Encyclopedia Astronautica
Kosberg


Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia.

AKA: S A Kosberg; OKB-154; KB Khimavtomatiki.

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Associated Countries
Associated Engines
  • 11D23 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. More...
  • 8D415K 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. More...
  • 8D43 + 11D43 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. More...
  • 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. More...
  • D-1 Kosberg isopropylnitrate monopropellant rocket engine. 39 kN. Developed 1955-56. Second thrust level at 50%. Explosion of D-1 on test bench in 1956 forced stop of work with mono-propellant OT-152. Sea level thrust 39 kN. More...
  • D-7 Kosberg isopropylnitrate monopropellant rocket engine. 11.8 kN. Missile by Toropov. Out of Production. Intended for air-air missile by I I Toropov. Uncooled thrust chamber. Sea level thrust 11.8 kN. More...
  • RD-0230 Kosberg N2O4/UDMH rocket engine. R-36M / RS-20A (SS-18 mod-1) stage 2 vernier. Out of Production. Vernier engine. Gas generator cycle. First flight 1974. More...
  • RD-0216 Kosberg N2O4/UDMH rocket engine. 219 kN. UR-100 stage 1. Isp=313s. Staged combustion cycle. Includes tank pressurization system (RD-0217 without tank press.). First launch November 1963, manufactured until 1974, operational until 1991. First flight 1965. More...
  • RD-0217 Kosberg N2O4/UDMH rocket engine. 219 kN. UR-100, UR-100K stage 1. Out of Production. Staged combustion cycle. Version of RD-0216 without tank pressurization system. Manufacturing until 1974, operational use until 1991. Isp=313s. More...
  • RD-0221 Kosberg N2O4/UDMH rocket engine. 78 kN. upper stage of unnamed missile by Mishin. Developed 1965-70. Isp=330s. More...
  • RD-0225 Kosberg N2O4/UDMH rocket engine. 3.923 kN. Almaz space station orbital maneuvering. Hardware. Originally designed for UR-100 follow-ons spaceships. Two engines used on Almaz space station for orbital maneuvering, Pressure fed. Isp=287s. First flight 1974. More...
  • RD-0228 Kosberg N2O4/UDMH rocket engine. 755 kN. R-36M / RS-20A (SS-18 mod-1) stage 2. Out of Production. Comprises single-chamber main engine RD-0229 plus four-chamber steering engine RD-0230. Further developed to RD-0255. More...
  • RD-0229M Kosberg Lox/LNG rocket engine. 883 kN. Vozdushnyy Start stage 1. Developed 1997. Derivative of RD-0229 for the propellants LOX and liquid natural gas (methane). Initial candidate for stage 1 propulsion of Vozdushnyy Start project by Kompomash. More...
  • RD-0213 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 3. Design 1962. Version of RD-0210. Staged combustion cycle (Oxidizer pre-burner gas routed to main chamber after driving turbine). Main engine for Proton Stage 3 in system RD-0212. Isp=326s. More...
  • RD-0231 Kosberg N2O4/UDMH rocket engine. 29 kN. P-700 Granit. Out of Production. Staged combustion cycle. Isp=275s. First flight 1970. More...
  • RD-0232 Kosberg N2O4/UDMH rocket engine. UR-100N / Rokot Stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0234 for tank pressurization and three RD-0233. First flight 1972. More...
  • RD-0233 Kosberg N2O4/UDMH rocket engine. 520 kN. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. Isp=310s. First flight 1974. More...
  • RD-0229 Kosberg N2O4/UDMH rocket engine. R-36M / RS-20A (SS-18 mod-1) stage 2. Out of Production. Main engine. Staged combustion cycle. Used on Ikar launch vehicle. First flight 1974. More...
  • RD-0215 Kosberg N2O4/UDMH rocket engine. 2450 kN. Developed 1962-65 for heavy Chelomei launcher (UR-900?) stage 1. Isp=310s. Engine unit consisting of 1 RD-0217 for tank pressurization and three RD-0216. Hardware not hot-tested. More...
  • RD-0750 Kosberg lox/lh2/kerosene rocket engine. 1412 kN. Alternative for Angara central stage, MAKS. Developed 1997-. Isp=455s. Tripropellant derivative of RD-0120. Some components tested in RD-0120TD technology demonstration in cooperation with Aerojet. More...
