocket stage.
Pakistani indigenous long-range missile, designed by Pakistani scientists using Chinese technology. Development cancelled in 2000.
Sanjiang Nitric acid/UDMH rocket engine.
Iranian manufacturer. Shahid Hemmat IG, Iran.
Shahroud
Shakhurin, Aleksei Ivanovich (1904-1975) Russian government official. People's Commissar for Aviation Industries 1940-1946.
Shane, Doug American test pilot, headed Flight Operations at Scaled Composites from 1989.
Chinese manufacturer of rocket engines and rockets. Shanghai Institute of Electro-mechanical Design, Shanghai, China.
Chinese manufacturer. Shanghai Astronautics Bureau, Shanghai, China.
Shanghai Institute of Satellite Engineering.
Shanghai Institute of Satellite Engineering.
Shanghai No. 2 Bureau of Mechanic-Electrical Indus.
Chinese manufacturer. Shanghai No. 2 Bureau of Mechanic-Electrical Industry, Shanghai, China
Shanghai Aerospace Research Technical Institute, China
Chinese manufacturer of rocket engines and rockets. Shanxi Institute of Power Machinery, China.
Shao Zhijian (1940-) Chinese pilot taikonaut, 1971, but program cancelled less than a year later. Joined PLA in 1958. He was a PLAAF regiment commander when selected. Selected as Chinese astronaut in March 1971.
Supersonic High Altitude Parachute Experiment
Shapley, Willis H (1917-2005) American manager, served at NASA 1965-1975 and 1987-1988.
Sharafutdinov, Ansar Ilgamovich (1939-) Tatar-Russian pilot cosmonaut, 1965-1968. Cosmonaut training November 1965 - December 1967. Withdrawn from cosmonaut team for medical reasons. Retired from active military duty in 1985. Later taught at a Higher School.
Shargin, Yuri Georgiyevich (1960-) Russian engineer cosmonaut. Flew on ISS EP-7. Russian Strategic Rocket Force
Sharik.
Russian nickname (sphere) for Vostok SA manned spacecraft module.
Sharipov, Saliszan Shakirovich (1964-) Tatar-Russian pilot cosmonaut. Flew on STS-89, ISS EO-10. First Uzbek astronaut. SU Air Force.
Sharma, Rakesh 'Rikki' (1949-) Indian pilot cosmonaut. Flew on Salyut 7 EP-3. First Indian astronaut. Indian Air Force
Sharman, Helen Patricia 'Lenochka' (1963-) British engineer cosmonaut. Flew on Mir Juno. Chemist. First British astronaut. First non-American, non-Soviet female astronaut.
Sharov, Valeri Yuriyevich (1953-) Russian journalist cosmonaut, 1990-1992.
American gun-launched test vehicle. The SHARP (Super High Altitude Research Project) light gas gun was developed by Lawrence Livermore Laboratory in California. The L-shaped gun consisted of the 82 m long, 36 cm calibre pump tube and the 47 m long, 10 cm calibre gun barrel. SHARP began operation in December 1992 and demonstrated velocities of 3 km/sec with 5 kg projectiles. However the $ 1 billion funding to elevate the tube and begin space launch tests of smaller projectiles at speeds of up to 7 km/sec was not forthcoming. By 1996 the gun was relegated to occasional test of sub-scale Mach 9 scramjet models.
Shatalov, Vladimir Aleksandrovich (1927-) Russian pilot cosmonaut. Flew on Soyuz 4, Soyuz 8, Soyuz 10. Made first Soviet space docking.
Satellite launcher derived from Jericho II MRBM, essentially identical to South African RSA-3. NEXT was a variant with an improved upper stage for proposed launch from Wallops Island, USA (launch from Israel is only possible into retrograde orbits since due East launch would be over territory of adjacent countries).
Israeli all-solid orbital launch vehicle. Satellite launcher derived from Jericho II MRBM, essentially identical to South African RSA-3.
Israeli all-solid orbital launch vehicle. Shavit 1 is an improved version of the original Shavit with a stretched first stage motor.
Shaviyt.
Alternate designation for Shavit all-solid orbital launch vehicle.
Shaviyt 1.
Alternate designation for Shavit 1 all-solid orbital launch vehicle.
Shavyrin, Boris Ivanovich (1902-1965) Russian engineer. From 1942-1965 Manager and Chief Designer of the Kolomna Mechanical Engineering Design Bureau. Designer of artillery and rocket equipment.
Shaw.
Shaw, Brewster Hopkinson Jr (1945-) American test pilot astronaut. Flew on STS-9, STS-61-B, STS-28.
Shcheglov, Vasily Dmitriyevich (1940-1973) Russian pilot cosmonaut, 1965-1972. Graduated from Yeisk Higher Military Pilot School, 1963 Cosmonaut training November 1965 - December 1967. Withdrawn from cosmonaut team for medical reasons. Died of lung cancer.
Shcheulov, Viktor Ivanovich (1922-) Russian officer, Deputy Chief Scientific Research Centre of the Ministry of Defence (1982-1983). From 1945, ascending positions in management of rocket development. Moved to space forces in 1961, worked with KIK space tracking network.
Shchukin, Alexandr Vladimirovich (1946-1988) Belarusian test pilot cosmonaut, 1980-1988.
Shea.
Shea, Joseph Francis (1926-1999) American engineer. Lead NASA manager responsible for development of the Apollo spacecraft
Sheffer, Yuri Petrovich (1947-2001) Russian test pilot cosmonaut, 1985-1996. Was married to cosmonaut Tamara Zakharova.
Shehab 4.
Alternate designation for Shahab 4 intermediate range ballistic missile.
Sheksna-N.
Launch System of R-16 intercontinental ballistic missile.
Sheksna-V.
Launch System of R-16U intercontinental ballistic missile.
Sheksnva-V.
Launch System of UR-200 intercontinental ballistic missile.
Sheldahl.
Shelter Module.
Alternate designation for Gemini LSSS SM manned spacecraft module.
Shen Qizhen (1906-1993) Chinese PLA Physician. Chairman of the Chinese Academy of Medical Sciences, one of three senior scientists that laid out plans for the first Chinese manned spacecraft in April 1966.
Shenjian.
Popular Name of CZ-2F orbital launch vehicle.
Chinese spaceplane. Study 2007. Chinese spaceplane photographed under the belly of an H-6 medium bomber in 2007. Probably a subscale drop test model of a potential space combat system.
Chinese manned spacecraft. Operational, first launch 1999.11.19. The Chinese Shenzhou manned spacecraft resembled the Russian Soyuz spacecraft, but was of larger size and all-new construction.
Shenzhou - Divine Military Vessel.
As the first Chinese astronauts rocket into orbit, their main concern will be completion of an ambitious programme of military experiments.
Crew: Yang Liwei. First Chinese man in space. Highly conservative mission. Single astronaut stayed in the re-entry capsule for the entire 21-hour mission, and did not enter the orbital module. Backup crew: Zhai Zhigang.Support crew: Nie Haisheng.
China's second manned mission took two astronauts into space for nearly five days, and featured use by a crew of the Shenzhou orbital module for the first time. Crew: Fei Junlong, Nie Haisheng. Backup crew: Liu Buoming, Jing Haipen.Support crew: Zhai Zhigang, Wu Jie.
Quick facts on the Shenzhou 6 mission.
Crew: Zhai Zhigang, Liu Buoming, Jing Haipen. First Chinese EVA. First Chinese three-crew spaceflight. Third Chinese manned space mission. The Shenzhou was flown with the full complement of three crew and astronaut Zhai conducted China's first spacewalk. Backup crew: Chen Quan, Fei Junlong, Nie Haisheng.
Chinese manned lunar flyby spacecraft. In January and February 2003 Chinese sources began discussing plans for a Chinese manned circumlunar mission by 2008. Nothing came of these plans.
Chinese manned spacecraft module. Operational, first launch 1999.11.19. The orbital module provided quarters for the crew during the space mission, and could be fitted out with different internal and external equipment according to mission requirements.
Chinese manned spacecraft module. Operational, first launch 1999.11.19. The re-entry vehicle was conceptually based on the Soyuz, but was not a copy.
Chinese manned spacecraft module. Operational, first launch 1999.11.19. The service module, developed by the Shanghai Academy of Space Technology, provides the electrical power, attitude, control and propulsion for the spacecraft in orbit.
Trivia and quick facts about the Shenzhou manned spacecraft
Shepard, Alan Bartlett Jr 'Al' (1923-1998) First American in space. Flew on Mercury MR-3, Apollo 14. Grounded due on medical grounds during Gemini, but reinstated, becoming fifth person to walk on the moon. Millionaire entrepreneur on the side.
Shepherd, William McMichael 'Bill' (1949-) American engineer mission specialist astronaut. Flew on STS-27, STS-41, STS-52, ISS EO-1. Shepherd was an ex-Navy SEAL and an expert in underwater demolition.
Sheremetyevskiy, Nikolai Nikolayevich (1916-) Russian engineer. Chief Designer 1974-1991 of losifyan design bureau. Specialised in power sources and earth survey satellites.
Shevardnadze, Eduard A (1927-) Georgian politician, reform leader in the Soviet Union, negotiated with the United States for international cooperation in space, including the building of a space station in the 1990s.
Shevchenko, Dmitri Panteyevich (1925-) Russian officer. Major General, Deputy Chief of GUKOS Space Forces for Political Units 1981-1984.
Shi Jian 1.
Alternate designation for SJ communications technology satellite.
Shi Jian 6.
Alternate designation for SJ-6 military naval signals reconnaisance satellite.
Shiborin, Serenti (-1958) Russian phantom cosmonaut. Oberth claimed in 1959 that a pilot was killed on a sub-orbital flight from Kapustin Yar in early 1958. Italian press linked Shiborin name to this flight. No other evidence.
Sounding rocket launch location known to have been used for 7 launches from 1960 to 1966, reaching up to 115 kilometers altitude.
Shinawatra Satellite, Bangkok, Thailand
Thai agency. Shinawat, Thailand.
Category of missiles.
Poem: We sail onboard space station "Alpha"...
Chinese civilian surveillance satellite. 2 launches, 2004.04.18 (Tansuo 1) to 2008.11.05 (Shiyan Weixing 3). The first 'Experiment Satellite', with a mass of 204 kg, was China's first transmission-type small satellite capable of stereo mapping.
Chinese resources. One launch, 2004.11.18. Remote Sensing Technology.
Shiyong Tongbu Tongxin Weixing.
Alternate designation for DFH-2 military communications satellite.
Shkaplerov, Anton Nikolayevich (1972-) Russian pilot cosmonaut, 2003-on.
Shlykov, Nikolair Fedorovich (1922-) Russian officer. Lieutenant General, Chief Commander of KIK for Satellites at Golintso-2 1976-1988.
Shonin, Georgi Stepanovich (1935-1997) Russian pilot cosmonaut. Flew on Soyuz 6.
British manufacturer. Short Brothers, UK.
Category of missiles.
Category of missiles.
American test vehicle. Three stage vehicle consisting of 2 x Recruit + 1 x Sergeant + 1 x Altair
Indian containerized solid-propellant tactical missile.
Shrimp.
Alternate designation for Midgetman missile.
Shriver, Loren James (1944-) American test pilot astronaut. Flew on STS-51-C, STS-31, STS-46. Grew up in Paton, Iowa.
Shtil.
Popular Name of R-29RM submarine-launched ballistic missile.
Russian intercontinental ballistic orbital launch vehicle. Three stage vehicle based on R-29RM SLBM.
Shtil'.
Alternate designation for Shtil missile.
Shtil'-1.
Alternate designation for Shtil-1-1N intercontinental ballistic orbital launch vehicle.
Russian intercontinental ballistic orbital launch vehicle. Three stage vehicle based on R-29RM SLBM.
N2O4/UDMH propellant rocket stage. Loaded mass 10,000 kg.
N2O4/UDMH propellant rocket stage. Loaded mass 10,000 kg.
Russian intercontinental ballistic orbital launch vehicle. Three stage vehicle based on R-29RM SLBM with a special shroud. Liftoff mass 40 tonnes. Stationary launch platform.
Russian intercontinental ballistic orbital launch vehicle. Proposed four-stage air-launched orbital launch vehicle based on R-29RM SLBM. Ignition mass 46 tonnes.
Russian submarine-launched ballistic missile. Proposed orbital launch vehicle based on R-29RM SLBM with new third and additional fourth stages. Stationary launch. Liftoff mass 46 tonnes.
Shu Guang Yi Hao.
Manufacturer's designation for Shuguang 1 manned spacecraft.
Shuang-cheng-tzu.
Alternate name for Jiuquan launch site.
Shubnikov, Georgi Maksimovich (1903-1965) Russian officer. Chief of Construction Directorate of Baikonur 1955-1965.
Chinese manned spacecraft. Cancelled 1972. Shuguang-1 (Dawn-1) was China's first manned spacecraft design. The two-man capsule would have been similar to the American Gemini capsule and been launched by the CZ-2 booster.
Requirement: pilot astronauts for the Shuguang program.
Shultz, George P (1920-) American politican, Reagan's Secretary of State, 1981-1989. During his negotiated strategic arms reductions with the Soviet Union.
Shurygin, Viktor Aleksandrovich Russian engineer. Director and General Designer of TsKB Titan, Volgograd. Designer of missile launchers.
American winged orbital launch vehicle. The manned reusable space system which was designed to slash the cost of space transport and replace all expendable launch vehicles. It did neither, but did keep NASA in the manned space flight business for 30 years. Redesign of the shuttle with reliability in mind after the Challenger disaster reduced maximum payload to low earth orbit from 27,850 kg to 24,400 kg.
The manned reusable space system which was designed to slash the cost of space transport and replace all expendable launch vehicles. It did neither, but did keep NASA in the manned space flight business for 30 years.
Poem: these are the laws of physics, immutable as those of Medes & Persians:...
American winged orbital launch vehicle. Shuttle using Advanced Solid Rocket Motors (development cancelled 1993).
Solid propellant rocket stage. Loaded/empty mass 625,000/75,000 kg. Thrust 15,566.12 kN. Vacuum specific impulse 286 seconds.
American orbital launch vehicle. NASA Marshall design for a cargo version of the shuttle system. The shuttle orbiter would be replaced by an unmanned recoverable main engine pod. The same concept was studied earlier as the Interim Heavy Lift Launch Vehicle (IHLLV) and as the Class I Shuttle Derived Vehicle (SDV). The Phase I two-SSME configuration would have a payload of 45,000 kg to low earth orbit. Design carried to an advanced phase in 1987-1990, but then abandoned when it was found the concept had no cost advantage over existing expenable launch vehicles.
N2O4/MMH propellant rocket stage. Loaded/empty mass 36,360/34,380 kg. Thrust 6,834.30 kN. Vacuum specific impulse 313 seconds.
American orbital launch vehicle. In August 1989 NASA studied a version of the Shuttle-C with two Advanced Solid Rocket Mortors (ASRM's) in place of the standard RSRM's. This would increase the payload by 4500 kg, but also require use of a new 10 m x 30 m payload module.
American winged orbital launch vehicle. Marshall Spaceflight Center shuttle concept of April 1970 using Faget low cross range stub-winged booster and orbiter.
Lox/LH2 propellant rocket stage. Loaded/empty mass 799,537/131,519 kg. Thrust 10,290.00 kN. Vacuum specific impulse 442 seconds. Faget Configuration
Lox/LH2 propellant rocket stage. Loaded/empty mass 199,238/54,422 kg. Thrust 2,940.00 kN. Vacuum specific impulse 459 seconds. Faget Configuration - Cross Range 323 km
American space suit, operational 1980. Space Shuttle Extravehicular Mobility Unit reusable suit. For a particular crew member and mission it was tailored from a stock of standard-size parts. Certified for eight EVA's.
American winged orbital launch vehicle. General Dynamics shuttle proposal phase A of October 1969. Unwinged flat-bottom configuration booster and orbiter with V butterfly-tails.
Lox/LH2 propellant rocket stage. Loaded/empty mass 2,169,691/234,467 kg. Thrust 30,088.43 kN. Vacuum specific impulse 442 seconds. Trapezoidal lifting body configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 388,189/130,159 kg. Thrust 4,549.05 kN. Vacuum specific impulse 459 seconds. Trapezoidal lifting body configuration. Cross range 2419 km.
American winged orbital launch vehicle. Grumman/Boeing alternate shuttle proposal of July 1971. Shuttle orbiter with drop tanks, delta booster.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,489,717/224,431 kg. Thrust 24,973.40 kN. Vacuum specific impulse 442 seconds. Swept wing configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 474,199/100,153 kg. Thrust 7,079.45 kN. Vacuum specific impulse 459 seconds. Delta wing configuration with drop tanks - Cross Range 1,774 km
The shuttle hatch was designed to be very easy to open outward, reflecting the lessons of the Apollo fire. On an early mission a non-astronaut payload specialist showed what the flight commander thought was a very unhealthy interest in how the opening mechanism worked. Opening the door in space would result in immediate loss of cabin atmosphere and death to the crew. After this NASA padlocked the hatch handle and the commanders held the key during the entire mission.
American winged orbital launch vehicle. McDonnell-Douglas/Martin Marrietta shuttle high cross-range proposal phase B of December 1970. Swept wing booster, delta wing orbiter.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,634,467/304,535 kg. Thrust 29,135.63 kN. Vacuum specific impulse 442 seconds. Swept wing configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 342,948/129,329 kg. Thrust 4,719.64 kN. Vacuum specific impulse 459 seconds. Delta winged configuration.
American orbital launch vehicle. In May 1988 NASA Langley studied a new-technology approach to improving the shuttle's payload capability. The design would allow 9,000 to 18,000 kg of additional payload to be carried in an external payload container or in the orbiter.
American winged orbital launch vehicle. Redesign of the shuttle with reliability in mind after the Challenger disaster reduced maximum payload to low earth orbit from 27,850 kg to 24,400 kg. When the decision was made to move the International Space Station to a high-inclination 51.6 degree orbit, net payload to the more challenging orbit dropped to unacceptable limits. The situation was improved by introduction of the Super Lightweight External Tank, which used 2195 Aluminium-Lithium alloy as the main structural material in place of the 2219 aluminium alloy of the original design. This saved 3,500 kg in empty mass, increasing shuttle payload by the same amount. The tank was first used on STS-91 in June 1998.
American winged orbital launch vehicle. McDonnell-Douglas/Martin Marrietta shuttle low cross-range proposal phase B of December 1970. Swept-wing booster, Faget straight wing orbiter.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,512,381/286,621 kg. Thrust 27,054.52 kN. Vacuum specific impulse 442 seconds. Swept wingd configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 322,449/120,816 kg. Thrust 4,719.64 kN. Vacuum specific impulse 459 seconds. Faget Straight Wing Configuration
American space suit, operational 1986. After the Challenger disaster, it was decided to provide the crew with pressure suits to be worn during launch and re-entry.
American winged orbital launch vehicle. Shuttle with Liquid Rocket Boosters in place of Solid Rocket Boosters.
Lox/LH2 propellant rocket stage. Loaded/empty mass 350,000/52,000 kg. Thrust 10,318.11 kN. Vacuum specific impulse 435 seconds.
American winged orbital launch vehicle. Original design for a shuttle with liquid rocket boosters, completed in March 1972 as part of the shuttle design decision process
American orbital launch vehicle. In July 1989 a NASA Langley/George Washington University joint study was made of various Liquid Rocket Booster configurations.
American winged orbital launch vehicle. Lockheed shuttle proposal phase A of December 1969. X-24B lifting body orbiter with delta-wing booster.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,225,668/162,494 kg. Thrust 26,076.59 kN. Vacuum specific impulse 442 seconds. Delta winged configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 406,344/104,891 kg. Thrust 6,823.56 kN. Vacuum specific impulse 459 seconds. High-fineness lifting-body configuration. Cross Range 2,419 km
American winged orbital launch vehicle. Lockheed Skunk Works alternate shuttle proposal of June 1971. X-24B lifting body orbiter with wrap-around external tank.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,730,803/133,514 kg. Thrust 27,422.00 kN. Vacuum specific impulse 455 seconds. High-fineness lifting-body configuration. Cross Range 2,419 km
American winged orbital launch vehicle. The McDonnell Douglas Space Shuttle Phase A studies were conducted under contract NAS9-9204. Their baseline Class III vehicle design was completed in November 1969 after 13 alternate configurations had been considered. The two-stage-to-orbit vehicle had a gross mass of 1,550,000 kg and a 11,300 kg payload was accommodated in a 4.6 m x 9.2 m payload bay.
American winged orbital launch vehicle. McDonnell-Douglas shuttle proposal phase A of November 1969. Delta wing first stage and HL-10 lifting body second stage.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,242,630/220,254 kg. Thrust 18,956.00 kN. Vacuum specific impulse 442 seconds. Delta winged configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 335,601/73,442 kg. Thrust 3,070.40 kN. Vacuum specific impulse 459 seconds. HL-10 lifting body configuration
American space mobility device, tested 1984. The MMU Manned Maneuvering Unit was designed for maneuvering by astronauts untethered from the shuttle. It was used on several satellite retrieval missions in the early 1980's.
North American's Phase A shuttle design was completed under contract NAS9-9205 in December 1969. North American had learned that the way to win a NASA design competition was to adhere to the design favoured by Max Faget, so they proposed a two-stage-to-orbit vehicle, with both booster and orbiter being of Faget's straight-wing, low cross-range configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,641,723/273,469 kg. Thrust 28,130.19 kN. Vacuum specific impulse 442 seconds. Faget Straight Wing Configuration
Lox/LH2 propellant rocket stage. Loaded/empty mass 395,011/121,542 kg. Thrust 5,256.89 kN. Vacuum specific impulse 459 seconds. Faget Straight Wing Configuration - Cross Range 2,000 km
Lox/LH2 propellant rocket stage. Loaded/empty mass 99,318/99,117 kg. Thrust 6,834.30 kN. Vacuum specific impulse 455 seconds.
N2O4/MMH propellant rocket stage. Loaded/empty mass 25,200/3,600 kg. Thrust 53.38 kN. Vacuum specific impulse 316 seconds. Two pods, mounted each side of vertical stabilizer, provide propulsion for orbit insertion, maneuver, and de-orbit.
Shuttle Pallet Satellite).
Alternate designation for SPAS military strategic defense satellite.
American winged orbital launch vehicle. Rockwell/General Dynamics shuttle proposal phase B, November 1970. Delta wing high-cross range orbiter and booster.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,764,039/351,538 kg. Thrust 28,824.77 kN. Vacuum specific impulse 442 seconds. Delta winged configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 424,449/138,910 kg. Thrust 4,804.13 kN. Vacuum specific impulse 459 seconds. Delta winged configuration.
American winged orbital launch vehicle. Rockwell/General Dynamics shuttle proposal phase B, November 1970. Straight wing low-cross range orbiter.
Lox/LH2 propellant rocket stage. Loaded mass 1,600,000 kg. Thrust 28,824.77 kN. Vacuum specific impulse 442 seconds.Delta winged configuration.
Lox/LH2 propellant rocket stage. Loaded mass 380,000 kg. Thrust 4,804.13 kN. Vacuum specific impulse 459 seconds.Straight winged configuration.
Solid propellant rocket stage. Loaded/empty mass 590,000/88,000 kg. Thrust 11,520.00 kN. Vacuum specific impulse 267 seconds. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements.
Lox/LH2 propellant rocket stage. Loaded/empty mass 2,040,816/226,757 kg. Thrust 31,980.52 kN. Vacuum specific impulse 455 seconds. Single stage to orbit, ballistic reentry.
Solid propellant rocket stage. Loaded/empty mass 589,670/86,183 kg. Thrust 11,520.00 kN. Vacuum specific impulse 269 seconds. Original configuration.
Shuttle Super Lightweight Tank.
Lox/LH2 propellant rocket stage. Loaded/empty mass 748,000/27,000 kg. Thrust 6,834.30 kN. Vacuum specific impulse 452.5 seconds. The Super Lightweight Tank used 2195 Aluminium-Lithium alloy as the main structural material in place of the 2219 aluminium alloy of the original design. This saved 3,500 kg in empty mass, increasing shuttle payload by the same amount. This change was made in anticipation of Shuttle-Mir and Shuttle-ISS flights to high inclination 51.6 degree orbits. The tank was first used on STS-91 in June 1998.
Lox/LH2 propellant rocket drop tank. Loaded/empty mass 750,975/29,930 kg. Vacuum specific impulse 455 seconds. Original version.
American orbital launch vehicle. Shuttle-Z was Shuttle-C on steroids, the ultimate development of the shuttle to be used to put Mars expeditions into orbit. It would use 4 SSME's, and a third stage with 181,000 kg of propellant powered by 1 SSSME. But such designs would require new handling facilities due to the extra height of the vehicle.
Shuttle; STS (Space Transportation System).
Alternate designation for Shuttle Orbiter rocket stage.
Shuttleworth, Mark Richard Republic 'Buranov' (1973-) South African tourist cosmonaut. Flew on ISS EP-3. First South African astronaut.
