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American manned rescue spacecraft. Study 1960. One crew ballistic re-entry capsule. Orbital escape - no abort capability. Mass per crew 327 kg.
American manned rescue spacecraft. Study 1959. One crew lifeboat capsule, separable, not re-entry capable, short duration. Mass per crew 266 kg.
American manned rescue spacecraft. Study 1959. One crew lifeboat capsule, separable, not re-entry capable, long duration. For use on Mars/Venus expedition.
Thiokol solid rocket engine. 156 kN.
Multiple-source American solid rocket engine. 35 kN.
American manned rescue spacecraft. Study 1963. Ten crew emergency shelter capsule, not separable, not re-entry capable, long duration. Mass per crew 301 kg.
Solid propellant rocket stage. Loaded/empty mass 115,350/12,000 kg. Thrust 3,330.00 kN. Vacuum specific impulse 260 seconds. Three-segment solid motor proposed for the Solid Titan II in the SLV-4 competition. Aerojet test fired motors with up to five segments, producing an average thrust of 268,000 kgf for 120 seconds.
105-KS-45,220.
Alternate designation for Star 75 Solid rocket engine.
10Kh.
Chelomei mobile-launched short range cruise missile derived from the German V-1. Did not reach production.
10Kh.
Chelomei developed a series of cruise missiles derived from the German V-1, none of which reached production.
10KhN.
Manufacturer's designation for 10Kh short range cruise missile.
118-KS-19,050.
Alternate designation for Star 63D Solid rocket engine.
11A510.
Article Number of Vostok 11A510 orbital launch vehicle.
11A511.
Article Number of Soyuz 11A511 orbital launch vehicle.
11A511L.
Article Number of Soyuz 11A511L orbital launch vehicle.
11A511M.
Article Number of the Soyuz 11A511M orbital launch vehicle. Reapplied 40 years later to the Soyuz M orbital launch vehicle.
11A511U.
Article Number of Soyuz 11A511U orbital launch vehicle.
11A511U2.
Article Number of Soyuz 11A511U2 orbital launch vehicle.
Russian intercontinental ballistic missile. FOBS version. Warhead accuracy 5 km along orbital track, 3 km to either side. OKB-1 estimated warhead would be detected by Western defences only two minutes before it detonated. The designation SS-10 was assigned by the DOD to the UR-200, but was commonly and erroneously applied to the GR-1, which was shown publicly after its cancellation.
11A514.
Article Number of Soyuz 11A514 orbital launch vehicle.
11A52.
11A53.
11A54.
Article Number of N111 heavy-lift orbital launch vehicle.
11A57.
Article Number of Voskhod 11A57 orbital launch vehicle.
11A59.
Article Number of Sputnik 11A59 orbital launch vehicle.
11B91.
Government designation of RD-0410 Nuclear-LH2 rocket engine.
Korolev nuclear electric/xenon rocket engine. 450 mN. Engine for Interorbital Tug for launch by Energia. Developed 1978-1986. Isp=3000s. Powered by nuclear reactor providing 50-150 kWt for 3 to 5 years operation.
11D111.
Government designation of NK-33 Lox-Kerosene rocket engine.
11D112.
Government designation of NK-43 Lox-Kerosene rocket engine.
11D113.
Government designation of NK-39 Lox-Kerosene rocket engine.
11D114.
Government designation of NK-31 Lox-Kerosene rocket engine.
11D119.
Government designation of RD-264 N2O4-UDMH rocket engine.
Korolev GOX/Kerosene rocket engine. 68.650 kN. N-1 stage 1 (block A) roll control engine. Developed 1969-74. Gimbaling +/- 45 degree. Propellants are fed from main engine (NK-15, NK-33) turbopumps. Isp=313s. Chamber Pressure: 71.60 bar.
11D122.
Government designation of RD-0120 Lox-LH2 rocket engine.
11D122A.
Government designation of RD-0120M Lox-LH2 rocket engine.
11D123.
Article Number of RD-120 Lox-Kerosene rocket engine. Also applied to the RD-134R and RD-146 variants.
11D130F.
Article Number of RD-302 LF2-Ammonia rocket engine.
11D14.
Article Number of the RD-303 LF2-Ammonia rocket engine.
Kosberg N2O4/UDMH rocket engine. 230.5 kN. Study 1968. Engine used in Block 1 and Block 11 stages of LK-700 manned lunar lander.
11D24.
Government designation of RD-0225 N2O4-UDMH rocket engine.
11D25.
Government designation of RD-861 N2O4-UDMH rocket engine.
11D25G.
Government designation of RD-861G N2O4-UDMH rocket engine.
11D26.
Alternate designation for RD-219 Nitric acid-UDMH rocket engine.
11D33.
Government designation of S1.5400 Lox-Kerosene rocket engine.
11D33M.
Government designation of S1.5400A Lox-Kerosene rocket engine.
11D414.
Government designation of KDU-414 Nitric acid-UDMH rocket engine.
Isayev N2O4/UDMH rocket engine. 16.4 kN. Study 1968. Three of these engines used for midcourse corrections and soft lunar landing in Block 11 and Block 1V stages of LK-700 manned spacecraft.
11D417.
Government designation of KTDU-417 Nitric acid-UDMH rocket engine.
11D417B.
Government designation of KTDU-417-B N2O4-UDMH rocket engine.
Izotov N2O4/UDMH rocket engine. 134 kN. LK-700S manned lunar lander ascent stage engine. Development ended 1968. Isp=326s. Based UR-100 stage 2 engine. Gas generator cycle; 2 large turbine exhaust pipes.
11D425.
Government designation of KTDU-425 N2O4-UDMH rocket engine.
11D425A.
Government designation of KTDU-425A N2O4-UDMH rocket engine.
11D426.
Government designation of KDU-426 N2O4-UDMH rocket engine.
Melnikov N2O4/UDMH rocket engine. 0.110 kN. Yantar-2K orbital propulsion. In Production. Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions.
Glushko N2O4/UDMH rocket engine. 1642 kN. Developed 1960-64. Isp=316s. Low-expansion ratio gimbaled variant for Proton stage 1 concept. Configuration 4 x 8D43 clustered with 4 x 11D43 abandoned in favor of 6 x Glushko 11D48 in final Proton design.
Melnikov N2O4/UDMH rocket engine. 29.430 kN. Yantar-2K orbital propulsion. In Production. Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 50 ignitions. Isp=307s. Chamber Pressure: 9.00 bar.
Melnikov N2O4/UDMH rocket engine. 6 N. Yantar-2K orbital propulsion. In Production. Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 150,000 ignitions.
11D442.
Government designation of KRD-442 N2O4-UDMH rocket engine.
Melnikov N2O4/UDMH rocket engine. 0.065 kN. Yantar-2K descent propulsion. In Production. Propulsion system of the Yantar-2K military satellite descent capsule. Up to 10,000 ignitions. Thrust from 0,065 - 0,012 kN.
Melnikov N2O4/UDMH rocket engine. 0.052 kN. Yantar-2K orbital propulsion. In Production. Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions.
Isayev N2O4/UDMH rocket engine. 0.392 kN. In Production. Isp=252s. Small attitude control thruster in Briz upper stage propulsion system S5.98M. Total summmary impulse 14,112 kg-s. Minimum impulse 4 kg-s. Specific impulse also reported as 275 sec.
11D48.
Government designation of RD-253-11D48 N2O4-UDMH rocket engine.
Isayev Nitric acid/UDMH rocket engine. 157.5 kN. Kosmos-3M stage 2. Engine has one main and four steering nozzles. Thrust 157.5 + 4 x 25 kN. Precessor was 11D47 in R-14 (derivative ?) stage 2. Isp=303s. First flight 1964.
11D51.
Government designation of NK-15 Lox-Kerosene rocket engine.
11D511.
Government designation of RD-107-11D511 Lox-Kerosene rocket engine.
11D511P.
Government designation of RD-107-11D511P Lox-Kerosene rocket engine.
11D511PF.
Government designation of RD-117PF Lox-Kerosene rocket engine.
11D512.
Government designation of RD-108-11D512 Lox-Kerosene rocket engine.
11D512P.
Government designation of RD-108-11D512P Lox-Kerosene rocket engine.
11D513.
Government designation of RD-8 Lox-Kerosene rocket engine.
Kuznetsov Lox/Kerosene rocket engine. 1918 kN. N1F 1965 - A. Study 1965. As described in N1 improvement study, 1965. Block A engine thrust increased. Isp=331s.
Kuznetsov Lox/Kerosene rocket engine. 2843 kN. N1M 1965 - A. Study 1965. As described in N1 improvement study, 1965. Huge modification of Block A engines - sea level thrust increased from 175 tonnes thrust to 250 tonnes. Isp=346s.
11D520.
Government designation of RD-170 Lox-Kerosene rocket engine.
11D521.
Government designation of RD-171 Lox-Kerosene rocket engine.
Kuznetsov Lox/Kerosene rocket engine. 1961 kN. N1F 1965 - B. Study 1965. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t. Isp=347s.
