Encyclopedia Astronautica
Glushko


Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia.

AKA: V P Glushko; OKB-456; NPO Energomash imeni V P Glushko.

More... - Chronology...


Associated Countries
Associated Engines
  • 11D43 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. More...
  • 8D725 Glushko N2O4/UDMH rocket engine. 117 kN. Developed 1963-1970. 10 to 12 tonne thrust engine developed for an unstated military requirement. Isp=325s. More...
  • ED-140 Glushko rocket engine. 68 kN. Glushko built this experimental engine, the next phase of the German Lilliput concept, in 1951. Configuration led to the successful RD-107 engines of the R-7. More...
  • Glushko C Glushko storable lqiuid rocket engine. 29,400 kN. Study 1970. Glushko studied liquid propellant engines of 'several thousand tonnes thrust' in the period 1963-1970. Largest thrust chamber ever tested in Russia was Glushko's RD-270 of 680 tf. More...
  • KS-50 Glushko Lox/Kerosene rocket engine. Experimental. Development 1948. Subscale versions of a radical new engine design. This featured a flat-plate injector, cylindrical combustion chamber, and a 60 atmosphere chamber pressure. More...
  • RD-160 Glushko Lox/LCH4 rocket engine. 19.6 kN. Upper stage. Developed 1993-1996. Isp=380s. Methane version of lox / kerosene upper stage engine RD-161. Gimbaling +/- 6 degree in two planes. More...
  • RD-161-1 Glushko Lox/Kerosene rocket engine. 19.6 kN. Development ended 2000. Proposed for use on Soyuz M-3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=360s. More...
  • RD-161-2 Glushko Lox/Kerosene rocket engine. 19.9 kN. Design concept 1990's. Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=365s. More...
  • RD-161P Glushko H2O2/Kerosene rocket engine. 24.5 kN. Soyuz M stage 3 (block LM). Developed 1993-. Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%. Isp=319s. More...
  • RD-146 Glushko Lox/Kerosene rocket engine. 883 kN. Angara stage 2. Design concept 1993-on. Sea-level variant of RD-120 engine. Proposed in initial study for Angara by RKK Energia in1993. Kerosene RG-1. More...
  • RD-118 Glushko Lox/Kerosene rocket engine. 999.601 kN. In production. Isp=311s. Update of RD-107, used in Soyuz ST launcher. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. First flight 2001. More...
  • RD-120K Glushko Lox/Kerosene rocket engine. 873 kN. Soyuz M stage 1, 2. Proposed for X-34. Isp=336s. Sea-level variant of RD-120. As of 1996 RD-120 prototype with 1.8 m diameter had been built, development time estimated for three years. More...
  • RD-169 Glushko Lox/LCH4 rocket engine. 167 kN. Riksha-0 stage 1. Design concept 1990's. Isp=351s. LOX/Methane engine derived from RD-120. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. More...
  • RD-167 Glushko Lox/LCH4 rocket engine. 353 kN. Upper stage. Design concept 1990's. Isp=379s. Proposed upper stage engine, a methane variant of RD-134. Gimbaling +/- 3 degree in two planes. Four chambers with one common turbopump. More...
  • RD-135 Glushko lox/lh2 rocket engine. upper stage. Developed -1976. Experimental cryogenic engine. (Ref. May be not correct.) More...
  • RD-134R Glushko Lox/Kerosene rocket engine. 343 kN. Angara stage 2 vernier. Design concept 1993-on. Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG-1. More...
  • RD-120M Glushko Lox/Kerosene rocket engine. 850.4 kN. PacAstro-2 stage 1. Out of Production. Sea-level variant of RD-120 engine, similar to RD-120K. Gimbaling +/- 6 degree in two planes. Isp=330s. More...
  • RD-120.03 Glushko Lox/Kerosene rocket engine. 882 kN. Design concept. Isp=353s. More...