Shyster.
S-I.
Saturn I booster first stage
Headquarters of an RVSN Division, 1960-1982. Division then moved to Irkutsk. Base for units deployed with two R-1/R-2 launchers, followed by six R-5, and probably finally R-12 missiles.
S-IB.
Saturn IB booster first stage
Sibling.
ASCC Reporting Name of R-2 intermediate range ballistic missile.
S-IC.
Saturn V booster first stage
American mobile small intercontinental ballistic missile. Developed 1986-1991, but cancelled as unnecessary at the end of the Cold War.
Thiokol solid rocket engine. 979 kN.
Solid propellant rocket stage. Loaded mass 11,600 kg. Thrust 979.00 kN.
Aerojet solid rocket engine. 267 kN.
Solid propellant rocket stage. Loaded mass 5,000 kg. Thrust 267.00 kN.
Hercules solid rocket engine. 88 kN.
Solid propellant rocket stage. Loaded mass 2,000 kg. Thrust 88.00 kN.
Martin solid rocket engine.
Solid propellant rocket stage. Loaded mass 500 kg.
Sich-1.
Alternate designation for Okean-O1 earth resources radar satellite.
Sich-2.
Alternate designation for Okean-O earth resources radar satellite.
Sickle.
ASCC Reporting Name of Topol missile.
SID.
Sudden Ionospheric Disturbance
American sounding rocket. Two stage sounding rocket.
Solid rocket stage. 17.70 kN (3,979 lbf) thrust. Mass 40 kg (88 lb).
American sounding rocket. Two stage sounding rocket.
Solid rocket stage. Mass 40 kg (88 lb).
Solid rocket stage. 7.70 kN (1,731 lbf) thrust. Mass 40 kg (88 lb).
Sidorenko, Valentin I (1926-) Russian engineer cosmonaut, 1962-1963. Pilot, Soviet Air Force. Selected as a cosmonaut on 3 December 1962, but on 8 January 1963 and again on 13 December 1963 the government commission refused to approve the appointment.
Siebe.
Sieber, Werner (1912-1995) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Siebold, Pete American test pilot, engineer, at Scaled Composites.
Siemens, Heinrich German expert in aerodynamics during World War II.
Siepert, Albert F (1915-) American manager. NASA, 1958-1969; Deputy Director, Kennedy Space Center 1963-1969.
Sounding rocket launch site, used in 1959.
Category of spacecraft.
Russian communications satellite. Study 1995. The RKK Energia and Polyot PO teamed up with other industries to propose the Signal constellation of low earth orbit communications satellites.
French technology satellite. One launch, 1977.06.17.
SII.
American agency. Space Industries Inc, Houston, Texas, Houston, USA.
S-II.
Saturn V second stage
SIL.
Pakistani manufacturer of spacecraft. Pakistan, Pakistan.
Category of missiles.
Siluet.
Code name for Yantar-1KFT military surveillance satellite.
Silve, Benoit M (1958-) French engineer cosmonaut, 1990-1993. Pilot, French Navy Selected for French astronaut team.
Silveira, Milton A (1929-) American manager, at NASA 1955-1986. Deputy Administrator, 1981-1983; NASA Chief Engineer, 1983-1986.
Air-launched rocket drop zone known to have been used for 14 launches from 1960 to 1967, reaching up to 41 kilometers altitude.
Sounding rocket launcher
Silverstein, Abe (1908-2001) American engineer. Chaired committee that set NASA's spaceflight plans for the 1960's. Director, NASA Cleveland 1961-1970.
SIM.
Scientific instrument module (Apollo SM component)
SIMED
Base for units deployed with two R-5 launchers.
Chinese manufacturer of spacecraft. SIMIT, China.
Simon, Dr George Warren (1934-) American physicist payload specialist astronaut, 1978-1985.
Simon, Dr German expert in the V-2 missile during World War II. As of January 1947, living c/o Fa. Dr. Simon Frankfurt/M.
Simonyi, Charles 'Karoly' (1948-) Hungarian-American computer scientist, space tourist cosmonaut. Flew on ISS EP-12, ISS EP-16. Inventor of the Macintosh/Windows visual interface.
American visible astronomy satellite. One launch, 2001.08.20. Simplesat was intended to test methods for building cheap astronomical satellites and controlling them from a inexpensive ground stations.
Russian technology satellite. 2 launched, 2000.05.16. 660 kg dummy satellite.
Russian liquid-propellant submarine-launched ballistic missile. First aunch 2004.02.18; entered service 2007. Competitor was the solid-propellant Bulava.
Singapore
Singelmann, Dietrich E G F German expert in guided missiles during World War II. As of January 1947, working at Wright Field, Ohio.
Singer, S Fred (1924-) American physicist, proposed a Minimum Orbital Unmanned Satellite of the Earth (MOUSE) in 1953.
Single Stage to Orbit And Return.
Alternate designation for SSOAR ssto vtovl orbital launch vehicle.
Single-Stage Earth-Orbital Reusable Vehicle.
Alternate designation for SERV vtovl orbital launch vehicle.
American military naval signals reconnaisance satellite. 3 launches, 1988.09.05 (USA 32) to 1992.04.25 (USA 81). Signals intelligence satellite; possibly some kind of imaging also done. On-board propulsion boosts spacecraft to 800 km operating orbit.
Singapore Telecom, Singapore, Singapore
Russian manufacturer of rockets. Sinilshchikov Design Bureau, Korolev, Russia.
Sinner.
ASCC Reporting Name of Temp-2S intercontinental ballistic missile.
Communications satellite network operated by Sino Satellite Communications Company of Shanghai for communications services in China.
Chinese agency. SinoSatCom, China.
SIP.
Satellite tracking aircraft (Russian abbreviation)
Sounding rocket launch location known to have been used for 11 launches from 1978 to 1981, reaching up to 211 kilometers altitude.
Arcas launch complex. Arcas launcher
Tomahawk Sandia launch complex. RAG launcher
SIR.
Shuttle Imaging Radar
Italian communications technology satellite. 2 launches, 1977.08.25 (Sirio 1) and 1982.09.09 (Sirio 2). SIRIO was a spin stabilized geostationary experimental communications satellite with a nominal life of two years.
Geosynchronous communications satellite network.
American agency. Sirius Satellite Inc. , USA
Sirobaba, Ya Ya (1917-) Russian officer. Deputy Commander for Research for KIK Space Tracking Network 1971-1975.
American sounding rocket. Single stage vehicle.
SDC solid rocket engine.
Solid rocket stage. Mass 100 kg (220 lb).
American infrared astronomy satellite. One launch, 2003.08.25. The SIRTF (Space Infrared Telescope Facility) was planned as a 1 meter class, cryogenically cooled space telescope to be operated as an observatory for infrared astronomy.
SIS.
SIS
Sisakyan, Norair Martirosovich (1907-1966) Russian scientist. Early space medicine specialist at the Second Division of Biological Sciences under the Academy of Sciences.
SISE.
Chinese manufacturer. Shanghai Institute of Satellite Engineering, Shangai, China.
SISP.
Swedish manufacturer of spacecraft. Swedish Inst. for Space Physics, Kiruna, Sweden
Sistem avariyovo spaceniya.
Alternate designation for TKS SAS manned spacecraft module.
Hughes electric/mercury rocket engine. 2.1 mN. Isp=3000s. 5 cm diameter mercury ion engine, developed 1970 for attitude control and north-south stationkeeping of geosynchronous satellites.
SITAB Consortium.
Fourth Owner of Alenia
SITE.
Satellite instructional television experiment (on ATS 6)
S-IV.
Saturn I second stage
Saturn IB second stage; Saturn V third stage
American manned space station. Study 1970. Follow-on to Skylab proposed by Douglas. The station would still use the S-IVB stage as the basis, but would be much more extensively outfitted for larger crews.
American manned space station module. One launch, 1973.05.14. Used for guidance during orbital insertion only.
SJ.
Technology test satellite series of varying configurations.
SJ.
Chinese communications technology satellite. First launch 1979.07.28. SJ (Shijian) series were Chinese scientific research, technological experiment and military operational satellites of a variety of configurations.
SJ-6.
Chinese military naval signals reconnaisance satellite. Operational, first launch 2004.09.08.
SK1.
Alternate designation for RD-0101 Lox-Alcohol rocket engine.
SK-1.
Manufacturer's designation for Sokol SK-1 space suit.
Ukrainian heavy-lift orbital launch vehicle. In 1962 Yangel produced his first design for a large clustered rocket. The SK-100 would have clustered seven R-16 ICBM first stages in order to put 100 metric tons into earth orbit. The concept was abandoned for the simpler R-56 design.
SK1K.
Alternate designation for RD-0102 Lox-Kerosene rocket engine.
Skantze, Lawrence Albert (1928-) American engineer payload specialist astronaut, 1985-1985.
SKB.
Special Design Bureau or Serial Design Bureau (Russian abbreviation)
SKB.
First name of Barmin
SKB-30.
Third Owner of Almaz
SKB-31.
Second Owner of Vympel
SKB-350.
SKB-385.
First Owner of Makeyev
Skean.
Skean; SS-5; R-14; 8K65; 65; 11K65.
Alternate designation for Kosmos-1 rocket stage.
SKG.
Special Design Group (Russian abbreviation)
Skif.
ASCC Reporting Name of R-29RM submarine-launched ballistic missile.
Skif-DM.
Code name for Polyus military anti-satellite system.
Russian materials science satellite. Cancelled 1992. In 1990 KB Salyut proposed using the back-up of the Polyus 'star wars' test bed as a huge zero-gravity materials production facility.
Russian technology satellite. One launch, 1995.12.28. Aerobraking investigation; satellite provided by Russia, instruments by Utah State University; solar array shorted immediately following deployment and ended mission.
Russian intermediate range ballistic missile. Soviet medium range ballistic missile, flown once but cancelled after being outlowed by INF Treaty.
Skripochka, Oleg Ivanovich (1969-) Russian engineer cosmonaut, 1997-on. Civilian Engineer, Energia NPO
Skua.
In 1959, the Royal Meteorological Office's High Altitude Research Unit contracted with Bristol Aerojet and RPE Wescott to develop a low-cost meteorological rocket designed to reach altitudes of 80 km. The resulting Skua design consisted of Chick boosters which burned for 0.2 seconds to blast the rocket 20 m above the 5 m launch tube. Then the Bantam second stage would ignite and boost the payload to altitude. Four Skua variants were flown over the years.
Skua.
British sounding rocket. In 1959, the Royal Meteorological Office's High Altitude Research Unit contracted with Bristol Aerojet and RPE Wescott to develop a low-cost meteorological rocket designed to reach altitudes of 80 km. The resulting Skua design consisted of Chick boosters which burned for 0.2 seconds to blast the rocket 20 m above the 5 m launch tube. Then the Bantam second stage would ignite and boost the payload to altitude. Four Skua variants were flown over the years.
British sounding rocket. In the original Skua version, 3 Chick boosters were used. The Bantam second stage burned for 30 seconds to boost the payload to 70 km. The payload deployed a radar-reflective parachute to allow winds aloft to be measured, and readings from a thermometer were radioed to the ground. More than 900 Skua 1's were launched from 11 sites in six countries.
Skua 2 was used 4 Chick boosters and a lengthened Bantam motor to take more complex 5 kg scientific payloads to 100 km altitude. More than fifty Skua 2's were fired between 1967 and 1972 as part of the British national space program.
Solid rocket stage. Mass 40 kg (88 lb).
British sounding rocket. Two stage vehicle.
Solid rocket stage. 80.00 kN (17,985 lbf) thrust.
Solid rocket stage. Mass 80 kg (176 lb).
British sounding rocket. Skua 4 was further enhanced to take a 7.5 kg paylaod to 140 km altitude. The vehicle used four Chick boosters and an improved Bantam upper stage.
Solid rocket stage. Mass 40 kg (88 lb).
SKV.
Space Military System (Russian abbreviation)
Skvortsov, Aleksandr Aleksandrovich (1942-) Russian pilot cosmonaut, 1965-1968. Father of cosmonaut Aleksandr Skvortsov, Jr.
Skvortsov, Aleksandr Aleksandrovich Jr (1966-) Russian pilot cosmonaut, 1997-on. Son of cosmonaut Aleksandr Skvortsov.
Taiwanese intermediate range ballistic missile.
American strategic air-to-surface ballistic missile, development started in 1959. Program cancelled amid huge controversy in 1963 after Britain had agreed to buy the weapon in place of its own Blue Streak.
Douglas solid rocket engine. 111 kN.
Douglas solid rocket engine.
Solid propellant rocket stage. Loaded mass 2,000 kg. Thrust 111.00 kN.
Solid propellant rocket stage. Loaded mass 800 kg.
British sounding rocket. Reusable sounding rocket design proposed by Starchaser Industries, Cheshire, England. As of 2006 the business case for completing development was being reviewed.
British manufacturer of rockets. Skychaser, UK.
First and only US space station to date. Project began life as Apollo Orbital Workshop - outfitting of an S-IVB stage with docking adapter with equipment launched by several subsequent S-1B launches. Curtailment of the Apollo moon landings meant that surplus Saturn V's were available, so the pre-equipped, five times heavier, and much more capable Skylab resulted.
American manned space station. One launch, 1973.05.14. First US space station. The project began life as the Orbital Workshop- outfitting of an S-IVB stage with a docking adapter with equipment launched by several subsequent S-1B launches.
Crew: Conrad, Kerwin, Weitz. Record flight duration. Crew had to conduct major repairs to get damaged station in operation. Astronaut flung into space during release of solar wing. High temperatures in station brought down by deployment of sunshade. Backup crew: McCandless, Musgrave, Schweickart.
Crew: Bean, Garriott, Lousma. Installed twinpole solar shield on EVA; performed major inflight maintenance; doubled record for length of time in space. Leaks in Apollo CSM thrusters led to preparation of a rescue mission. Decided to make landing with faulty thrusters instead. Backup crew: Brand, Lenoir, Lind.
Crew: Carr, Gibson Edward, Pogue. Record flight duration. Final Skylab mission; included observation and photography of Comet Kohoutek among numerous experiments. Rebellion by crew against NASA Ground Control overtasking led to none of the crew ever flying again. Backup crew: Brand, Lenoir, Lind.
Crew: Brand, Lind, Lenoir. After completion of the three programmed Skylab flights, NASA considered using the remaining backup Saturn IB and Apollo CSM to fly a fourth manned mission to Skylab. It would have been a short 20 day mission - the CSM systems would not have powered down.
American manned space station module. One launch, 1973.05.14. Airlock for EVA's, mounting of STS and TNL.
American space mobility device, tested 1974. Another of the EVA maneuvering units tested by the Skylab astronauts within the capacious station.
American space mobility device, tested 1973. One of several extravehicular mobility devices tested by the Skylab astronauts within the spacious station.
American manned space station module. One launch, 1973.05.14. Solar Telescope module.
After the completion of Apollo, Skylab, and ASTP programs there was still significant Apollo surplus hardware. Plans to use it were cancelled; an opportunity to launch an International Space Station, at a tenth the cost and twenty years earlier, was lost.
American manned lunar orbiter. Study 1970. McDonnell Douglas (Seal Beach, CA) did a study on modifying the to modify the Skylab as a moon-orbiting observatory and station
American manned space station module. One launch, 1973.05.14. Docking module for two CSM, one ATM.
American manned space station module. One launch, 1973.05.14. Main laboratory.
American logistics spacecraft. Cancelled 1980. Module developed for Shuttle to deliver to Skylab to boost it to a higher orbit for use during the Shuttle program.
Crew: Brand, Lind. Influenced by the stranded Skylab crew portrayed in the book and movie 'Marooned', NASA provided a crew rescue capability for the only time in its history. Prepared for launch during Skylab 3. Scrubbed, Skylab 3 made landing with faulty thrusters instead.
James Oberg tells the sad story of how the United States abandoned the largest space station ever built and spent a quarter century trying to regain the capability.
The Skylark sounding rocket (originally named the Gassiot High Altitude Vehicle) was produced by the Royal Aircraft Establishment and first introduced in 1957, during the International Geophysical Year. It remained in European service until 2005.
British sounding rocket. The Skylark sounding rocket (originally named the Gassiot High Altitude Vehicle) was produced by the Royal Aircraft Establishment and first introduced in 1957, during the International Geophysical Year. It remained in European service until 2005. The original basic single-stage Skylark version used a Raven 1 motor (Rook derivative). The RPE Raven 1 burned 840 kg of propellant (ammonium perchlorate, polyisobutylene binder and aluminium powder) in thirty seconds with a 1450 kNs total impulse at sea level.
British sounding rocket. Two stage Skylark version consisting of 1 x Raven 8 + 1 x Raven 1/1A/2A
British sounding rocket. Two stage Skylark version consisting of 1 x Goldfinch + 1 x Gosling 4T
Skylark 10A.
Alternate designation for Skylark 10 sounding rocket.
Solid rocket stage. 137.00 kN (30,799 lbf) thrust. Mass 300 kg (661 lb).
British sounding rocket. Skylark version consisting of 1 x Goldfinch II + 1 x Raven VI + 1 x Cuckoo II or IV. Never flown.
Solid rocket stage. 44.50 kN (10,004 lbf) thrust. Mass 1,000 kg (2,205 lb).
British sounding rocket. Three stage Skylark version consisting of 1 x Goldfinch + 1 x Raven 11 + 1 x Cuckoo 4. The AC version uses an uprated Goldfinch II booster. The Raven XI is loaded with 990 kg of propellant and produced 2500 kN-sec total impulse over 39 seconds. The Cuckoo IV stage provides 452 kN-sec impulse over 15 seconds.
British sounding rocket.
Solid rocket stage. 105.00 kN (23,605 lbf) thrust. Mass 1,300 kg (2,866 lb).
Solid propellant rocket stage. Loaded mass 200 kg.
British sounding rocket. Skylark version using Rook 3 booster + Raven 11 upper stage. Never built. Skylark 13 designation not used for superstitious reasons.
British sounding rocket. Skylark version using Rook 3 booster + Raven 11 + Cuckoo 5. Never built.
British sounding rocket. Skylark version with shortened Stonechat motor. Never built.
British sounding rocket. Skylark version with Stonechat booster and Mage 2 second stage motor. Never built.
British sounding rocket. Three stage Skylark version consisting of 1 x Cuckoo IA + 1 x Raven 2 + 1 x Raven 8. The Cuckoo booster burned for 4 seconds and provided 364 kN-sec total impulse. The Raven 2 provided 1540 N-sec total impulse.
British sounding rocket. Two stage Skylark version consisting of 1 x Cuckoo IA + 1 x Raven 8
Solid rocket stage. 44.50 kN (10,004 lbf) thrust. Mass 1,000 kg (2,205 lb).
British sounding rocket. Two stage Skylark version consisting of 1 x Cuckoo IA + 1 x Raven 2
British sounding rocket. Two stage Skylark version consisting of 1 x Cuckoo IA + 1 x Raven 6
British sounding rocket.
Solid rocket stage. 52.50 kN (11,802 lbf) thrust. Mass 1,200 kg (2,646 lb).
British sounding rocket. Two stage Skylark version consisting of 1 x Goldfinch + 1 x Raven 8
British sounding rocket.
Solid rocket stage. 175.00 kN (39,342 lbf) thrust. Mass 400 kg (882 lb).
Solid rocket stage. 50.10 kN (11,263 lbf) thrust. Mass 1,100 kg (2,425 lb).
British sounding rocket. Single stage Skylark version consisting of 1 x Raven 5. The Raven 5 increased total impulse to 1780 kN-sec.
Solid rocket stage. 44.50 kN (10,004 lbf) thrust. Mass 1,000 kg (2,205 lb).
British sounding rocket. Two stage Skylark version consisting of 1 x Cuckoo IA + 1 x Raven 5
British sounding rocket. Two stage Skylark version consisting of 1 x Goldfinch II + 1 x Raven 6. The Goldfinch provided 700 kN-sec total impulse.
British sounding rocket.
Solid rocket stage. Mass 400 kg (882 lb).
British sounding rocket. Three stage Skylark version consisting of 1 x Raven 7 + 1 x Goldfinch II + 1 x Raven 11
British sounding rocket. Two stage Skylark version consisting of 1 x Goldfinch II + 1 x Raven 11
British sounding rocket. Two stage Skylark version consisting of 1 x Cuckoo IA + 1 x Raven 7
Solid rocket stage. 44.50 kN (10,004 lbf) thrust. Mass 1,000 kg (2,205 lb).
British sounding rocket. Skylark version with Stonechat booster and Waxwing second stage motor. Never built.
British sounding rocket. Skylark single-stage version with Stonechat motor. This would make it similar to the Falstaff test version. Never built.
British single-stage-to-orbit, horizontal-takeoff-horizontal-landing turborocket orbital launch vehicle design of the mid-1990's. The novel lightweight structural design was based on lessons learned in the many iterations of the HOTOL concept. The classified Sabre turbojet-rocket combined-cycle engine was taken to a high level of test by Alan Bond at Rolls Royce. Despite the extreme promise of the design, neither British government or private financing was forthcoming.
Air/Lox/LH2 propellant rocket stage. Loaded/empty mass 263,000/42,319 kg. Thrust 1,300.00 kN. Specific impulse 425 seconds. Engine thrust, burn time estimated.
British military communications satellite. 2 launches, 1974.01.19 (Skynet 2A) and 1974.11.23 (Skynet 2B).
Military communications satellite network.
Brazilian agency.
British military communications satellite. One launch, 2008.06.12. The Skynet 5 program contract was signed by the EADS subsidiary Paradigm Secure Communications Ltd and the UK MOD in October 2003.
SL-.
Space launcher (designation numbering series - US DoD); or Skylab mission (designation numbering series); or SpaceLab (designation numbering series)
SL-1.
Department of Defence Designation of Sputnik 8K71PS intercontinental ballistic orbital launch vehicle.
SL-10.
Department of Defence Designation of Sputnik 11A59 orbital launch vehicle.
SL-11.
Department of Defence Designation of Tsiklon-2 and Tsiklon-2A orbital launch vehicles.
SL-12.
Department of Defence Designation of Proton-K-D, Proton-K-17S40, Proton-K-DM, Proton-K-DM-2, Proton-K-DM-2M, Proton-K-D-1, and Proton-K-D-2 orbital launch vehicle.
SL-13.
Department of Defence Designation of Proton-K orbital launch vehicle.
SL-14.
Department of Defence Designation of Tsiklon-3 orbital launch vehicle.
SL-15.
Department of Defence Designation of N1 heavy-lift orbital launch vehicle.
SL-16.
Department of Defence Designation of Zenit-2 orbital launch vehicle.
SL-17.
Department of Defence Designation of Energia winged orbital launch vehicle.
SL-18.
SL-2.
Department of Defence Designation of Sputnik 8A91 intercontinental ballistic orbital launch vehicle.
SL-3.
Department of Defence Designation of Luna 8K72, Vostok 8K72, Vostok 8K72K, Vostok 8A92, and Vostok 8A92M orbital launch vehicles.
SL-4.
Department of Defence Designation of Voskhod 11A57, Soyuz 11A511, Soyuz 11A511U, Soyuz 11A511L, Soyuz 11A511U2, Soyuz FG, Soyuz ST orbital launch vehicles.
SL-5.
Department of Defence Designation of Vostok 11A510 orbital launch vehicle.
SL-6.
Department of Defence Designation of Molniya 8K78 and Molniya 8K78M orbital launch vehicles.
SL-7.
Department of Defence Designation of Kosmos 63S1, Kosmos 63S1M, and Kosmos 11K63 orbital launch vehicle.
SL-8.
Department of Defence Designation of Kosmos 65S3, Kosmos 65MP, Kosmos 11K65, and Kosmos 11K65M orbital launch vehicle.
SL-9.
Department of Defence designation of UR-500 launch vehicle.
SLA.
Spacecraft-lunar module adapter; also spacecraft launch vehicle adapter
SLAM.
American intercontinental Mach-3-at-sea-level cruise missile, powered by a nuclear ramjet. Development begun 1957. Cancelled 1964 over cost and environmental concerns.
SLAR.
Side-Looking Airborne Radar
Base for units deployed with two R-5 launchers.
Slayton, Donald Kent 'Deke' (1924-1993) American test pilot astronaut. Slated to fly third Mercury mission, grounded due to a medical issue and became astronaut commander, assigning crews for lunar landings. Later finally flew on Apollo (ASTP).
SLBM.
Submarine-launched ballistic missile
SLC.
Space Launch Complex
American air-launched orbital launch vehicle. Nanosat air-launched orbital vehicle which would be dropped from a boosted F-4 carrier aircraft.
Rocketdyne Lox/Alcohol rocket engine. 666 kN. Pressure-fed. From 35,000 to 150,000 lbf. Cook Sled, Air Force Sleds 1 and 2, RS-2 Sled, operated at Edwards and Holloman Air Force Bases.
Category of launch vehicles.
slew.
To change the direction of an antenna or telescope in order to follow a moving target, or to change from one target to another.
SLI.