Kuznetsov Lox/Kerosene rocket engine. 2745 kN. N1M 1965 - B. Study 1965. As per N1 improvement study, 1965. Thrust increased to 280 tonnes per engine. Isp=330s.
11D52V.
Government designation of NK-15V Lox-Kerosene rocket engine.
11D52VM.
Government designation of NK-15VM Lox-LH2 rocket engine.
11D53.
Article Number of the NK-9V-11D53 Lox-Kerosene rocket engine and its NK-21 and NK-9V variants .
Kuznetsov Lox/Kerosene rocket engine. 612 kN. N1F 1965 - V. Study 1965. As per N1 improvement study, 1965. Engine thrust increased and stretched propellant tanks resulting in 20% longer burn time. Isp=346s.
Kuznetsov Lox/Kerosene rocket engine. 735 kN. N1M 1965 - V. Study 1965. As per N1 improvement study, 1965. Further increase in thrust of Block V engines. Isp=347s. Used on N-IM 1965 launch vehicle.
11D54.
Article Number of the NK-9V-11D54 and NK-19 Lox-Kerosene rocket engine. Reused for the RD-54 Lox-LH2 rocket engine.
11D55.
Government designation of RD-0110 Lox-Kerosene rocket engine.
11D56.
Government designation of RD-56 Lox-LH2 rocket engine.
11D56M.
Government designation of RD-56M Lox-LH2 rocket engine.
11D57.
Government designation of RD-57 Lox-LH2 rocket engine.
11D57M.
Government designation of RD-57M Lox-LH2 rocket engine.
11D58.
Government designation of RD-58 Lox-Kerosene rocket engine.
11D58M.
Government designation of RD-58M Lox-Kerosene rocket engine.
11D58MF.
Government designation of RD-58MF Lox-Kerosene rocket engine.
11D58S.
Government designation of RD-58S Lox-Kerosene rocket engine.
11D58Z.
Government designation of RD-58Z Lox-Kerosene rocket engine.
11D614.
Government designation of RD-216 Nitric acid-UDMH rocket engine.
11D62.
Government designation of KTDU-35 Nitric acid-UDMH rocket engine.
11D68.
Government designation of S5.51 N2O4-UDMH rocket engine.
11D69.
Alternate designation for RD-218 Nitric acid-UDMH rocket engine.
Stepanov N2O4/UDMH rocket engine. 44 kN. Blok D SOZ. In Production. Thrust 1.1-4.5 tf variable.
11F35.
Article Number of Buran manned spaceplane.
11F36.
Article Number of Energia-Buran manned spaceplane.
11F37.
Article Number of Kvant manned space station.
11F61.
Article Number of Zenit-2 military surveillance satellite.
11F610.
Russian military satellite. Unknown mission.
11F614.
Article Number of Meteor M earth weather satellite.
11F615.
Article Number of Soyuz 7K-OK and Soyuz Kontakt manned spacecraft.
11F615A12.
Article Number of Soyuz 7K-TM manned spacecraft.
11F615A15.
Article Number of Progress logistics spacecraft.
11F615A55.
Article Number of Progress M logistics spacecraft.
11F615A75.
Alternate designation for Progress M2 logistics spacecraft.
11F615A77.
Article Number of Progress M2 logistics spacecraft.
11F615A8.
Article Number of Soyuz 7K-T manned spacecraft.
11F615A9.
Article Number of Soyuz 7K-T-A9 manned spacecraft.
11F616.
Article Number of Tselina-O military naval signals reconnaisance satellite.
11F617.
Article Number of Tsiklon navigation satellite and Tselina-OM military naval signals reconnaisance satellite.
11F618.
Article Number of DS-P1-Yu military target satellite.
11F619.
Article Number of Tselina-D military naval signals reconnaisance satellite.
11F620.
Article Number of DS-P1-I military target satellite.
11F621.
Article Number of Sfera earth geodetic satellite.
11F622.
11F624.
Article Number of Yantar-2K military surveillance satellite.
11F625.
Article Number of Svetoch military communications satellite.
11F626.
Article Number of Forpost military communications satellite.
11F627.
Article Number of Parus navigation satellite.
11F628.
Article Number of Molniya-2 communications satellite.
11F629.
Article Number of Zenit-4MT military surveillance satellite.
11F630.
Article Number of Yantar-1KF military surveillance satellite.
11F631.
Article Number of Tyulpan military anti-satellite system target satellite.
11F632.
Article Number of Meteor-2 earth weather satellite.
11F633.
Article Number of Taifun-1 military target satellite.
11F634.
Article Number of Romb military target satellite.
11F635.
Article Number of Zenit-4MKT military surveillance satellite.
11F637.
Article Number of Molniya-3 communications satellite.
11F638.
Article Number of Raduga communications satellite.
11F639.
Article Number of Ekspress communications satellite.
11F642.
Article Number of Yantar-2K-M military surveillance satellite.
11F643.
Article Number of Tsikada navigation satellite.
11F644.
Article Number of Tselina-2 military naval signals reconnaisance satellite.
11F645.
Article Number of Zenit-6U military surveillance satellite.
11F647.
Article Number of Ekran communications satellite.
11F647M.
Article Number of Ekran-M communications satellite.
11F649.
Article Number of Yantar-3KF military surveillance satellite.
11F650.
Article Number of Yantar-6K military surveillance satellite.
11F651.
Article Number of Resurs-OE earth land resources satellite.
11F652.
Article Number of Elektro earth weather satellite.
11F653.
Article Number of Astrofizika earth geodetic satellite.
11F654.
Article Number of Glonass navigation satellite.
11F658.
Article Number of Molniya-1T military communications satellite.
11F660.
Article Number of Yantar-1KFT military surveillance satellite.
11F661.
Article Number of Yantar-6KS military surveillance satellite.
11F662.
Article Number of Gorizont communications satellite.
11F663.
Article Number of Potok military communications satellite.
11F664.
Article Number of Arkon-1 military surveillance satellite.
11F666.
Article Number of Geo-IK earth geodetic satellite.
11F668.
Article Number of Almaz-T civilian surveillance radar satellite.
11F669.
Article Number of Luch military communications satellite.
11F67.
Article Number of Molniya-1 military communications satellite.
11F69.
Article Number of Zenit-4 military surveillance satellite.
11F690.
Article Number of Zenit-2M military surveillance satellite.
11F691.
Article Number of Zenit-4M military surveillance satellite.
11F692M.
Article Number of Zenit-4MK and Zenit-4MKM military surveillance satellite.
11F693.
Article Number of Yantar-4K1 military surveillance satellite.
11F694.
Article Number of Yantar-4KS1 military surveillance satellite.
11F695.
Article Number of Yantar-4K2 military surveillance satellite.
11F697.
Article Number of Resurs-O1 earth land resources satellite.
11F71.
Article Number of the Soyuz R, Soyuz PPK, and Soyuz P manned combat spacecraft. Reused for the Almaz, Almaz OPS, and Almaz OPS-2 manned space stations to the same requirement.
11F71+111F74.
Article Number of Almaz APOS manned space station.
11F715.
11F72.
Article Number of TKS manned spacecraft.
11F73.
Article Number of the Soyuz VI manned combat spacecraft and replacment OPS + TKS manned space station.
11F732.
Article Number of the Soyuz 7K-S manned spacecraft and its follow-ons, the Soyuz T, Soyuz TM, and Soyuz TMA.
Russian military satellite. Unknown mission.
11F76.
Article Number of KSI logistics spacecraft.
11F77.
Article Number of Mir Modules-FGB manned space station.
11F77D.
Article Number of Kvant-2 manned space station.
11F77I.
Article Number of Priroda manned space station.
11F77O.
Article Number of Spektr manned space station.
11F77T.
Article Number of Kristall manned space station.
11F91.
Article Number of Soyuz 7K-L1 manned lunar flyby spacecraft.
11F92.
Article Number of Soyuz 7K-L1A manned lunar orbiter.
11F93.
Article Number of Soyuz 7K-LOK manned lunar orbiter.
11F94.
Article Number of LK manned lunar lander.
11K.
Manufacturer's designation for Soyuz V logistics spacecraft.
11K25.
Article Number of Energia winged orbital launch vehicle.
11K54.
Complex of N111 heavy-lift orbital launch vehicle.
11K55.
Article Number of Soyuz 11K55 orbital launch vehicle.
11K56.
Article Number of Soyuz 11K56 orbital launch vehicle.
11K63.
Article Number of Kosmos 11K63 orbital launch vehicle.
11K64.
Article Number of 64S5 intercontinental ballistic missile.
11K65.
Article Number of Kosmos 11K65 orbital launch vehicle.
11K65M.
Article Number of Kosmos 11K65M orbital launch vehicle.
11K67.
Article Number of Tsiklon-2A orbital launch vehicle.
11K68.
Article Number of Tsiklon-3 orbital launch vehicle.
11K69.
Article Number of Tsiklon-2 orbital launch vehicle.
11K77.
Article Number of Zenit-2 orbital launch vehicle.
11S510.
Alternate designation for Soyuz 11A511-2 rocket stage.
11S59 Block D.
Alternate designation for Soyuz 11A511-1 rocket stage.
11S59 Blocks A,B,V,G.