  • RD-120.01 Glushko Lox/Kerosene rocket engine. 784 kN. Design concept. Isp=329s. More...
  • RD-120 Glushko Lox/Kerosene rocket engine. 833 kN. Zenit stage 2. In production. Isp=350s. High altitude engine used in the Zenit second stage. First production Russian engine to be test fired in the United States (3 test burns were made). First flight 1985. More...
  • RD-119 Glushko lox/udmh rocket engine. 105.5 kN. Kosmos 1 stage 2. Out of production. Isp=352s. Derived from RD-109 motor originally intended for the second stage of a Lox/UDMH version of the R-7. First flight 1961. More...
  • RD-192S Glushko Lox/LCH4 rocket engine. 2128 kN. Developed 1996-on. Isp=371s. Proposed variant of RD-192. Staged combustion cycle with oxidizer-rich gas generator. Gimbaling +/- 8 degree in two planes. More...
  • RD-134 Glushko Lox/Kerosene rocket engine. 343 kN. upper stage. Design concept. Isp=357s. Proposed upper stage kerosene engine. Gimbaling +/- 3 degree in two planes. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400. More...
  • RD-185 Glushko Lox/LCH4 rocket engine. 179 kN. Riksha-0 stage 2. Developed 1996-. Isp=378s. Upper stage version of RD-169 with larger nozzle. Gimbaling +/- 4 degree in two planes. More...
  • RD-1KhZ Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. take-off acelleration of Pe-2R, La-7R, Yak-3, Su-6, Su-7, La-120R airplanes. Developed 1941-46. The RD-1KhZ was a variant of the RD-1 engine with chemical ignition. Production 1944-45. Isp=200s. More...
  • RD-170 Glushko Lox/Kerosene rocket engine. 7903 kN. Energia strap-on. Developed 1973-1985. Isp=337s. First flight 1987. Used one-plane gimablling versus the two-plane gimablling required on the RD-171 of the Zenit launch vehicle. Designed for 10 reuses. More...
  • RD-192.3 Glushko Lox/LCH4 rocket engine. 2089 kN. Developed 1996-on. Proposed variant of RD-192. Gas generator cycle. Gimbaling +/- 8 degree in two planes. Status 1998 was project based on RD-191 protoype, development estimated for four years. Isp=341s. More...
  • RD-117PF Glushko Lox/Kerosene rocket engine. manned Soyuz-launcher stage 1. Design concept. Update of RD-107. Probably version using Sintin instead of kerosene. More...
  • RD-192 Glushko Lox/LCH4 rocket engine. 2138 kN. Isp=356s. Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. Nozzle expansion ratio is 262/0.75=349. More...
  • RD-191M Glushko Lox/Kerosene rocket engine. 1976 kN. Angara stage I. Developed 1996-. Single chamber version of the RD-170 / RD-171. Isp=337s. More...
  • RD-192.2 Glushko Lox/LCH4 rocket engine. 1942 kN. Developed 1996-on. Isp=354s. Proposed variant of RD-192. Staged combustion cycle with fuel-rich gas generator. Gimbaling +/- 8 degree in two planes. More...
  • RD-190 Glushko Lox/LCH4 rocket engine. 1000 kN. Riksha-0 stage 1. Developed 1996-. The RD-190 consists of 6 RD-169 engines. Each chamber can be gimbaled individually in two planes by +/- 8 degree. Isp=351s. More...
  • RD-171 Glushko Lox/Kerosene rocket engine. 7903 kN. Zenit stage 1. In production. Isp=337s. RD-171 used two-plane gimablling versus one-plane gimablling on RD-170 developed in parallel for Energia. First flight 1985. More...
  • RD-184 Glushko Lox/LCH4 rocket engine. Developed 1996-on. Isp=322s. Attitude correction engine for apogee stage of Riksha-1 launcher project (together with RD-183). Gimbaling +/- 20 degree in two planes. More...