Space Launch Initiative
Base for units deployed with twelve R-12, and later nine Pioner missile launchers.
Dutch technology satellite. One launch, 2005.02.12. Test satellite to study the sloshing of fluids in zero gravity, developed by the Netherlands Aerospace Laboratory. Equipped with a tank with 33.5 liters of water and an attitude control system.
Slovak AF.
Slovakia
Slovenia
SLS.
Space(lab) Life Sciences
SLS.
American orbital launch vehicle. In the mid-1950's, US Air Force-funded studies identified the optimum long-term solution for space launch. The studies indicated the desirability of segmented solids for a first stage to achieve low cost, high reliability and flexibility of basic booster size by adding or subtracting segments. Studies further showed that oxygen-hydrogen propellants, with their very high specific impulse, were a preferred choice for upper stages, where mass was more important. This choice also resulted in minimum systems cost.
SLS.
In the mid-1950's, US Air Force-funded studies identified the optimum long-term solution for space launch. The studies indicated the desirability of segmented solids for a first stage to achieve low cost, high reliability and flexibility of basic booster size by adding or subtracting segments. Studies further showed that oxygen-hydrogen propellants, with their very high specific impulse, were a preferred choice for upper stages, where mass was more important. This choice also resulted in minimum systems cost.
American orbital launch vehicle. The A-388 was the version of the Space Launching System family proposed to fill the SLV-4 requirement - boost to orbit of the Dynasoar manned spaceplane. The booster was dubbed 'Phoenix' - perhaps a hope it could be rescued from the ashes of the manned space program having been turned over to NASA....
American orbital launch vehicle. The smallest identified member of the SLS family, selected to place the Air Force Lunex lunar lander re-entry vehicle in a low earth orbit for initial tests, was the A-410. This consisted of the 'A' Lox/LH2 stage supplemented by 100-inch diameter solid fuel booster rockets.
American orbital launch vehicle. The AB-825 represented a medium launch vehicle of the USAF 1961 Space Launching System family. The AB-825 would have conducted earth orbit tests of partially-fuelled Lunex lunar lander stages, and also have boosted the Lunex manned glider on circumlunar test flights. It consisted of the 'A' stage and 'B' stages with 180 inch diameter short-length solid fuel booster motors.
American orbital launch vehicle. The BC-2720 was the member of the SLS family selected to boost the Air Force Lunex lunar lander on a direct lunar trajectory. This would have used four 180 inch solid rocket boosters strapped around an the 'C' Lox/LH2 core vehicle. The core would have required either 12 J-2 engines or 2 M-1 engines. The translunar injection third stage was the 'B', with a single J-2 engine.
Solid propellant rocket stage. Loaded/empty mass 366,716/56,000 kg. Thrust 8,130.00 kN. Vacuum specific impulse 260 seconds. Four such 180 inch segmented solid rocket motors provided first stage thrust for Project Lunex. A liquid propellant first stage was considered as an alternative, but the solid stage was the baseline. Empty mass, specific impulse estimated.
Solid propellant rocket stage. Loaded/empty mass 88,000/13,000 kg. Thrust 2,083.90 kN. Vacuum specific impulse 260 seconds. Booster for SLS A series launch vehicles.
Lox/LH2 propellant rocket stage. Loaded/empty mass 59,000/6,000 kg. Thrust 889.33 kN. Vacuum specific impulse 424 seconds. Smallest Lox/LH2 stage planned for SLS series. Empty mass estimated. Sized for rail transport within USA.
Lox/LH2 propellant rocket stage. Loaded/empty mass 160,000/11,200 kg. Thrust 1,778.65 kN. Vacuum specific impulse 424 seconds. Tranlunar injection stage for Project Lunex. Masses estimated based on optimum apportioning of B+C stage total masses.
Lox/LH2 propellant rocket stage. Loaded/empty mass 825,000/58,000 kg. Thrust 10,673.32 kN. Vacuum specific impulse 428 seconds. Launch vehicle core stage for Project Lunex. Masses estimated based on optimum apportioning of B+C stage total masses. Thrust, engines estimated based on requirements.
Slush hydrogen is formed by taking liquid hydrogen down to nearly the melting point. This produces a partly-solidified but still mobile version of the fuel with 20% greater density than liquid hydrogen itself. Proposed for use from the 1980's in air-breathing and rocket-powered single-stage-to-orbit vehicles where maximization of fuel weight to empty weight is absolutely essential.
Base for units deployed with nine Pioner launchers.
SLV.
Standard launch vehicle
SLV.
Family of launch vehicles.
SLV.
Indian all-solid orbital launch vehicle.
SLV-1.
Article Number of KT-1 all-solid orbital launch vehicle.
ISRO solid rocket engine. 502.6 kN. Isp=253s. Used on ASLV, PSLV, SLV. First flight 1979.
Solid propellant rocket stage. Loaded/empty mass 10,800/2,140 kg. Thrust 502.60 kN. Vacuum specific impulse 253 seconds.
SLV-2.
Department of Defence Designation of Thor Agena D orbital launch vehicle.
SLV-2.
Article Number of KT-2 all-solid orbital launch vehicle.
Solid propellant rocket stage. Loaded/empty mass 4,900/1,750 kg. Thrust 267.01 kN. Vacuum specific impulse 267 seconds.
ISRO solid rocket engine. 267 kN. Isp=267s. Used on ASLV, SLV. First flight 1979.
SLV-2A.
Department of Defence Designation of Thor SLV-2A Agena D orbital launch vehicle.
SLV-2A.
Article Number of KT-2A all-solid orbital launch vehicle.
SLV-2C.
Department of Defence Designation of Thor SLV-2A Agena B orbital launch vehicle.
SLV-2G.
Department of Defence Designation of Thorad SLV-2G Agena D orbital launch vehicle.
SLV-2H.
Department of Defence Designation of Thorad SLV-2H Agena D orbital launch vehicle.
SLV-3.
Department of Defence Designation of Atlas SLV-3 orbital launch vehicle.
Indian all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x SLV-3-1 + 1 x SLV-3-2 + 1 x SLV-3-3 + 1 x SLV-3-4
Solid propellant rocket stage. Loaded/empty mass 1,500/440 kg. Thrust 90.70 kN. Vacuum specific impulse 277 seconds.
ISRO solid rocket engine. 90.7 kN. Isp=277s. Used on ASLV, SLV. First flight 1979.
American orbital launch vehicle. Standardized Atlas booster with Agena B upper stage.
Indian all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x SLV-3-1 + 1 x SLV-3-2 + 1 x SLV-3-3 + 1 x AS-4
Solid propellant rocket stage. Loaded/empty mass 360/98 kg. Thrust 26.83 kN. Vacuum specific impulse 283 seconds.
ISRO solid rocket engine. 26.8 kN. Isp=283s. Used on ASLV, SLV. First flight 1979.
SLV-5.
Department of Defence Designation of Titan 2G intercontinental ballistic orbital launch vehicle.
SLV-5A.
Department of Defence Designation of Titan 3A orbital launch vehicle.
SLV-5B.
Department of Defence Designation of Titan 3B orbital launch vehicle.
SLV-5C.
Department of Defence Designation of Titan 3C orbital launch vehicle.
SLV-5D.
Department of Defence Designation of Titan 3D orbital launch vehicle.
SLV-5E.
Department of Defence Designation of Titan 3E orbital launch vehicle.
SM.
Service module (Apollo spacecraft component)
SM Logistic Lander.
Alternate designation for Apollo SMLL lunar logistics spacecraft.
Solid rocket stage. 257.50 kN (57,888 lbf) thrust. Mass 900 kg (1,984 lb).
Solid propellant rocket stage. Loaded mass 400 kg.
SM-2-IV.
Alternate designation for Standard SM-2ER Block IV surface-to-air missile.
Solid rocket stage. Mass 700 kg (1,543 lb).
SM-3.
Alternate designation for Standard SM-3 anti-ballistic missile.
Thiokol solid rocket engine. 7 kN.
SM-3 TSRM.
Alternate designation for SM-3-3 rocket stage.
Solid rocket stage. Mass 500 kg (1,102 lb).
Solid propellant rocket stage. Loaded mass 100 kg. Thrust 7.00 kN.
SM-62.
Department of Defence Designation of Snark intercontinental cruise missile.
SM-64A.
Department of Defence Designation of Navaho G-38 intercontinental cruise missile.
SM-65A.
Alternate Designation of Atlas A test vehicle.
SM-65B.
Alternate Designation of Atlas B test vehicle.
SM-65C.
Alternate Designation of Atlas C test vehicle.
SM-65E.
Alternate Designation of CGM-16E intercontinental ballistic missile.
SM-65F.
Alternate Designation of HGM-16F intercontinental ballistic missile.
SM-68A.
Alternate Designation of Titan 1 intercontinental ballistic missile.
SM-75.
Alternate Designation of Thor intermediate range ballistic missile.
SM-78.
Alternate Designation of Jupiter intermediate range ballistic missile.
SM-80A.
Alternate Designation of Minuteman 1A intercontinental ballistic missile.
Smakula, Alexander German expert in guided missiles infra-red during World War II. As of January 1947, working at Fort Belvoir, Virginia.
Small Astronomy Satellite.
Alternate designation for SAS solar satellite.
Small Expendable-tether Deployer System..
Alternate designation for SEDS tether technology satellite.
A series of relatively low-cost satellites launched by NASA for solar and astronomical studies.
Small Scientific Satellite.
Alternate designation for SSS earth magnetosphere satellite.
Small Self-Contained Payloads.
Manufacturer's designation for GAS technology satellite.
European lunar orbiter. One launch, 2003.09.27, Insat 3E. ESA's SMART-1 was to test miniaturization technology while exploring the Moon from orbit.
SMC.
Air Force Space and Missiles Command; or Small Magellanic Cloud
SMDC.
American agency. U. S. Army Space & Missile Defense Center (U. S. ), USA
SME.
American solar satellite. One launch, 1981.10.06. The Solar Mesosphere Explorer satellite was developed to investigate the processes that create and destroy ozone in the Earth's upper atmosphere.
SMEX.
SMEX.
SMall EXplorers series of satellites.
Smirenny, Dr Lev Nikolayevich (1932-) Russian physician cosmonaut, 1972-1986. Medical Doctor. Graduated from Moscow Physical-Engineering Institute, 1956. Civilian Physician, Institute of Biological Medical Problems. Chief of a laboratory at IMBP.
Smirnitskiy, Nikolai Nikolayevich (1918-1993) Russian officer. Commander of GURVO 1967-1975. Thereafter moved to Ministry of General Machine Building.
Smirnov, Leonid Vasilyevich (1916-) Russian government official. Chaired the Military-Industrial Commission 1963-1985. Director of YuzhMash Plant 1952-1961.
Smith, Michael John (1945-1986) American test pilot astronaut. Flew on STS-51-L. Died in Challenger accident.
Air-launched rocket drop zone known to have been used for 10 launches from 1963 to 1968, reaching up to 107 kilometers altitude.
Sounding rocket launcher
Smith, Steven Lee (1958-) American engineer mission specialist astronaut. Flew on STS-68, STS-82, STS-103, STS-110.
SMM.
American solar satellite. One launch, 1980.02.14. The Solar Maximum Mission (SMM) was intended primarily to study solar flares and related phenomena.
Base for units deployed with 18 Pioner launchers.
System for Increased Quality Assurance (Russian abbreviation)
SMS.
Shuttle Mission Simulator. NASA had two programmable, functional replicas of the shuttle cockpit, used to train astronauts in all manner of abort scenarios and multiple equipment breakdowns. Only the first simulator run and the last simulator run before each mission would expose each crew to a nominal mission.
SMS.
American earth weather satellite. 2 launches, 1974.05.17 (SMS 1) and 1975.02.06 (SMS 2). Synchronous Meteorological Satellite.
SN.
SuperNova (e.g., SN1987A)
SNAP.
Systems for nuclear auxiliary power (nuclear-electric spacecraft power supply)
SNAP.
British technology satellite. One launch, 2000.06.28. Basic Surrey Nanosat bus.
American ion engine technology satellite. One launch, 1965.04.03. Carried SNAP-9A nuclear power source. The on-board reactor provided electrical power for a 2.2-lb ion engine.
EOS electric/cesium rocket engine. 8.5 mN. In Development, 1962-1964. Isp=5100s. Launched on Blue Scout Junior launch vehicle on Snapshot test; a contact ionization engine; thruster anode diameter was 5 cm.
American intercontinental subsonic cruise missile. Developed 1946-1959; deployed only briefly in 1961 before being made obsolete by ICBM's.
Intercontinental range subsonic cruise missile. The only intercontinental surface-to-surface cruise missile ever deployed by the US Air Force. Deployed only briefly, but the control and navigation technology developed for it during the 1950's provided the basis for later Northrop navigation systems used in strategic ballistic missiles.
Solid rocket stage.
French manufacturer of rocket engines and rockets. SNECMA, France.
SNG.
Sodruzhestva Nezabisimikh Gosudarst, Commonwealth of Independent States, Russia (Russian abbreviation)
SNIP.
Pressurisation Control System (Russian abbreviation)
Snipe.
ASCC Reporting Name of R-31 submarine launched ballistic missile.
RO solid rocket engine. 16 kN.
SNOE.
American technology satellite. One launch, 1998.02.26.
Supersonic Naval Ordnance Research Track
Sud solid rocket engine. 20 kN.
SNPE.
French manufacturer of rocket engines. Societe Nationale des Poudres et Explosifs, France.
SNR.
Signal to Noise Ratio
SNTK imeni N. D. Kuznetsova.
Third Owner of Kuznetsov
SNU.
Solar Neutrino Units
SO.
Orientation System (Russian abbreviation)
ISAS solid rocket engine.
Simultaneous emptying of tanks (Russian abbreviation)
Sobol.
Launch System of RM-207 target drone.
SOBT.
Quality Assurance System (Russian abbreviation)
Joint Kazakh-Russian-Ukrainian project announced in 2000 to produce an 'ecologically safe' replacement of the Proton booster that would use Energia launch facilities at Baikonur. No details available, and no more heard about it.
Stratospheric Observatory For Infrared Astronomy
(Computer) programs and formulation of programs.
Japanese military surveillance radar satellite. One launch, 2009.01.23. Satellite built by the Space Oriented Higashi-osaka Leading Association, Osaka, carrying a cloud cover imager.
Sohn.
Sohn German rocket engineer in WW2; later worked in France as part of the engine group at LRBA from 1947-1957, then returned to Germany.
SOHO.
European solar satellite. One launch, 1995.12.02. SOHO was a component of the Collaborative Solar-Terrestrial Research (COSTR) Program of the International Solar Terrestrial Physics (ISTP) Program.
American military target satellite. 2 launches, 1969.09.30 (SOICAL Cone) and (SOICAL Cylinder). Space craft engaged in investigation of spaceflight techniques and technology.
SOK.
Jettisonable support cone
SOKB.
Union Experimental Design Bureau (Russian abbreviation)
Sokol.
Alternate designation for Potok military communications satellite.
Russian space suit, operational 1961 for the Vostok spacecraft.
Russian space suit, operational 1971. After the Soyuz 11 tragedy, in which all three unsuited cosmonauts died in a decompression accident, the Soviets scrambled to produce new IVA suits.
Russian space suit, operational 1990. Improved version of the Sokol IVA suit developed for use aboard Soyuz T.
Sokolov, Andrei Illarionovich (1910-1976) Russian officer. Director of Nll-4 during the early space program 1955-1970.
Sokolova, Marina Russian engineer cosmonaut candidate, 1962. Pilot. Selected as a cosmonaut on 28 February 1962, but on 3 March 1962 her selection was rejected by the government commission. In 1965 she set the world speed record for a female pilot while flying a MIG-21.
Sokolovskiy, Mikhail Ivanovich Russian engineer. From 1996 general designer and director of NPO Iskra in Perm. Designer of solid propellant rocket engines.
Sokovykh, Anatoli Mikhailovich (1944-) Russian test pilot cosmonaut, 1979-1986.
By use of concentrating mirrors, solar power can be used to heat a propellant (usually hydrogen) to produce thrust in space.
Japanese solar satellite. One launch, 1991.08.30. X-ray imaging of Sun.
Category of spacecraft.
Solar and Heliospheric Observatory.
Alternate designation for SOHO solar satellite.
Solar Anomalous and Magnetospheric Particle Explorer.
Alternate designation for SAMPEX earth magnetosphere satellite.
SOLAR B.
Code name for Hinode solar satellite.
Solar Maximum Mission.
Alternate designation for SMM solar satellite.
Solar Mesosphere Explorer.
Alternate designation for SME solar satellite.
Category of spacecraft.
Category of spacecraft.
Streams of particles (mostly ions of hydrogen and helium, and electrons ) emanating from the Sun and flowing approximately radially outward at velocities from 300 to 800 km per sec.
By use of concentrating mirrors, solar power can be used to heat a propellant (usually hydrogen) to produce thrust in space. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks.
American manned spacecraft. Study 2004. X-Prize suborbital ballistic spacecraft concept of Interorbital Systems of Mojave, California.
French solid rocket engine. 120 kN. 1500 kg Isolane propellant. Used on Topaze launch vehicle. First flight 1962.
Nord solid rocket engine. 147 kN. 2200 kg Isolane propellant. Stretched version of the NA802. Used on Topaze launch vehicle. First flight 1964.
Category of engines.
Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems.
Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems.
Solid propellant tables by Andre Bedard.
Solid Rocket Booster.
Alternate designation for Shuttle SRB rocket stage.
Sologub, Mikhail Vladimirovich (1936-1996) Russian navigator cosmonaut, 1967-1968.
Solomonov, Yuri Semenovich Russian engineer. From 1997 Director and General Designer of Moscow Institute of Thermal Technology. Solid propellant missile designer.
Solovova, Ludmilla Russian engineer cosmonaut candidate, 1962. Selected as a cosmonaut on 28 February 1962, but in March 1962 her selection was rejected by the government commission.
Solovyev, Vsevolod Nikolayevich Russian engineer. Chief Designer 1963-1992 of KB TransMash Designed missile and booster launch complexes.
Solovyov, Anatoliy Yakovlevich (1948-) Russian test pilot cosmonaut. Flew on Mir EP-2, Mir EO-6, Mir EO-12, Mir EO-19, Mir EO-24. 651 cumulative days in space.
Solovyov, Vsevolod Nikolayevich Russian engineer. Head of the KB Transport Mechanical Engineering (KB TM) 1963-1991. KB TM developed launch equipment and complexes for a range of missiles, including the R-36 heavy ICBM.
Solovyov, Vladimir Alekseyevich (1946-) Russian engineer cosmonaut. Flew on Salyut 7 EO-3, Mir EO-1. Member of first crew to fly between two space stations during a single mission. Civilian Engineer, Energia NPO
Solovyova, Irina Bayanovna (1937-) Russian pilot cosmonaut, 1962-1969.
Solrad.
Alternate designation for GRAB military naval signals reconnaisance satellite.
American solar satellite. 4 launches, 1968.03.05 (Explorer 37) to 1976.03.15 (Solrad 11B). SOLRAD was Satellite Techniques' first major project and NRL's first post-Vanguard satellite.
American orbital launch vehicle. The progenitor of the Titan 3 was this design, which used two, 3 segment, 100 inch diameter solid rocket boosters. The 100 inch segmented boosters had already been ground-fired by Aerojet. However the final decision was to develop the more-capable Titan 3C with 5 segment, 120 inch diameter solid rocket boosters.
American earth magnetosphere satellite. One launch, 1979.02.24. Ionosphere and magnetosphere studies; destroyed 9/13/85 (while still functioning) as part of ASAT test.
SO-M.
Manufacturer's designation for Prognoz earth magnetosphere satellite.
SO-M2.
Manufacturer's designation for Prognoz-M earth magnetosphere satellite.
Brazilian sounding rocket family.
Brazilian sounding rocket family.
IAE solid rocket engine family.
Brazilian sounding rocket. Two stage vehicle consisting of 1 x Sonda 1-1 + 1 x Sonda 1-2
IAE solid rocket engine. 4.2 kN.
IAE solid rocket engine. 27 kN.
Brazilian sounding rocket. Single stage vehicle.
Brazilian sounding rocket. Two stage vehicle consisting of 1 x Sonda 3-1 + 1 x Sonda 2A
Brazilian sounding rocket. Two stage vehicle consisting of 1 x Sonda 3-1 + 1 x Sonda 2M
Brazilian sounding rocket. Two stage vehicle consisting of 1 x S-43 + 1 x Sonda 3-1
The Danish Meteorological Institute established this sounding rocket range in 1971. The site was located next to an airport at the end of the fjord and was only occupied during launch campaigns. The location was well-suited for observation of the Arctic aurora and ionosphere. Known to have been used for 31 launches from 1971 to 1987, reaching up to 816 kilometers altitude.
Danish Launcher
HAD Launcher
HAD Launcher No 3
MRL Launcher
Test Launcher
Song Jian Chinese Engineer. Theoretician that made important contributions to Chinese missile and satellite control systems. Updated Qian Xuesen's primary textbook for Chinese rocket engineers.
Sounding rocket launch location known to have been used for 90 launches from 1962 to 2007, reaching up to 423 kilometers altitude.
Sope.
Simulated off-the-pad ejection
American solar satellite. One launch, 2003.01.25.
Sorlie, Donald Milton (1923-) American test pilot, 1962-1973. Flights of the M2-F2. Colonel, USAF Selected as a military astronaut candidate in 1973. Later made flights of the M2-F2 lifting body. Retired on 30 June 1973.
Sorokin, Dr Aleksey Vasilyevich (1931-1976) Russian physician cosmonaut, 1964-1964. Soviet Air Force Physician. On the staff of the cosmonaut training center, working in the field of aerospace medicine.Later head of department at several scientific institutes.
American manned spacecraft. Study 1982.
SOUD.
System of Orientation and Motion Control (Russian abbreviation)
Category of launch vehicles.
Taiwanese sounding rocket.
Sounding Rocket Motor.
Manufacturer's designation of T-7A Booster Solid rocket engine.
Solid propellant rocket stage. Loaded mass 1,000 kg.
Solid propellant rocket stage. Loaded mass 1,000 kg.
need summary - see links
South Africa
Sounding rocket launch location known to have been used for 1 launch in 1995, reaching up to 100 kilometers altitude.
British missile test range, occupying a good portion of northwest South Uist island in the Hebrides. Aside from missile testing, it has also been used for launch of Skua and Petrel meteorological rockets. Known to have been used for 222 launches from 1962 to 1982, reaching up to 174 kilometers altitude.
Sounding rocket launch location known to have been used for 2 launches in 1980, reaching up to 156 kilometers altitude.
Southwest Regional Spaceport.
Alternate name for Spaceport America launch site.
Russian communications satellite. Study 1990. One of the early Russian-Western satellite programs was SovCanStar, a 1990 joint venture with Canada.
Sounding rocket launch location known to have been used for 6 launches from 1963 to 1964, reaching up to 402 kilometers altitude.
Sovetskaya Molodyozh, Russian newspaper.
The story of Soviet space stations in Earth orbit - Korolev's star wars of 1963!
The Russians were never able to have enough success with the N1 booster to have a serious schedule for the first Soviet lunar landing. In January 1969, before the first N1 launch, it was not expected that a Soviet landing would take place until 1972.
The failed Soviet lunar program, and the follow-on lunar base projects that came to nothing.
Soviet Mars Propulsion - Nuclear Electric.
Soviet Mars Propulsion - Nuclear Electric
Soviet Mars Propulsion - Nuclear Thermal.
Soviet Mars Propulsion - Nuclear Thermal
The previously unrevealed history of the Soviet space program...
Soviet Space History - Era of the Chief Designers.
Era of the Chief Designers
Soviet Space History at a Glance.
Soviet Space Quality Assurance.
Soviet Space Quality Assurance
James Oberg lists those secrets remaining to be disclosed...
Category of spacecraft.
Soviet Space System Development Process.
Soviet Space System Development Process
Soviet Space Tracking Systems.
Soviet Space Tracking Systems
Soviet Strategic Cruise Missiles.
As in America, in the 1946 assessments of German military technology, the technical problems of the intercontinental ballistic missile seemed far less than a high-speed cruise missile for the same mission. The Soviet Union developed several such missiles, counterparts to the American Navaho. As in America, it turned out that the ICBM was ready before the cruise missiles were - the navigation and propulsion issues of Mach 3 intercontinental flight were much more difficult than those for Mach 22 ballistic flight. As in America, the projects were cancelled, although they contributed greatly to the national technological base.
Soviets Recovered an Apollo Capsule!.
The truth only emerged 32 years later - the Soviets recovered an Apollo space capsule in 1970...
Base for units deployed with R-12 missiles.
The Russian Soyuz spacecraft has been the longest-lived, most adaptable, and most successful manned spacecraft design. In production for fifty years, more than 240 have been built and flown on a wide range of missions. The design will remain in use with the international space station well into the 21st century, providing the only manned access to the station after the retirement of the shuttle in 2011.