Alternate designation for Soyuz 11A511-0 rocket stage.
11S681.
Alternate designation for Tsyklon 2-1 rocket stage.
11S682.
Alternate designation for Tsyklon 2-2 rocket stage.
11S691.
Alternate designation for Tsyklon 3-1 rocket stage.
11S692.
Alternate designation for Tsyklon 3-2 rocket stage.
11S693; S5M.
Alternate designation for Tsyklon 3-3 rocket stage.
11S824.
Article number of Proton 11S824 rocket stage.
11S824F.
Article number of Proton 11S824F rocket stage.
11S824M.
Article number of Proton 11S824M rocket stage.
120-KS-23,520.
Alternate designation for Star 63F Solid rocket engine.
12KS.
Manufacturer's designation for Bion biology satellite.
Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 300 kg (661 lb).
Bristol solid rocket engine. 45 kN.
13KS.
Manufacturer's designation for Energia sattelite.
14.8-KS-1,708.
Alternate designation for Star 13B Solid rocket engine.
14D14.
Government designation of RD-253-14D14 N2O4-UDMH rocket engine.
14D23.
Article number of RD-0124 and RD-0124-14D23 Lox-Kerosene rocket engines.
14D30.
Government designation of S5.98M N2O4-UDMH rocket engine.
14D451M.
Government designation of RD-0124 Lox-Kerosene rocket engine.
14F10.
Article Number of IS-MU military anti-satellite system.
14F33.
Article Number of LO manned space station.
14F40.
Article Number of Resurs F1-14F40 earth land resources satellite.
14F43.
Article Number of Resurs F1-14F43 earth land resources satellite.
14F70.
Article Number of Zarya satellite.
15.3-KS-1,320.
Alternate designation for Star 13A Solid rocket engine.
15A10.
15A11.
Article Number of Perimetr 15A11 strategic communications missile.
15A14.
Article Number of R-36M intercontinental ballistic missile.
15A15.
Article Number of MR-UR-100 intercontinental ballistic missile.
15A16.
Article Number of MR-UR-100U 15A16 intercontinental ballistic missile.
15A18.
Article Number of R-36MU 15A18 intercontinental ballistic missile.
15A18M2.
Article Number of R-36M2 15A18M intercontinental ballistic missile and Dnepr space launch vehicle.
15A20.
Article Number of UR-100K intercontinental ballistic missile.
15A20U.
Article Number of UR-100U intercontinental ballistic missile.
15A30.
Article Number of UR-100N intercontinental ballistic missile and Strela and Rokot space launch vehicles.
15A35.
Article Number of UR-100NU intercontinental ballistic missile.
15B86.
Standard RV of R-36M intercontinental ballistic missile.
15D12.
Government designation of RD-857 N2O4-UDMH rocket engine.
15D13.
Article Number of 8D423 N2O4-UDMH rocket engine.
Klimov N2O4/UDMH rocket engine. 131.4 kN. Study 1968. Main engine for midcourse Block 1V ascent/trans-earth injection stage of LK-700 manned spacecraft. See also 11D423.
Solid propellant rocket stage. Loaded/empty mass 19,150/2,450 kg. Thrust 647.00 kN. Vacuum specific impulse 260 seconds. Four nozzles. Length with interstage 9.8 m. Sea level thrust 60,000 kgf. Specific impulse estimated.
NII-125 solid rocket engine. Combined missile (RT-20P) stage 1. Out of production. Launch thrust 588 kN. Designed for first stage of combined missile and SLBM; flight tested, no production. First flight 1967.
15D169.
Article Number of RD-862 N2O4-UDMH rocket engine.
Yuzhnoye solid rocket engine. 142 kN.
15D2.
Yuzhnoye solid rocket engine. RT-23 early models stage I. Out of Production. The case-bound T9-BK composite solid propellant charge had a star shape channel. The case was of organic fibre-wound plastic material.
Solid rocket stage. 893.00 kN (200,754 lbf) thrust. Mass 34,600 kg (76,280 lb).
KBMash solid rocket engine. 892 kN. RT-2 Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. Chamber pressure 40 kgf/cm2.
Solid rocket stage. 980.00 kN (220,313 lbf) thrust. Mass 34,550 kg (76,170 lb).
TsKB-7 solid rocket engine. 980 kN. RT-2P Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 56 kgf/cm2.
TsKB-7 solid rocket engine. 431 kN. RT-2 Stage 2. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. Chamber pressure 40 kgf/cm2. Average thrust 33 tonnes.
Solid rocket stage. 432.00 kN (97,117 lbf) thrust. Mass 9,600 kg (21,164 lb).
TsKB-7 solid rocket engine. 437.3 kN. RT-2P Stage 2. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 48 kgf/cm2.
KBMash solid rocket engine. 137 kN. RT-2 Stage 3. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant.
Solid rocket stage. 215.00 kN (48,334 lbf) thrust. Mass 3,500 kg (7,716 lb).
Arsenal solid rocket engine. 432 kN.
Solid rocket stage. 432.00 kN (97,117 lbf) thrust. Mass 11,300 kg (24,912 lb).
Yuzhnoye, Tsurilnikov solid rocket engine. RT-23 stage I. Out of Production. Case-bound OPAL composite solid propellant charge with a star shape channel. The case was of organic fibre-wound plastic material.
Solid propellant rocket stage. Loaded mass 25,000 kg. Thrust 1,050.00 kN.
Yuzhnoye. Tsurilnikov solid rocket engine. RT-23 stage II. Out of Production. The case-bound START composite solid propellant charge had a cylindrical-conical umbrella shape channel. The case was of organic fibre-wound plastic material.
TsKB-7 solid rocket engine. 180.4 kN. RT-2P Stage 3. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 48 kgf/cm2.
Solid rocket stage. 180.40 kN (40,556 lbf) thrust. Mass 4,640 kg (10,229 lb).
15D95.
Government designation of RD-0232 N2O4-UDMH rocket engine.
15F1.
Standard RV of RT-2 intercontinental ballistic missile.
15F173.
Standard RV of R-36M2 15A18M intercontinental ballistic missile.
15F183.
Standard RV of R-36MU 15A18 intercontinental ballistic missile.
15F842.
Standard RV of UR-100 and UR-100M SLBM intercontinental ballistic missiles.
Bristol solid rocket engine. 111 kN.
Solid rocket stage. 111.00 kN (24,954 lbf) thrust. Mass 1,000 kg (2,205 lb).
15P015.
Launch System of MR-UR-100 intercontinental ballistic missile.
15P016.
Launch System of MR-UR-100U 15A16 intercontinental ballistic missile.
15P020.
Launch System of UR-100U intercontinental ballistic missile.
15P030.
Launch System of UR-100N missile.
15P035.
Launch System of UR-100NU intercontinental ballistic missile.
15P084.
Launch System of UR-100M missile.
15P098.
Launch System of RT-2 intercontinental ballistic missile.
15P098P.
Launch System of RT-2P intercontinental ballistic missile.
15P696.
Launch System of RT-15 intermediate range ballistic missile.
15P784.
15P884.
Launch System of UR-100K intercontinental ballistic missile.
15Zh41.
Article Number of RT-21 intercontinental ballistic missile.
15Zh42.
Article Number of Temp-2S intercontinental ballistic missile.
15Zh44.
Article Number of RT-23 15Zh44 intercontinental ballistic missile.
Russian intermediate range ballistic missile. The missile was given a different DOD mod designation according to the number of warheads - Mod 1 for the single warhead version, Mod 2 for the triple warhead version.
Russian intermediate range ballistic missile. The UTTKh model featured improved accuracy, range, and MIRV dispersal spread. It was not given a separate DoD 'mod' number.
15Zh52.
Article Number of RT-23 15Zh52 intercontinental ballistic missile.
Russian intermediate range ballistic missile. Development of a modernised version of the 15Zh45 IRBM began at the beginning of the 1980's. Flight trials either began in 1985 or were cancelled prior to their planned start in 1986. In 1988 the project was cancelled following the signature of the INF Treaty that banned intermediate range ballistic missiles. The missile (known to the Pentagon as both the SS-20 Mod 3 and the SS-28) would have had a range of 7500 km with a single warhead, or 5500 km with multiple warheads.
Compared to the Pioner-U it used a larger launch container, a larger MIRV bus with greater accuracy. The KB Minsk Auto Factory developed a lighter, more comfortable crew cabin - important on constant field deployments.
15Zh58.
Article Number of Topol intercontinental ballistic missile, and Start and Start-1 orbital launch vehicles.
MITT solid rocket engine. 980 kN.
MITT solid rocket engine. 490 kN.
MITT solid rocket engine. 245 kN.
15Zh60.
Article Number of RT-23U 15Zh60 intercontinental ballistic missile.
15Zh61.
Article Number of RT-23U 15Zh61 intercontinental ballistic missile.
US Navy gun for launch of rocket-boosted projectile. 1,470,981 kN. Development ended 1966. The proposed Martlet gun-launched small satellite launcher used a converted 16 inch naval gun to propell the rocket sabot. Isp=43s.
16.8-KS-7,870.
Alternate designation for Star 26C Solid rocket engine.