  • RD-0206 Kosberg N2O4/UDMH rocket engine. 575.5 kN. UR-200 stage 2. Developed 1961-64. Staged combustion cycle. Isp=326s. First flight 1964. More...
  • RD-0212 Kosberg N2O4/UDMH rocket engine. 613 kN. Proton stage 3. Engine unit consisting of 1 RD-0213 maine engine and 4 RD-0214 vernier/steering engines. 8D48 essentially similar to 8D411 and 8D412 and has the same combustion chamber. Isp=324s. First flight 1967. More...
  • RD-0211 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 2. Out of Production. Variant of RD-0210 providing tank pressurization. Staged combustion cycle. Isp=326s. More...
  • RD-0210-HC Kosberg Lox/Kerosene rocket engine. 592 kN. Design concept 1990's. Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=342s. More...
  • RD-0210 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Isp=326s. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle. First flight 1965. More...
  • RD-0209 Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Engine unit consisting of 1 RD-0211 for tank pressurization and three RD-0210. Modification of RD-0208 with tank pressurization. Further developed into RD--0211. First flight 1965. More...
  • RD-0208 Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Stage 1 had three RD-0208 plus one RD-0209. Further developed into RD-0210. More...
  • RD-0234 Kosberg N2O4/UDMH rocket engine. 520 kN. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. Modification of RD-0233 including tank pressurization system. Isp=310s. First flight 1974. More...
  • RD-0207 Kosberg N2O4/UDMH rocket engine. 30.9 kN. UR-200 stage 2 vernier. Developed 1961-64. Gas generator cycle. Four vernier thrusters. Isp=297s. First flight 1964. More...
  • RD-0246 Kosberg N2O4/UDMH rocket engine. Design concept. Project for further development of RD-0243. More...
  • RD-0214 Kosberg N2O4/UDMH rocket engine. 30.980 kN. Proton stage 3 vernier. In Production. Based on RD-0207. Four used as steering engines for Proton Stage 3 in system RD-0212. Isp=293s. First flight 1967. More...
  • RD-0244-HC Kosberg Lox/Kerosene rocket engine. 690 kN. Design concept 1990's. Proposed variant of RD-0244 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=332s. More...
  • RD-0410 Kosberg nuclear/lh2 rocket engine. 35.3 kN. Experimental nuclear engine, propellant LH2. Developed 1965-94. Isp=910s. Tested at Semipalatinsk test range in 1980s and was "the only operational nuclear engine in the USSR". First flight 1985. More...
  • RD-0411 Kosberg nuclear/lh2 rocket engine. 392 kN. Full-size nuclear thermal engine. Design concept 1965-94. Planned full-size nuclear thermal engine for Mars expeditions. Never progressed beyond study stage. Isp=900s. More...
  • RD-0600 Kosberg laser rocket engine. Space station "Skif". Developed 1970-85. Gas dynamic laser. Working medium gaseous carbon monoxide + air + nitrogen + ethanol. Flow rate up to 100 kg/s. Tests were performed at NII TP. More...
  • RD-0257 Kosberg N2O4/UDMH rocket engine. R-36M2 / RS-20V (SS-18 Mod-4) stage 2 vernier. Out of Production. Steering engine of system RD-0255. Gas generator cycle. First flight 1987. More...
  • RD-0256-Methane Kosberg Lox/LCH4 rocket engine. 836 kN. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants. Isp=353s. More...
  • RD-0256-HC Kosberg Lox/Kerosene rocket engine. 820 kN. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=344s. More...
  • RD-0256 Kosberg N2O4/UDMH rocket engine. R-36M2 / RS-20V (SS-18 Mod-4) stage 2. Out of Production. Main engine of system RD-0255. Staged combustion cycle. First flight 1987. More...
  • RD-0255 Kosberg N2O4/UDMH rocket engine. 755 kN. R-36M2 / RS-20V (SS-18 Mod-4) stage 2. Comprises of single-chamber main engine RD-0256 plus four-chamber steering engines RD-0257. Development based on RD-0228 with thrust increase by 11%. First flight 1986. More...
  • RD-0251 Kosberg N2O4/UDMH rocket engine. Further development of RD-0236 steering engine for projected modification of stage 2 of classified Chelomei rocket. Development ceased during study phase. Gas generator cycle. More...