The Soyuz spacecraft was designed in 1962 for rendezvous and docking operations in near earth orbit, leading to piloted circumlunar flight. Versions remained in production into the 21st Century as a space station ferry, resupply craft, and lifeboat. After the retirement of the American space shuttle in 2011, it became the only means for regular human access to space.
Russian orbital launch vehicle. The world's first ICBM became the most often used and most reliable launch vehicle in history. The original core+four strap-on booster missile had a small third stage added to produce the Vostok launch vehicle, with a payload of 5 metric tons. Addition of a larger third stage produced the Voskhod/Soyuz vehicle, with a payload over 6 metric tons. Using this with a fourth stage, the resulting Molniya booster placed communications satellites and early lunar and planetary probes in higher energy trajectories. By the year 2000 over 1,628 had been launched with an unmatched success rate of 97.5% for production models. Improved models providing commercial launch services for international customers entered service in the new millenium, and a new launch pad at Kourou was to be inaugurated in 2009. It appeared that the R-7 could easily still be in service 70 years after its first launch.
Crew: Artyukhin, Popovich. Planned first crew to the first Almaz space station. Cancelled after the loss of control of Almaz OPS 1 (Salyut 2) in orbit. Backup crew: Volynov, Zholobov.
Crew: Demin, Sarafanov. Planned second crew to the first Almaz space station. Cancelled after the loss of control of Almaz OPS 1 (Salyut 2) in orbit. Backup crew: Rozhdestvensky, Zudov.
Crew: Komarov. Space disaster that put back Soviet lunar program 18 months. Soyuz 1 was to dock with Soyuz 2 and transfer crew. Instead Soyuz 1 solar panel didn't deploy; manual reentry; tangled parachute lines; astronaut killed on impact with earth. Backup crew: Gagarin.
Crew: Rukavishnikov, Shatalov, Yeliseyev. Intended first space station mission. Hard dock with station could not be achieved. Then stuck and could separate from the station only after repeated attempts. Toxic fumes in air supply during landing overcame one astronaut. Backup crew: Kolodin, Kubasov, Leonov.Support crew: Dobrovolsky, Patsayev, Volkov.
Crew: Dobrovolsky, Patsayev, Volkov. First space station mission. Record flight duration. Main telescope inoperative. Fire in space station put out. Fail-safe valve opening during re-entry, resulted in decompression and death of entire crew. Backup crew: Kolodin, Kubasov, Leonov.
Soyuz 11A510.
Alternate designation for Vostok 11A510 orbital launch vehicle.
Russian orbital launch vehicle. Standardized launch vehicle designed to replace a proliferation of earlier models (8K72, 8A91, 8K74, 8K78, 11A57). Designed initially to support launch of the Soyuz complex (7K manned, 9K rocket stage, and 11k tanker) and Zenit-4 reconnaisance satellite. Later 'U' model extended to cover a range of follow-on satellites. Compared to 11A57, the telemetry system was reduced in mass to no more than 150 kg, and engines were cherry-picked for the vehicle core to ensure that specific impulse was no less than 252 seconds at sea level, 315 in vacuum.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 43,000/3,550 kg. Thrust 994.30 kN. Vacuum specific impulse 314 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 100,500/6,500 kg. Thrust 977.70 kN. Vacuum specific impulse 315 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,400/2,700 kg. Thrust 294.00 kN. Vacuum specific impulse 330 seconds.
Russian orbital launch vehicle. 11A511 with reinforced second stage, large fairing for earth orbit test of LK lunar lander.
Russian orbital launch vehicle. Development of the Soyuz-M began in 1967 to launch the 6.6 metric ton Soyuz 7K-VI manned military spacecraft into a 65-degree inclination earth orbit. The spacecraft was cancelled, but development continued, and eight were Soyuz-M's were built and used to launch Zenit-4MT reconnaissance satellites in 1971-1976. The differences compared to the Soyuz-U are not known, and what (if anything) differentiated these Zenit-4MT missions from others is also a mystery.
Russian standardised man-rated orbital launch vehicle derived from the original R-7 ICBM of 1957. It has been launched in greater numbers than any orbital launch vehicle in history. Not coincidentally, it has been the most reliable as well. After over 40 years service in Russia, ESA built a new launch pad at Kourou which will keep it in service from three launch sites in three countries well into the mid-21st Century.
Russian orbital launch vehicle. Standard Soyuz universal booster with the Fregat upper stage, derived from the propulsion system for Lavochkin interplanetary probes.
Russian orbital launch vehicle. Standard Soyuz universal booster with the Ikar upper stage, derived from the propulsion system for the Kozlov Yantar series of spy satellites.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 44,500/3,784 kg. Thrust 994.30 kN. Vacuum specific impulse 310 seconds. Gross mass includes 1190 kg of hydrogen peroxide and 280 kg of liquid nitrogen expended during ascent but not contributing to propulsion.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 105,400/6,875 kg. Thrust 997.09 kN. Vacuum specific impulse 311 seconds. Current version. Gross mass includes 2600 kg of hydrogen peroxide and 520 kg of liquid nitrogen expended during ascent but not contributing to propulsion.
Russian orbital launch vehicle. Soyuz 11A511U2 used synthetic kerosene ('Sintin') in first stage for launch of premium reconnaisance satellite and manned payloads requiring just a bit more payload than the standard 11A511 could offer. Further use of the 11A511U2 abandoned in 1996 due to Sintin production stoppage. Later Soyuz spacecraft launched on standard Soyuz, with reduced payload and rendezvous with Mir in lower orbit accepted.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,200/2,355 kg. Thrust 298.10 kN. Vacuum specific impulse 330 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 42,810/3,550 kg. Thrust 996.30 kN. Vacuum specific impulse 314 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 101,160/6,500 kg. Thrust 1,011.00 kN. Vacuum specific impulse 319 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,400/2,400 kg. Thrust 298.10 kN. Vacuum specific impulse 330 seconds.
Russian orbital launch vehicle. Version of Soyuz launcher with increased payload, designed to launch Soyuz R military reconnaisance satellite. Cancelled along with the Soyuz R project in 1966. Unknown differences to standard Soyuz to reach payload requirement of circa 6700 kg to 65 degree orbit.
Russian orbital launch vehicle. Version of the Soyuz launcher envisioned for the cancelled Soyuz B translunar rocket stage.
Russian orbital launch vehicle. Version of the Soyuz launcher envisioned for the cancelled Soyuz V tanker spacecraft.
Crew: Lazarev, Makarov. Experimental flight for the purpose of further development of manned space craft Soyuz 7K-T modifications. After the Soyuz 11 disaster, the Soyuz underwent redesign for increased reliability. Backup crew: Grechko, Gubarev.Support crew: Klimuk, Sevastyanov.
Crew: Kolodin, Leonov, Rukavishnikov. If the Soyuz 11 crew had not perished during return to the earth, the Leonov crew would have been sent for a second visit to the Salyut 1 space station. A 30-day mission duration was planned. Backup crew: Gubarev, Sevastyanov, Voronov.
Crew: Kubasov, Leonov. Planned first mission to the Salyut DOS 2 space station. Cancelled after DOS 2 was destroyed during launch. Backup crew: Lazarev, Makarov.Support crew: Grechko, Gubarev.
Crew: Kubasov, Leonov. Planned first mission to the Salyut DOS 3 space station (Cosmos 557). Cancelled after Cosmos 557 failed in orbit. Backup crew: Lazarev, Makarov.Support crew: Grechko, Gubarev.
Crew: Klimuk, Lebedev. First Byelorussian astronaut. First space mission devoted to a single scientific instrument. A unique flight of the 7K-T/AF modification of the Soyuz spacecraft. The orbital module was dominated by the large Orion 2 astrophysical camera. Backup crew: Vorobyov, Yazdovsky.
Crew: Lazarev, Makarov. Planned second mission to the Salyut DOS 2 space station. Cancelled after DOS 2 was destroyed during launch. Backup crew: Grechko, Gubarev.Support crew: Klimuk, Sevastyanov.
Crew: Lazarev, Makarov. Planned second mission to the Salyut DOS 3 space station (Cosmos 557). Cancelled after Cosmos 557 failed in orbit. Backup crew: Grechko, Gubarev.Support crew: Klimuk, Sevastyanov.
Crew: Artyukhin, Popovich. First military space station mission. Manned military reconnaissance of the earth's surface, assessing the fundamental value of such observations, and some supplemental medico-biological research. Backup crew: Demin, Sarafanov.Support crew: Rozhdestvensky, Volynov, Zholobov, Zudov.
Crew: Demin, Sarafanov. Second phase of manned operations aboard the Salyut 3 military space station, aborted when the Igla rendezvous system electronics failed and no docking was made. Backup crew: Volynov, Zholobov.Support crew: Rozhdestvensky, Zudov.
Crew: Filipchenko, Rukavishnikov. ASTP Manned Test Flight. Check-out of the Soyuz systems modified for Apollo-Soyuz docking in space. Backup crew: Andreyev, Dzhanibekov.Support crew: Ivanchenkov, Romanenko.
Crew: Volynov, Zholobov. Planned but cancelled third mission to the Salyut 3 space station. Backup crew: Rozhdestvensky, Zudov.
Crew: Grechko, Gubarev. First successful Russian civilian space station mission. Manned two crew. Docked with Salyut 4. Backup crew: Lazarev, Makarov.Support crew: Klimuk, Sevastyanov.
Crew: Klimuk, Sevastyanov. Manned two crew. Docked with Salyut 4. Backup crew: Kovalyonok, Ponomaryov.
Crew: Lazarev, Makarov. First manned spaceflight abort. During launch third stage separation failed to occur. Crew aborted to 20 G landing in mountains near Chinese border, sliding down a slope towards a cliff until their parachute snagged on a tree. Backup crew: Klimuk, Sevastyanov.
Crew: Kubasov, Leonov. First docking between two spacecraft launched from different nations. Culmination of the Apollo-Soyuz Test Project, a post-moon race 'goodwill' flight to test a US/Soviet common docking system. Backup crew: Filipchenko, Rukavishnikov.Support crew: Andreyev, Dzhanibekov, Ivanchenkov, Romanenko.
Soyuz 2.
Alternate designation for Soyuz ST orbital launch vehicle.
Crew: Volynov, Zholobov. Military space station mission. Hand-docked with the Salyut 5 station after failure of automated Igla system. Crew member became psychotic and mission was returned to earth from space station early. Toxic gases in station were suspected. Backup crew: Rozhdestvensky, Zudov.Support crew: Berezovoi, Glazkov, Gorbatko, Lisun.
Crew: Aksyonov, Bykovsky. Surplus Soyuz ASTP spacecraft modified with a multi-spectral camera manufactured by Carl Zeiss-Jena in place of the universal docking apparatus. Eight days were spent photographing the earth. Backup crew: Malyshev, Strekalov.Support crew: Andreyev, Popov.
Crew: Rozhdestvensky, Zudov. Docking with Salyut 5 military station aborted due to electronics failure. Crew nearly froze to death after an emergency landing in a lake in a blizzard at -20 deg C. It took hours before the capsule could be dragged to shore. Backup crew: Glazkov, Gorbatko.Support crew: Berezovoi, Lisun.
Crew: Glazkov, Gorbatko. First complete change of cabin atmosphere for a space station. Special apparatus brought up to Salyut 5 to vent the entire station through the EVA airlock. However analysis after arrival showed no toxins in the air. Backup crew: Berezovoi, Lisun.Support crew: Kozelsky, Preobrazhensky.
Crew: Kovalyonok, Ryumin. Manned two crew. Unsuccessful mission. Failed to dock with Salyut 6 due to damage to spacecraft's docking mechanism. Backup crew: Ivanchenkov, Romanenko.
Crew: Berezovoi, Lisun. Mission to the Salyut 5 space station, cancelled when fuel reserves aboard the station were 70 kg below those required for the planned 14 day mission. Backup crew: Kozelsky, Preobrazhensky.
Soyuz 26.
Flight up of Salyut 6 EO-1 manned spaceflight.
Crew: Dzhanibekov, Kolodin. Planned mission to Salyut 6 that would make first docking with rear docking port and be the first crew to swap spacecraft and return in the spacecraft that ferried the Soyuz 25 crew. But Soyuz 25 failed to dock with Salyut 6. Backup crew: Lazarev, Makarov.
Soyuz 27.
Flight back of Salyut 6 EO-1 manned spaceflight.
Soyuz 28.
Alternate designation for Salyut 6 EP-2 manned spaceflight.
Soyuz 29.
Alternate designation for Salyut 6 EO-2 manned spaceflight.
Crew: Bykovsky, Khrunov, Yeliseyev. Soyuz 2 was to dock with Soyuz 1 and transfer crew. Instead Soyuz 1 solar panel didn't deploy; manual reentry; tangled parachute lines; death of cosmonaut. Soyuz 2 cancelled. Backup crew: Gorbatko, Kubasov, Nikolayev.
Crew: Beregovoi. Second manned Soyuz flight. Rendezvoused with the unmanned Soyuz 2 but failed to dock, blamed on manual control by cosmonaut who repeatedly overrode automatic systems, and used nearly all of his orientation fuel in his first attempt to dock. Backup crew: Shatalov, Volynov.
Soyuz 30.
Alternate designation for Salyut 6 EP-3 manned spaceflight.
Soyuz 31.
Alternate designation for Salyut 6 EP-4 manned spaceflight.
Soyuz 32.
Flight up of Salyut 6 EO-3 manned spaceflight.
Soyuz 32.
Alternate designation for Salyut 6 EO-3 manned spaceflight.
Soyuz 33.
Alternate designation for Salyut 6 EP-5-1 manned spaceflight.
Soyuz 34.
Flight back of Salyut 6 EO-3 manned spaceflight.
Soyuz 35.
Alternate designation for Salyut 6 EO-4 manned spaceflight.
Soyuz 36.
Alternate designation for Salyut 6 EP-5 manned spaceflight.
Soyuz 37.
Alternate designation for Salyut 6 EP-7 manned spaceflight.
Soyuz 38.
Alternate designation for Salyut 6 EP-8 manned spaceflight.
Soyuz 39.
Alternate designation for Salyut 6 EP-9 manned spaceflight.
Soyuz 4.
Flight back of Soyuz 4-5 manned spaceflight.
Crew: Shatalov. First Russian docking. Mission successfully completed the simulated lunar orbit docking and crew transfer mission attempted by Soyuz 1 in April 1967. Two crew from Soyuz 5 returned in Soyuz 4. Backup crew: Shonin.
Crew: Khrunov, Yeliseyev. First crew transfer in space. Two crew from Soyuz 5 returned in Soyuz 4. Suit hung up on attempt to exit and flow of oxygen shut off; diverted crew, resulting in no film of the world's first space crew transfer. Backup crew: Filipchenko, Gorbatko, Kubasov.
Soyuz 40.
Alternate designation for Salyut 6 EP-10 manned spaceflight.
Soyuz 5.
Flight up of Soyuz 4-5 manned spaceflight.
Crew: Volynov. Two crew transferred to and returned in Soyuz 4. Remaining astronaut barely survived nose-first reentry of Soyuz 5, still attached to its service module. Backup crew: Filipchenko, Gorbatko, Kubasov.
Soyuz 5 (Khrunov, Yeliseyev).
Alternate designation for Soyuz 4-5 manned spaceflight.
Soyuz 5 (Volynov).
Alternate designation for Soyuz 5 manned spaceflight.
Crew: Kubasov, Shonin. First simultaneous flight of three manned spacecraft. First vacuum welding in space. Rendezvous electronics failed in all three craft, scrubbing three-way spacecraft rendezvous mission. Backup crew: Shatalov, Yeliseyev.
Crew: Filipchenko, Gorbatko, Volkov. First simultaneous flight of three manned spacecraft. The spacecraft was to have docked with Soyuz 8 and exchanged one crew member from each spacecraft while Soyuz 6 took film from nearby. However rendezvous electronics failed in all three craft. Backup crew: Kolodin, Shatalov, Yeliseyev.
Russian manned lunar flyby spacecraft. 12 launches, 1967.03.10 (Cosmos 146) to 1970.10.20 (Zond 8). The Soyuz 7K-L1, a modification of the Soyuz 7K-OK, was designed for manned circumlunar missions.
Crew: Leonov, Makarov. Planned first manned circumnavigation of the moon. It was decided after the American Apollo 8 lunar orbital flight in December 1968 to cancel any 'second place' Soviet manned circumlunar flights. Backup crew: Kuklin.
Crew: Bykovsky, Rukavishnikov. Planned second Soviet circumlunar flight. Cancelled after the success of the American Apollo 8. Backup crew: Klimuk.
Crew: Popovich, Sevastyanov. Planned third and final Russian circumlunar flight. Cancelled after the success of the American Apollo 8 in December 1968. Backup crew: Voloshin.
Russian manned spacecraft module. 12 launches, 1967.03.10 (Cosmos 146) to 1970.10.20 (Zond 8). Modification of Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section.
Russian manned spacecraft module. 12 launches, 1967.03.10 (Cosmos 146) to 1970.10.20 (Zond 8). Increased heat shield protection and presumably reaction control system propellant for re-entry from lunar distances. Reentry capsule.
Russian manned spacecraft module. 12 launches, 1967.03.10 (Cosmos 146) to 1970.10.20 (Zond 8). Separates before trans-lunar injection. Jettisonable support cone.
Russian manned lunar orbiter. 2 launches, 1969.02.21 (N-1 3L) to 1969.07.03 (N-1 5L). Hybrid spacecraft used in N1 launch tests.
Russian manned lunar orbiter. 2 launches, 1969.11.28 (Soyuz 7K-L1E s/n 1) and 1970.12.02 (Cosmos 382). Modification of Soyuz circumlunar configuration used in propulsion tests of the Block D stage.
Soyuz 7K-L1S.
Alternate designation for Soyuz 7K-L1A manned lunar orbiter.
Russian manned lunar orbiter. 2 launches, 1971.06.26 (N-1 6L) to 1972.11.23 (LOK). The two-crew LOK lunar orbiting spacecraft was the largest derivative of Soyuz developed.
Russian manned spacecraft module. 2 launches, 1971.06.26 (N-1 6L) to 1972.11.23 (LOK). Living section.
Russian manned spacecraft module. 2 launches, 1971.06.26 (N-1 6L) to 1972.11.23 (LOK). Increased heat shield protection and presumably reaction control system propellant for re-entry from lunar distances. Reentry capsule.
Russian manned spacecraft. One launch, 1976.09.15, Soyuz 22. Soyuz 7K-T modified with installation of East German MF6 multispectral camera. Used for a unique solo Soyuz earth resources mission.
Russian manned spacecraft module. One launch, 1976.09.15, Soyuz 22. MKF6 Camera replaced docking system and Igla automatic rendezvous and docking system deleted. Four windows, BO separated after retrofire. Living section.
Russian manned spacecraft module. One launch, 1976.09.15, Soyuz 22. Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section.
Russian manned spacecraft module. One launch, 1976.09.15, Soyuz 22. Post-Soyuz 11 modification for crew of two in spacesuits. Reentry capsule.
Russian manned spacecraft. 17 launches, 1966.11.28 (Cosmos 133) to 1970.06.01 (Soyuz 9). Development of a three-manned orbital version of the Soyuz, the 7K-OK was approved in December 1963.
Russian manned spacecraft module. 17 launches, 1966.11.28 (Cosmos 133) to 1970.06.01 (Soyuz 9). Heavy-duty male/female docking system with no internal transfer tunnel. Igla automatic rendezvous and docking system. Living section.
Russian manned spacecraft module. 17 launches, 1966.11.28 (Cosmos 133) to 1970.06.01 (Soyuz 9). Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section.
Russian manned spacecraft module. 17 launches, 1966.11.28 (Cosmos 133) to 1970.06.01 (Soyuz 9). Post-Soyuz 1 modification, allowing crew of three without spacesuits. Analogue sequencer and computers operate spacecraft. Reentry capsule.
Russian manned spacecraft. Study 1965. Korolev was always interested in application of artificial gravity for large space stations and interplanetary craft. He sought to test this in orbit from the early days of the Vostok program.
Russian manned spacecraft module. 2 launches, 1971.04.23 (Soyuz 10) to 1971.06.06 (Soyuz 11). Lightweight male/female docking system with roller-type probe, internal transfer tunnel. Living section.
Russian manned spacecraft module. 2 launches, 1971.04.23 (Soyuz 10) to 1971.06.06 (Soyuz 11). Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section.
Russian manned spacecraft module. 2 launches, 1971.04.23 (Soyuz 10) to 1971.06.06 (Soyuz 11). Post-Soyuz 1 modification, allowing crew of three without spacesuits. Analogue sequencer and computers operate spacecraft. Reentry capsule.
Russian manned spacecraft. 3 launches, 1974.08.06 (Cosmos 670) to 1976.11.29 (Cosmos 869). The Soyuz 7K-S had its genesis in military Soyuz designs of the 1960's.
Russian manned spacecraft. 23 launches, 1972.06.26 (Cosmos 496) to 1981.05.14 (Soyuz 40).
Russian manned spacecraft module. 23 launches, 1972.06.26 (Cosmos 496) to 1981.05.14 (Soyuz 40). Lightweight male/female docking system with roller-type probe, internal transfer tunnel (Collar Length: 0.22 m. Probe Length: 0. Living section.
Russian manned spacecraft module. 23 launches, 1972.06.26 (Cosmos 496) to 1981.05.14 (Soyuz 40). Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section.
Russian manned spacecraft module. 23 launches, 1972.06.26 (Cosmos 496) to 1981.05.14 (Soyuz 40). Post-Soyuz 11 modification for crew of two in spacesuits. Reentry capsule.
Russian manned spacecraft. 8 launches, 1974.05.27 (Cosmos 656) to 1978.06.27 (Soyuz 30). Version of 7K-T for flights to Almaz. Known difference with the basic 7K-T included systems for remote control of the Almaz station and a revised parachute system.
Russian manned spacecraft. Cancelled 1966. To deliver crews to the Soyuz R 11F71 station Kozlov developed the transport spacecraft 11F72 Soyuz 7K-TK.
Russian manned spacecraft. 4 launches, 1974.04.03 (Cosmos 638) to 1975.07.15 (Soyuz 19 (ASTP)). The Soyuz 7K-T as modified for the docking with Apollo.
Russian manned spacecraft. 2 launches, 1971.04.23 (Soyuz 10) to 1971.06.06 (Soyuz 11). This was a modification of Soyuz 7K-OK with a lightweight docking system and a crew transfer tunnel.
Crew: Shatalov, Yeliseyev. First simultaneous flight of three manned spacecraft. The spacecraft was to have docked with Soyuz 7 and exchanged one crew member from each spacecraft while Soyuz 6 took film from nearby. However rendezvous electronics failed in all three craft. Backup crew: Nikolayev, Sevastyanov.
Crew: Nikolayev, Sevastyanov. Record flight duration. Head-over-heels rotation of Soyuz to conserve fuel and lack of exercise resulted in terrible condition of astronauts on return. The Soviets almost reconsidered their space station plans as a result. Backup crew: Filipchenko, Grechko.Support crew: Lazarev, Yazdovsky.
Russian manned spacecraft. Study 1962. The 7K Soyuz spacecraft was initially designed for rendezvous and docking operations in near earth orbit, leading to piloted circumlunar flight.
Russian manned spacecraft module. Study 1962. Original design with notional docking system with no probe and internal transfer tunnel. Living section.
Russian manned spacecraft module. Study 1962. Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system but with no base flange for a shroud. Equipment-engine section.
Russian manned spacecraft module. Study 1962. Original Soyuz design, allowing crew of three without spacesuits. Reentry capsule.
Crew: Nikolayev, Demin. Planned Soyuz circumlunar mission. Soyuz would dock with a refuelled rocket stage and be accelerated on a loop around the moon. Cancelled in mid-1964 due to delays in Soyuz and decision to race Americans to moon landing. Backup crew: Shonin, Kugno.
Crew: Bykovsky, Artyukhin. The planned second manned Soyuz circumlunar mission in 1965 would have been commanded by Bykovsky. The cosmonauts trained docking with the 9K and 11K rocket stages for months before the mission concept was dumped in August 1964. Backup crew: Zaikin, Gulyayev.
Crew: Popovich, Ponomaryova. Popovich was to have been accompanied by female cosmonaut Ponomaryova in what would have been the first mixed crew crew flight to the moon in 1965. The program was cancelled in August 1964. Backup crew: Gorbatko, Kolodin.
Crew: Beregovoi, Solovyova. Planned fourth Soyuz circumlunar mission. Cancelled August 1964. Backup crew: Shatalov, Zholobov.
Crew: Malyshev, Laveykin. Planned Soyuz flight to a dock with the Almaz OPS 4 space station. The mission was cancelled together with the Almaz program in 1981.
Russian manned spacecraft module. 4 launches, 1974.04.03 (Cosmos 638) to 1975.07.15 (Soyuz 19 (ASTP)). Universal docking system designed for ASTP with three petaled locating system and internal transfer tunnel. No automated rendezvous and docking system. Living section.
