Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia.
AKA: V P Glushko; OKB456; NPO Energomash imeni V P Glushko.
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11D43 Glushko N2O4/UDMH rocket engine. 1642 kN. Developed 196064. Isp=316s. Lowexpansion 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 19631970. 10 to 12 tonne thrust engine developed for an unstated military requirement. Isp=325s. More...

ED140 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 RD107 engines of the R7. 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 19631970. Largest thrust chamber ever tested in Russia was Glushko's RD270 of 680 tf. More...

KS50 Glushko Lox/Kerosene rocket engine. Experimental. Development 1948. Subscale versions of a radical new engine design. This featured a flatplate injector, cylindrical combustion chamber, and a 60 atmosphere chamber pressure. More...

RD160 Glushko Lox/LCH4 rocket engine. 19.6 kN. Upper stage. Developed 19931996. Isp=380s. Methane version of lox / kerosene upper stage engine RD161. Gimbaling +/ 6 degree in two planes. More...

RD1611 Glushko Lox/Kerosene rocket engine. 19.6 kN. Development ended 2000. Proposed for use on Soyuz M3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=360s. More...

RD1612 Glushko Lox/Kerosene rocket engine. 19.9 kN. Design concept 1990's. Proposed for use on Soyuz M3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=365s. More...

RD161P 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 M3. Version for H2O2 fuel, concentration 9698%. Isp=319s. More...

RD146 Glushko Lox/Kerosene rocket engine. 883 kN. Angara stage 2. Design concept 1993on. Sealevel variant of RD120 engine. Proposed in initial study for Angara by RKK Energia in1993. Kerosene RG1. More...

RD118 Glushko Lox/Kerosene rocket engine. 999.601 kN. In production. Isp=311s. Update of RD107, used in Soyuz ST launcher. Little performance change from RD107, changes may mainly relate to use of allRussian components. First flight 2001. More...

RD120K Glushko Lox/Kerosene rocket engine. 873 kN. Soyuz M stage 1, 2. Proposed for X34. Isp=336s. Sealevel variant of RD120. As of 1996 RD120 prototype with 1.8 m diameter had been built, development time estimated for three years. More...

RD169 Glushko Lox/LCH4 rocket engine. 167 kN. Riksha0 stage 1. Design concept 1990's. Isp=351s. LOX/Methane engine derived from RD120. Gimbaling +/ 8 degree in two planes. In 1996 prototype development was estimated to take four years from goahead. More...

RD167 Glushko Lox/LCH4 rocket engine. 353 kN. Upper stage. Design concept 1990's. Isp=379s. Proposed upper stage engine, a methane variant of RD134. Gimbaling +/ 3 degree in two planes. Four chambers with one common turbopump. More...

RD135 Glushko lox/lh2 rocket engine. upper stage. Developed 1976. Experimental cryogenic engine. (Ref. May be not correct.) More...

RD134R Glushko Lox/Kerosene rocket engine. 343 kN. Angara stage 2 vernier. Design concept 1993on. Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG1. More...

RD120M Glushko Lox/Kerosene rocket engine. 850.4 kN. PacAstro2 stage 1. Out of Production. Sealevel variant of RD120 engine, similar to RD120K. Gimbaling +/ 6 degree in two planes. Isp=330s. More...

RD120.03 Glushko Lox/Kerosene rocket engine. 882 kN. Design concept. Isp=353s. More...

RD120.01 Glushko Lox/Kerosene rocket engine. 784 kN. Design concept. Isp=329s. More...

RD120 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...

RD119 Glushko lox/udmh rocket engine. 105.5 kN. Kosmos 1 stage 2. Out of production. Isp=352s. Derived from RD109 motor originally intended for the second stage of a Lox/UDMH version of the R7. First flight 1961. More...

RD192S Glushko Lox/LCH4 rocket engine. 2128 kN. Developed 1996on. Isp=371s. Proposed variant of RD192. Staged combustion cycle with oxidizerrich gas generator. Gimbaling +/ 8 degree in two planes. More...

RD134 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...

RD185 Glushko Lox/LCH4 rocket engine. 179 kN. Riksha0 stage 2. Developed 1996. Isp=378s. Upper stage version of RD169 with larger nozzle. Gimbaling +/ 4 degree in two planes. More...