Solid propellant rocket stage. Loaded/empty mass 907,000/91,000 kg. Thrust 13,788.00 kN. Vacuum specific impulse 263 seconds. Notional 160 inch solid motor considered in cluster of 7 as alternative to Nova 8 F-1 stage. Led to 156 inch motors tested in late 1960's.
17.6-KS-2,460.
Alternate designation for Star 17 Solid rocket engine.
17.8-KS-7,500.
Alternate designation for Star 26 Solid rocket engine.
17.8-KS-7,784.
Alternate designation for Star 26B Solid rocket engine.
1700.
Government designation of KH-8 military surveillance satellite.
17D.
Russian surface-to-air missile. Prototype air-breathing surface-to-air missile, using air-augmented solid propellant.
Korolev Lox/Kerosene rocket engine. 86.3 kN. Buran OMS and verniers. Out of Production. Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT-200K Isp=362s.
Korolev Lox/Kerosene rocket engine. 86.3 kN. Out of Production. Isp=362s. Version of RD-58 for Buran orbital propulsion system 17D11. Used synthetic kerosene ('Sintin') for higher specific impulse.
Korolev GOX/Sintin rocket engine. 4 kN. Buran OMS large verniers. Out of Production. Isp=295s. Large verniers for Buran orbital propulsion system 17D11. Uses synthetic kerosene ('Sintin') for high specific impulse. Oxygen is gaseous in system.
17D58E.
Government designation of RDMT-12 N2O4-UDMH rocket engine.
Isayev N2O4/UDMH rocket engine.13 N. In Production. Isp=247s. Small attitude control thruster used in Briz, Briz-M upper stage propulsion system S5.98M.
Melnikov N2O4/UDMH rocket engine. 2.943 kN. Ikar stage 4 for Soyuz-Ikar. Design 1999. Isp=325s. Derived from propulsion module of Yantar spysat, with over 30 flights to 1998. Increased versatility compared to Block L due to capability for 50 restarts.
17F114.
Article Number of Taifun-3 military target satellite.
17F115.
Article Number of Koltso military target satellite.
17F116.
Article Number of Zenit-8 military surveillance satellite.
17F118.
Article Number of Nadezhda navigation satellite.
17F12.
Article Number of Orlets-1 military naval signals reconnaisance satellite.
17F120.
17F13.
Article Number of Strela-3 military store-dump communications satellite.
17F15.
Article Number of Raduga-1 communications satellite.
17F16.
Article Number of US-A military naval surveillance radar satellite.
17F17.
Article Number of US-P military naval signals reconnaisance satellite.
17F19DM.
Article Number of Polyus military anti-satellite system.
17F31.
Article Number of Taifun-2 military target satellite.
17F32.
Article Number of NPG manned space station.
17F41.
Article Number of Resurs F1-17F41 earth land resources satellite.
17F42.
Article Number of Resurs F2 earth land resources satellite.
17F43.
Article Number of Okean-O earth resources radar satellite.
17F45.
Article Number of Meteor-3 earth weather satellite.
17F45M.
Article Number of Meteor-3M earth weather satellite.
17F71.
Article Number of Gals communications satellite.
17K s/n 121.
Manufacturer's designation for Salyut 1 manned space station.
17K s/n 124.
Manufacturer's designation for Salyut 4 manned space station.
17K114.
Alternate designation for US-A military naval surveillance radar satellite.
A small two stage to orbit horizontal takeoff / horizontal landing vehicle proposed for the Russian Air Force in 1993.
17KS s/n 125.
Manufacturer's designation for Salyut 6 manned space station.
17KS s/n 126.
Manufacturer's designation for Salyut 7 manned space station.
17KS12000.
Alternate designation for Nihka Solid rocket engine.
Solid propellant rocket stage. Loaded/empty mass 399/70 kg. Thrust 50.50 kN. The Nihka rocket motor was developed specifically for the Black Brant X rocket system by Bristol Aerospace.
18D.
Russian surface-to-air missile. Variant of the 18D air-breathing surface-to-air missile using a magnesium alloy in the fuel to double the initial launch thrust.
19.4-KS-3,600.
Alternate designation for Star 17A Solid rocket engine.
1900.
Government designation of KH-9 military surveillance satellite.
American manned Mars orbiter. Study 1956. Using the same basic systems as the Passenger Ship, the Cargo Ship would substitute a 177 metric ton Landing Boat for the surface expedition in place of the Passenger Sphere and propellant for the return home.
American manned Mars lander. Study 1956. The 1956 modification of Von Braun's Landing Boat design was reduced in mass by 12%, and the wingspan by 10%.
1956 Von Braun Passenger Ship.
American manned Mars orbiter. Study 1956. The 1956 version of Von Braun's Mars design was slashed by 50% in mass, while the number of passengers was increased from 10 to 12.
19K.
Manufacturer's designation for MKBS manned space station.
19KA30.
Manufacturer's designation for Gamma gamma ray astronomy satellite.
1A.
Manufacturer's designation for Astron x-ray astronomy satellite.
1AS.
Manufacturer's designation for Granat x-ray astronomy satellite.
1K, 1KP.
Alternate designation for Vostok manned spacecraft.
1M.
Manufacturer's designation for Mars 1M mars flyby probe.
1MS.
Russian technology satellite. 2 launches, 1962.04.06 (Cosmos 2) to 1962.10.25 (1MS). Early Kosmos launcher payloads of unknown purpose, possibly from Korolev OKB.
1MV.
Family of spacecraft.
1st Academy.
First name of CALT
1V (V-67).
Manufacturer's designation for Venera 1V (V-67) venus probe.
1VA.
Manufacturer's designation for Venera 1VA venus probe.
2.4KS5600.
Alternate designation for Hopi 2.4KS5600 Solid rocket engine.
Multiple-source solid rocket engine. 80 kN. Typical ideal dV=259 m/s; gravity and drag losses = 25 m/s.
2.67-KS-459.
Alternate designation for Star 5C Solid rocket engine.
2.80-KS-439.
Alternate designation for Star 5C-CB Solid rocket engine.
American communications satellite. Design of 2008, provided greater digital communications capacity by integrating next-generation technologies with the proven reliability of traditional concepts and products of the FS 1300 series.
Notional solid rocket engine. 11,120 kN. Study 1960. Isp=285s. 4 used as first stage of NASA all-solid Nova design. Extended high-expansion nozzles.
Notional solid rocket engine. 28,017 kN. NASA Nova study 1960. Isp=263s. 5 used as first stage of solid Nova design.
Selection of female astronauts for future Shenzhou missions was announced, but no details forthcoming tod ate.
205.
Standard warhead of Tu-121 intermediate range cruise missile, Tu-123 intercontinental boost-glide missile, and Tu-133 intercontinental cruise missile.
205.
Russian surface-to-air missile. Original missile of the S-25 system, development described above.
206.
Russian surface-to-air missile. The 206 was a version of the 205 using a single-chamber Isayev engine in place of the four-chamber design of the 205. Cancelled in April 1953.
207.
Russian surface-to-air missile. This was an improvement of the 205 with an improved warhead and reduced cruise thrust. Trials were conducted of the missile in 1953, but it was decided not to put it into service.
207A.
Russian surface-to-air missile. The 207A, with numerous improvements to the 205 which had been developed in a crash program, completed trials in 1955 and rapidly replaced the 205 in PVO service. It basically doubled all of the performance characteristics of the 205.
207T.
Russian surface-to-air missile. The 207T was an alternative derivative of the 207A with a nuclear warhead. It was developed during 1958 but does not seem to have entered service.
208.
Russian surface-to-air missile. In this version of the V-300 the warhead was increased to 430 kg to compensate for accuracy problems in the original production version. Cancelled in favour of the 207A.
212.
Russian air-to-surface missile. Korolev's second design for a rocket-propelled cruise missile. It was flight tested twice after his arrest in 1939 but work was then abandoned.
215.
Russian surface-to-air missile. The 215 was a derivative of the 207A with a nuclear warhead. It entered service in 1957.
217.
Family of missiles.
217.
Russian surface-to-air missile. The 217 was a version of the V-300 with a variable thrust engine. Entered production.
First anti-aircraft missile flown in the USSR. The 217/I had a conventional aircraft layout, with a main wing and aerodynamic control surfaces on the tail.
Pre-World War II anti-aircraft missile flown in the USSR. The 217/II follow-on to the 217/I had the first 'rocket' layout - four small wings, each all-moving.
217M.
Russian surface-to-air missile. Developed together with the improved S-25M missile system, the 217M entered production and gave the S-25 an enormous performance in improvement.
218.
Russian surface-to-air missile. The 218 was a version of the 217M with a nuclear warhead, which entered service in 1964.
Aerojet Nitric acid/Amine rocket engine. Nike Ajax. Launch thrust 11.7 kN. Development begun January 1946. Regeneratively cooled. Development and production First flight 1953.
21KS.
Manufacturer's designation for SPK space suit.
Multiple-source American solid rocket engine. 5.5 kN.
22D.
Russian surface-to-air missile. Prototype surface-to-air missile, using liquid-propellant ramjets in place of the air-augmented solid propellant of the 17D.