Russian manned spacecraft module. 4 launches, 1974.04.03 (Cosmos 638) to 1975.07.15 (Soyuz 19 (ASTP)). Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section.
Russian manned spacecraft module. 4 launches, 1974.04.03 (Cosmos 638) to 1975.07.15 (Soyuz 19 (ASTP)). Post-Soyuz 11 modification for crew of two in spacesuits. Reentry capsule.
Russian space tug. Study 1962. In the definitive December 1962 Soyuz draft project, the Soyuz B (9K) rocket acceleration block would be launched into a 225 km orbit by a Soyuz 11A511 booster.
Crew: Bachurin, Ivanchenkov. Planned Soyuz flight to Mir. Main purpose was to provide spaceflight experience to Bachurin and Borodai, who had been selected as back-up crew of the first manned Buran flight. Cancelled in cut-backs after fall of the Soviet Union. Backup crew: Borodai, Balandin.
Soyuz Circumlunar.
Alternate designation for DSE-Alpha manned lunar flyby spacecraft.
Uprated Soyuz booster designed for high performance Russian government missions and delivery of Soyuz and Progress spacecraft to the International Space Station. Upgraded engines, modern avionics, reduced non-Russian content. Unknown differences to Soyuz ST.
Russian manned spacecraft. Cancelled 1974. Modification of the Soyuz 7K-OK spacecraft to test in earth orbit the Kontakt rendezvous and docking system.
Crew: Filipchenko, Gorbatko. Final crews selected for a dual Soyuz mission in Earth orbit to test the Kontakt docking system to be used on the lunar landing LOK and LK spacecraft. The Kontakt-A Soyuz would have been the active spacecraft, simulating the LOK lunar orbiter. Backup crew: Vorobyov, Yazdovsky.
Crew: Lazarev, Makarov. Final crews selected for a dual Soyuz mission in Earth orbit to test the Kontakt docking system to be used on the lunar landing LOK and LK spacecraft. The Kontakt-P Soyuz would have been the passive spacecraft, simulating the LK lunar lander. Backup crew: Fartushny, Klimuk.
Soyuz M.
Alternate designation for Soyuz 7K-TM manned spacecraft.
Rus project was to result in first major propulsion upgrade to R-7 family in forty years, using first stage engines derived from those developed for Zenit second stage to boost performance. It would have permitted launches from Plesetsk with same or greater payload than launch of standard Soyuz-U from Baikonur, permitting move of more launch operations back onto Russian territory. Instead the more modest Soyuz ST / Soyuz FG upgrades were made.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 42,200/3,000 kg. Thrust 872.00 kN. Vacuum specific impulse 336 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 100,500/6,000 kg. Thrust 872.00 kN. Vacuum specific impulse 336 seconds. Proposed improved version. Not developed.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 5,000/1,000 kg. Thrust 20.00 kN. Vacuum specific impulse 360 seconds. Empty mass estimated. Multiple restart engine.
Crew: Grechko, Kuklin. Cancelled 16 day mission with Soyuz n 18 to conduct rendezvous and docking operations and demonstrate life support system for the LK manned lunar lander.
Crew: Khrunov, Yeliseyev. Cancelled 16 day mission with Soyuz n 18 to conduct rendezvous and docking operations and demonstrate life support system for the LOK manned lunar orbiter.
Crew: Fartushny, Shatalov. The active spacecraft in the second planned test of the Kontakt lunar rendezvous/docking system. 15 to 16 day missions to demonstrate the new SZhO life support system for the LOK manned lunar orbiter.
Crew: Patsayev, Shonin, Yazdovsky. Passive spacecraft in the second planned test of the Kontakt lunar rendezvous/docking system. One or two of the crew would have spacewalked to the Soyuz 11 Kontakt and returned in the other spacecraft.
Russian manned space station. Cancelled 1970. In December 1967 OKB-1 chief designer Mishin managed to have Kozlov's Soyuz VI project killed. In its place he proposed to build a manned military station based on his own Soyuz 7K-OK design.
Russian manned combat spacecraft. Study 1963. In December 1962 Sergei Korolev released his draft project for a versatile manned spacecraft to follow Vostok. The Soyuz A was primarily designed for manned circumlunar flight.
Russian manned combat spacecraft. Study 1964. The Soyuz 7K-PPK (pilotiruemiy korabl-perekhvatchik, manned interceptor spacecraft) was a revised version of the Soyuz P manned satellite inspection spacecraft.
Russian manned spacecraft. Cancelled 1966. A military reconnaissance version of Soyuz, developed by Kozlov at Samara from 1963-1966. It was to consist of an the 11F71 small orbital station and the 11F72 Soyuz 7K-TK manned ferry.
Crew: Kubasov, Shonin. As of February 1969 Soyuz s/n 14 was set for a solo seven day mission in April-May 1969. The spacecraft and crew were reassigned to the three-spacecraft Soyuz 6/7/8 mission and flew as Soyuz 6.
Crew: Filipchenko, Gorbatko, Volkov, Shatalov, Yeliseyev. As of February 1969 Soyuz s/n 15 and 16 were set for a mission with a total of 5 cosmonauts aboard in August-September 1969. They would have remained docked together for three days.
Soyuz s/n 18.
Alternate designation for Soyuz sn 18 manned spaceflight.
Soyuz s/n 19.
Alternate designation for Soyuz sn 19 manned spaceflight.
Soyuz s/n 20.
Alternate designation for Soyuz sn 20 manned spaceflight.
Soyuz s/n 21.
Alternate designation for Soyuz sn 21 manned spaceflight.
Soyuz s/n 22.
Alternate designation for Soyuz sn 22 manned spaceflight.
Soyuz s/n 23.
Alternate designation for Soyuz sn 23 manned spaceflight.
Prior to the Soyuz 1 disaster, planned second dual Soyuz manned docking mission. Crew Komarov, Bykovsky, Khrunov, and Yeliseyev.
Prior to the Soyuz 1 disaster, planned third dual Soyuz manned docking mission. Crew Gagarin, Nikolayev, Gorbatko, and Kubasov
Prior to Soyuz 1 disaster, planned solo Soyuz mission to test Vulkan space welding device. Commander was to be either Komarov, Bykovsky, Gagarin, Nikolayev, Beregovoi, or Shatalov. The other two crewmembers were to be either Lankin and Fartushniy from the Paton Institute, VVS cosmonaut Kolodin, or an engineer from OKB-1.
Crew: Filipchenko, Grechko. Soyuz s/n 18 would have been the active spacecraft of the first dual-spacecraft test of the Kontakt docking system. A crew transfer using the Krechet spacesuit would presumably have taken place. Backup crew: Lazarev, Makarov.
Crew: Lazarev, Makarov. Soyuz s/n 19 was to have been equipped with the passive Kontakt rendezvous/docking system of the LK lunar lander. It would have been the docking target for Soyuz s/n 18. A crew transfer using the Krechet spacesuit would presumably have taken place. Backup crew: Vorobyov, Yazdovsky.
Crew: Vorobyov, Yazdovsky. Soyuz s/n 20 would have been the active spacecraft of the second dual launch to test the Kontakt lunar orbit rendezvous system. A crew transfer using the Krechet spacesuit would presumably have taken place. Backup crew: Yakovlev, Porvatkin.
Crew: Yakovlev, Porvatkin. Soyuz s/n 21 equipped with the passive Kontakt rendezvous/docking system of the LK lunar lander. Would have served as a docking target for Soyuz s/n 20 . A crew transfer using the Krechet spacesuit would presumably have taken place. Backup crew: Kovalyonok, Isakov.
Crew: Kovalyonok, Isakov. Soyuz s/n 22 would have been the active spacecraft of the second dual launch to test the Kontakt lunar orbit rendezvous system. A crew transfer using the Krechet spacesuit would presumably have taken place. Backup crew: Shcheglov.
Crew: Shcheglov. Soyuz s/n 23 would have been equipped with the passive Kontakt rendezvous/docking system of the LK lunar lander. The spacecraft would have served as a docking target for Soyuz s/n 22.
Uprated Soyuz booster designed for commercial customers. Upgraded engines, modern digital avionics, reduced non-Russian content. Can be used with either Ikar or Fregat upper stages. The 'FG' was the military version.
Uprated Soyuz booster designed for commercial customers. Upgraded engines, modern avionics, reduced non-Russian content. Uses Fregat upper stage.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 44,400/3,810 kg. Thrust 1,021.10 kN. Vacuum specific impulse 310 seconds. Gross mass includes 1190 kg of hydrogen peroxide and 280 kg of liquid nitrogen expended during ascent but not contributing to propulsion.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 105,400/6,875 kg. Thrust 999.60 kN. Vacuum specific impulse 311 seconds. Gross mass includes 2600 kg of hydrogen peroxide and 520 kg of liquid nitrogen expended during ascent but not contributing to propulsion.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,200/2,355 kg. Thrust 294.00 kN. Vacuum specific impulse 359 seconds.
Russian manned spacecraft. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Soyuz T had a long gestation, beginning as the Soyuz VI military orbital complex Soyuz in 1967.
Russian manned spacecraft module. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Lightweight male/female docking system with flange-type probe, internal transfer tunnel. Igla automatic rendezvous and docking system. Living section.
Russian manned spacecraft module. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Improved PAO service module derived from Soyuz 7K-S with pressure-fed main engines and unitary RCS/main engine propellant feed system. Equipment-engine section.
Russian manned spacecraft module. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Significantly improved Soyuz re-entry capsule, based on development done in Soyuz 7K-S program. Accommodation for crew of three in spacesuits. Reentry capsule.
Soyuz T-10.
Alternate designation for Salyut 7 EO-3 manned spaceflight.
Crew: Strekalov, Titov Vladimir. First manned pad abort. Launch vehicle blew up on pad, crew rescued by launch escape tower, which pulled their capsule away at 20 G's. Backup crew: Kizim, Solovyov Vladimir.
Soyuz T-11.
Alternate designation for Salyut 7 EP-3 manned spaceflight.
Soyuz T-12.
Alternate designation for Salyut 7 EP-4 manned spaceflight.
Soyuz T-13.
See Salyut 7 EO-4-1a, Salyut 7 EO-4-1b and Salyut 7 EP-5 manned spaceflights.
Soyuz T-13 (Dzhanibekov).
Alternate designation for Salyut 7 EO-4-1b manned spaceflight.
Soyuz T-13 (Savinykh).
Alternate designation for Salyut 7 EO-4-1a manned spaceflight.
Crew: Savinykh, Vasyutin, Volkov Aleksandr. Planned mission to operate military experiments aboard Salyut 7. Cancelled due to technical and personnel problems aboard station. Backup crew: Aleksandrov, Saley, Viktorenko.
Soyuz T-14.
See Salyut 7 EP-5, Salyut 7 EO-4-1a, and Salyut 7 EO-4-2 manned spaceflights.
Soyuz T-14 (Grechko).
Alternate designation for Salyut 7 EP-5 manned spaceflight.
Soyuz T-14 (Vasyutin, Volkov Aleksandr).
Alternate designation for Salyut 7 EO-4-2 manned spaceflight.
Soyuz T-15.
Alternate designation for Mir EO-1 manned spaceflight.
Crew: Volynov, Manarov, Levchenko. Final 'civilian' expedition to Salyut 7 station with Buran pilot aboard for spaceflight familiarisation was cancelled when control of the station was lost. Backup crew: Solovyov, Berezovoi, Shchukin.
Crew: Aleksandrov, Saley, Viktorenko. Cancelled second crew to operate TKS-3 military experiments aboard Salyut 7. These had been left uncompleted with the early return of the EO-4-2 crew due to Vasyutin's illness. Backup crew: Moskalenko, Serebrov, Solovyov.
Crew: Dobrokvashina, Ivanova, Savitskaya. Cancelled all-female flight to be launched on International Woman's Day. Breakdown of Salyut 7, exhaustion of stock of Soyuz T spacecraft, and official resistance led to cancellation of the mission. Backup crew: Viktorenko, Aleksandrov, Solovyov.
Soyuz T-2.
Alternate designation for Salyut 6 EP-6 manned spaceflight.
Soyuz T-3.
Alternate designation for Salyut 6 EO-5 manned spaceflight.
Crew: Lazarev, Polyakov, Strekalov. Planned but cancelled manned flight. Crew dissolved when Lazarev failed physical in early 1981. Backup crew: Isaulov, Potapov, Rukavishnikov.
Soyuz T-4.
Alternate designation for Salyut 6 EO-6 manned spaceflight.
Soyuz T-5.
Alternate designation for Salyut 7 EO-1 manned spaceflight.
Soyuz T-6.
Alternate designation for Salyut 7 EP-1 manned spaceflight.
Soyuz T-7.
Alternate designation for Salyut 7 EP-2 manned spaceflight.
Crew: Serebrov, Strekalov, Titov Vladimir. Manned three crew. Unsuccessful mission. Igla approach system antenna was damaged during ascent; failed to rendezvous with Salyut 7. Further attempts toman Salyut 7 could not take place for two months because of launch and abort lighting constraints. Backup crew: Aleksandrov, Lyakhov, Savinykh.
Soyuz T-9.
Alternate designation for Salyut 7 EO-2 manned spaceflight.
Russian manned spacecraft. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34).
Russian manned spacecraft module. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34). Lightweight male/female docking system with flange-type probe, internal transfer tunnel. Kurs automatic rendezvous and docking system . Living section.
Russian manned spacecraft module. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34). Further improvement of Soyuz T PAO service module with pressure-fed main engines and unitary RCS/main engine propellant feed system. Equipment-engine section.
Russian manned spacecraft module. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34). Significantly improved Soyuz re-entry capsule, based on development done in Soyuz 7K-S program. Accommodation for crew of three in spacesuits. Reentry capsule.
Soyuz TM-10.
Alternate designation for Mir EO-7 manned spaceflight.
Soyuz TM-11.
Alternate designation for Mir EO-8 manned spaceflight.
Soyuz TM-11 (Afanasyev, Manarov).
Alternate designation for Mir EO-8 manned spaceflight.
Soyuz TM-11 (Akiyama).
Alternate designation for Mir Kosmoreporter manned spaceflight.
Soyuz TM-12.
Alternate designation for Mir EO-9 manned spaceflight.
Soyuz TM-12 (Artsebarsky).
Alternate designation for Mir EO-9 manned spaceflight.
Soyuz TM-12 (Krikalyov).
Alternate designation for Mir LD-3 manned spaceflight.
Soyuz TM-12 (Sharman).
Alternate designation for Mir Juno manned spaceflight.
Soyuz TM-13.
Alternate designation for Mir EO-10 manned spaceflight.
Soyuz TM-13 (Aubakirov, Viehboeck).
Alternate designation for Mir Austromir manned spaceflight.
Soyuz TM-13 (Volkov Aleksandr).
Alternate designation for Mir EO-10 manned spaceflight.
Crew: Kaleri, Viehboeck, Volkov Aleksandr. Soyuz TM-13 and TM-14 crews were reshuffled extensively due to commercial considerations and necessity of flying a Kazakh cosmonaut. This was the original crew assignment. Kaleri and Avdeyev were replaced by Kazakh researchers in the final crew. Backup crew: Avdeyev, Lothaller, Viktorenko.
Soyuz TM-14.
Alternate designation for Mir EO-11 manned spaceflight.
Soyuz TM-14 (Flade).
Alternate designation for Mir 92 manned spaceflight.
Soyuz TM-14 (Kaleri, Viktorenko).
Alternate designation for Mir EO-11 manned spaceflight.
Crew: Aubakirov, Avdeyev, Viktorenko. Soyuz TM-13 and TM-14 crews were reshuffled extensively due to commercial seat bookings by Austria and Germany and the necessity of flying a Kazakh-born cosmonaut as part of the Baikonur rental agreement. Backup crew: Musabayev, Polishchuk, Solovyov.
Crew: Korzun, Aleksandrov, Aubakirov. Soyuz TM-13 and TM-14 crews were reshuffled extensively due to commercial seat bookings by Austria and Germany and the necessity of flying a Kazakh-born cosmonaut as part of the Baikonur rental agreement. Backup crew: Tsibliyev, Laveykin, Musabayev.
Soyuz TM-15.
Alternate designation for Mir EO-12 manned spaceflight.
Soyuz TM-15 (Avdeyev, Solovyov).
Alternate designation for Mir EO-12 manned spaceflight.
Soyuz TM-15 (Tognini).
Alternate designation for Mir Antares manned spaceflight.
Soyuz TM-16.
Alternate designation for Mir EO-13 manned spaceflight.
Soyuz TM-17.
Alternate designation for Mir EO-14 manned spaceflight.
Soyuz TM-17 (Haignere).
Alternate designation for Mir Altair manned spaceflight.
Soyuz TM-17 (Serebrov, Tsibliyev).
Alternate designation for Mir EO-14 manned spaceflight.
Soyuz TM-18.
Alternate designation for Mir EO-15 manned spaceflight.
Soyuz TM-18 (Afanasyev, Usachyov).
Alternate designation for Mir EO-15 manned spaceflight.
Soyuz TM-18 (Polyakov).
Alternate designation for Mir LD-4 manned spaceflight.
Soyuz TM-19.
Alternate designation for Mir EO-16 manned spaceflight.
Soyuz TM-2.
Alternate designation for Mir EO-2 manned spaceflight.
Soyuz TM-2 (Laveykin).
Alternate designation for Mir EO-2 manned spaceflight.
Soyuz TM-2 (Romanenko).
Alternate designation for Mir LD-1 manned spaceflight.
Soyuz TM-20.
Alternate designation for Mir EO-17 manned spaceflight.
Soyuz TM-20 (Kondakova, Viktorenko).
Alternate designation for Mir EO-17 manned spaceflight.
Soyuz TM-20 (Merbold).
Alternate designation for Mir Euromir 94 manned spaceflight.
Soyuz TM-21.
Alternate designation for Mir EO-18 manned spaceflight.
Soyuz TM-22.
Alternate designation for Mir EO-20 manned spaceflight.
Soyuz TM-23.
Alternate designation for Mir EO-21 manned spaceflight.
Soyuz TM-24.
Alternate designation for Mir EO-22 manned spaceflight.
Soyuz TM-24 (Andre-Deshays).
Alternate designation for Mir Cassiopee manned spaceflight.
Soyuz TM-24 (Kaleri, Korzun).
Alternate designation for Mir EO-22 manned spaceflight.
Soyuz TM-25.
Alternate designation for Mir EO-23 manned spaceflight.
Soyuz TM-25 (Ewald).
Alternate designation for Mir 97 manned spaceflight.
Soyuz TM-25 (Lazutkin, Tsibliyev).
Alternate designation for Mir EO-23 manned spaceflight.
Soyuz TM-26.
Alternate designation for Mir EO-24 manned spaceflight.
Soyuz TM-27.
Alternate designation for Mir EO-25 manned spaceflight.
Soyuz TM-27 (Budarin, Musabayev).
Alternate designation for Mir EO-25 manned spaceflight.
Soyuz TM-27 (Eyharts).
Alternate designation for Mir Pegase manned spaceflight.
Soyuz TM-28.
Alternate designation for Mir EO-26 manned spaceflight.
Soyuz TM-28 (Avdeyev).
Alternate designation for Mir EO-26--27 manned spaceflight.
Soyuz TM-28 (Baturin).
Alternate designation for Mir EP-4 manned spaceflight.
Soyuz TM-28 (Padalka).
Alternate designation for Mir EO-26 manned spaceflight.
Soyuz TM-29.
Alternate designation for Mir EO-27 manned spaceflight.
Soyuz TM-29 (Afanasyev, Haignere).
Alternate designation for Mir EO-27 manned spaceflight.
Soyuz TM-29 (Bella).
Alternate designation for Mir Stefanik manned spaceflight.
Soyuz TM-3.
Crew: Aleksandrov. Aleksandrov replaced the ailing EO-2 crew member Laveykin and remained aboard Mir with Romanenko. Backup crew: Savinykh.
Soyuz TM-3 (Aleksandrov).
Alternate designation for Soyuz TM-3 manned spaceflight.
Soyuz TM-3 (Faris, Viktorenko).
Alternate designation for Mir EP-1 manned spaceflight.
Soyuz TM-30.
Alternate designation for Mir EO-28 manned spaceflight.
Soyuz TM-31.
Alternate designation for ISS EO-1 manned spaceflight.
Soyuz TM-32.
Alternate designation for ISS EP-1 manned spaceflight.
Soyuz TM-33.
Alternate designation for ISS EP-2 manned spaceflight.
Soyuz TM-34.
Alternate designation for ISS EP-3 manned spaceflight.
Soyuz TM-4.
Alternate designation for Mir EO-3 manned spaceflight.
Soyuz TM-4 (Levchenko).
Alternate designation for Mir LII-1 manned spaceflight.
Soyuz TM-4 (Manarov, Titov Vladimir).
Alternate designation for Mir EO-3 manned spaceflight.
Soyuz TM-5.
Alternate designation for Mir EP-2 manned spaceflight.
Soyuz TM-5.
Flight back of Mir EP-3 manned spaceflight.
Soyuz TM-5.
Flight up of Mir EP-2 manned spaceflight.
Soyuz TM-6.
See Mir EP-3, Mir LD-2, Mir EO-3, and Mir Aragatz manned spaceflights.
Soyuz TM-6 (Lyakhov, Mohmand).
Alternate designation for Mir EP-3 manned spaceflight.
Soyuz TM-6 (Polyakov).
Alternate designation for Mir LD-2 manned spaceflight.
Soyuz TM-7.
Alternate designation for Mir EO-4 manned spaceflight.
Soyuz TM-7 (Chretien).
Alternate designation for Mir Aragatz manned spaceflight.
Soyuz TM-7 (Krikalyov, Volkov Aleksandr).
Alternate designation for Mir EO-4 manned spaceflight.
Soyuz TM-8.
Alternate designation for Mir EO-5 manned spaceflight.
Crew: Afanasyev, Sevastyanov, Stankiavicius. Planned flight to ensure continuous occupation cancelled due to budget cutbacks and delay in launching Kvant 2 and Kristall modules.
Soyuz TM-9.
Alternate designation for Mir EO-6 manned spaceflight.
Russian three-crew manned spacecraft. Operational, first launch 2002.10.30. Designed for use as a lifeboat for the International Space Station. After the retirement of the US shuttle in 2011, Soyuz TMA was the only conveying crews to the ISS. Except for the Chinese Shenzhou, it became mankind's sole means of access to space.
Russian manned spacecraft module. Operational. First launch 2002.10.30. Lightweight male/female docking system with flange-type probe, internal transfer tunnel. Kurs automatic rendezvous and docking system with two Kurs antennae, no tower. Living section.
Russian manned spacecraft module. Operational. First launch 2002.10.30. Further improvement of Soyuz T PAO service module with pressure-fed main engines and unitary RCS/main engine propellant feed system. Equipment-engine section.
Russian manned spacecraft module. Operational. First launch 2002.10.30. Reentry capsule.
Soyuz TMA-1.
Alternate designation for ISS EP-4 manned spaceflight.
Soyuz TMA-10.
Alternate designation for ISS EO-15 manned spaceflight.
Soyuz TMA-11.
Alternate designation for ISS EO-16 manned spaceflight.
Soyuz TMA-12.
Alternate designation for ISS EO-17 manned spaceflight.
Soyuz TMA-13.
Alternate designation for ISS EO-18 manned spaceflight.
Soyuz TMA-14.
Alternate designation for ISS EO-19 manned spaceflight.
Soyuz TMA-15.
Alternate designation for ISS EO-20 manned spaceflight.
Soyuz TMA-16.
Alternate designation for ISS EO-21 manned spaceflight.
Soyuz TMA-17.
Flight up of ISS EO-22 manned spaceflight.
Soyuz TMA-18.
Flight up of ISS EO-23 manned spaceflight.
Soyuz TMA-19.
Flight up of ISS EO-24 manned spaceflight.
Soyuz TMA-2.
Alternate designation for ISS EO-7 manned spaceflight.
Soyuz TMA-20.
Flight up of ISS EO-25 manned spaceflight.
Crew: Padalka, Duque, Kotov. Soyuz TMA-2 was originally to switch lifeboats on the ISS. After the loss of Columbia, and grounding of the remaining shuttles, it was instead flown by a two-man skeleton crew to keep the station alive until shuttle flights could resume.
Soyuz TMA-3.
Alternate designation for ISS EO-8 manned spaceflight.
Soyuz TMA-3 (Duque).
Alternate designation for ISS Cervantes manned spaceflight.
Crew: Dezhurov, Kuipers, Skripochka. Soyuz TMA-3 was originally to switch lifeboats on the ISS. After the Columbia disaster, the remaining shuttles were grounded. Soyuz TMA-3 instead flew with a skeleton crew to provide minimal manning of space station while shuttle was grounded.
Soyuz TMA-4.
Alternate designation for ISS EO-9 manned spaceflight.
Crew: Musabayev, Schlegel. Soyuz TMA-4 was originally to switch lifeboats on the ISS. After the Columbia disaster, the remaining shuttles were grounded. Soyuz TMA-4 instead flew with a skeleton crew to provide minimal manning of space station while shuttle was grounded.