RD1KhZ Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. takeoff acelleration of Pe2R, La7R, Yak3, Su6, Su7, La120R airplanes. Developed 194146. The RD1KhZ was a variant of the RD1 engine with chemical ignition. Production 194445. Isp=200s. More...

RD170 Glushko Lox/Kerosene rocket engine. 7903 kN. Energia strapon. Developed 19731985. Isp=337s. First flight 1987. Used oneplane gimablling versus the twoplane gimablling required on the RD171 of the Zenit launch vehicle. Designed for 10 reuses. More...

RD192.3 Glushko Lox/LCH4 rocket engine. 2089 kN. Developed 1996on. Proposed variant of RD192. Gas generator cycle. Gimbaling +/ 8 degree in two planes. Status 1998 was project based on RD191 protoype, development estimated for four years. Isp=341s. More...

RD117PF Glushko Lox/Kerosene rocket engine. manned Soyuzlauncher stage 1. Design concept. Update of RD107. Probably version using Sintin instead of kerosene. More...

RD192 Glushko Lox/LCH4 rocket engine. 2138 kN. Isp=356s. Proposed methanevariant of RD191. Gimbaling +/ 8 degree in two planes. In 1996 prototype development was estimated to take four years from goahead. Nozzle expansion ratio is 262/0.75=349. More...

RD191M Glushko Lox/Kerosene rocket engine. 1976 kN. Angara stage I. Developed 1996. Single chamber version of the RD170 / RD171. Isp=337s. More...

RD192.2 Glushko Lox/LCH4 rocket engine. 1942 kN. Developed 1996on. Isp=354s. Proposed variant of RD192. Staged combustion cycle with fuelrich gas generator. Gimbaling +/ 8 degree in two planes. More...

RD190 Glushko Lox/LCH4 rocket engine. 1000 kN. Riksha0 stage 1. Developed 1996. The RD190 consists of 6 RD169 engines. Each chamber can be gimbaled individually in two planes by +/ 8 degree. Isp=351s. More...

RD171 Glushko Lox/Kerosene rocket engine. 7903 kN. Zenit stage 1. In production. Isp=337s. RD171 used twoplane gimablling versus oneplane gimablling on RD170 developed in parallel for Energia. First flight 1985. More...

RD184 Glushko Lox/LCH4 rocket engine. Developed 1996on. Isp=322s. Attitude correction engine for apogee stage of Riksha1 launcher project (together with RD183). Gimbaling +/ 20 degree in two planes. More...

RD183 Glushko Lox/LCH4 rocket engine. 9.8 kN. Developed 1996. Isp=360s. Main engine for apogee stage of Riksha1 launcher project. Gimbaling +/ 10 degree in two planes. Nozzle expansion ratio is 75/0.055=1364. More...

RD182M Glushko Lox/LNG rocket engine. 882 kN. Vozdushnyy Start stage 1. Developed 1998. Variant of RD182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash. More...

RD182 Glushko Lox/LCH4 rocket engine. 902 kN. Riksha (1, 2) stage 1. Developed 1994. Isp=353s. Methane variant of RD120K engine. Thrust range and Isp range due to throat diameter and chamber pressure. Gimbaling +/ 6 degree in two planes. More...

RD180 Glushko Lox/Kerosene rocket engine. 4152 kN. Atlas III, Atlas V stage 1. In production. Isp=337s. First flight 2000. Twothrustchamber derivative of the fourchamber RD170 used on Zenit. More...

RD174 Glushko Lox/Kerosene rocket engine. 7905 kN. Angara stage I. Developed 1995. More...

RD173 Glushko Lox/Kerosene rocket engine. 8181 kN. Zenit3 stage 1 (?). Design concept 1990's. Uprated version of RD171 with 4 chambers, 1 turbopump and 2 gas generators. Intended for uprated Zenit named Zenit 3 Isp=337s. More...

RD191 Glushko Lox/Kerosene rocket engine. 2079 kN. Isp=337s. Proposed for stage 1 of Angara. Single chamber from 4chamber RD170 would have been cheap and fast to develop. Only reached the draft project stage by 2003. Gimbaling +/ 8 degree in two planes. More...