  • RD-183 Glushko Lox/LCH4 rocket engine. 9.8 kN. Developed 1996-. Isp=360s. Main engine for apogee stage of Riksha-1 launcher project. Gimbaling +/- 10 degree in two planes. Nozzle expansion ratio is 75/0.055=1364. More...
  • RD-182M Glushko Lox/LNG rocket engine. 882 kN. Vozdushnyy Start stage 1. Developed 1998-. Variant of RD-182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash. More...
  • RD-182 Glushko Lox/LCH4 rocket engine. 902 kN. Riksha (-1, -2) stage 1. Developed 1994-. Isp=353s. Methane variant of RD-120K engine. Thrust range and Isp range due to throat diameter and chamber pressure. Gimbaling +/- 6 degree in two planes. More...
  • RD-180 Glushko Lox/Kerosene rocket engine. 4152 kN. Atlas III, Atlas V stage 1. In production. Isp=337s. First flight 2000. Two-thrust-chamber derivative of the four-chamber RD-170 used on Zenit. More...
  • RD-174 Glushko Lox/Kerosene rocket engine. 7905 kN. Angara stage I. Developed 1995-. More...
  • RD-173 Glushko Lox/Kerosene rocket engine. 8181 kN. Zenit-3 stage 1 (?). Design concept 1990's. Uprated version of RD-171 with 4 chambers, 1 turbo-pump and 2 gas generators. Intended for uprated Zenit named Zenit 3 Isp=337s. More...
  • RD-191 Glushko Lox/Kerosene rocket engine. 2079 kN. Isp=337s. Proposed for stage 1 of Angara. Single chamber from 4-chamber RD-170 would have been cheap and fast to develop. Only reached the draft project stage by 2003. Gimbaling +/- 8 degree in two planes. More...
  • RD-103M Glushko Lox/Alcohol rocket engine. 500.1 kN. R-5M 8K51. Isp=248s. First flight 1953. More...
  • RD-107-8D74K Glushko Lox/Kerosene rocket engine. 996 kN. Developed in 1957-1960. Used in strap-ons for Molniya 8K78, R-7A 8K74, Voskhod 11A57, Vostok 8A92, Vostok 8A92M. Isp=313s. Fuel T-1 or RG-1 kerosene. First flight 1959. More...
  • RD-107-8D74-1959 Glushko Lox/Kerosene rocket engine. 996 kN. Out of production. Diameter is per chamber. Isp=313s. Used on Vostok 8K72K launch vehicle. First flight 1960. More...
  • RD-107-8D74-1958 Glushko Lox/Kerosene rocket engine. 996 kN. Luna 8K72-0. Out of production. Diameter is per chamber. Isp=312s. First flight 1958. More...
  • RD-107-8D74 Glushko Lox/Kerosene rocket engine. 971 kN. R-7 8K71, Vostok 8K72, Vostok 8K72K strap-ons. Isp=306s. First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's. More...
  • RD-107-8D728 Glushko Lox/Kerosene rocket engine. 996 kN. Molniya 0, Molniya 8K78M-0. OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=314s. First flight 1964. More...
  • RD-107-11D511P Glushko Lox/Kerosene rocket engine. 996.4 kN. Soyuz 11A511U2-0. Out of production. OKB Glushko. Used on 11A511U2 Stage 0. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=314s. First flight 1982. More...
  • RD-107-8D74PS Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8K71PS-0. Out of Production. OKB Glushko. Used on 8K71PS Stage 0. Developed in 1956-1957. Flown 1957-1958. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=306s. More...
  • RD-105 Glushko Lox/Kerosene rocket engine. 627.6 kN. R-7 ICBM stage 1 (strap-on) initial project. Out of Production. Isp=302s. Single chamber engine intended for the R-7 strap-ons in mid-1950s. Subsequently replaced by the 4 chamber RD-107. More...