Soyuz TMA-5.
Alternate designation for ISS EO-10 manned spaceflight.
Soyuz TMA-6.
Alternate designation for ISS EO-11 manned spaceflight.
Soyuz TMA-7.
Alternate designation for ISS EO-12 manned spaceflight.
Soyuz TMA-8.
Alternate designation for ISS EO-13 manned spaceflight.
Soyuz TMA-9.
Alternate designation for ISS EO-14 manned spaceflight.
Russian logistics spacecraft. Cancelled 1964. In the definitive December 1962 Soyuz draft project, the Soyuz B (9K) rocket acceleration block would be launched into a 225 km orbit by a Soyuz 11A511 booster.
Russian manned combat spacecraft. Cancelled 1965. To determine the usefulness of manned military space flight, two projects were pursued in the second half of the 1960's.
Crew: Kolesnikov, Popovich. The planned first flight of the Soyuz VI combat spacecraft was planned for early 1969, beating America's equivalent Manned Orbiting Lab. The project was cancelled in 1968 in favour of Mishin's OIS (in turn cancelled in 1970) and Chelomei's Almaz stations. Backup crew: Belousov, Gubarev.
Out-of-date article -the development of the Soyuz spacecraft, as known in 1987.
Soyuz-2-1A.
Alternate designation for Soyuz ST orbital launch vehicle.
Russian orbital launch vehicle.
Soyuz-3.
Alternate designation for Onega orbital launch vehicle.
Planned launch to tend Almaz-T-1 station. Cancelled after the station's booster exploded on the way to orbit on 29 November 1986.
Soyuz-FG.
Alternate designation for Soyuz FG missile.
Russian orbital launch vehicle. Alternate designation for Soyuz 11A511U.
SOZ.
Auxilliary thruster package (Russian abbreviation)
SP.
Special Publication (NASA)
SpaB-17.
Manufacturer's designation of EPKM Solid rocket engine.
Fourth Academy solid rocket engine. In Production. Kick stage for orbital insertion of Iridium satellites Used on CZ-2C/SD launch vehicle. First flight 1997.
American space suit, tested 1971. Prototype for a Mechanical Counter Pressure suit made up of six layers of elastic material accompanied by a full bubble helmet.
Space Adentures.
After being exposed to sustained zero-G, the human spine lengthens about 5 cm. This causes sometimes intense pain in the lower back muscles for the first day or so in space.
American manned space station. Study 1970. Growth of Space Station into a 50 man Space Base was a required capability in the Phase B NASA Space Station studies of 1969-1970.
American military anti-satellite system. Study 1996. The Operational SBLOV (Space Based Laser Orbital Vehicle) was the final space based chemical laser system envisioned at the end of the SDI / Star Wars program.
Space Biotechnological Complex.
Russian materials science satellite. Study 1992. In 1991 the Salyut Design Bureau proposed a Space Biotechnological Complex, for production of pharmaceutical products in zero gravity.
Space Block.
Alternate designation for R-56 Block K rocket stage.
The future that never was...
Space Complex for a Piloted Expedition to Mars.
Alternate designation for KK manned mars expedition.
American manned combat spacecraft. Study 1973. The space cruiser was a US Navy design for a single-place crewed space interceptor designed to destroy Soviet satellites used to track the location of US warships.
American sounding rocket. Three stage vehicle consisting of 1 x Talos + 1 x Sergeant + 1 x M57A1
Space Electric Rocket Test.
Alternate designation for SERT ion engine technology satellite.
Space Flyer Unit.
Alternate designation for SFU materials science satellite.
Space Gnat.
Government designation of Star 5A Solid rocket engine.
Space Imaging.
American manufacturer of spacecraft. Space Industries Inc, Houston, USA.
Space Infrared Telescope Facility.
Alternate designation for SIRTF infrared astronomy satellite.
American military anti-satellite system. Study 1996. By 1996 the Star Lite space laser was replaced by the more refined and slightly heavier SLD (Space Laser Demo), weighing 17.4 metric tons). Two versions of the 20 meter long spacecraft were envisioned.
American manufacturer of rockets. Space Launch Corporation, USA.
Space Launching System A-388.
Alternate designation for SLS A-388 orbital launch vehicle.
Space Launching System A-410.
Alternate designation for SLS A-410 orbital launch vehicle.
Space Launching System AB-825.
Alternate designation for SLS AB-825 orbital launch vehicle.
Space Launching System BC-2720.
Alternate designation for SLS BC-2720 orbital launch vehicle.
American manned space station. Study 1979. The Space Operations Center was proposed by NASA's Johnson Spaceflight Center in 1979.
Space Recovery Experiment.
Alternate designation for SRE re-entry vehicle technology satellite.
Space Services.
Space Ship Experimental.
Alternate designation for SSX ssto vtovl orbital launch vehicle.
Space Shuttle Solid Rocket Motor.
Alternate designation for Redesigned SRM Solid rocket engine.
American space mobility device, tested 1965. Marquardt developed a sled design in the mid-1960's for maneuvering in the vicinity of a spacecraft. The space sled approach was dropped in preference to the shuttle manned maneuvering unit.
Space Solid Fuel Rocket Carrier Co Ltd.
Chinese manufacturer of rockets. Space Solid Fuel Rocket Carrier Co Ltd, China.
Category of spacecraft.
American manned space station. Study 1969.
American manned space station. Design as of 1984. President Reagan finally approved a space station project for NASA in January 1984.
American manned space station. Study 1982. NASA regarded a permanently manned space station as the next 'logical step' in manned spaceflight after the Space Shuttle entered service in April 1981.
American manned space station. Design as of 1991. Following the collapse of the Space Station Freedom project, NASA unveiled its new Space Station design in March 1991.
American manned space station. Design as of 1988. NASA's first detailed cost assessment for the US space station caused a political uproar in Congress, where many politicians had started to express doubt about the project.
Category of spacecraft.
American manned space station. Study 1993. Following the collapse of Space Station Fred, NASA quickly formed a Space Station redesign team which identified three major redesign options in April 1993....
Category of spacecraft.
Pressurized garment worn by an astronaut in vacuum conditions.
To explore and work in space, human beings must take their environment with them because there is no atmospheric pressure and no oxygen to sustain life. Inside the spacecraft, the atmosphere can be controlled so that special clothing is not needed. But in order to work outside the spacecraft, humans need the protection of a spacesuit.
American manufacturer of spacecraft. Space Systems, USA.
Space Systems/Loral (1990).
Sixth Owner of Palo Alto
Space Technology Research Vehicle.
Alternate designation for STRV technology satellite.
Going to the bathroom in space is a messy affair, for there was no gravity to prevent the solids and liquids from floating about.
Astronaut training group.
Paid space tourist mission to ISS.
Paid space tourist mission to ISS.
Paid space tourist mission to ISS.
Space Transportation System.
Manufacturer's designation for Shuttle winged orbital launch vehicle.
American space tug. Study 1971. The original Boeing Space Tug design of the early 1970's was sized to be flown either in a single shuttle mission or as a Saturn V payload. Optimum mass was found to be 20.6 metric tons regardless.
Category of spacecraft.
Category of spacecraft.
The same redistribution of body fluids in zero-G that gives astronauts puffy faces and swollen sinuses also causes involuntary expansion of a portion of the male anatomy during sleep. Female astronauts experience similar effects, with the thighs slimming and the breasts enlarging and firming.
American manufacturer of rockets. Space Vector, USA.
British manned spaceplane. Study 1990. 50 passenger orbiter portion of a two-stage vehicle proposed by David Ashford of Bristol Spaceplanes Ltd. in the 1980`s / 1990's.
British winged orbital launch vehicle. The Bristol Spaceplanes Spacebus was a Two Stage To Orbit (TSTO) Manned Spaceplane, with an airbreathing supersonic / hypersonic, delta winged first stage and a second stage powered by a liquid fuelled rocket engine. It was proposed by David Ashford of Bristol Spaceplanes Ltd. in the 1980`s / 1990's. The 6-crew Concorde-sized Spacecab would serve as a prototype for the larger 50-person Spacebus.
French communications satellite. 12 launches, 1975.08.26 (Symphonie 2) to 1994.01.24 (Eutelsat II F5). 3-axis stabilized using bipropellant thrusters (750 kg propellant - unified with apogee insertion and maneuvering propulsion) and momentum wheels.
French communications satellite. 5 launches, 1994.01.24 (Turksat 1A) to 1997.01.30 (Nahuel 1A).
French communications satellite. 5 launches, 1987.11.21 (TVSAT 1) to 1990.07.24 (TDF 2). 3-axis stabilized using bipropellant thrusters (1220 kg propellant - unified with apogee insertion and maneuvering propulsion) and momentum wheels.
French communications satellite bus. Operational, first launch 1996.07.09.
European communications satellite bus. Operational, first launch 2005.02.03. The Spacebus 4000 represented a new larger platform to meet customer demand.
British manned spaceplane. Study 1990. Six passenger orbiter portion of a two-stage vehicle proposed by David Ashford of Bristol Spaceplanes Ltd. in the 1980`s / 1990's. It would serve as the prototype for the even more ambitious Spacebus.
British winged orbital launch vehicle. The Bristol Spaceplanes Spacecab was a Two Stage To Orbit (TSTO) Manned Spaceplane, with an airbreathing supersonic / hypersonic, delta winged first stage and a second stage powered by a liquid fuelled rocket engine. It was proposed by David Ashford of Bristol Spaceplanes Ltd. in the 1980`s / 1990's. The Concorde-sized spacecraft would deliver a payload of 6 persons to low Earth orbit. It would serve as a prototype for the larger 50-person Spacebus.
Spacecraft Charging at High Altitude.
Alternate designation for SCATHA communications technology satellite.
Spaceflight is dangerous and unforgiving, which is all the more reason for the astronauts to seek relief in humour...
SpaceDev, USA.
SpaceDev N2O/Solid hybrid rocket engine. 73.5 kN. Rocketplane boost. Out of production. Isp=250s. Used on Tier One launch vehicle. First flight 2002.
American radio astronomy satellite. Study 2003. Unmanned lunar radio astronomy observatory concept, designed to be landed on the South Pole.
American manned space station. Study 1986.
American manned space station module. 14 launches, 1993.06.21 (Spacehab SH-01) to 1999.05.27 (Spacehab-DM). Founded by Bob Citron in 1982, Spacehab Inc. was the only entrepreneurial company to successfully develop a commercial manned spaceflight module.
American manufacturer of spacecraft. Spacehab, Inc. , Houston, Houston, USA
American agency. Space Imaging, Thornton. , Thornton, USA
European/American joint project provided the Spacelab pressurized module that remained attached to space shuttle and permitted conduct of a range of experiments.
American manned space station module. 20 launches, 1983.11.28 (Spacelab 1) to 1998.04.17 (Neurolab).
American sounding rocket. Series of commercial suborbital rockets marketed by Up Industries. Data given is for first-launched prototype.
Series of commercial suborbital rockets marketed by Up Industries.
UPAero solid rocket engine. 45 kN.
American single-stage commercial sounding rocket. Operational, first launch 2006.09.25.
Solid propellant rocket stage. Loaded mass 200 kg. Thrust 45.00 kN.
American winged orbital launch vehicle. Martin-Marrietta shuttle Phase A design. X-24B type lifting body orbiter with unique catamaran-configuration booster.
Lox/LH2 propellant rocket stage. Loaded/empty mass 1,224,490/203,342 kg. Thrust 28,082.54 kN. Vacuum specific impulse 442 seconds. Unique Catamaran configuration.
Lox/LH2 propellant rocket stage. Loaded/empty mass 362,812/80,000 kg. Thrust 4,549.05 kN. Vacuum specific impulse 459 seconds. Delta Winged, Cross Range 2,742 km
Category of spacecraft.
American manufacturer of spacecraft. Spaceplane, USA.
Spaceport America was conceived in the early 1990s by the Southwest Space Task Force, a private group of New Mexican space activists. Studies led them to concentrate on 70 square-km of state-owned land, 72 km north of Las Cruces, New Mexico, near a locale known as Upham. In 2003 the governor and state legislature were finally sold on the idea of developing the site as America's premiere inland commercial spaceport.
N2O/Solid propellant rocket stage. Loaded/empty mass 3,600/1,200 kg. Thrust 73.50 kN. Vacuum specific impulse 250 seconds. Wing area 15 sq m.
American manned spaceplane. 14 launches, 2003.05.20 to 2004.05.13 . X-Prize suborbital spaceplane concept of Scaled Composites, Mojave, California.
Crew: Melvill. First private manned spaceflight. Fourth powered flight of SpaceShipOne and first flight above 100 km altitude. Spacecraft rolled 90 degrees right and left at motor ignition; attitude control lost at engine shut down; engine fairing collapsed.
Crew: Melvill. Fifth powered flight of Burt Rutan's SpaceShipOne and first of two flights over 100 km that needed to be accomplished in a week to win the $10 million X-Prize. Spacecraft did a series of 60 rolls during last stage of engine burn.
Crew: Binnie. Suborbital altitude record for a manned spaceplane Sixth powered flight of Burt Rutan's SpaceShipOne and winner of the $10 million X-Prize by becoming the second flight over 100 km within a week.
American manned spaceplane. Study 2009. Development of the much larger SpaceShipTwo suborbital commercial manned spacecraft was announced in July 2005.
Spacewedge.
Code name for X-38 manned spaceplane.
American manufacturer of rockets, spacecraft, and rocket engines. SpaceX, USA.
Spain
SPAN.
Space Physics and Analysis Network. Solar Particle Alert Network.
Space and range radar
Spanker.
ASCC Reporting Name of MR-UR-100 and MR-UR-100U 15A16 intercontinental ballistic missiles.
Spar.
Canadian manufacturer of spacecraft. Spar Aerospace, Canada.
Air-launched two stage vehicle consisting of tandem Sparrow air-to-air missile motors.
American air-launched sounding rocket. Air-launched two stage vehicle consisting of tandem Sparrow air-to-air missile motors.
American sounding rocket. Three stage vehicle consisting of 1 x F3H Cougar + 1 x Sparrow + 1 x Sparrow
American sounding rocket. Three stage vehicle consisting of 1 x F3H Cougar + 1 x Sparrow + 1 x Sparrow
Solid propellant rocket stage. Loaded mass 100 kg. Thrust 35.00 kN.
American sounding rocket. Three stage vehicle consisting of 1 x F4B Phantom + 1 x Sparrow + 1 x 22.6KS1245
Solid propellant rocket stage. Loaded mass 100 kg. Thrust 5.50 kN.
Naval Prop Plant solid rocket engine.
American sounding rocket. Two stage vehicle.
Solid rocket stage. 1.50 kN (337 lbf) thrust.
American orbital launch vehicle. Three stage vehicle consisting of 1 x Redstone + 1 x Antares 2 + 1 x BE-3
Solid rocket stage. 34.00 kN (7,644 lbf) thrust. Mass 100 kg (220 lb).
American anti-ballistic missile evolved from the Nike Zeus and designed to intercept ICBM warheads in space. Three stage vehicle consisting of 1 x TX-500 + 1 x TX-454 + 1 x TX-239 solid propellant motors. Nearly as large and just as costly as the missiles it was designed to intercept. After 20 years of development, deployment was limited by arms agreements, and 30 were only briefly in service in 1975-1976.
American solar satellite. 8 launches, 1985.06.17 (Spartan 1) to 1998.10.29 (Spartan 201).
Solid propellant rocket stage. Loaded mass 5,000 kg. Thrust 2,000.00 kN.
Solid propellant rocket stage. Loaded mass 5,000 kg.
Spartan TX-500.
Alternate designation for Spartan ABM-1 rocket stage.
SPAS.
American military strategic defense satellite. 6 launches, 1983.06.18 (SPAS-01) to 1997.08.07 (CRISTA).
Spate, Wolfgang (1911-1997) German Luftwaffe Captain, Commander of the test squadrons for the Me-163.
SPB 7.35.
Alternate designation for Ariane 3-0 rocket stage.
SNPE solid rocket engine. 690 kN. Isp=263s. Strap-on booster for Advanced Scout, Ariane 2/3. First flight 1984.
SPB235.
Alternate designation for Ariane 5-0 rocket stage.
SPD 649-1.
Manufacturer's designation of LR47 rocket engine.
SPDM.
Special Purpose Dextrous Manipulator
Modification of a spectroscope in which the spectrum is photographed or recorded electronically. A spectroheliograph is a modification of the spectrograph which permits taking pictures of the complete solar disk in monochromatic light.
An optical instrument which spreads a beam of electromagnetic radiation into a spectrum of different wavelengths for visual inspection.
Spectrum Astro.
First Owner of Gilbert
Russian x-ray astronomy satellite.
SPED.
Supersonic Planetary Entry Decelerator (suborbital flight test)
Speer, Albert (1905-1981) German manager. Hitler's right-hand man. Architect and Reichminister for Armaments and Ammunition. He sponsored V-2 development and tried to keep operation in Wehrmacht hands.
Russian manned space station. One launch, 1995.05.20. Spektr was a module of the Mir space station. It began life as a dedicated military research unit.
Russian military anti-satellite system. Study 1989. Chelomei designed a spacecraft bus for space based weapons based on his TKS space tug. This was an alternate / competitive design to the NPO Energia USB.
American manufacturer. Sperry, USA.
American agency overseeing development of rockets. Florida Spaceport Authority, USA.
Spherical Heat Shield escape concept.
Alternate designation for Rockwell SHS manned rescue spacecraft.
American military technology satellite. One launch, 1974.02.11. Space Plasma High Voltage Interaction Experiment. Research payload carried on test flight of Titan 3E booster.
Spider.
ASCC Reporting Name of 9K714B intermediate range ballistic missile.
American military anti-satellite system. Study 1975. Project SPIKE was a 1970's suborbital conventional warhead ASAT air-launched from an F-106 interceptor. Considerable work was done from the early 1970s under the Missile and Space Defense Program.
Spin-2.
Alternate designation for Yantar-1KFT military surveillance satellite.
Russian winged orbital launch vehicle. The Soviet Air Force had an enduring interest in a horizontal takeoff/horizontal landing, manned, reusable space launch system that could ferry crews and priority supplies between earth and space on the same basis as conventional aircraft. Between 1960 and 1976 Mikoyan developed this manned partially reusable space launch system. It consisted of a reusable hypersonic air-breathing booster; two expendable rocket stages; and the reusable Spiral manned spaceplane. The effort was never properly funded by the government, and by the mid-1970's had only reached the stage of flight tests of subscale versions of Spiral. Development was discontinued in 1976 in favor of the Buran, a copy of the US space shuttle. However it was resurrected in improved form in the 1980's as the MAKS spaceplane.
Spiral EPOS.
Code name for MiG 105-11 manned spaceplane.
Russian manned spaceplane, developed 1965-1980s, including subscale flight article tests. Evolved into the MAKS spaceplane. The Spiral was an ambitious air-launched manned space system designed in the 1960's.
Système Préparatoire Infra-Rouge pour l'ALErte - preparatory infrared warning system. French government program to develop a missile early warning system, using infrared satellite imagery to detect ballistic missile launch and trajectory during boost phase. The demonstrator system included two 120 kilogram (260 lb) microsatellites and an alert and monitoring ground segment.
Spiridinov, Aleksei Sergeyevich Russian officer. Seventh Chief Directorate of Ministry of Armaments and Director of Nll-88 1953-1959.
Spirit.
Code name for MER mars lander.
An instrument to measure the breathing volume.
Spitsa, Ivan Ivanovich (1919-1992) Russian officer. Commander of TsKIK 1965-1973.
SPK.
Russian space mobility device, tested 1990. The Soviet Union developed a manned maneuvering unit and flew it from Mir in 1990.
Standard Precision Navigator/Gimbaled Electrostatically Suspended Aircraft Navigator
Spohn, Eberhard Julius (1906-2005) German 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 Heidelberg, Germany.
Sponable, Jess Mitchell (1955-) American engineer military spaceflight engineer astronaut, 1982-1987.
SPOT.
Systeme Probatoire pour l'Observation de la Terre - French remote sensing satellite network.
French earth land resources satellite. 3 launches, 1986.02.22 (SPOT 1) to 1993.09.26 (SPOT 3). SPOT was the French government-sponsored civil earth observation program, with support from Belgium and Sweden.
French earth land resources satellite. One launch, 1998.03.24, SPOT 4. SPOT was the French government-sponsored civil earth observation program. A single SPOT satellite provides complete coverage of the Earth every 26 days.
French earth land resources satellite. Two launches, 2002.05.04, 2009.12.18. SPOT was the French government sponsored civil Earth observation program. A single SPOT satellite provided complete coverage of the Earth every 26 days.
French agency.
American manufacturer of spacecraft. Sprague, Temecula, California, USA.
French solid rocket engine.
Kartukov solid rocket engine. 402 kN. S-2 Strela-2 missile, Sopka. Out of Production. Thrust 27 tf at cutout - 41at ignition.
Kartukov solid rocket engine. 294 kN. P-15 Termit. Out of Production. Thrust 28 tf at cutout - 30 tf at ignition.
Kartukov solid rocket engine. 24.5 kN. MiG-21PFM. Out of Production.
Spring, Sherwood Clark 'Woody' (1944-) American test pilot mission specialist astronaut. Flew on STS-61-B.
Springer, Robert Clyde 'Bob' (1942-) American test pilot mission specialist astronaut. Flew on STS-29, STS-38. US Marine Corps. Flew 550 combat missions in Southeast Asia. Grew up in Ashland, Ohio.
Nuclear-armed point defense anti-ballistic missile, an incredible high-acceleration weapon that would intercept incoming Soviet ICBMs in the atmosphere within 15 seconds of launch. Deployment limited by arms agreements and only 70 were briefly in service in 1975-1976.
Solid propellant rocket stage. Loaded mass 4,000 kg.
Solid rocket stage.
Sprint X265.
Alternate designation for Sprint ABM-1 rocket stage.
Japanese science. One launch, 2009.01.23. Microsatellite stabilized by a gravity gradient boom to study atmospheric sprites, built by by Tohoku University, Sendai.
SPRN.
Early Warning System (Russian abbreviation)
SPRN-1.
Alternate designation for Oko military early warning satellite.
SPRN-2.
Alternate designation for Prognoz SPRN military early warning satellite.
SPS.
Solar Power Satellite; or Secondary Propulsion System
Russian communications satellite. Study 1995.
Stechkin electric rocket engine family. Meteor, Gals. Marketed in USA by Space Systems/Loral and Fakel.
Stechkin electric rocket engine. 0.196 kN. Meteor, Gals. In Production. 1.35 kW Hall thruster. Thrust variable 2 to 20 kgf. Marketed in USA by Space Systems/Loral and Fakel. Isp=2500s.
Stechkin solid rocket engine. In Production. The French company SEP is developing this uprated version of the SPT-100 in cooperation with OKB Fakel. Isp=2200s.
Stechkin solid rocket engine. In Production.
Stechkin solid rocket engine. 0.780 kN. In Production. Thrust variable 8 to 80 kgf Isp=3000s.
Stechkin solid rocket engine. In Production.
Stechkin solid rocket engine. Meteor-Priroda. In Production.
Stechkin solid rocket engine. 0.098 kN. Yamal. In Production. Thrust variable 1 to 10 kgf Isp=2500s.
Spuskaemiy apparat.
Russian name (descent module) for Soyuz TMA SA manned spacecraft module.
Russian technology satellite. One launch, 1957.10.04. Tikhonravov's 1.4 metric ton ISZ satellite was to have been launched by the new R-7 ICBM as the Soviet Union's first satellite, during the International Geophysical Year.
Russian orbital launch vehicle. Two stage version of Vostok 11A57. Used for flight test of prototype Chelomei ASAT after cancellation of UR-200 booster and before availability of Tsiklon.
Russian biology satellite. One launch, 1957.11.03.
Russian earth magnetosphere satellite. 2 launches, 1958.04.27 (Sputnik failure) to 1958.05.15 (Sputnik 3). In July 1956 OKB-1 completed the draft project for the first earth satellite, designated ISZ (Artificial Earth Satellite).
Russian intercontinental ballistic orbital launch vehicle. Modified R-7 ICBM used to launch Sputnik 3.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 95,000/7,100 kg. Thrust 804.00 kN. Vacuum specific impulse 315 seconds.
Russian intercontinental ballistic orbital launch vehicle. Relatively unmodified R-7 ICBM test vehicles used to launch first two Sputniks.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 94,000/7,495 kg. Thrust 912.00 kN. Vacuum specific impulse 308 seconds.
The real story of the race to space
SNECMA, Pratt and Whitney lox/lh2 rocket engine. 230.4 kN. Design 2000. New upper-stage cryogenic engine for the upgraded Ariane-5, the Atlas-5, and other new vehicles.
American anti-ballistic test vehicle.
Solid propellant rocket stage. Loaded mass 4,000 kg.
SR.
Suborbital Rocket-Glider (Russian abbreviation); or Special Relativity
Aerojet solid rocket engine. 12.75" Improved FFAR .