RD103M Glushko Lox/Alcohol rocket engine. 500.1 kN. R5M 8K51. Isp=248s. First flight 1953. More...

RD1078D74K Glushko Lox/Kerosene rocket engine. 996 kN. Developed in 19571960. Used in strapons for Molniya 8K78, R7A 8K74, Voskhod 11A57, Vostok 8A92, Vostok 8A92M. Isp=313s. Fuel T1 or RG1 kerosene. First flight 1959. More...

RD1078D741959 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...

RD1078D741958 Glushko Lox/Kerosene rocket engine. 996 kN. Luna 8K720. Out of production. Diameter is per chamber. Isp=312s. First flight 1958. More...

RD1078D74 Glushko Lox/Kerosene rocket engine. 971 kN. R7 8K71, Vostok 8K72, Vostok 8K72K strapons. Isp=306s. First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's. More...

RD1078D728 Glushko Lox/Kerosene rocket engine. 996 kN. Molniya 0, Molniya 8K78M0. OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG1 or T1) / Lox. Diameter is per chamber. Isp=314s. First flight 1964. More...

RD10711D511P Glushko Lox/Kerosene rocket engine. 996.4 kN. Soyuz 11A511U20. Out of production. OKB Glushko. Used on 11A511U2 Stage 0. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=314s. First flight 1982. More...

RD1078D74PS Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8K71PS0. Out of Production. OKB Glushko. Used on 8K71PS Stage 0. Developed in 19561957. Flown 19571958. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=306s. More...

RD105 Glushko Lox/Kerosene rocket engine. 627.6 kN. R7 ICBM stage 1 (strapon) initial project. Out of Production. Isp=302s. Single chamber engine intended for the R7 strapons in mid1950s. Subsequently replaced by the 4 chamber RD107. More...

RD106 Glushko Lox/Kerosene rocket engine. 645.3 kN. R7 ICBM stage 2 (core) initial project. Out of Production. Isp=310s. Single chamber engine intended for the R7 sustainer. Version of RD105 with larger nozzle. Subsequently replaced by the 4 chamber RD108. More...

RD103 Glushko Lox/Alcohol rocket engine. 500 kN. R5. Out of Production. Isp=243s. Final extrapolation of the V2 rocket engine in Russia. First flight 1953. More...

RD102 Glushko Lox/Alcohol rocket engine. 428 kN. R3A. Development ended 1951. Project for R3A experimental missile. Stopped in favor of RD103. Isp=235s. More...

RD101 Glushko Lox/Alcohol rocket engine. 404 kN. R2 and V2A. Isp=237s. Developed simultaneously with the RD100 but with no German involvement. More compact, increased thrust, increased chamber pressure and higher alcohol concentration. First flight 1949. More...

RD100 Glushko Lox/Alcohol rocket engine. 304 kN. R1, V1A. Isp=237s. Russian copy of the V2 engine using Russian materials  which made it very difficult! German rocket scientists assisted in its development. First flight 1948. More...

RD1 Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. Takeoff acelleration of Pe2, La7, Yak3, Su6 airplanes. Developed 194145. First Russian liquid propellant rocket engine. Production 194445. Ignition was by an ethaneair mixture. Isp=200s. More...

RD117 Glushko Lox/Kerosene rocket engine. 1021.097 kN. Soyuz ST stage 1. In production. Update of RD107. Little performance change from RD107, changes may mainly relate to use of allRussian components. Isp=310s. First flown 2001. More...

RD172 Glushko Lox/Kerosene rocket engine. 8354 kN. Zenit3 stage 1 (?). Developed 1994. Uprated version of RD171. To have been qualified for flight 1994. Isp=337s. More...

RD10711D511 Glushko Lox/Kerosene rocket engine. 992 kN. Soyuz 11A5110, Soyuz 11A511U0. Design 2000. Diameter is per chamber. Isp=314s. First flight 1965. More...

RD109 Glushko lox/udmh rocket engine. 101.6 kN. Developed 195760. Isp=334s. Intended for second stage of Lox/UDMH 8K73 version of R7. Abandoned because of Korolev's refusal to use such a toxic fuel. Later basis for RD119 used on the Kosmos space launcher. More...