  • RD-106 Glushko Lox/Kerosene rocket engine. 645.3 kN. R-7 ICBM stage 2 (core) initial project. Out of Production. Isp=310s. Single chamber engine intended for the R-7 sustainer. Version of RD-105 with larger nozzle. Subsequently replaced by the 4 chamber RD-108. More...
  • RD-103 Glushko Lox/Alcohol rocket engine. 500 kN. R-5. Out of Production. Isp=243s. Final extrapolation of the V-2 rocket engine in Russia. First flight 1953. More...
  • RD-102 Glushko Lox/Alcohol rocket engine. 428 kN. R-3A. Development ended 1951. Project for R-3A experimental missile. Stopped in favor of RD-103. Isp=235s. More...
  • RD-101 Glushko Lox/Alcohol rocket engine. 404 kN. R-2 and V-2A. Isp=237s. Developed simultaneously with the RD-100 but with no German involvement. More compact, increased thrust, increased chamber pressure and higher alcohol concentration. First flight 1949. More...
  • RD-100 Glushko Lox/Alcohol rocket engine. 304 kN. R-1, V-1A. Isp=237s. Russian copy of the V-2 engine using Russian materials - which made it very difficult! German rocket scientists assisted in its development. First flight 1948. More...
  • RD-1 Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. Take-off acelleration of Pe-2, La-7, Yak-3, Su-6 airplanes. Developed 1941-45. First Russian liquid propellant rocket engine. Production 1944-45. Ignition was by an ethane-air mixture. Isp=200s. More...
  • RD-117 Glushko Lox/Kerosene rocket engine. 1021.097 kN. Soyuz ST stage 1. In production. Update of RD-107. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. Isp=310s. First flown 2001. More...
  • RD-172 Glushko Lox/Kerosene rocket engine. 8354 kN. Zenit-3 stage 1 (?). Developed -1994. Uprated version of RD-171. To have been qualified for flight 1994. Isp=337s. More...
  • RD-107-11D511 Glushko Lox/Kerosene rocket engine. 992 kN. Soyuz 11A511-0, Soyuz 11A511U-0. Design 2000. Diameter is per chamber. Isp=314s. First flight 1965. More...
  • RD-109 Glushko lox/udmh rocket engine. 101.6 kN. Developed 1957-60. Isp=334s. Intended for second stage of Lox/UDMH 8K73 version of R-7. Abandoned because of Korolev's refusal to use such a toxic fuel. Later basis for RD-119 used on the Kosmos space launcher. More...
  • RD-103RD Glushko Lox/Alcohol rocket engine. M5RD. Out of Production. More...
  • RD-114 Glushko lox/udmh rocket engine. 1653 kN. Used in ICBM stage 1 (stage 2 was RD-115). Developed 1961-65. Isp=341s. More...
  • RD-107-8D76 Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8A91-0. Out of Production. OKB Glushko. Used on 8A91 Stage 0. Developed in 1956-1957. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=310s. First flight 1958. More...
  • RD-113 Glushko lox/udmh rocket engine. 1138 kN. ICBM stage 2 (stage 1 was RD-112). Developed 1960. Upper stage version of RD-112 with larger nozzle. Isp=360s. More...
  • RD-112 Glushko lox/udmh rocket engine. 1089 kN. ICBM stage 1 (stage 2 was RD-113). Developed 1960. Isp=344s. More...
  • RD-110 Glushko Lox/Kerosene rocket engine. 1374 kN. Development ended 1949. Isp=285s. For R-3 IRBM, 19 ED-140 7 tonne chambers used as preburners to feed a main mixing chamber, a scale-up of the V-2 production motor. Tested, but technical problems too severe. More...
  • RD-108-8D77 Glushko Lox/Kerosene rocket engine. 804 kN. Sputnik 8A91-1. Out of Production. Diameter is per chamber. Isp=315s. First flight 1958. More...
  • RD-108-8D75PS Glushko Lox/Kerosene rocket engine. 912 kN. Sputnik 8K71PS-1. Out of Production. Diameter is per chamber. Isp=308s. First flight 1957. More...