Aerojet solid rocket engine. 49 kN.
Solid propellant rocket stage. Loaded/empty mass 1,000/150 kg. Thrust 89.00 kN. Two-finned version.
Bristol Aerospace solid rocket engine. 89 kN. Two-finned version.
Solid propellant rocket stage. Loaded/empty mass 1,633,000/163,000 kg. Thrust 24,457.00 kN. Vacuum specific impulse 263 seconds. Notional 240 inch solid motor considered in cluster of 4 as alternative to Nova 8 F-1 stage. Led to 260 inch motor tested in late 1960's.
Aerojet Nitric acid/Amine rocket engine. A-20 ATO. Launch thrust 4.41 kN. Development begun May 1942. Production version of GALCIT unit. First flight 1944.
Aerojet Nitric acid/Amine rocket engine. JATO, Droppable for P-38, B-24, and B-25J. Thrust 4.41 kN. Development begun May 1942. Droppable version of XLR1, packaged compactly with parachute. First flight 1944.
Solid propellant rocket stage. Loaded/empty mass 1,648,355/156,126 kg. Thrust 35,391.40 kN. Vacuum specific impulse 263 seconds. 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations.
Solid propellant rocket stage. Loaded/empty mass 831,345/85,321 kg. Thrust 17,695.70 kN. Vacuum specific impulse 263 seconds. 260 inch solid rocket booster half length.
Solid propellant rocket stage. Loaded/empty mass 561,000/60,600 kg. Thrust 10,105.31 kN. Vacuum specific impulse 275 seconds. Study NASA 1969
Solid propellant rocket stage. Loaded/empty mass 1,264/268 kg. Thrust 75.70 kN. Four-finned version.
Bristol Aerospace solid rocket engine. 75.7 kN. Four-finned version.
27.5-KS-6,100.
Alternate designation for Star 20 Solid rocket engine.
27KS.
Manufacturer's designation for Mir complex manned space station.
Notional solid rocket engine. 46,208 kN. Study 1963. Operational date would have been February 1973 Isp=265s. Used on Nova MM 14B launch vehicle.
28-KS-4,825.
Alternate designation for Star 24C Solid rocket engine.
29.6-KS-4,170.
Alternate designation for Star 24 Solid rocket engine.
Kartukov solid rocket engine. P-70 Ametist. Out of Production.
2K.
Manufacturer's designation for Zenit-2 military surveillance satellite.
2K11.
Article Number of Krug surface-to-air missile.
2K12.
Complex of Kub surface-to-air missile.
2K6.
2KM.
Manufacturer's designation for Zenit-2M military surveillance satellite.
2MS.
Russian technology satellite. 2 launches, 1962.04.24 (Cosmos 3) to 1962.05.28 (Cosmos 5). Early Kosmos launcher payloads of unknown purpose, possibly from Korolev OKB.
2MV.
Family of spacecraft.
2MV-1.
Manufacturer's designation for Mars 2MV-1 venus probe.
2MV-2.
Manufacturer's designation for Mars 2MV-2 venus probe.
2MV-3.
Manufacturer's designation for Mars 2MV-3 venus probe.
2MV-4.
Manufacturer's designation for Mars 2MV-4 mars flyby probe.
2V (V-69).
Manufacturer's designation for Venera 2V (V-69) venus probe.
American manned rescue spacecraft. Study 1959. Three crew bailout lifeboat separable, not re-entry capable, short duration. Mass per crew 239 kg.
American manned rescue spacecraft. Study 1959. Three crew lifeboat capsule, separable, not re-entry capable, long duration. For use on Mars/Venus expedition. Mass per crew 511 kg.
3 Crew Lifting Re-Entry Concept.
American manned rescue spacecraft. Study 1960. Three crew lifting re-entry capsule. Orbital escape - no abort capability. Mass per crew 434 kg.
3 stage vehicle consisting of 1 x TX-500 + 1 x TX-454 + 1 x TX-239.
Alternate designation for Spartan anti-ballistic missile.
3.0KS4000.
Alternate designation for Hopi 3.0KS4000 Solid rocket engine.
30% Beryllium+Pentaborane in 70% Hydrazine.
High performance fuel developed in Russia. Never flown due to toxicity.
30.1-KS-5,500.
Alternate designation for Star 20B Solid rocket engine.
Notional solid rocket engine. 63,595 kN. Study 1963. Operational date would have been April 1973 Isp=263s. Used on Nova MM 14A launch vehicle.
Aerojet Nitric acid/Amine rocket engine. XP-79 Launch thrust .882 kN. Development begun January 1943. Planned successor to XCALT-6000, developed under 'Project X' for the Northrop XP-79 Flying Wing rocket fighter. First flight 1945.
Aerojet Nitric acid/Amine rocket engine. GAPA. Launch thrust 4.41 kN. Development begun March 1947. Boeing surface-to-air missile, which would evolve into Bomarc and reach IOC in 1959.
30-KS-8000.
Manufacturer's designation of Alcor Solid rocket engine.
316GK SM.
Manufacturer's designation for Mir-Shuttle Docking Module manned space station.
31KS.
Manufacturer's designation for Nauka earth magnetosphere satellite.
32.02-KS-38.
Alternate designation for Star 5A Solid rocket engine.
Notional solid rocket engine in GD Nova studies. 69,047 kN. Study 1963. Isp=263s. Recoverable motors; separation at 1,972 m/s at 53,000 m altitude; splashdown using retrorockets under 3 61 m diameter parachutes 610 km downrange.
32B.
Russian surface-to-air missile. Alternate missile developed for the S-25 system. Technically superior but not put into production, it led to the S-75 and later Soviet surface-to-air missiles.
34.35-KS-6,010.
Alternate designation for Star 27 Solid rocket engine.
346.
Russian manned rocketplane. 4 flights from 1946. Post-war Soviet version of the German supersonic DFS 8-346 rocket reconnaissance aircraft. Abandoned in 1951 after the prototype crashed.
36KS.
Manufacturer's designation for Efir earth magnetosphere satellite.
37KB.
Russian manned space station module. One launch, 1988.11.15. Carried in the payload bay of the Buran space shuttle. They could remain attached to the bay or (modified to the 37KBI configuration) be docked to the Mir-2 station.
Russian manned space station. Cancelled 1983. The basic 37K design consisted of a 4.2 m diameter pressurized cylinder with a docking port at the forward end. It was not equipped with its own propulsion system.
37KS.
Russian manned space station module. Cancelled 1983. Would have been launched by Proton and delivered and docked to the Mir station by a new lighter weight FGO tug.
Aerojet Nitric acid/Amine rocket engine. ATO Seaplanes. Launch thrust 6.66 kN. Development begun July 1943. Regeneratively cooled. Also a few 45ALDW-1500 were built. Droppable version. First flight 1945.
American technology satellite. 2 launched, 2004.12.21. The Three-Corner Sat mission was to obtain stereo images of clouds and test artificial intelligence software.
3D65.
Government designation of RD-866 N2O4-UDMH rocket engine.
Hercules solid rocket engine. 209 kN.
3KA.
Manufacturer's designation for Vostok manned spacecraft.
3KD.
Manufacturer's designation for Voskhod manned spacecraft.
3KV.
Alternate designation for Voskhod manned spacecraft.
3KZh.
Manufacturer's designation for Vostok-Zh manned spacecraft.
3M17.
Article Number of R-31 submarine launched ballistic missile.
3M20.
Russian submarine-launched ballistic missile. First flight 1979. Four unsuccessful tests in 1980, two successful in 1981. Development completed 1983. SLBM on Typhoon subs.
3M30.
Missile of Bulava intercontinental ballistic missile.
3M37.
Missile of R-29RM submarine-launched ballistic missile.
3M40.
Missile of R-29R submarine-launched ballistic missile.
3M41.
Alternate Designation of S-300F surface-to-air missile.
3M65.
Missile of R-29RL submarine-launched ballistic missile.
3M65.
First flight 1983. As of March 1986 only Russian SLBM in production.
3M9.
Alternate designation for Kub surface-to-air missile.
3M91.
3M9M / 9M9.
Missile of Kub surface-to-air missile.
3MV.
Family of spacecraft.
3MV-1.
Manufacturer's designation for Venera 3MV-1 venus probe.
3MV-1A.
Manufacturer's designation for Venera 3MV-1A venus probe.
3MV-3.
Manufacturer's designation for Venera 3MV-3 venus probe.
3MV-4.
Manufacturer's designation for Venera 3MV-4 venus probe.
3MV-4A.
Manufacturer's designation for Mars 3MV-4A mars flyby probe.
3R1.
Article Number of Mars tactical ballistic rocket.
3R10.
Russian tactical ballistic rocket.
3R2.
Article Number of Filin tactical ballistic rocket.
3R65.
Article Number of 3M20 submarine-launched ballistic missile.
3R9.
Missile of Frog 5 tactical ballistic rocket.
3R9.
Russian tactical ballistic rocket.
3V (V-70).
Manufacturer's designation for Venera 3V (V-70) venus probe.
3V (V-72).