Thiokol solid rocket engine. Maverick AGM-65.
SR11.
Hercules solid rocket engine. LGM-30 Retro Motor . Used on Minuteman 1 launch vehicle.
Aerodyne solid rocket engine. Super Loki PWN-10, PWN-11, PWN-12.
Thiokol solid rocket engine. HARM AGM-88.
Thiokol solid rocket engine. Maverick AGM-65.
Aerojet solid rocket engine. Maverick AGM-65.
Aerojet solid rocket engine. Sidewinder AIM-9J/P.
Solid propellant rocket stage. Loaded/empty mass 53,020/4,211 kg. Thrust 1,606.59 kN. Vacuum specific impulse 286 seconds. Modification of Peackeeper ICBM first stage.
Aerojet solid solid rocket engine. 1365 kN.
Hercules solid rocket engine. 329 kN.
Naval Propellant Plant solid rocket engine. Streaker MQM-107 Booster.
Rocketdyne solid rocket engine. Also designated WPU-9/B1 (AGM-130).
SR13.
Lockheed solid rocket engine.
SR19.
Aerojet solid rocket engine family.
SR19.
Government designation of SR-19 Solid rocket engine.
SR19.
American air-launched target missile. Single stage vehicle consisting of 1 surplus Minuteman 2 SR19AJ1 motor air-dropped from a C-130 transport. Similar to the SVC AltAir concept.
Aerojet solid rocket engine. 267.7 kN. Minuteman 2 2nd stage. In production. Second stage of Minuteman 2. Surplus motors used as second stage of Minotaur launch vehicle and various SDI targets in 1980's. Isp=287s. First flight 2000.
American target missile. Three stage vehicle consisting of 2 x MLRS + 1 x SR19 + 1 x SR19
Solid propellant rocket stage. Loaded mass 300 kg.
SR-3.
Alternate designation for Blackstar manned spaceplane.
SR45.
Atlantic Research solid rocket engine. Kitty PWN-6, Rooster PWN-7.
SR-47.
Government designation of UA1205 Solid rocket engine.
SR49.
Thiokol solid rocket engine. Genie AIR-2.
SR51.
Thiokol solid rocket engine. Titan 2 LGM-25C Retro Motor.
SR55.
United Technology Center solid rocket engine. Titan 2 LGM-25C Staging Motor.
SR59.
Atlantic Research solid rocket engine. Minuteman 1 LGM-30 Pitch Motor.
SR61.
Atlantic Research solid rocket engine. Minuteman 1 LGM-30 Spin Motor.
SR71.
Aerodyne solid rocket engine. Loki PWN-8.
Jet-powered rocket carrier vehicle. Loaded/empty mass 66,122/27,210 kg. Specific impulse 2084 seconds. Lockheed Reconaissance-delta wing. Maximum release conditions: Piggy-back, 9,091 kg (12.1 m length x 5.2 m span) at 3,300 kph at 24,390 m (D-21).
SR73.
Aerojet solid rocket engine. Minuteman 1 LGM-30 3rd stage.
SR73.
Solid rocket stage. 152.00 kN (34,171 lbf) thrust. Mass 3,600 kg (7,937 lb).
SR75.
Lockheed solid rocket engine. SRAM AGM-69, ASAT ASM-135.
SR9.
Hercules solid rocket engine. .
SRAM.
Short Range Attack Missile, a relatively small standoff missile for use by USAF's B-52 and FB-111A strategic bombers.
SRAM.
American Short Range Attack Missile, an air-launched nuclear-armed solid-propellant stand-off weapon to allow B-52 and FB-111 bombers to penetrate Soviet air space. In service 1972-1990. Retired after the collapse of the Soviet Union.
SRAM II.
Popular Name of SRAM-2 air-to-surface missile.
SRAM T.
ASCC Reporting Name of SRAM-2 air-to-surface missile.
Solid propellant rocket stage. Loaded mass 1,000 kg.
American Short Range Attack Missile, an air-launched nuclear-armed solid-propellant stand-off weapon to replace the SRAM. Mission was to allow B-52 and B-1 bombers to penetrate Soviet air space. Cancelled in 1991 after the collapse of the Soviet Union without going into service.
SRB.
Thiokol solid rocket engine family. Segmented solid rocket boosters for the compromised space shuttle design. Field joint design led to Challenger shuttle disaster. Production 1981-1985, after which superseded by RSRM's.
SRB.
Thiokol solid rocket engine. 11,520 kN. Isp=269s. Segmented solid rocket boosters for the compromised space shuttle design. Field joint design led to Challenger shuttle disaster. Production 1981-1985, after which superseded by RSRM's.
American heavy-lift orbital launch vehicle. Launch vehicle design preferred by NASA Administrator Mike Griffin to boost the manned CEV Crew Exploration Vehicle into low earth orbit. A single shuttle solid rocket booster would be mated with an upper stage in the 100 tonne class.
Nissan solid rocket engine family. Monolithic motor, shorter than that for H-2, using Thiokol filament wound composite structure.
Nissan solid rocket engine. 2250 kN. In production. Monolithic motor, shorter than that for H-2, using Thiokol filament wound composite structure. Isp=280s. First flight 2001.
SRC.
British National Space Research Council, UK.
SRDL.
US Army Signal Research and Development Laboratory
SRE.
Indian re-entry vehicle technology satellite. One launch, 2007.01.10. Indian experimental subscale Discoverer-type re-entry capsule. A testbed for a projected $ 3 billion Indian project to orbit a manned spacecraft by 2014.
SRET.
French technology satellite. 2 launches, 1972.04.04 (SRET 1) and 1975.06.05 (SRET 2). Test satellite.
India's primary space launch center, located on the east coast of the peninsula with a firing sector over the Bay of Bengal. In use from 1971 to present.
GSLV pad
PSLV, GSLV launch complex. PSLV pad
Sounding rocket complex
PSLV, GSLV launch complex.
SLV, ASLV launch complex. SLV pad
SRM.
Solid Rocket Motor
CSD solid rocket engine. 181.5 kN. Used in TOS; IUS-1 on Shuttle, Titan 34D. Known by manufacturer as Orbus 21. Propellant: 86% solids made up of HTPB UTP-19360A. Shape: cylindrical. Isp=296s. First flight 1982.
CSD solid rocket engine. 78.4 kN. Used in Shuttle, Titan 34D; IUS-2. Known by manufacturer as Orbus 6. Isp=304s. First flight 1982.
SRNS.
Satellite Radio Navigation System (Russian abbreviation)
Indian earth magnetosphere satellite. 4 launches, 1987.03.24 (SROSS A) to 1994.05.04 (SROSS-C2).
SS.
SS
SS.
Japanese earth magnetosphere satellite. 6 launches, 1970.09.25 (SS) to 1985.08.18 (SS-11 Suisei). Scientific observations in outer space.
SS-.
Surface-to-surface missile (designation numbering series - US DoD)
Space Systems/Loral, USA, USA
SS-10.
Department of Defence Designation of UR-200 intercontinental ballistic missile.
Brazilian intermediate range ballistic missile.
SS-11 Mod.1.
Department of Defence designation of UR-100 missile.
SS-11 Mod.2.
Department of Defence designation of UR-100M missile.
SS-11 Mod.3.
Department of Defence Designation of UR-100K intercontinental ballistic missile.
SS-11 Mod.4.
Department of Defence Designation of UR-100U intercontinental ballistic missile.
SS-12.
Department of Defence Designation of 9K76 intermediate range ballistic missile.
SS-12M.
Department of Defence Designation of 9K76B intermediate range ballistic missile.
SS-13 Mod.1.
Department of Defence Designation of RT-2 intercontinental ballistic missile.
SS-13 Mod.2.
Department of Defence Designation of RT-2P intercontinental ballistic missile.
SS-14.
Department of Defence Designation of RT-15 intermediate range ballistic missile.
SS-15.
SS-16.
Department of Defence Designation of Temp-2S intercontinental ballistic missile.
SS-17 Mod 1 and Mod 2.
Department of Defence Designation of MR-UR-100 intercontinental ballistic missile.
SS-17 Mod.3.
Department of Defence Designation of MR-UR-100U 15A16 intercontinental ballistic missile.
SS-18 Mod. 1-Mod. 2.
Department of Defence Designation of R-36M intercontinental ballistic missile.
SS-18 Mod.4.
Department of Defence Designation of R-36MU 15A18 intercontinental ballistic missile.
SS-18 Mod.5 and 6.
Department of Defence Designation of R-36M2 15A18M intercontinental ballistic missile.
SS-19 Mod 1 and Mod 2.
Department of Defence designation of UR-100N missile.
SS-19 Mod 3.
Department of Defence Designation of UR-100NU intercontinental ballistic missile.
SS-1A.
Department of Defence designation of R-1 missile.
SS-1B.
Department of Defence Designation of R-11 submarine-launched ballistic missile.
SS-1C.
Department of Defence Designation of R-17 short-range ballistic missile.
SS-2.
Department of Defence Designation of R-2 intermediate range ballistic missile.
SS-20 Mod 1.
Department of Defence Designation of 15Zh45 intermediate range ballistic missile.
SS-20 Mod 2.
Department of Defence Designation of 15Zh45UTTKh intermediate range ballistic missile.
SS-20 Mod 3.
Department of Defence Designation of 15Zh53 intermediate range ballistic missile.
SS-21.
SS-22.
Alternate Designation of 9K76B intermediate range ballistic missile.
SS-23.
Department of Defence Designation of 9K714B intermediate range ballistic missile.
SS-24.
Department of Defence Designation of RT-23 15Zh44 intercontinental ballistic missile.
SS-24 Mod 1.
Department of Defence Designation of RT-23U 15Zh60 intercontinental ballistic missile.
SS-24 Mod 2.
Department of Defence Designation of RT-23 15Zh52 and RT-23U 15Zh61 intercontinental ballistic missile.
Brazilian tactical ballistic missile.
SS-25 Mod 1 and 2.
Department of Defence designation of Topol missile.
SS-26.
Department of Defence Designation of RSS-40 intercontinental ballistic missile.
SS-28.
Alternate Designation of 15Zh53 intermediate range ballistic missile.
SS-3 Mod 1.
Department of Defence Designation of R-5 intermediate range ballistic missile.
SS-3 Mod.2.
Department of Defence Designation of R-5M intermediate range ballistic missile.
Brazilian short range ballistic missile.
SS-4 Mod 2.
Department of Defence Designation of R-12U intermediate range ballistic missile.
SS-4 Mod.1.
Department of Defence designation of R-12 missile.
SS-5 Mod 1.
Department of Defence designation of R-14 missile.
SS-5 Mod 2.
Department of Defence Designation of R-14U intermediate range ballistic missile.
Japanese test vehicle. The SS-520 was a two-stage rocket, the first stage consisting of the main booster of the S-520. It had a capability of launching a 140 kg payload to an altitude of about 1,000 km, and with addition of a third stage, as a satellite launch vehicle.
ISAS solid rocket engine.
Solid rocket stage. 143.10 kN (32,170 lbf) thrust. Mass 2,300 kg (5,071 lb).
Solid rocket stage. Mass 400 kg (882 lb).
SS-6 Mod 1.
Department of Defence designation of R-7 missile.
SS-6 Mod 2.
Department of Defence designation of R-7A missile.
Brazilian tactical ballistic missile.
SS-7 Mod 1.
Department of Defence Designation of R-16 intercontinental ballistic missile.
SS-7 Mod.2.
Department of Defence Designation of R-16U intercontinental ballistic missile.
SS-8 Mod. 1.
Department of Defence Designation of Romashka intercontinental ballistic missile.
SS-8 Mod. 2.
SS-9 Mod 1.
Department of Defence designation of Tsiklon missile.
SS-9 Mod 4.
Department of Defence Designation of R-36 8K67P intercontinental ballistic missile.
SS-9 Mod.3.
Department of Defence Designation of R-36-O orbital missile.
SSBS.
French medium-range ballistic missile.
SSBS.
French medium-range ballistic missile.
SSBS S01.
Manufacturer's designation for SSBS submarine-launched ballistic missile.
French submarine-launched ballistic missile.
Solid propellant rocket stage. Loaded mass 10,000 kg. Thrust 440.00 kN.
French submarine-launched ballistic missile.
French submarine-launched ballistic missile. Test vehicle.
French submarine-launched ballistic missile. Two stage vehicle.
French submarine-launched ballistic missile. Two stage vehicle consisting of 1 x SEP 902 + 1 x Rita II
Solid propellant rocket stage. Loaded mass 16,000 kg. Thrust 540.00 kN.
French submarine-launched ballistic missile.
SSC.
Swedish manufacturer of rockets and spacecraft. Swedish Space Corporation, Sweden.
SSC/MBB/ERNO.
Second Owner of Bremen
SSD.
Space Systems Division, Air Force
SSDC.
US Army Space and Strategic Defense Command
Chinese manufacturer of spacecraft. Shanghai Satellite Engineering and Research Centre, Shanghai, China.
spent stage experimental support module
SSETI.
European civilian surveillance satellite. One launch, 2005.10.27. Student-built technology satellite sponsored by the ESA. It ejected three 1-kg Cubesats after separating from the booster, but then itself lost power less than 14 hours later.
SSF.
American military naval signals reconnaisance satellite. 54 launches, 1963.03.18 (P-11 No. 1) to 1989.08.08 (USA 41).
SSI.
American agency. Space Services Incorporated, USA.
South Korean short range ballistic missile.
SSM-A-12.
Alternate Designation of Lacrosse tactical ballistic missile.
SSM-A-13.
Alternate Designation of Hermes A-2 tactical ballistic missile.
SSM-A-14.
Alternate Designation of Redstone short range ballistic missile.
SSM-A-15.
Department of Defence Designation of Hermes A-1 tactical ballistic missile.
SSM-A-16.
Department of Defence Designation of Hermes A-3B tactical ballistic missile.
SSM-A-17.
Alternate designation of Corporal missile.
SSM-A-17 / M2.
Alternate Designation of MGM-5B short range ballistic missile.
SSM-A-17 / M2A1.
Alternate Designation of MGM-5A short range ballistic missile.
SSM-A-23.
Department of Defence Designation of Dart tactical ballistic missile.
SSM-A-26 / M15.
Alternate designation of Sergeant missile.
SSM-A-6.
Alternate Designation of Navaho G-38 intercontinental cruise missile.
SSM-A-9.
Department of Defence Designation of Hermes B-1 tactical ballistic missile.
SSME.
Rocketdyne lox/lh2 rocket engine family. Space Shuttle Main Engines; only high-pressure closed-cycle reusable cryogenic rocket engine ever flown. Three mounted in the base of the American space shuttle. First flight 1981.
SSME.
Rocketdyne lox/lh2 rocket engine. 2278 kN. In production. Isp=453s. Space Shuttle Main Engines; only high-pressure closed-cycle reusable cryogenic rocket engine ever flown. . Three mounted in the base of the American space shuttle. First flight 1981.
Rocketdyne lox/lh2 rocket engine. 2445.7 kN. Pressure-fed. Isp=465s.
Notional lox/lh2 rocket engine. 3728.7 kN. VTOHL studies, 1978. Isp=467s.
Notional lox/lh2 rocket engine. 1535.2 kN. Study 1967. Isp=459s.
SSM-G-13.
Department of Defence Designation of Hermes C-1 tactical ballistic missile.
SSM-G-15.
Alternate Designation of Hermes A-1 tactical ballistic missile.
SSM-G-8.
Alternate Designation of Hermes A-3A tactical ballistic missile.
SSM-G-9.
Popular Name of Hermes B-1 tactical ballistic missile.
SSM-N-1.
Department of Defence Designation of Loon short range cruise missile.
SSM-N-2.
Department of Defence Designation of Triton intermediate range cruise missile.
SSM-N-4.
Department of Defence Designation of Taurus SSM-N-4 intermediate range cruise missile.
SSM-N-6.
Department of Defence Designation of Rigel SSM-N-6 intermediate range cruise missile.
SSM-N-8.
Alternate Designation of Regulus 1 intermediate range cruise missile.
SSM-N-9.
Alternate Designation of Regulus 2 intermediate range cruise missile.
Naval surface-to-surface missile (designation numbering series - US DoD)
SS-N-17.
Department of Defence Designation of R-31 submarine launched ballistic missile.
SS-N-18.
Department of Defence Designation of Volna SLV intercontinental ballistic orbital launch vehicle.
SS-N-18 Mod 1.
Department of Defence Designation of R-29R submarine-launched ballistic missile.
SS-N-18 Mod 2.
Department of Defence Designation of R-29K submarine-launched ballistic missile.
SS-N-18 Mod 3.
Department of Defence Designation of R-29RL submarine-launched ballistic missile.
SS-N-20.
Department of Defence designation of Rif-MA missile.
SS-N-20 Mod 1.
Department of Defence Designation of 3M20 submarine-launched ballistic missile.
SS-N-20 Mod 2.
Department of Defence designation of 3M65 missile.
SS-N-23.
Department of Defence Designation of R-29RM submarine-launched ballistic missile.
SS-N-24.
Department of Defence Designation of P-750 intermediate range cruise missile.
SS-N-28.
SS-N-3C.
Department of Defence Designation of P-6 intermediate range cruise missile.
SS-N-4.
Department of Defence designation of R-13 missile.
SS-N-5.
Department of Defence Designation of R-21 submarine-launched ballistic missile.
SS-N-6.
Department of Defence Designation of R-21A submarine-launched ballistic missile.
SS-N-6 Mod 1.
Department of Defence Designation of R-27 submarine-launched ballistic missile.
SS-N-6 Mod 2.
Department of Defence Designation of R-27K submarine-launched ballistic missile.
SS-N-6 Mod 3.
Department of Defence Designation of R-27U submarine-launched ballistic missile.
SS-N-8.
Department of Defence designation of Vysota missile.
SS-N-8 Mod 1.
Department of Defence Designation of R-29 submarine-launched ballistic missile.
SS-N-8 Mod 2.
Department of Defence Designation of R-29D submarine-launched ballistic missile.
SS-NX-30.
Department of Defence Designation of Bulava intercontinental ballistic missile.
American SSTO VTOVL orbital launch vehicle. P Seigler founded a company in 1976 to promote his design for a VTOVL SSTO vehicle using a lox/hydrogen aerospike engine.
SSPF.
Space Station Processing Facility
SSPS.
Sky Survey Prototype System
Space Station Remote Manipulator System
SSRT.
Single Stage Rocket Technology
SSS.
American earth magnetosphere satellite. One launch, 1971.11.15, Explorer 45. Studies magnetosphere, energetic particles.
Japanese technology satellite. One launch, 2006.09.22. Solar sail experiment.
SSSR.
USSR, Union of Soviet Socialist Republics (Russian abbreviation)
SST.
Super Sonic Transport
SST.
Chinese solar satellite. Study 1998. The SST, an advanced Chinese solar telescope, was to have been part of a sun monitoring system built along the earth's meridian circle at 120 degrees east.
SSTL.
First Owner of Surrey
German civilian surveillance satellite. Surrey satellite bus, notably used for the RapidEye constellation of five environmental monitoring satellites. Mass of 152 kg including 12 kg of propellant.
SSTO.
Category of launch vehicles. Single Stage To Orbit.
SSTO.
Single Stage To Orbit
Thiokol solid rocket engine. In Production. A slightly modified stage 3 Minuteman 3 with TVC and roll control systems removed, provided propulsion for the Douglas Spinning Solid Upper Stage for use with Space Shuttle payloads.
SSX.
American SSTO VTOVL orbital launch vehicle. The X-Rocket was a VTOVL SSTO design by Maxwell Hunter II at Lockheed in the late 1980's. The 227 tonne vehicle was powered by clustered RL10 engines. Internal reviews at Lockheed rejected the feasibility of the vehicle. After Hunter retired he worked with Gary Hudson to refine the design as the SSX. This was briefed by the pair to Space Defence Inititive Organization (SDIO) officials in 1988. It was largely through their efforts that the US government funded the DC-X demonstrator in the 1990's.
SS-X-26.
Department of Defence Designation of Iskander short range ballistic missile.
SS-X-27 / SS-X-29.
Department of Defence Designation of Topol M intercontinental ballistic missile.
SS-XZ.
Alternate Designation of RT-20 intermediate range ballistic missile.
ST.
Japanese test vehicle. Single stage vehicle.
ST.
Singapore/Taiwan communications satellite network operated by Singapore Telecom and Chunghwa Telecom of Taiwan.
ST.
Mitsubishi solid rocket engine.
ST-1.
Solid rocket stage.
ST5.
American technology satellite. 3 launched, 2006.03.22 (ST5-A) to (ST5-C).
NASDA solid rocket engine.
Japanese test vehicle. Two stage vehicle consisting of 1 x ST-735 + 1 x ST-735 stage 2
Solid propellant rocket stage. Loaded mass 7,400 kg.
ISAS solid rocket engine.
ISAS solid rocket engine.
Solid propellant rocket stage. Loaded mass 4,000 kg.
STA.
Japanese agency overseeing development of rockets. Science and Technology Agency, Japan.
Staats, Friedrich (1913-2002) German electronics engineer, worked for Steinhoff at Peenemuende, but stayed in Germany after war. Founded and led the leading German rocket society 1952-1990 (designated sequentially DAFRA, DRG, HOG, DGLR).
Romanian manned spacecraft. Study 2013. Stabilo was a suborbital manned system developed by ARCA.
Stack, John (1906-1972) American engineer, at NASA 1928-1962. Conducted fundamental research on transonic flight which resulted in X-1 being the first manned aircraft to break the sound barrier in 1947.
American technology satellite. 3 launched, 1990.04.11 (USA 56) to (USA 58). The U. S. military's STACKSAT mission involved the launch of three similar spacecraft, POGS, TEX and SCE.
Space Tracking and Data Acquisition Network (see also STDN)
Stafford, Thomas Patten 'Tom' (1930-) American test pilot astronaut. Flew on Gemini 6, Gemini 9, Apollo 10, Apollo (ASTP). Member of first crew to rendezvous in space. Space speed record (11,107 m/s).
Stahl, Karl German engineer in WW2, member of the Rocket Team in the Soviet Union thereafter. One of the group that fired V-2 rockets at Kapustin Yar in 1946.
Staib, David Paul Jr (1955-) American engineer military spaceflight engineer astronaut, 1985-1988. Left the astronaut corps in July 1988. Later worked at the Pentagon, then at Colorado Springs.
Stainer, Fritz (1897-1969) German Engineer. Engineer, German glider pilot and rocket pioneer.
Stalin, losif Vissarionovich (1879-1953) Georgian-Russian politician. Leader of the Soviet Union, 1924-1953.
Stamer, Friedrich 'Fritz' German pilot of first rocket-boosted glider. Stamer was the first soaring-teacher at the Wasserkuppe, flew the first rocket airplane and constructed a wide range of gliders.
Standard 2 ER.
Popular Name of RIM-67D surface-to-air missile.
Standard 3 ER.
Popular Name of Standard SM-3 anti-ballistic missile.
Standard Missile 2 (ER).
Alternate Designation of RIM-67D surface-to-air missile.
American surface-to-air missile. Extended-range surface-to-air missile for use by AEGIS naval vessels. A version with lower tier anti-missile capability against tactical ballistic missiles was tested but not put into production.
American surface-to-air missile with anti-ballistic missile capability using the LEAP homing vehicle for use by AEGIS naval vessels. Modification for anti-satellite use demonstrated in 2008.
Standard-ER.
American Navy long range surface-to-air missile family. Later versions had anti-ballistic missile and anti-satellite capability.
American Navy long range surface-to-air missile. Later versions have anti-ballistic missile capability.
Standley, Lloyd William (1912-1998) American engineer. Chief of Mechanical Design for the Atlas.
American manufacturer of spacecraft. Stanford University, USA.
Stankiavicius, Rimantas Antanas-Antonovich (1944-1990) Lithuanian test pilot cosmonaut, 1977-1990. Buran Test Pilot, died in crash of a Su-27 fighter at an air show at Treviso, Italy.
Stanley, Wellington J 'Bill' (1916-2002) American engineer. Headed Atlas process engineering and facilities planning.
Stapp, John Paul (1910-1999) American USAF flight surgeon. In 1946-1958 pioneer research with rocket sleds and balloons; defined human tolerances for G-forces, altitude, and blast, essential data for design of aerospacecraft. Personally underwent the most grueling tests.
Thiokol solid rocket engine. 3.353 kN. In Production. Isp=251s. SARV Retro MK I was a small, high-performance motor designed for use as a retrograde rocket for an unmanned satellite vehicle.
Thiokol solid rocket engine family.
Thiokol solid rocket engine. 5.560 kN. In Production. Isp=252s. SARV Retro, MK IV and V was a 60-pound motor using 40 pounds of propellant. It was designed for use as a retrograde rocket for an unmanned satellite vehicle.
Thiokol solid rocket engine. 7.247 kN. In Production. Isp=270s. Super SARV Retro was a longer, higher impulse version of the STAR 12, used as a retrograde rocket for an unmanned satellite vehicle.