RD103RD Glushko Lox/Alcohol rocket engine. M5RD. Out of Production. More...

RD114 Glushko lox/udmh rocket engine. 1653 kN. Used in ICBM stage 1 (stage 2 was RD115). Developed 196165. Isp=341s. More...

RD1078D76 Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8A910. Out of Production. OKB Glushko. Used on 8A91 Stage 0. Developed in 19561957. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=310s. First flight 1958. More...

RD113 Glushko lox/udmh rocket engine. 1138 kN. ICBM stage 2 (stage 1 was RD112). Developed 1960. Upper stage version of RD112 with larger nozzle. Isp=360s. More...

RD112 Glushko lox/udmh rocket engine. 1089 kN. ICBM stage 1 (stage 2 was RD113). Developed 1960. Isp=344s. More...

RD110 Glushko Lox/Kerosene rocket engine. 1374 kN. Development ended 1949. Isp=285s. For R3 IRBM, 19 ED140 7 tonne chambers used as preburners to feed a main mixing chamber, a scaleup of the V2 production motor. Tested, but technical problems too severe. More...

RD1088D77 Glushko Lox/Kerosene rocket engine. 804 kN. Sputnik 8A911. Out of Production. Diameter is per chamber. Isp=315s. First flight 1958. More...

RD1088D75PS Glushko Lox/Kerosene rocket engine. 912 kN. Sputnik 8K71PS1. Out of Production. Diameter is per chamber. Isp=308s. First flight 1957. More...

RD1088D727K Glushko Lox/Kerosene rocket engine. 976 kN. Molniya 8K783. Out of Production. Isp=316s. More...

RD10811D512 Glushko Lox/Kerosene rocket engine. 997 kN. Soyuz 11A5111, Soyuz 11A511U1. Design 2000. Diameter is per chamber. Isp=315s. First flight 1965. More...

RD111 Glushko Lox/Kerosene rocket engine. 1628 kN. R9 stage 1. Isp=317s. Developed for R9 ICBM. It had special flexible pipelines and gimbals, allowing lox loading in 20 minutes. First flight 1961. More...

RD1088D727 Glushko Lox/Kerosene rocket engine. 977 kN. Molniya 1, Molniya 8K78M1. OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG1 or T1) / Lox. Diameter is per chamber. Isp=316s. First flight 1964. More...

RD115 Glushko lox/udmh rocket engine. 1726 kN. ICBM stage 2 (stage 1 was RD114). Developed 196165. Upper stage version of RD114 with larger nozzle. Isp=357s. More...

RD1088D75 Glushko Lox/Kerosene rocket engine. 912 kN. R7 8K711, Vostok 8K721, Vostok 8K72K1. OKB Glushko. Used on 8K71 R7 Stage 1. Developed in 19541955. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=308s. First flight 1957. More...

RD1088D751958 Glushko Lox/Kerosene rocket engine. 941 kN. Luna 8K721. Out of production. Diameter is per chamber. Isp=315s. First flight 1958. More...

RD1088D751959 Glushko Lox/Kerosene rocket engine. 941 kN. Out of production. Further development of 8D741958, 19581959. Diameter is per chamber. Isp=315s. Used on Vostok 8K72K launch vehicle. First flight 1960. More...

RD1088D75K Glushko Lox/Kerosene rocket engine. 941 kN. Molniya 8K781, R7A 8K741, Voskhod 11A571, Vostok 8A921, Vostok 8A92M1. Diameter is per chamber. Isp=315s. First flight 1959. More...

RD10811D512P Glushko Lox/Kerosene rocket engine. 1011 kN. Soyuz 11A511U21. Out of production. Isp=319s. A 12 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. First flight 1982. More...

RD262 Glushko N2O4/UDMH rocket engine. 941 kN. Tsyklon 3 stage 2. In production. Based on RD252 Isp=317s. First flight 1977. More...

RD280 Glushko N2O4/Aerozine50 rocket engine. 117.6 kN. Experimental engine. Study 1961. Experimental engine using Aerozine 50 (50% UDMH + 50% hydrazine) as fuel. Isp=350s. More...