  • RD-108-8D727K Glushko Lox/Kerosene rocket engine. 976 kN. Molniya 8K78-3. Out of Production. Isp=316s. More...
  • RD-108-11D512 Glushko Lox/Kerosene rocket engine. 997 kN. Soyuz 11A511-1, Soyuz 11A511U-1. Design 2000. Diameter is per chamber. Isp=315s. First flight 1965. More...
  • RD-111 Glushko Lox/Kerosene rocket engine. 1628 kN. R-9 stage 1. Isp=317s. Developed for R-9 ICBM. It had special flexible pipelines and gimbals, allowing lox loading in 20 minutes. First flight 1961. More...
  • RD-108-8D727 Glushko Lox/Kerosene rocket engine. 977 kN. Molniya 1, Molniya 8K78M-1. OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=316s. First flight 1964. More...
  • RD-115 Glushko lox/udmh rocket engine. 1726 kN. ICBM stage 2 (stage 1 was RD-114). Developed 1961-65. Upper stage version of RD-114 with larger nozzle. Isp=357s. More...
  • RD-108-8D75 Glushko Lox/Kerosene rocket engine. 912 kN. R-7 8K71-1, Vostok 8K72-1, Vostok 8K72K-1. OKB Glushko. Used on 8K71 R-7 Stage 1. Developed in 1954-1955. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=308s. First flight 1957. More...
  • RD-108-8D75-1958 Glushko Lox/Kerosene rocket engine. 941 kN. Luna 8K72-1. Out of production. Diameter is per chamber. Isp=315s. First flight 1958. More...
  • RD-108-8D75-1959 Glushko Lox/Kerosene rocket engine. 941 kN. Out of production. Further development of 8D74-1958, 1958-1959. Diameter is per chamber. Isp=315s. Used on Vostok 8K72K launch vehicle. First flight 1960. More...
  • RD-108-8D75K Glushko Lox/Kerosene rocket engine. 941 kN. Molniya 8K78-1, R-7A 8K74-1, Voskhod 11A57-1, Vostok 8A92-1, Vostok 8A92M-1. Diameter is per chamber. Isp=315s. First flight 1959. More...
  • RD-108-11D512P Glushko Lox/Kerosene rocket engine. 1011 kN. Soyuz 11A511U2-1. Out of production. Isp=319s. A 1-2 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. First flight 1982. More...
  • RD-262 Glushko N2O4/UDMH rocket engine. 941 kN. Tsyklon 3 stage 2. In production. Based on RD-252 Isp=317s. First flight 1977. More...
  • RD-280 Glushko N2O4/Aerozine-50 rocket engine. 117.6 kN. Experimental engine. Study 1961. Experimental engine using Aerozine 50 (50% UDMH + 50% hydrazine) as fuel. Isp=350s. More...
  • RD-252 Glushko N2O4/UDMH rocket engine. 940.5 kN. R-36-0 stage 2; Tsyklon 2 stage 2. In production. Used modified chamber from RD-219, nozzle is conventional, so performance is higher. Isp=317s. First flight 1965. More...
  • RD-253 Glushko N2O4/UDMH rocket engine. 1745 kN. In Production. Version of RD-253 with thrust increased by 7%. Included an additional gas generator for tank pressurization. First flight 1986. More...
  • RD-253-11D48 Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle. First flown in 1965. More...
  • RD-253-14D14 Glushko N2O4/UDMH rocket engine. 1746 kN. Proton KM-1. In production. Developed in 1990s. Isp=317s. First flight 1999. More...
  • RD-253-UR-700 Glushko N2O4/UDMH rocket engine. 1745 kN. Designed 1964-1968. UR-700 Stage 3. Development of RD-253 with increased expansion ratio for upper stage use. More...
  • RD-254 Glushko N2O4/UDMH rocket engine. 1716 kN. N-1 upper stage, UR-700 stage 3. Study 1961. Proposed for use in N-1. High altitude version of RD-253 for 2nd stages. First flight 1974. More...