  • RD-0250 Kosberg N2O4/UDMH rocket engine. Further development of RD-0235 main engine for projected modification of stage 2 of classified Chelomei rocket. Development ceased during study phase. Staged combustion cycle. More...
  • RD-0245 Kosberg N2O4/UDMH rocket engine. 211 kN. R-29RM / RSM-54 (SS-N-23) stage 1 vernier. Out of Production. Four-chamber steering engine in system RD-0243 driven by turbine exhaust gas. Isp=300s. First flight 1985. More...
  • RD-0201 Kosberg Nitric acid/Amine rocket engine. 58.060 kN. SAM V1100 by Grushin stage 3. Out of Production. Thrust range 59 - 28 kN. Isp=260s. First flight 1960. More...
  • RD-0234-CH Kosberg Lox/LCH4 rocket engine. 442 kN. Developed 1996-. Proposed variant of RD-0234 engine using LOX-liquid methane instead of N2O4/UDMH as propellants. Isp=343s. More...
  • RD-0244 Kosberg N2O4/UDMH rocket engine. 682 kN. R-29RM / RSM-54 (SS-N-23) stage 1. Out of Production. Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank. Isp=310s. First flight 1985. More...
  • RD-0243 Kosberg N2O4/UDMH rocket engine. 825.8 kN. R-29RM stage 1. Out of Production. Isp=300s. Consisted pf single-chamber main engine RD-0244 plus four-chamber steering engines RD-0245 driven by turbine exhaust gas. Engine submerged in propellant tank. More...
  • RD-0242M1 Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998-. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market ?). Reusable for 6 ignitions total. Throttling to 80%. Isp=343s. More...
  • RD-0242M Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998-. Isp=335s. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH. Reusable for 6 ignitions total. Throttling to 80%. More...
  • RD-0242-HC Kosberg Lox/Kerosene rocket engine. 125 kN. Developed 1998-. Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=312s. More...
  • RD-0242 Kosberg N2O4/UDMH rocket engine. 123.6 kN. sea-based missile booster stage developed 1977-83. Isp=302s. First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. Single ignition, 297 development tests. 50 engines for sale. More...
  • RD-0237 Kosberg N2O4/UDMH rocket engine. 4.9 kN. UR-100N / RS-18 (SS-19) stage 3. MIRV service block. Open cycle. Analogous to RD-0225, pressure fed. Steering engine for space vehicles gimbaling +/- 45 degree. Isp=200s. First flight 1972. More...
  • RD-0236 Kosberg N2O4/UDMH rocket engine. 15.760 kN. UR-100N / RS-18 (SS-19) stage 2 vernier. Out of Production. Developed in 1969-1974 / problems not solved until 1978. Vernier engines. Gas generator cycle. Isp=293s. More...
  • RD-0235 Kosberg N2O4/UDMH rocket engine. 240 kN. UR-100N / RS-18 (SS-19) stage 2. Main engine based on RD-0217 with larger nozzle for altitude operation. Staged combustion cycle. Isp=320s. First flight 1972. More...
  • RD-0234-HC Kosberg Lox/Kerosene rocket engine. 516 kN. Developed 1996-. Proposed variant of RD-0234 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=331s. More...
  • RD-0245-HC Kosberg Lox/Kerosene rocket engine. 214 kN. Design concept 1990's. Proposed variant of RD-0245 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=320s. More...
  • RD-0110 Kosberg Lox/Kerosene rocket engine. 297.9 kN. Soyuz 11A511, Molniya-M 8K78M. Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability. Isp=326s. First flight 1964. More...
  • RD-0126 Kosberg lox/lh2 rocket engine. 39.2 kN. Space tugs or upper stage for Onega or Yastreb versions of Soyuz. Isp=476s. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Design concept 1993. Hot-tests in 1998. More...
  • RD-0124M1 Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber with larger nozzle extension compared to RD-0124M. Isp=359s. More...
  • RD-0124M Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber. Isp=348s. More...
  • RD-0124-14D23 Kosberg Lox/Kerosene rocket engine. 298.640 kN. Propoed in 1993 for Angara stage 2 verniers, Kvant-1 stage 1 vernier. Designed 1986-1990. Isp=331s. Variant of RD-0124 with shortened nozzle for sea-level operation. More...