RD252 Glushko N2O4/UDMH rocket engine. 940.5 kN. R360 stage 2; Tsyklon 2 stage 2. In production. Used modified chamber from RD219, nozzle is conventional, so performance is higher. Isp=317s. First flight 1965. More...

RD253 Glushko N2O4/UDMH rocket engine. 1745 kN. In Production. Version of RD253 with thrust increased by 7%. Included an additional gas generator for tank pressurization. First flight 1986. More...

RD25311D48 Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD253s provide the first stage power for the UR500 Proton launch vehicle. First flown in 1965. More...

RD25314D14 Glushko N2O4/UDMH rocket engine. 1746 kN. Proton KM1. In production. Developed in 1990s. Isp=317s. First flight 1999. More...

RD253UR700 Glushko N2O4/UDMH rocket engine. 1745 kN. Designed 19641968. UR700 Stage 3. Development of RD253 with increased expansion ratio for upper stage use. More...

RD254 Glushko N2O4/UDMH rocket engine. 1716 kN. N1 upper stage, UR700 stage 3. Study 1961. Proposed for use in N1. High altitude version of RD253 for 2nd stages. First flight 1974. More...

RD261 Glushko N2O4/UDMH rocket engine. 3032 kN. Tsyklon 3 stage 1. In production. Based on RD251 Isp=301s. First flight 1977. More...

RD263 Glushko N2O4/UDMH rocket engine. 1155 kN. R36M / RS20A (SS18 Mod 1) stage 1. Out of Production. Four RD263 engines combined into RD264 system. Isp=318s. More...

RD263F Glushko N2O4/UDMH rocket engine. Developed 1980. Project to upgrade RD263. Upgrade was realized in RD273 engine. More...

RD264 Glushko N2O4/UDMH rocket engine. 4521 kN. R36M / RS20A (SS18 Mod 1) stage 1. Consists of four RD263 engines. Isp=318s. Used on Dnepr launch vehicle. First flight 1986. More...

RD268 Glushko N2O4/UDMH rocket engine. 1236 kN. MRUR100 / RS16 (SS17) stage 1. Out of Production. First flight 1976. Modification of RD263 engine. Isp=319s. First flight 1990. More...

RD270 Glushko N2O4/UDMH rocket engine. 6713 kN. UR700, R56 stage 1. Development ended 1968. Isp=322s. Developed 19621971, largest rocket engine ever built in the Soviet Union, answer to F1. Tested but cancelled before combustion instability problems solved. More...

RD270M Glushko exotic N2O4/Pentaborane rocket engine. 7159 kN. Isp=365s. In 19621970 Glushko studied use of Pentaborane 'zip' propellants in his monster RD270 engine. Created immense toxicity problems but increased specific impulse of the engine by 42 seconds. More...

RD273 Glushko N2O4/UDMH rocket engine. 1238 kN. Developed 197582. Upgrade of RD263 in 1982 based on RD263F project. More...

RD275 Glushko N2O4/UDMH rocket engine. 1745 kN. Proton stage 1. In Production. Uprated version of RD253, developed in the 1980's. Isp=317s. First flight 1986. More...

RD251 Glushko N2O4/UDMH rocket engine. 2643 kN. R360 stage 1, Tsyklon 2 stage 1. In production. Assembly of 3 RD250type units. Isp=301s. First flight 1965. More...

RD223 Glushko Nitric acid/UDMH rocket engine. 1697 kN. missile stage 2 (stage 1 used RD222). Developed 196061. Precursor to RD253. Isp=314s. More...

RD274 Glushko N2O4/UDMH rocket engine. 4952 kN. Developed 197585. Upgrade of RD264 engine with increased chamber pressure and thrust. Development stopped due to problems with turbopump shaft balance. More...

RD214 Glushko Nitric acid/Kerosene rocket engine. 730 kN. R12, Kosmos 11K63 stage 1. Isp=264s. Single turbopump driven by H2O2 gas generator feeding four fixed chambers. Ignition with propellant TG02. First flight 1957. More...

RD225 Glushko Nitric acid/UDMH rocket engine. 889 kN. R26 stage 1. Out of Production. Two clustered together to make RD224. Isp=294s. First flight 1961. More...

RD2 Glushko Nitric acid/Kerosene rocket engine. 6 kN. experimental. Developed 194547. The RD2 was based on the RD1 engine. Used chemical ignition. Isp=200s. More...