  • RD-261 Glushko N2O4/UDMH rocket engine. 3032 kN. Tsyklon 3 stage 1. In production. Based on RD-251 Isp=301s. First flight 1977. More...
  • RD-263 Glushko N2O4/UDMH rocket engine. 1155 kN. R-36M / RS-20A (SS-18 Mod 1) stage 1. Out of Production. Four RD-263 engines combined into RD-264 system. Isp=318s. More...
  • RD-263F Glushko N2O4/UDMH rocket engine. Developed 1980. Project to upgrade RD-263. Upgrade was realized in RD-273 engine. More...
  • RD-264 Glushko N2O4/UDMH rocket engine. 4521 kN. R-36M / RS-20A (SS-18 Mod 1) stage 1. Consists of four RD-263 engines. Isp=318s. Used on Dnepr launch vehicle. First flight 1986. More...
  • RD-268 Glushko N2O4/UDMH rocket engine. 1236 kN. MR-UR-100 / RS-16 (SS-17) stage 1. Out of Production. First flight 1976. Modification of RD-263 engine. Isp=319s. First flight 1990. More...
  • RD-270 Glushko N2O4/UDMH rocket engine. 6713 kN. UR-700, R-56 stage 1. Development ended 1968. Isp=322s. Developed 1962-1971, largest rocket engine ever built in the Soviet Union, answer to F-1. Tested but cancelled before combustion instability problems solved. More...
  • RD-270M Glushko exotic N2O4/Pentaborane rocket engine. 7159 kN. Isp=365s. In 1962-1970 Glushko studied use of Pentaborane 'zip' propellants in his monster RD-270 engine. Created immense toxicity problems but increased specific impulse of the engine by 42 seconds. More...
  • RD-273 Glushko N2O4/UDMH rocket engine. 1238 kN. Developed 1975-82. Upgrade of RD-263 in 1982 based on RD-263F project. More...
  • RD-275 Glushko N2O4/UDMH rocket engine. 1745 kN. Proton stage 1. In Production. Uprated version of RD-253, developed in the 1980's. Isp=317s. First flight 1986. More...
  • RD-251 Glushko N2O4/UDMH rocket engine. 2643 kN. R-36-0 stage 1, Tsyklon 2 stage 1. In production. Assembly of 3 RD-250-type units. Isp=301s. First flight 1965. More...
  • RD-223 Glushko Nitric acid/UDMH rocket engine. 1697 kN. missile stage 2 (stage 1 used RD-222). Developed 1960-61. Precursor to RD-253. Isp=314s. More...
  • RD-274 Glushko N2O4/UDMH rocket engine. 4952 kN. Developed 1975-85. Upgrade of RD-264 engine with increased chamber pressure and thrust. Development stopped due to problems with turbopump shaft balance. More...
  • RD-214 Glushko Nitric acid/Kerosene rocket engine. 730 kN. R-12, Kosmos 11K63 stage 1. Isp=264s. Single turbopump driven by H2O2 gas generator feeding four fixed chambers. Ignition with propellant TG-02. First flight 1957. More...
  • RD-225 Glushko Nitric acid/UDMH rocket engine. 889 kN. R-26 stage 1. Out of Production. Two clustered together to make RD-224. Isp=294s. First flight 1961. More...
  • RD-2 Glushko Nitric acid/Kerosene rocket engine. 6 kN. experimental. Developed 1945-47. The RD-2 was based on the RD-1 engine. Used chemical ignition. Isp=200s. More...
  • RD-200 Glushko Nitric acid/Kerosene rocket engine. 98.508 kN. vertical sounding rocket. Developed -1951. Isp=234s. More...
  • RD-210 Glushko Nitric acid/Kerosene rocket engine. 29.850 kN. vertical sounding rocket. Developed -1954. Isp=241s. More...