  • RD-0124 Kosberg Lox/Kerosene rocket engine. 294.3 kN. In development. Isp=359s. Engine to succeed RD-0110 in second stage of Soyuz. Used staged combustion; chamber pressure increased from 70 to 160 bar, specific impulse from 326 to 359 seconds First flight 2001. More...
  • RD-0122 Kosberg lox/lh2 rocket engine. 2313 kN. Energia-M core stage. Planned for Angara central stage. Developed 1990-. Isp=460s. Upgrade of RD-0120 engine for Energia-M launcher with increased thrust. Prototype from RD-0120 hardware. More...
  • RD-0120TD Kosberg tri-propellant (lox/lh2/kerosene) rocket engine. 1317 kN. Developed 1990's. Isp=419 / 452s. Experimental version of the RD-0120 engine. Tested by supply of high-pressure kerosene from test bench or adapted existing kerosene pump for tests. More...
  • RD-0120M-CH Kosberg Lox/LCH4 rocket engine. 1720 kN. Design concept 1990's. Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant. Isp=372s. More...
  • RD-0120M Kosberg lox/lh2 rocket engine. 1961 kN. Energia-M core stage. Development ended 1993. Isp=455s. From 1987 KBKhA worked on upgrading the 11D122 (RD-0120) engine for Energia-M launcher, including the possibility to throttle the engine down to 28% thrust. More...
  • RD-0126A Kosberg lox/lh2 rocket engine. 98 kN. Upper stages. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump. Isp=476s. More...
  • RD-0120 Kosberg lox/lh2 rocket engine. 1961 kN. Energia core stage. Design 1987. Isp=455s. First operational Russian cryogenic engine system, built to the same overall performance specifications as America's SSME, but using superior Russian technology. More...
  • RD-0110MD Kosberg Lox/LNG rocket engine. 245 kN. Developed 1994-on. Prototype engine for tests with propellants LOX/liquified natural gas. Tests performed from 30 April 1998 on, test duration 20s. More...
  • RD-0108 Kosberg Lox/Kerosene rocket engine. 297.9 kN. Voskhod 11A57, Molniya 8K78 stage 3. Isp=326s. First flight 1960. More...
  • RD-0107 Kosberg Lox/Kerosene rocket engine. 297.9 kN. R-9, Molniya 8K78, Voskhod 11A57 stage 3. Out of Production. Gas generator cycle. Isp=326s. More...
  • RD-0106 Kosberg Lox/Kerosene rocket engine. 304 kN. R-9 stage 2. Gas generator cycle. Isp=330s. First flight 1961. More...
  • RD-0105 Kosberg Lox/Kerosene rocket engine. 49.4 kN. Luna 8K72, Vostok 8K72 upper stage. Out of production. Isp=316s. Developed jointly with OKB-1 in nine months on the basis of OKB-1'ssteering chamber from the RD-107 engine. First flight 1958. More...
  • RD-0103 Kosberg Lox/Kerosene rocket engine. 34.6 kN. T-3, P-1 aircraft by Sukhoy. Out of Production. Based on RD-0102. Chamber pressure 37.3 - 15.7 bar. Isp=277s. More...
  • RD-0102 Kosberg Lox/Kerosene rocket engine. 39.2 kN. Yak-27V aircraft by Yakovlev. Out of Production. Based on RD-0101. Two ignitions possible. Chamber pressure 41,2 - 16,4 bar. Isp=260s. More...
  • RD-0101 Kosberg Lox/Alcohol rocket engine. 39.2 kN. E-50A aircraft by Mikoyan. Out of Production. Chamber pressure 42,7 - 22,1 bar. Specific impulse 255 - 248,5 sec. Isp=255s. More...
  • RD-0205 Kosberg N2O4/UDMH rocket engine. 606.4 kN. UR-200 stage 2. Engine unit consisting of 1 RD-0206 maine engine and 4 RD-0207 vernier/steering engines. Version of 8D44 and 8D45 with extended nozzle. Developed 1961. Isp=322s. First flight 1963. More...
  • RD-0203 Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. DU consisting of 4 RD-0204 gimballed motors. Staged combustion cycle. Isp=311s. First flight 1964. More...