Manufacturer's designation for Venera 3V (V-72) venus probe.
4.4KS4800.
Alternate designation for Kisha I 4.4KS4800 Solid rocket engine.
Aerojet Nitric acid/Amine rocket engine. B-29 droppable ATO. Launch thrust 13.33 kN. Development begun October 1943. Droppable version, pressure fed, regeneratively cooled, supplied with 331 kg of propellant. First flight 1945.
Aerojet Nitric acid/Amine rocket engine. PB2Y-3 ATO. Launch thrust 17.6 kN. Development begun July 1943. Gasoline engine driven pumps. Also 40ALD-6000 and 60ALD-8000 versions First flight 1945.
44N6.
Alternate Designation of 218 surface-to-air missile.
Aerojet Nitric acid/Amine rocket engine. Aerobee B. Launch thrust 11.7 kN. Development begun June 1948. Manufacture of complete Aerobee systems First flight 1955.
45-KS-18,500.
Alternate designation for Star 31 Solid rocket engine.
Aerojet Nitric acid/UDMH rocket engine. Bomarc. Out of Production. Launch thrust 159.583 kN. Development begun 1953. Pressure-fed, uncooled, ceramic-lined engine. First flight 1959.
46A.
Standard warhead of R-7A missile.
48N6.
48N6E.
Missile of S-300PMU-1 48N6E surface-to-air missile.
Russian surface-to-air missile. Improved version of the 48N6E for the S-400 system, capable of shooting down tactical ballistic missiles at incoming speeds of 4.8 km/s or hypersonic targets flying at 3.0 km/s at 150 km altitude.
48N6E2.
Missile of S-300PMU-2 surface-to-air missile.
49FUE.
Standard RV of Variant S submarine-launched ballistic missile.
49-KS-7,955.
Alternate designation for Star 30E Solid rocket engine.
4D10.
Isayev N2O4/UDMH rocket engine. 255 kN. R-27 / RSM-25 (SS-N-6). Out of Production. First engine system to be submerged in propellant tank. One main engine chamber plus unknown number (probably 4) of steering thrusters. Thrust 226 + 29 kN.
4K.
Manufacturer's designation for Zenit-4 military surveillance satellite.
4K10.
Article Number of R-27 submarine-launched ballistic missile.
4K18.
Article Number of R-27K submarine-launched ballistic missile.
4K22.
Article Number of RT-15M submarine-launched ballistic missile.
4K48.
Article Number of P-6 intermediate range cruise missile.
4K50.
Article Number of R-13 missile.
4K55.
Article Number of R-21 submarine-launched ballistic missile.
4K75.
Article Number of R-29 submarine-launched ballistic missile.
4K75D.
Article Number of R-29D submarine-launched ballistic missile.
4K75DU.
Article Number of R-29R submarine-launched ballistic missile.
4K75K.
Article Number of R-29K submarine-launched ballistic missile.
4K75R.
Article Number of R-29RL submarine-launched ballistic missile.
4K75RM.
Article Number of R-29RM submarine-launched ballistic missile.
4KM.
Manufacturer's designation for Zenit-4M military surveillance satellite.
4KMK.
Manufacturer's designation for Zenit-4MK military surveillance satellite.
4KMKM.
Manufacturer's designation for Zenit-4MKM military surveillance satellite.
4KMT.
Manufacturer's designation for Zenit-4MKT military surveillance satellite.
4KT.
Manufacturer's designation for Zenit-4MT military surveillance satellite.
4MV.
Family of spacecraft.
4NM.
Alternate designation for Mars 5NM mars lander.
4th Academy.
First name of Fourth Academy
4V-1.
Manufacturer's designation for Venera 4V-1 venus probe.
4V-2.
Manufacturer's designation for Venera 4V-2 venus probe.
4Ya11.
Article Number of IS-A military anti-satellite system.
American manned rescue spacecraft. Study 1962. Five crew lifeboat capsule, separable, not re-entry capable, short duration. Mass per crew 284 kg.
Canadian gun-launched sounding rocket. When most people think of the HARP Program they usually think of the big 16 inch guns roaring skywards as they launch test probes into the upper atmosphere. What most people do not realise was that even before HARP small portable gun launchers were used for the same purpose and even during HARP hundreds of high altitude flights were conducted using small guns. The 5 inch gun-launch system was initially designed to satisfy the requirements of the Meteorological Rocket Network This required that an 0.9 kg (2 lb) payload be carried to an altitude of 65 km (40 miles). Typical payloads were radar reflective chaff ejected at apogee, which was tracked by radar to yield wind data, and small Metsondes which drifted to earth under large parachutes and returned radio telemetry of temperature, humidity and the like.
Notional lox/lh2 rocket engine. 41,361 kN. OOST, ROOST studies 1963. Isp=410s. First flight 1977.
Notional Lox/Kerosene rocket engine. 24,459 kN. Study 1963. Operational date would have been July 1977. Recoverable stage. 10% plug nozzle. Isp=299s. Used on Nova-1 DAC launch vehicle.
Solid propellant rocket stage. Loaded/empty mass 751,212/100,350 kg. Thrust 15,480.36 kN. Vacuum specific impulse 265 seconds. Five-segment version of Shuttle RSRM studied in 1999-2003 to increase shuttle payload to ISS. Test fired in 2003 but not proceeded with. Another version proposed in 2005 for use as lateral boosters for the Constellation Cargo Vehicle.
5.5KS6100.
Alternate designation for Kiva 5.5KS6100 Solid rocket engine.
Multiple-source American solid rocket engine. 24 kN.
5.9-KS-565.
Alternate designation for Star 6B Solid rocket engine.
500 Ibf Centrojet.
Manufacturer's designation of Centrojet Nitric acid-Amine rocket engine.
509th Research Institute.
Fourth name of SISE
51-KS-7,340.
Alternate designation for Star 30C Solid rocket engine.
51T6.
Russian anti-ballistic missile. Exo-atmospheric interceptor component of A-135 ABM system.
Fakel solid rocket engine.
51T6, 53T6.
Missile article number for A-135 missile.
Fakel N2O4/UDMH rocket engine.
53T6.
Russian anti-ballistic missile. Endo-atmospheric interceptor component of A-135 ABM system.
Solid propellant rocket stage. Loaded mass 12,000 kg.
54-KS-6,070.
Alternate designation for Star 30BP Solid rocket engine.
5500.
Article Number of KH-11 military surveillance satellite.
5D22.
SKB-350 solid rocket engine.
5D25.
Government designation of S5.44 Nitric acid-Amine rocket engine.
5K.
Manufacturer's designation for Sever manned spacecraft.
5MV.
Manufacturer's designation for Taifun-1 military target satellite.
5MV.
Family of spacecraft.
5NM.
Manufacturer's designation for Mars 5NM mars lander.
5S47.
SKB-350 solid rocket engine.
5th Academy.
First name of CAST
5V11.
Manufacturer's designation for Dal surface-to-air missile.
5V21.
5V28.
5V28E.
Manufacturer's designation for V-880E surface-to-air missile.
5V28M.
Manufacturer's designation for V-880M surface-to-air missile.
5V55R.
Missile article number for S-300 missile.
5V55RM.
Missile of S-300F surface-to-air missile.
5V55U.
Missile of S-300PMU-1 5V55U surface-to-air missile.
5V91T.
Article Number of IS-P military anti-satellite system target satellite.
5VK.
Manufacturer's designation for Vega 5VK venus probe.
5VS.
Manufacturer's designation for Vega 5VS venus probe.
5Ya24.
Manufacturer's designation for 218 surface-to-air missile.
5Ya25.
Manufacturer's designation for 217 surface-to-air missile.
5Ya25M.
Manufacturer's designation for 217M surface-to-air missile.
5Ya26, 5Ya27.
Manufacturer's designation for S-225 anti-ballistic missile.
63-KS-10,625.
Alternate designation for Star 37FM Solid rocket engine.
63S1.
Manufacturer's designation for Kosmos 63S1 orbital launch vehicle.
63S1M.
Manufacturer's designation for Kosmos 63S1M orbital launch vehicle.
63SM.
Manufacturer's designation for Kosmos 11K63 orbital launch vehicle.
64S5.
Ukrainian intercontinental ballistic missile. Space launch version, never went beyond design stage.
65MP.
Manufacturer's designation for Kosmos 65MP orbital launch vehicle.
65S3.
Manufacturer's designation for Kosmos 65S3 orbital launch vehicle.
66-KS-8,550.
Alternate designation for Star 37XFP Solid rocket engine.
698BK.
Manufacturer's designation for Ferret military naval signals reconnaisance satellite.
6K.
Manufacturer's designation for Zenit-6U military surveillance satellite.
Canadian gun-launched sounding rocket. The highly successful 5 inch HARP gun had demonstrated the immense versatility of small portable gun systems for atmospheric exploration. The 7 inch HARP gun system represented the 5 inch system scaled up to the largest barrel size practical, while still remaining portable.
7.5-KS-1,250.
Alternate designation for Star 12 Solid rocket engine.
7.5-KS-1,630.
Alternate designation for Star 12A Solid rocket engine.
761.