  • RD-211 Glushko Nitric acid/Kerosene rocket engine. 642.3 kN. long-distance missile. Developed 1952-55. Original four-chamber engine design planned for use on the R-12 IRBM. Abandoned due to limited thrust and the RD-214 was developed in its place. Isp=261s. More...
  • RD-250 Glushko N2O4/UDMH rocket engine. 881 kN. R-36-0 stage 1, Tsyklon 2 stage 1. Out of Production. Assembly of 3 RD-250 units make RD-251. Isp=301s. More...
  • RD-213 Glushko Nitric acid/Kerosene rocket engine. 755 kN. Winged rocket M-40 (2). Development ended 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level. Isp=254s. More...
  • RD-215 Glushko Nitric acid/UDMH rocket engine. 864 kN. R-14, Kosmos 11K63 stage 1. Out of Production. Original intended use unknown. Two RD-215 clustered to make RD-216. Isp=291s. First flight 1966. More...
  • RD-221 Glushko Nitric acid/UDMH rocket engine. 1118 kN. missile stage 2 (stage 1 used RD-220). Developed 1960-. Isp=318s. More...
  • RD-212 Glushko Nitric acid/Kerosene rocket engine. 623 kN. Developed 1952-56. Isp=253s. Original four-chamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust; RD-213 was developed instead. More...
  • RD-222 Glushko Nitric acid/UDMH rocket engine. 1634 kN. missile stage 1 (stage 2 used RD-223). Developed 1960-61. Precursor to RD-253. Isp=302s. More...
  • RD-216 Glushko Nitric acid/UDMH rocket engine. 1728 kN. R-14, Kosmos 11K65 stage 1. Isp=291s. RD-216 was an assembly of 2 RD-215's with 2 combustion chambers and 2 turbines. Two sets of these were in turn used in the first stage of the R-14. First flight 1964. More...
  • RD-220 Glushko Nitric acid/UDMH rocket engine. 1074 kN. missile stage 1 (stage 2 used RD-221). Developed 1960-. Isp=306s. More...
  • RD-219 Glushko Nitric acid/UDMH rocket engine. 883 kN. R-16 stage 2. Isp=293s. Derivative of RD-217 with a truss and piping changes. Despite higher expansion ratio, engine was shorter than first stage version, with relatively low performance. Flown 1960-1972. More...
  • RD-218 Glushko Nitric acid/UDMH rocket engine. 2592 kN. R-16 stage 1. Isp=289s. Consisted of three RD-217; had 6 combustion chambers and 3 turbines; powered the R-16 ICBM. First flight 1960. More...
  • RD-217 Glushko Nitric acid/UDMH rocket engine. 865 kN. R-16 stage 1. Out of Production. Original intended use unknown. Three RD-217 clustered to make RD-218. Isp=289s. First flight 1961. More...
  • RD-216M Glushko Nitric acid/UDMH rocket engine. Kosmos-3M stage I. Out of Production. More...
  • RD-224 Glushko Nitric acid/UDMH rocket engine. 1778 kN. R-26 stage 1. Out of production. RD-224 is a block of 2 RD-225s. An upper stage thrust chamber was developed under designation U102-000. Isp=294s. First flight 1961. More...
  • RD-3A Glushko Lox/Alcohol rocket engine. R-3A. Out of Production. Project for R-3A experimental missile. Stopped in favour of RD-103. More...
  • RD-3 Glushko Nitric acid/Kerosene rocket engine. 9 kN. experimental. Developed 1950's. The RD-3 was a cluster of three RD-1 engines with a new common turbopump. Ignition was by an ethane-air mixture. Isp=190s. More...
  • RD-301 Glushko exotic LF2/Ammonia rocket engine. 96.670 kN. Proton K stage 4. Developed 1965-77. Developed by Glushko beginning in 1965. Planned for use in Proton K-4H high energy upper stage. Motor tested but never flown. Isp=400s. First flight 1977. More...