Thiokol solid rocket engine family.
Thiokol solid rocket engine. 3.8 kN. Out of Production. Isp=273s. A braking motor used by NASA for the Anchored Interplanetary Monitoring Platform program.
Thiokol solid rocket engine. 5.874 kN. In Production. Isp=286s. Orbit insertion motor incorporated the lightweight titanium case developed for the STAR 13 with the propellant and nozzle design of the earlier TE-M-444 apogee motor.
Thiokol solid rocket engine. 7.6 kN. Out of Production. Isp=285s. Orbit insertion motor incorporated the lightweight case developed for the STAR 13 with the propellant and nozzle design of the earlier TE-M-516 apogee motor.
Thiokol solid rocket engine. Out of Production. Total impulse 8,252 kgf-sec. Motor propellant mass fraction 0.795. Isp=218s.
Thiokol solid rocket engine. Out of Production. Total impulse 7,799 kgf-sec. Motor propellant mass fraction 0.81. Isp=223s.
Thiokol solid rocket engine. Out of Production. Total impulse 6,438 kgf-sec. Motor propellant mass fraction 0.822. Isp=211s.
Thiokol solid rocket engine. Out of Production. Total impulse 9,608 kgf-sec. Motor propellant mass fraction 0.83. Isp=240s.
Thiokol solid rocket engine. Out of Production. Total impulse 11,109 kgf-sec. Motor propellant mass fraction 0.926. Isp=228s.
Thiokol solid rocket engine family.
Solid propellant rocket stage. Loaded/empty mass 124/14 kg. Thrust 19.60 kN. Vacuum specific impulse 280 seconds.
Thiokol solid rocket engine. 10.9 kN. Skynet 1, NATO 1, and IMP-H & J. Out of production. Isp=286s. Used on Atlas LV-3A / Agena D launch vehicle. First flight 1963.
Thiokol solid rocket engine. 16.014 kN. In Production. Isp=286s. Apogee kick motor, modified with 175 mm straight section added to the Star 17. The 17A was used to circularize orbits for the Skynet 1, NATO 1, and IMP-H & J satellites.
Thiokol solid rocket engine family.
Solid rocket stage. 27.14 kN (6,100 lbf) thrust. Mass 301 kg (664 lb).
Thiokol solid rocket engine. 27.135 kN. In Production. Isp=286s. Altair III was developed as the propulsion unit for the fourth stage of the Scout launch vehicle. A filament-wound, fiberglass-epoxy case contained the CTPB propellant grain.
Thiokol solid rocket engine. Out of Production. Total impulse 30,198 kgf-sec. Motor propellant mass fraction 0.934. Isp=234s.
Thiokol solid rocket engine. Out of Production. Total impulse 83,839 kgf-sec. Motor propellant mass fraction 0.91. Isp=291s.
Thiokol solid rocket engine. 24.467 kN. In Production. Isp=289s. Modified version of the STAR 20 with increased case structural capability over the. A filament-wound, fiberglass-epoxy case contained the CTPB propellant grain.
Thiokol solid rocket engine family.
Thiokol solid rocket engine. 20 kN. Skynet 2. In Production. Isp=282s. Apogee boost motor was qualified and flown for the Skynet II, later apogee boost motor for NRL and SAMSO.
Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 50,965 kgf-sec. Motor propellant mass fraction 0.903. Isp=282s.
Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 57,236 kgf-sec. Motor propellant mass fraction 0.915. Isp=282s.
Thiokol solid rocket engine. 21.466 kN. In Production. Isp=282s. Apogee motor designed and qualified for the NASA International Ultraviolet Experiment satellite.
Thiokol solid rocket engine. Out of Production. Total impulse 61,086 kgf-sec. Motor propellant mass fraction 0.917. Isp=240s.
Thiokol solid rocket engine family.
Thiokol solid rocket engine. 39.1 kN. In Production. Upper stage motor used in the Sandia Strypi IV vehicle. Total flown included in total for Star-26C. Total impulse 62,800 kgf-sec. Motor propellant mass fraction 0.86. Isp=271s. First flight 1965.
Solid rocket stage. 34.63 kN (7,784 lbf) thrust. Mass 261 kg (575 lb).
Thiokol solid rocket engine. 34.627 kN. In Production. Isp=271s. Upper stage motor flown on the Burner IIA spacecraft for Boeing and the U.S. Air Force.
Solid rocket stage. 35.00 kN (7,868 lbf) thrust. Mass 264 kg (582 lb).
Thiokol solid rocket engine. 35 kN. In Production. Isp=272s. Upper stage motor used the titanium alloy case and nozzle attachment ring of the STAR 26B design to provide high propellant mass fraction and was insulated for high-spin-rate applications.
Thiokol solid rocket engine family.
Solid rocket stage. 27.00 kN (6,070 lbf) thrust. Mass 361 kg (796 lb).
Thiokol solid rocket engine. 27 kN. Apogee motor used on CTS, GMS, BS, GPS, GOES satellites. In Production. Isp=288s.
Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 89,684 kgf-sec. Motor propellant mass fraction 0.919. Isp=287s.
Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 92,296 kgf-sec. Motor propellant mass fraction 0.921. Isp=288s.
Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 88,555 kgf-sec. Motor propellant mass fraction 0.918. Isp=287s.
Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 88,668 kgf-sec. Motor propellant mass fraction 0.921. Isp=287s.
Thiokol solid rocket engine. In Production. Total impulse 88,301 kgf-sec. Motor propellant mass fraction 0.921. Isp=287s.
Thiokol solid rocket engine family.
Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-30A. Total impulse 136,455 kgf-sec. Motor propellant mass fraction 0.943. Isp=293s.
Thiokol solid rocket engine. Out of Production. Total impulse 137,095 kgf-sec. Motor propellant mass fraction 0.942. Isp=294s.
Thiokol solid rocket engine. Out of Production. Total impulse 148,816 kgf-sec. Motor propellant mass fraction 0.941. Isp=293s.
Thiokol solid rocket engine. 27 kN. In Production. Isp=292s. Apogee motor used for the HS 376 satellite bus. Incorporated an 89-percent-solids HTPB propellant in a 6AI-4V titanium case insulated with silica-filled EPDM rubber.
Thiokol solid rocket engine. 32.6 kN. AS 3000. In Production. Isp=286s. Apogee motor used for the RCA G-STAR and Martin Marietta series 3000 telecom satelllites.
Thiokol solid rocket engine. 35.4 kN. Koreasat. In Production. Isp=290s. Apogee motor used for the BAe Skynet 4 satellite, Koreasat and by the ORBEX small orbital launcher.
Thiokol solid rocket engine. 80 kN. In Production. Isp=293s. Antares III, third-generation third stage for Scout launch vehicle. Propellant: AP/HTPB/Al propellant in a filament wound Kevlar case.
Thiokol solid rocket engine family.
Thiokol solid rocket engine. 43.5 kN. Total impulse 161,512 kgf-sec. Motor propellant mass fraction 0.899. Isp=260s. First flight 1963.
Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. Isp=291s.
Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 718 kg (1,583 lb).
Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 275,959 kgf-sec. Motor propellant mass fraction 0.921. Isp=285s.
Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 1,048 kg (2,310 lb).
Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 718 kg (1,583 lb).
Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. Isp=266s.
Solid rocket stage. 68.00 kN (15,287 lbf) thrust. Mass 1,123 kg (2,476 lb).
Thiokol solid rocket engine. 68 kN. Out of Production. Total impulse 296,635 kgf-sec. Motor propellant mass fraction 0.926. Isp=283s.
Thiokol solid rocket engine. 55.5 kN. Out of Production. Total impulse 249,177 kgf-sec. Motor propellant mass fraction 0.928. Isp=286s.
Solid rocket stage. 55.50 kN (12,477 lbf) thrust. Mass 934 kg (2,059 lb).
Thiokol solid rocket engine. 47.9 kN. In Production. Isp=289s. Apogee kick motor for the FLTSTACOM satellite. The motor case contained the same volume as the discontinued STAR 37E.
Solid rocket stage. 47.90 kN (10,768 lbf) thrust. Mass 1,147 kg (2,529 lb).
Thiokol solid rocket engine. Out of Production. Total impulse 304,620 kgf-sec. Motor propellant mass fraction 0.925. Isp=289s.
Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 623 kg (1,373 lb).
Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 162,102 kgf-sec. Motor propellant mass fraction 0.898. Isp=290s.
Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 190,590 kgf-sec. Motor propellant mass fraction 0.925. Isp=287s.
Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 711 kg (1,567 lb).
Thiokol solid rocket engine. 51.1 kN. Out of Production. Total impulse 310,668 kgf-sec. Motor propellant mass fraction 0.928. Isp=295s.
Thiokol solid rocket engine. 45 kN.
Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 900 kg (1,984 lb).
Thiokol solid rocket engine. 45 kN. Out of Production. Total flown included in total for Star-37XF-8. Total impulse 259,123 kgf-sec. Motor propellant mass fraction 0.929. Isp=290s.
Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 953 kg (2,101 lb).
Thiokol solid rocket engine. Out of Production. Total impulse 238,809 kgf-sec. Motor propellant mass fraction 0.924. Isp=291s.
Thiokol solid rocket engine. 31.5 kN. In Production. Isp=290s. Orbit insertion motor qualified for Global Positioning Satellite. Used as a replacement for the discontinued STAR 37F. Propellant: 884 kg of AP/HTPB/Al in 6Al-4V titanium case.
Solid rocket stage. 31.50 kN (7,081 lbf) thrust. Mass 955 kg (2,105 lb).
Thiokol solid rocket engine. Out of Production. Total impulse 317,856 kgf-sec. Motor propellant mass fraction 0.93. Isp=297s.
Thiokol solid rocket engine. Out of Production. Total impulse 200,882 kgf-sec. Motor propellant mass fraction 0.925. Isp=207s.
Thiokol solid rocket engine family. Used in Delta 3900; Conesotga; PAM-S; PAM-D.
Thiokol solid rocket engine. 67.2 kN. Used in Delta 3900; Conesotga; PAM-S; PAM-D. Total flown included in total for Star-48-8. Total impulse 575,682 kgf-sec. Motor propellant mass fraction 0.946. Isp=286s. First flight 1982.
Thiokol solid rocket engine. Out of Production. Total impulse 587,784 kgf-sec. Motor propellant mass fraction 0.945. Isp=292s.
Thiokol solid rocket engine. In Production. Total impulse 709,062 kgf-sec. Motor propellant mass fraction 0.941. Isp=289s.
Thiokol solid rocket engine. 77.109 kN. In Production. Isp=283s. Short nozzle upper-stage motor designed to fit within the dimensional envelope of the long nozzle.
Thiokol solid rocket engine. 66 kN. In Production. Isp=286s. Long nozzle upper-stage motor qualified for the McDonnell Payload Assist Module (PAM) Delta.
Thiokol solid rocket engine. In Production. Isp=292s. Lengthened version of Star 48B to provide increased payload capability. The design incorporates a longer cylindrical section in the motor case.
Thiokol solid rocket engine. 77.109 kN. In Production. Isp=286s. Short nozzle upper-stage motor qualified for the McDonnell Douglas Payload Assist Module (PAM) Space Transportation System (STS).
Thiokol solid rocket engine. In Production. Developed for Conestoga's upper stage, providing some ±4 degrees capability at 30 degree/sec using the same loaded casing as the 48B. First Flight: 1994.
Solid rocket stage. 68.70 kN (15,444 lbf) thrust. Mass 2,200 kg (4,850 lb).
Thiokol solid rocket engine family.
Thiokol solid rocket engine. Out of Production. Total impulse 405 kgf-sec. Motor propellant mass fraction 0.87. Isp=189s.
Thiokol solid rocket engine. 0.166 kN. In Production. Isp=249s. Space Gnat was designed to provide a minimum acceleration, extended burn delta-V impulse, for small payload replacement or spin-up applications.
Thiokol solid rocket engine. 2.039 kN. Out of Production. Titan Retro designed to separate the second stage from the upper stage of the Titan IV launch vehicle.
Thiokol solid rocket engine. 1.951 kN. In Production. Isp=266s. Titan Retro designed to separate the second stage from the transtage on the Titan II missile and Titan launch vehicle. The motor was also adapted for other uses.
Thiokol solid rocket engine. 2 kN. In Production. Reduced Al HTPB propellant (2.1 kg) minimizes contamination when Used in a Titan 4 stage separation motor. Diameter: 121 mm. Length: 341 mm. Mass: 4.5 kg. Itotal: 5.5 kNs. Burn Time: 2.77 sec.
Thiokol solid rocket engine family.
Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-6A. Total impulse 1,395 kgf-sec. Motor propellant mass fraction 0.795. Isp=287s.
Thiokol solid rocket engine. Out of Production. Total impulse 725,491 kgf-sec. Motor propellant mass fraction 0.94. Isp=294s.
Thiokol solid rocket engine family.
Thiokol solid rocket engine. 107.2 kN. Used in Shuttle,Titan 34D. Isp=282s. Used on Delta 7925 launch vehicle. First flight 1990.
Thiokol solid rocket engine. 84.739 kN. In Production. Isp=283s. Perigee motor with a range of propellant loads, yielding GTO payloads from 3,080 to 4,588 pounds at a constant velocity of 8,012 feet per second.
Thiokol solid rocket engine. 104.627 kN. In Production. Isp=297s. Provided perigee kick for the McDonnell PAM-D2 system. Another version was the Star 63D (TU-936).
Thiokol solid rocket engine. Out of Production. Total impulse 935 kgf-sec. Motor propellant mass fraction 0.723. Isp=285s.
Thiokol solid rocket engine. 2.510 kN. In Production. Isp=273s. Delta-V reentry motor developed as a spin-up and propulsion motor for reentry vehicles. The design incorporated an aluminum case and a plastic nozzle assembly.
Thiokol solid rocket engine. 242.8 kN. In Production. Isp=288s. A demonstration motor tested as a first step in the development of a perigee kick motor in the 4080-7940 kg propellant range.
American communications satellite bus. Operational, first launch 1997.11.12 (Cakrawarta 1). The Orbital Star bus was designed for reliable and robust performance in a variety of LEO and GEO missions.
American military anti-satellite system. Study 1991. In 1991 the Star Lite space laser experiment was made public. Star Lite would weigh half that of the previously planned Zenith Star with a launch mass of 16.
Category of spacecraft.
American test vehicle. Four stage vehicle consisting of 1 x Talos + 1 x Sergeant + 1 x Orbus 1 + 1 x Orbus 1
Solid rocket stage. 88.00 kN (19,783 lbf) thrust. Mass 500 kg (1,102 lb).
British manned spacecraft. Study 2004. X-Prize suborbital ballistic spacecraft concept of Starchaser Industries, Cheshire, England. The concept used a rocket powered vertical takeoff followed by a parachute descent to land.
British manufacturer of spacecraft. Starchaser Industries, UK.
Starclipper.
Alternate designation for Shuttle LS200 winged orbital launch vehicle.
American winged orbital launch vehicle. Lockheed ILRV design created for the USAF in 1966. X-24B lifting body configuration orbiter with linear aerospike engine and wrap-around drop tank. Related to Lockheed Shuttle LS200 proposal.
American winged orbital launch vehicle. Downsized version of the Starclipper, equipped with conventional bell nozzle engines, released by NASA for public consumption in 1968.
American comet probe. One launch, 1999.02.07. Stardust was scheduled to encounter comet Wild-2 early in 2004 and collect samples of cometary dust and volatiles while flying through the coma at a distance of 100 km on the sunlit side of the nucleus.
American earth magnetosphere satellite. 2 launches, 1962.10.26 (Starfish Radiation 1) and 1965.09.02 (Starfish Radiation 2). Satellite collected artificial radiation data (resulting from atmospheric and exoatmospheric nuclear explosions).
American earth magnetosphere satellite. 2 launches, 1964.06.13 (Starflash 1A) and 1964.08.21 (Starflash 1B). Sub-satellite of unknown purpose, released from KH-5 photo reconnaisance satellites on two missions.
French winged orbital launch vehicle. Mach 6 hypersonic first stage would launch Hermes spaceplane with an expendable second stage.
French earth geodetic satellite. One launch, 1975.02.06. Geodesic satellite.
Starlifter.
Alternate designation for Shuttle LS200-1 rocket stage.
Starlifter.
Alternate designation for Starclipper Light and Starclipper winged orbital launch vehicle.
Lox/LH2 propellant rocket stage. Loaded/empty mass 42,630/19,955 kg. Thrust 5,217.00 kN. Vacuum specific impulse 455 seconds.
Lox/LH2 rocket stage. Mass 257,778 kg (568,303 lb).
American winged orbital launch vehicle. Rockwell International's Star-raker was an enormous 1979 heavy-lift ramjet/rocket horizontal takeoff/horizontal landing single-stage-to-orbit concept capable of atmospheric cruise and powered landing for maximum operational flexibility.
American test vehicle. Three stage target vehicle for anti-ballistic missile tests, consisting of a surplus Polaris A3 SLBM (A3P first stage + X-260 second stage) and an Orbus 1 third stage.
Solid rocket stage. Mass 4,900 kg (10,803 lb).
French agency. Starsem SA, Paris, France.
American technology satellite. 2 launches, 1999.05.27 (Starshine) and 2001.09.30 (Starshine 3). The small Starshine satellite, built by NRL, was to be observed by students as part of an educational exercise.
American manufacturer of rocket engines. Starstruck Incorporated, USA.
Strategic Arms Reduction Treaty
Russian communications technology satellite. One launch, 1993.03.25. Experimental satellite carried on test flight of the Start-1 carrier rocket, a new booster based on SS-25 ICBM.
Russian orbital launch vehicle. Launch vehicle based on decommissioned SS-25 ICBM's (differs from ICBM/basic Start-1 in having second stage used twice, in tandem, for increased payload). Launched from mobile transporter. Liftoff mass 60 tonnes.
Russian orbital launch vehicle. Launch vehicle based on decommissioned ICBM's. Launched from mobile transporter. Liftoff mass 47 tonnes.
Solid propellant rocket stage. Loaded/empty mass 26,000/3,000 kg. Thrust 980.00 kN. Vacuum specific impulse 263 seconds. All estimated
Russian orbital launch vehicle.
Solid propellant rocket stage. Loaded/empty mass 13,000/1,500 kg. Thrust 490.00 kN. Vacuum specific impulse 280 seconds. All estimated except stage gross mass
Solid rocket stage. Mass 500 kg (1,102 lb).
Statsenko, Igor Demyanovich (1918-1987) Russian officer. Major General, Commander of the KIK space tracking forces 1971-1975. After service in WW2, ascending positions in antiaircraft forces. Moved to RVSN in 1961.
STC.
American manufacturer of spacecraft. STC, USA.
American manned Mars expedition. Study 1991. The STCAEM cryogenic / aerobrake (CAB) concept was used as the NASA reference vehicle.
STCAEM Cryogenic AeroBrake MTV.
American manned Mars orbiter. Study 1991. The Mars Transfer Vehicle (MTV) configuration consisted of a transit habitat sized for four crew, an aerobrake, and a TEl Propulsion system.
STCAEM Cryogenic AeroBrake TMIS.
American space tug. Study 1991. The Trans-Mars Injection Stage (TMIS) consisted of a core unit with four advanced space engines (ASE), avionics and cryogenic propellant tanks, and provision for up to four "strap-on" propellant tank sets.
American manned Mars lander. Study 1991. The reference Mars Excursion vehicle (MEV) was a manned lander that could transport a crew of four to the surface.
American manned Mars expedition. Study 1991.
American manned Mars expedition. Study 1991.
American manned Mars expedition. Study 1991. The solar electric propulsion (SEP) Mars transfer concept was the only non-nuclear advanced propulsion option in the STCAEM study.
STDN.
Spacecraft Tracking and Data Network (formerly STADAN)
Steadman, Bernice Trimble (1923-) American pilot, winner of many awards and races, one of the Mercury 13 female astroauts proposed in 1961, but never entered training.
Steam rockets used water, heated by an external source prior to launch and stored under pressure, to provide thrust. The heavy pressure vessel means use is usually confined to ground-based reusable applications, such as launch sleds.
Stearns, Edward V (1922-2001) American physicist, with Rand 1949-1954; assistant Chief Engineer, Lockheed Missile and Space, after 1954.
Stechkin, Boris Sergeyevich (1891-1969) Russian engineer. Chief Designer 1955-1969 of OKB Fakel. At the Academy of Sciences performed attitude control engine work.
Russian manufacturer of rocket engines. Stechkin Design Bureau, Russia.
The small STEDI (Student Explorer Demonstration Initiative) program was also known as the University Explorer (UNEX) series. First launch was the HETE astronomy satellite built by the Massachusetts Institute of Technology. This was followed by SNOE, the Student Nitric Oxide Explorer, built by the University of Colorado.
Stefanyshyn-Piper, Heidemarie Martha (1963-) American engineer mission specialist astronaut, 1996-2009. Flew on STS-115, STS-126. Engineer.
Stein, Joseph A (1912-) American journalist and public information manager at NASA 1955-on.
Steinhoff, Ernst August Wilhelm (1908-1987) Austrian-German engineer in WW2, member of the Rocket Team in the United States thereafter.
Steinhoff, Friedrich (1909-1945) German Kriegsmarine Officer, commander of submarine of U-511 and U-873, brother of Dr. Ernst Steinhoff. Promoted the idea of missile launch from submarines within the German navy during World War II.
Steklov, Vladimir Aleksandrovich (1949-) Russian actor cosmonaut, 1997-2000.
French earth geodetic satellite. One launch, 1993.09.26. Laser reflectors.
French agency. Stellat, France.
Stellenbosch University, Cape Town, South Africa
South African manufacturer of spacecraft. Stellenbosch University, Cape Town, South Africa.
Stelzner, Armin German expert in guided missiles during World War II. As of January 1947, working "c/o Klinger", British Zone.
American technology satellite. One launch, 2000.01.27. Picosat built by built by the AMSAT-NA (Amateur Satellite, North America) group, and carried an amateur radio transponder.
American manufacturer of spacecraft. STENSAT, Washington DC, Washington, DC, USA.
STEP.
American technology satellite. 2 launches, 1995.06.22 (STEP 3) and 2000.06.07 (TSX 5).
STEP.
Space Test Experiment Program; series of USAF technology test satellites.
Russian manufacturer of rocket engines. Stepanov Design Bureau, Russia.
Stepanov, Gherman Vasilyevich (1934-) Russian officer. Major General, Deputy Commander of 50 TsNII KS military space research institute 1983-1988.
Stepanov N2O4/UDMH rocket engine. 10 N. IS/US. Out of Production.
Stepanov N2O4/UDMH rocket engine. 0.157 kN. IS/US. Out of Production.
Stepanov N2O4/UDMH rocket engine. 0.098 kN. LK/LOK attitude. Out of Production.
Stepanov N2O4/UDMH rocket engine. 0.390 kN. LK/LOK attitude. Out of Production.
Stepanov, Eduard Nikolayevich (1937-) Russian engineer cosmonaut, 1965-1992.
Stepanov, Yuri Nikolayevich (1936-) Russian engineer cosmonaut, 1985-1996.
Stephens, Robert American test pilot. Flew the X-1B.
American solar satellite. 2 launched, 2006.10.26 (Stereo Ahead) and (Stereo Behind).
Steurer, Wolfgang Hermann (1913-1986) Austrian-German engineer in WW2, member of the Rocket Team in the United States thereafter.
British manufacturer. Stevenage, Stevenage, UK.
Stevenson, Robert Everett (1921-2001) American oceanographer payload specialist astronaut, 1984-1984.
Stever, Horton Guyford (1916-) American physicist, led numerous US government committees, advisory positions, and panels on science policy from 1947-1986.
Stewart, Robert Lee (1954-) American test pilot mission specialist astronaut. Flew on STS-41-B, STS-51-J.
Stewart, Homer J (1915-) American engineer, worked on rocketry and robotic space exploration at Caltech, JPL, and NASA 1938-1967.
STEX.
American tether technology satellite. One launch, 1998.10.03. STEX's (Space Technology EXperiments) main equipment was provided by the Naval Research Laboratory.
STG.
Space Task Group
Stilleto.
Stingray.
STIS.
Space Telescope Imaging Spectrometer (to replace FOC and GHRS)
STL.
Space Technology Laboratories
STLC.
American agency. STLC, USA.
STME.
Rocketdyne lox/lh2 rocket engine. 2890 kN. Cancelled 1984. Isp=430s. Space Transportation Main Engine. Rocketdyne was teamed with Aerojet and Pratt & Whitney on the STME, which was to have powered the next generation of large launch vehicles.
Stoerk German rocket engineer in WW2; later worked in France in the engine group at LRBA from 1947 until retiring in 1971.
STOL.
Short takeoff and landing aircraft
Stolpe, Felix (1908-) German telemetry engineer in WW2, worked afterwards in the Soviet Union. One of the group that fired V-2 rockets at Kapustin Yar in 1946.
Stone.
ASCC Reporting Name of Iskander short range ballistic missile.