Chinese sounding rocket. Lightweight two-stage solid propellant sounding rocket. Designation indicates development was authorised in January 1976. Evidently replaced both the HP2 and HP6 from about 1980 on. Used for routine measurement of the upper atmosphere.
77KM.
Manufacturer's designation for ISS Zarya manned space station.
7K.
Manufacturer's designation for Soyuz A manned spacecraft.
7K-L1.
Manufacturer's designation for Soyuz 7K-L1 manned lunar flyby spacecraft.
7K-L1E.
Manufacturer's designation for Soyuz 7K-L1E manned lunar orbiter.
7K-L1S, 7K-L1T.
Manufacturer's designation for Soyuz 7K-L1A manned lunar orbiter.
7K-LOK.
Manufacturer's designation for Soyuz 7K-LOK manned lunar orbiter.
7K-MF6.
Manufacturer's designation for Soyuz 7K-MF6 manned spacecraft.
7K-OK.
Manufacturer's designation for Soyuz 7K-OK manned spacecraft.
7K-OKS.
Manufacturer's designation for Soyuz 7KT-OK manned spacecraft.
7K-P, 7K-PPK.
Manufacturer's designation for Soyuz P manned combat spacecraft.
7K-PPK.
Manufacturer's designation for Soyuz PPK manned combat spacecraft.
7K-R.
Manufacturer's designation for Soyuz R manned spacecraft.
7K-S.
Manufacturer's designation for Soyuz 7K-S manned spacecraft.
7K-ST.
Manufacturer's designation for Soyuz T manned spacecraft.
7K-STM.
Manufacturer's designation for Soyuz TM manned spacecraft.
7K-STMA.
Manufacturer's designation for Soyuz TMA manned spacecraft.
7K-T, 7K-T/AF/.
Manufacturer's designation for Soyuz 7K-T manned spacecraft.
7K-TA.
Manufacturer's designation for Soyuz 7K-T-A9 manned spacecraft.
7K-TG.
Manufacturer's designation for Progress logistics spacecraft.
7K-TGM.
Manufacturer's designation for Progress M logistics spacecraft.
7K-TGM2.
Manufacturer's designation for Progress M2 logistics spacecraft.
7K-TM/F/.
Manufacturer's designation for Soyuz 7K-TM manned spacecraft.
7K-VI.
Manufacturer's designation for Soyuz VI manned combat spacecraft.
87.2-KS-17,335.
Alternate designation for Star 48A s and Star 48B s solid rocket engines.
87.2-KS-17,735.
Alternate designation for Star 48B Solid rocket engine.
8A11.
Article number for R-1 missile.
8A61.
Article Number of R-11 submarine-launched ballistic missile.
8A62.
Alternate designation for R-5 rocket stage.
8A62M.
Missile of R-5M intermediate range ballistic missile.
8A63.
Article Number of R-3A intermediate range ballistic missile.
8A67.
Article Number of R-3 intermediate range ballistic missile.
8A91.
Article Number of Sputnik 8A91 intercontinental ballistic orbital launch vehicle.
8A92.
Article Number of Vostok 8A92 orbital launch vehicle.
8A92M.
Article Number of Vostok 8A92M orbital launch vehicle.
8D21.
Article Number of RD-301 LF2-Ammonia rocket engine.
8D411K.
Government designation of RD-0210 N2O4-UDMH rocket engine.
8D412K.
Government designation of RD-0211 N2O4-UDMH rocket engine.
Kosberg Lox/Kerosene rocket engine. 1471 kN. Designed for use in N-1. Development canceled in 1960 when Korolev turned to Kuznetsov for R-9 and N-1 engines after continuous rows with Glushko over performance and propellant types. First flight 1966.
8D419.
Manufacturer's designation of 8D423 N2O4-UDMH rocket engine.
8D420.
Government designation of RD-270 N2O4-UDMH rocket engine.
8D420M.
Government designation of RD-270M N2O4-Pentaborane rocket engine.
Izotov N2O4/UDMH rocket engine. 131 kN. Production from 1964. Isp=325s. Single chamber engine for UR-100 stage 2. Gas generator cycle with two large turbine exhaust pipes. First flight 1965.
8D43.
Kosberg N2O4/UDMH rocket engine family. Low-expansion ratio gimballed variant developed for UR-500. In initial configuration 4 would be clustered with 4 x Glushko 11D43. Abandoned in favor of 6 x Glushko 11D48. Further developed into the RD-0208 and RD-0210 engines.
8D43.
Kosberg N2O4/UDMH rocket engine. 559 kN. UR-500 stage 1 original concept. Hardware. Isp=316s. In early Proton design would be clustered with 4 x Glushko 11D43. Abandoned in favor of 6 x Glushko 11D48, but later developed into the RD-0208 and RD-0210.
Kosberg N2O4/UDMH rocket engine. 2247.450 kN. Design 1962. Isp=310s. Originally the first stage of the Proton was designed for 4 x fixed 11D43 and 4 x gimballed Kosberg 8D43; replaced by 6 x 11D48 from Glushko in final Proton design.
8D44.
Government designation of RD-0203 N2O4-UDMH rocket engine.
8D45.
Government designation of RD-0202 N2O4-UDMH rocket engine.
8D46.
Government designation of RD-0205 N2O4-UDMH rocket engine.
8D47.
Government designation of RD-0206 N2O4-UDMH rocket engine.
8D48.
Government designation of RD-0213 N2O4-UDMH rocket engine.
8D49.
Government designation of RD-0212 N2O4-UDMH rocket engine.
8D515.
Government designation of RD-217 Nitric acid-UDMH rocket engine.
8D52.
Government designation of RD-103 Lox-Alcohol rocket engine.
8D52M.
Government designation of RD-103M Lox-Alcohol rocket engine.
8D63.
Government designation of RD-851 Nitric acid-UDMH rocket engine.
8D67.
Government designation of RD-0207 N2O4-UDMH rocket engine.
8D71.
8D710.
Government designation of RD-119 Lox-UDMH rocket engine.
8D711.
Government designation of RD-109 Lox-UDMH rocket engine.
8D712.
Government designation of RD-218 Nitric acid-UDMH rocket engine.
8D713.
Government designation of RD-219 Nitric acid-UDMH rocket engine.
8D714.
Government designation of RD-0105 Lox-Kerosene rocket engine.
8D715.
Government designation of RD-0106 Lox-Kerosene rocket engine.
8D715K.
Government designation of RD-0107 Lox-Kerosene rocket engine.
8D715P.
Government designation of RD-0108 Lox-Kerosene rocket engine.
8D716.
Government designation of RD-111 Lox-Kerosene rocket engine.
8D719.
Government designation of RD-0109 Lox-Kerosene rocket engine.
8D72?.
Government designation of RD-106 Lox-Kerosene rocket engine.
8D721.
Government designation of RD-224 Nitric acid-UDMH rocket engine.
8D723.
Glushko N2O4/UDMH rocket engine. 117 kN. Developed 1963-1970. 10 to 12 tonne thrust engine developed for an unstated military requirement. Isp=325s.
Korolev Lox/Kerosene rocket engine. 66.7 kN. GR-1 Stage 3, N-11GR - V. Development based on S1.5400. Isp=350s.
8D727.
Government designation of RD-108-8D727 Lox-Kerosene rocket engine.
8D727K.
Government designation of RD-108-8D727K Lox-Kerosene rocket engine.
8D727K, 8D727P.
Alternate designation for RD-108-8D727 Lox-Kerosene rocket engine.
8D728.
Government designation of RD-107-8D728 Lox-Kerosene rocket engine.
8D74.
Government designation of RD-107-8D74 Lox-Kerosene rocket engine.
8D74-1958.
Government designation of RD-107-8D74-1958 Lox-Kerosene rocket engine.
8D74-1959.
Government designation of RD-107-8D74-1959 Lox-Kerosene rocket engine.
8D74K.
Government designation of RD-107-8D74K Lox-Kerosene rocket engine.
8D74PS.
Government designation of RD-107-8D74PS Lox-Kerosene rocket engine.
8D75.
Government designation of RD-108-8D75 Lox-Kerosene rocket engine.
8D75-1958.
Government designation of RD-108-8D75-1958 Lox-Kerosene rocket engine.
8D75-1959.
Government designation of RD-108-8D75-1959 Lox-Kerosene rocket engine.
8D75K.
Government designation of RD-108-8D75K Lox-Kerosene rocket engine.
8D75PS.
Government designation of RD-108-8D75PS Lox-Kerosene rocket engine.
8D76.
Government designation of RD-107-8D76 Lox-Kerosene rocket engine.
8D77.
Government designation of RD-108-8D77 Lox-Kerosene rocket engine.
8D811.
Government designation of RD-0214 N2O4-UDMH rocket engine.
8EK.
Article Number of Luna Ye-8 lunar rover.
8F021.
Article Number of OGCh military orbital bombing system.
8F17.
Standard RV of R-16 intercontinental ballistic missile.
8K.
Manufacturer's designation for Zenit-8 military surveillance satellite.
8K11.
Article Number of R-1 missile.
8K14.
Article Number of R-11A suborbital launch vehicle and R-11 and R-11M submarine-launched ballistic missiles.