  • RD-302 Glushko exotic LF2/Ammonia rocket engine. 98 kN. Developed 1960-69. Successor to RD-303 and predecessor to RD-301. Staged combustion cycle. Isp=405s. More...
  • RD-303 Glushko exotic LF2/Ammonia rocket engine. Developed 1960-65. Predecessor to RD-302 and RD-301. More...
  • RD-350 Glushko exotic LF2/LH2 rocket engine. 98 kN. Design concept 1963-. Studied by Glushko as engine concept with high-energy propellants. Isp=464s. More...
  • RD-410 Glushko nuclear/lh2 rocket engine. 68 kN. UR-700M concept. Developed 1960s. More...
  • RD-502 Glushko H2O2/Pentaborane rocket engine. 98.1 kN. Experimental upper stage engine. Developed 1960-66. Isp=380s. Experimental upper stage engine. Program stopped due to toxicity of propellants. Intended for Proton upper stage. First flight 1966. More...
  • RD-510 Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975. More...
  • RD-510T Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975. More...
  • RD-511 Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975. More...
  • RD-550 Glushko exotic rocket engine. 98.060 kN. Experimental upper stage engine. Developed 1963-70. Isp=400s. Propellants Lox/30% Beryllium+Pentaborane in 70% Hydrazine. More...
  • RD-600 Glushko nuclear/lh2 rocket engine. 1960 kN. Isp=2000s. Gas core nuclear engine worked developed 1962-1970 for use in second stage of two-stage interplanetary rockets. More...
  • RD-701 Glushko lox/lh2/kerosene tripropellant rocket engine for air-launched MAKS spaceplane. 4003 kN. Development ended 1988. Isp=415 / 460s. First flight 2001. More...
  • RD-704 Glushko Lox/Kerosene/LH2 tripropellant engine. 1966 kN. Developed 1990's. Isp=407 / 452 s. Tripropellant engine, single chamber, derived from RD-701 project. Chamber pressure 294 / 124 bar. First flight 1999. More...
  • RKDS-100 Glushko Lox/Kerosene rocket engine. 980 kN. Keldysh Bomber. Design 1946. Nominal design engine for 1946 Keldysh bomber design. The Soviet Union would not produce an engine with these propellants and thrust levels until nearly 20 years later. Isp=285s. More...
  • RLA-600 Glushko Lox/Kerosene rocket engine. 6370 kN. Design 1972. Two-chamber version of RLA-300. Proposed for the RLA series launch vehicles and the UR-700M Mars booster. More...
  • RLA-1200 Glushko Lox/Kerosene rocket engine. 12,700 kN. Design 1974. Proposed engines for the RLA series launch vehicles. This version would use four chambers. 'Down-sized' to 200 tonnes thrust for Energia. More...
  • RLA-300 Glushko Lox/Kerosene rocket engine. 3187 kN. Design 1974. Proposed for the RLA series launch vehicles and the UR-700M Mars booster. Following rejection of RLA, design 'down-sized' to 200 tonnes thrust for Energia and Zenit. More...
  • U102-000 Glushko Nitric acid/UDMH rocket engine. 468 kN. R-26 stage 2. Out of production. Isp=307s. More...
  • YaRD OKB-456 Glushko nuclear/ammonia rocket engine. 1373 kN. Development ended 1960. Isp=470s. Used nuclear reactor in cylindrical housing, operating at 3000 deg K. Propellant heated in the reactor and exhausted through four expansion nozzles More...

See also
Associated Launch Vehicles
  • R-8 Russian intercontinental ballistic missile. Glushko project 1956 for multistage 650t ICBM powered by Lox/UDMH. More...
  • R-10 Russian heavy-lift orbital launch vehicle. Glushko booster - 1500t, Korolev I evo delo p. 307 More...
  • R-20 Russian orbital launch vehicle. Glushko booster - 2000t, Korolev I evo delo p. 307 More...

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