  • RD-0120-CH Kosberg Lox/LCH4 rocket engine. 1576 kN. Design concept 1990's. Proposed variant of the RD-0120 engine using liquid methane instead of hydrogen as propellant. Isp=363s. More...
  • RD-0155 Kosberg Lox/Kerosene rocket engine. Design concept 2007. Launch thrust 902.5 kN. Engine proposed to replace RD-107 in Onega and Avrora versions of the Soyuz launch vehicle. More...
  • RD-0109 Kosberg Lox/Kerosene rocket engine. 54.520 kN. 8A92 Vostok stage 3, 8K72K stage 3 (block E-Vostok). Out of production. Developed in 15 months. Isp=323s. First flight 1960. More...
  • RD-0126E Kosberg lox/lh2 rocket engine. 39.2 kN. Upper stages. Design concept 1998-. Concept for a cryogenic engine for upper stages. Single annular chamber with straight expansion nozzle, common turbopump. Isp=472s. More...
  • RD-0200 Kosberg Nitric acid/Amine rocket engine. 58.8 kN. Lavochkin SAM, flew 1960. Out of Production. First liquid rocket engine by OKB-154, evolution of Isayev S2.1200 transferred to Kosberg. Thrust range 59 - 5.9 kN. Sea level specific impulse 230 - 166 sec More...
  • RD-0204 Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. Diameter is per chamber. Staged combustion cycle. Variant of RD-0203 with additional pressure sensor. Isp=311s. First flight 1964. More...
  • RD-0154 Kosberg Lox/Kerosene rocket engine. 294.3 kN. Design concept 2007. Engine proposed to replace RD-110 in Avrora improved version of Soyuz launch vehicle. The single chamber engine had a deployable nozzle extension for improved vacuum specific impulse. More...
  • RD-0149 Kosberg Lox/LNG rocket engine. 49 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Variant of RD-0141 with larger nozzle. Isp=370s. More...
  • RD-0146 Kosberg lox/lh2 rocket engine. 98.1 kN. Centaur upper stage (Atlas); high performance upper stages for Onega, Proton, Angara launch vehicles. Design concept 1998-. Isp=463s. More...
  • RD-0145 Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Four-chamber variant of RD-0144. Isp=374s. More...
  • RD-0144 Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Radiation cooled nozzle extension. Isp=374s. More...
  • RD-0143A Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 1. Design concept 1998-. Proposed single chamber variant of RD-0143. Selected for stage 1 of Vozdushnyy Start project by Kompomash. Isp=370s. More...
  • RD-0143 Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 2. Design concept 1998-. Proposed variant of RD-0124, replacing kerosene by liquid natural gas. Selected for stage 2 of Vozdushnyy Start project by Kompomash. Isp=372s. More...
  • RD-0202 Kosberg N2O4/UDMH rocket engine. 2236 kN. UR-200 stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0204 for tank pressurization and three RD-0203. Isp=311s. First flight 1963. More...
  • RD-0141 Kosberg Lox/LNG rocket engine. 2251 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle. Isp=353s. More...
  • RD-0140 Kosberg Lox/LNG rocket engine. 2086 kN. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=349s. More...
  • RD-0139 Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=341s. More...
  • RD-0134 Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle variant of RD-0139. Isp=358s. More...
  • RD-0133 Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Four chambers with bell nozzles, common turbopump. Isp=467s. More...
  • RD-0132M Kosberg Lox/LNG rocket engine. 98 kN. Vozdushnyy Start stage 2. Design concept 1998-. Proposed variant of RD-0132, replacing hydrogen by liquid natural gas. Initially selected for stage 2 of Vozdushnyy Start project by Kompomash. More...
  • RD-0132 Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump. Isp=469s. More...
  • RD-0131 Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump. Isp=467s. More...
  • RD-0142 Kosberg Lox/LNG rocket engine. 2353 kN. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle. Isp=369s. More...
  • RD-0128 Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. One single chamber with bell nozzle, separate turbopumps. Isp=474s. More...
  • RO-31 Kosberg nuclear/lh2 rocket engine. 392 kN. UR-700 Third Stage. Study 1967. Engine proposed for UR-700 third stage to achieve 250 tonne payload to low earth orbit. Probably closely related to RD-0411. More...

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