8K14, SS-1C Scud B, 9K72 Elbrus.
Alternate designation for R-17 rocket stage.
8K51.
Article Number of R-5M intermediate range ballistic missile.
Russian anti-satellite missile. ASAT version. Little has emerged about Korolev's ASAT project, designed in competition with Chelomei's in 1961-1964.
8K513 Blok A.
Alternate designation for GR-1 Stage 1 rocket stage.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,000/2,100 kg. Thrust 441.00 kN. Vacuum specific impulse 340 seconds. Masses estimated based on total vehicle mass of 117 tonnes. Developed into Molniya/Soyuz second stage.
8K513 Blok V.
Alternate designation for GR-1 Stage 3 rocket stage.
8K61.
Article Number of R-11FM submarine-launched ballistic missile.
8K62.
Article Number of R-5 intermediate range ballistic missile.
8K63.
Article Number of R-12 missile.
8K63U.
Article Number of R-12U intermediate range ballistic missile.
8K64.
Article Number of R-16 intercontinental ballistic missile.
8K64U.
Article Number of R-16U intercontinental ballistic missile.
8K65.
Article Number of R-14 missile.
8K65U.
Article Number of R-14U intermediate range ballistic missile.
8K66.
Article Number of R-26 intercontinental ballistic missile.
8K67.
Article Number of Tsiklon missile.
8K67P.
Article Number of R-56 Polyblock, R-56 Polyblock ICBM, R-56, and R-36 8K67P intercontinental ballistic missiles and space launch vehicles.
8K69.
Article Number of R-36-O orbital missile.
8K71.
Article Number of R-7 missile.
Russian ballistic missile. Korolev project. No other information available.
8K713.
Article Number of GR-1 intercontinental ballistic missile.
Russian intercontinental ballistic missile. ICBM version. Article number sometimes erroneously given as 8K73.
8K71PS.
Article Number of Sputnik 8K71PS intercontinental ballistic orbital launch vehicle.
8K72.
Article Number of Luna 8K72, Vostok 8K72, and Vostok 8K72K orbital launch vehicles.
8K73.
Alternate designation of GR-1 intercontinental ballistic missile.
8K73.
Russian ballistic missile. Korolev project. Possibly designation for variant of GR-1.
8K74.
Article Number of R-7A missile.
8K75.
8K75M.
Complex of R-9M intercontinental ballistic missile.
8K76.
Article Number of R-9M intercontinental ballistic missile.
8K76.
Russian intercontinental ballistic missile. Version using storable propellants and Isayev engines. Studied but rejected prior to start of development.
8K77.
Russian intercontinental ballistic missile. Version with vacuum-isolated liquid oxygen tanks to provide capability to hold ready for instant launch. Studied but never developed.
8K77 Blok A.
Alternate designation for R-9A Stage 1 rocket stage.
8K77 Blok B.
Alternate designation for R-9A Stage 2 rocket stage.
8K78.
Article Number of Molniya 8K78 orbital launch vehicle.
8K78L.
Article Number of Molniya 8K78L orbital launch vehicle.
8K78M.
Article Number of Molniya 8K78M orbital launch vehicle.
8K79.
Russian intermediate range ballistic missile. Korolev 1961 design for a single stage military rocket. A competing missile was selected for the requirement.
8K81.
Article Number of UR-200 intercontinental ballistic missile.
8K81 Stage 1.
Alternate designation for UR-200-1 rocket stage.
8K81 Stage 2.
Alternate designation for UR-200-2 rocket stage.
8K82.
Article Number of UR-500 missile.
8K82K.
Article Number of Proton-K orbital launch vehicle.
8K82K / 11S824.
Article Number of Proton-K-D orbital launch vehicle.
8K82K / 11S824F.
Article Number of Proton-K-D-2 orbital launch vehicle.
8K82K / 11S824M.
Article Number of Proton-K-D-1 orbital launch vehicle.
8K82K / 11S86.
Article Number of Proton-K-DM orbital launch vehicle.
8K82K / 11S861.
Article Number of Proton-K-DM-2 orbital launch vehicle.
8K82K / 11S861-01.
Article Number of Proton-K-DM-2M orbital launch vehicle.
8K82K / 17S40.
Article Number of Proton-K-17S40 orbital launch vehicle.
8K82KM.
Article Number of Proton-K-Briz-M orbital launch vehicle.
8K82M.
Article Number of Proton-M-Briz-M orbital launch vehicle.
8K82M / 11S861.
Article Number of Proton-M-DM-2 orbital launch vehicle.
8K83.
Article Number of UR-200B orbital missile.
8K84.
8K84 Stage 1.
Alternate designation for 8S816 rocket stage.
8K84 Stage 2.
Alternate designation for 8S817 rocket stage.
8K84K.
Alternate Designation of UR-100K intercontinental ballistic missile.
8K84M.
Article Number of UR-100M missile.
8K84UTTKh.
Complex of UR-100M missile.
8K94.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 9,800/900 kg. Thrust 147.00 kN. Vacuum specific impulse 330 seconds. Empty mass estimated.
8K94.
Ukrainian intermediate range ballistic missile. Unusual designation for the upper stages of another Yangel project - possibly reflecting design originally was stand-alone IRBM?
8K95.
Article Number of RT-1 intermediate range ballistic missile.
8K96.
Article Number of RT-15 intermediate range ballistic missile.
8K97.
Article Number of RT-25 intermediate range ballistic missile.
8K98.
Article Number of RT-2 intercontinental ballistic missile.
8K98M.
Article Number of RT-2M intercontinental ballistic missile.
8K98P.
Article Number of RT-2P intercontinental ballistic missile.
8K99.
8S810K.
Alternate designation for Proton K-1 rocket stage.
8S811K.
Alternate designation for Proton K-2 rocket stage.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 32,799/3,000 kg. Thrust 868.80 kN. Vacuum specific impulse 310 seconds. Orevo has sectioned hardware. Total mass, sea level thrust accurate; Isp, empty mass and burn time estimated. Source: Placard, Orevo.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 8,611/900 kg. Thrust 131.45 kN. Vacuum specific impulse 325 seconds. Orevo has sectioned hardware. Total mass, thrust accurate; Isp, empty mass and burn time estimated. Source: Placard, Orevo.
8th Academy.
First name of SAST
8Zh38.
Article Number of R-2 intermediate range ballistic missile.
9.00-KS-755.
Alternate designation for Star 10 Solid rocket engine.
9.0KS1800.
Alternate designation for Hopi 9.0KS1800 Solid rocket engine.
American manned Mars expedition. Study 1989. Following the Ride Report, the Bush administration indicated a willingness to support a new manned space initiative after completion of the space station.
90 day study lunar outpost.
Alternate designation for Lunar Outpost manned lunar base.
9K.
Manufacturer's designation for Soyuz B space tug.
9K21.
Article Number of R-65 tactical ballistic rocket.
9K52.
Russian intermediate range ballistic missile. First flight 1974. SS-21 is Tochka SRBM mounted on a ZIL-375 transporter, while SS-23 is the same missile on an 8-wheeled TEL.
9K72.
Article Number of R-17 short-range ballistic missile.
9K76.
Russian intermediate range ballistic missile.
Russian intermediate range ballistic missile. Initially designated SS-22 by DoD; redesignated SS-12M Scaleboard B
9K79.
Russian intermediate range ballistic missile. Tactical ballistic missile. SS-21 is Tochka SRBM mounted on a ZIL-375 transporter, while SS-23 is the same missile on an 8-wheeled TEL.
Russian intermediate range ballistic missile. Improved version.
Bristol Aerospace solid rocket engine. 49 kN.
Solid rocket stage. 49.00 kN (11,016 lbf) thrust. Mass 300 kg (661 lb).
Bristol Aerospace solid rocket engine. 7.4 kN.
Solid rocket stage. 7.40 kN (1,664 lbf) thrust. Mass 100 kg (220 lb).
9KS2150.
Alternate designation for Judi-I 1.9KS2150 Solid rocket engine.
Russian short range ballistic missile. Two-stage deployed short range missile. Four solid motors strapped together, operating in staged pairs.
9M76.
9M79.
9M79M1.
Missile of 9K79-1 intermediate range ballistic missile.
9M8.
Missile of Krug surface-to-air missile.
9M82.
Russian surface-to-air missile. Anti-tactical ballistic missile; outer-layer defense.
Russian surface-to-air missile. Anti-tactical ballistic missile; outer-layer defense.
9M82M, 9M83M.
Missile of Antey-2500 surface-to-air missile.
9M83.
Russian surface-to-air missile. Anti-tactical ballistic missile; inner-layer defense.
Russian surface-to-air missile. Anti-tactical ballistic missile; inner-layer defense.
9M96.
Article number of missile of S-400 missile system.
9M96.
Russian surface-to-air missile. Improved, longer range version of 9M96 for the S-400. Four 9M96's can be housed in a single 48N6E launch container position.
9M96E.
Missile of S-300PMU-1 9M96E surface-to-air missile.
9M96E2.
Missile of S-300PMU-1 9M96E2 surface-to-air missile.