RD200 Glushko Nitric acid/Kerosene rocket engine. 98.508 kN. vertical sounding rocket. Developed 1951. Isp=234s. More...

RD210 Glushko Nitric acid/Kerosene rocket engine. 29.850 kN. vertical sounding rocket. Developed 1954. Isp=241s. More...

RD211 Glushko Nitric acid/Kerosene rocket engine. 642.3 kN. longdistance missile. Developed 195255. Original fourchamber engine design planned for use on the R12 IRBM. Abandoned due to limited thrust and the RD214 was developed in its place. Isp=261s. More...

RD250 Glushko N2O4/UDMH rocket engine. 881 kN. R360 stage 1, Tsyklon 2 stage 1. Out of Production. Assembly of 3 RD250 units make RD251. Isp=301s. More...

RD213 Glushko Nitric acid/Kerosene rocket engine. 755 kN. Winged rocket M40 (2). Development ended 1957. Two thrust levels. Ignition with propellant TG02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level. Isp=254s. More...

RD215 Glushko Nitric acid/UDMH rocket engine. 864 kN. R14, Kosmos 11K63 stage 1. Out of Production. Original intended use unknown. Two RD215 clustered to make RD216. Isp=291s. First flight 1966. More...

RD221 Glushko Nitric acid/UDMH rocket engine. 1118 kN. missile stage 2 (stage 1 used RD220). Developed 1960. Isp=318s. More...

RD212 Glushko Nitric acid/Kerosene rocket engine. 623 kN. Developed 195256. Isp=253s. Original fourchamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust; RD213 was developed instead. More...

RD222 Glushko Nitric acid/UDMH rocket engine. 1634 kN. missile stage 1 (stage 2 used RD223). Developed 196061. Precursor to RD253. Isp=302s. More...

RD216 Glushko Nitric acid/UDMH rocket engine. 1728 kN. R14, Kosmos 11K65 stage 1. Isp=291s. RD216 was an assembly of 2 RD215's with 2 combustion chambers and 2 turbines. Two sets of these were in turn used in the first stage of the R14. First flight 1964. More...

RD220 Glushko Nitric acid/UDMH rocket engine. 1074 kN. missile stage 1 (stage 2 used RD221). Developed 1960. Isp=306s. More...

RD219 Glushko Nitric acid/UDMH rocket engine. 883 kN. R16 stage 2. Isp=293s. Derivative of RD217 with a truss and piping changes. Despite higher expansion ratio, engine was shorter than first stage version, with relatively low performance. Flown 19601972. More...

RD218 Glushko Nitric acid/UDMH rocket engine. 2592 kN. R16 stage 1. Isp=289s. Consisted of three RD217; had 6 combustion chambers and 3 turbines; powered the R16 ICBM. First flight 1960. More...

RD217 Glushko Nitric acid/UDMH rocket engine. 865 kN. R16 stage 1. Out of Production. Original intended use unknown. Three RD217 clustered to make RD218. Isp=289s. First flight 1961. More...

RD216M Glushko Nitric acid/UDMH rocket engine. Kosmos3M stage I. Out of Production. More...

RD224 Glushko Nitric acid/UDMH rocket engine. 1778 kN. R26 stage 1. Out of production. RD224 is a block of 2 RD225s. An upper stage thrust chamber was developed under designation U102000. Isp=294s. First flight 1961. More...

RD3A Glushko Lox/Alcohol rocket engine. R3A. Out of Production. Project for R3A experimental missile. Stopped in favour of RD103. More...

RD3 Glushko Nitric acid/Kerosene rocket engine. 9 kN. experimental. Developed 1950's. The RD3 was a cluster of three RD1 engines with a new common turbopump. Ignition was by an ethaneair mixture. Isp=190s. More...

RD301 Glushko exotic LF2/Ammonia rocket engine. 96.670 kN. Proton K stage 4. Developed 196577. Developed by Glushko beginning in 1965. Planned for use in Proton K4H high energy upper stage. Motor tested but never flown. Isp=400s. First flight 1977. More...

RD302 Glushko exotic LF2/Ammonia rocket engine. 98 kN. Developed 196069. Successor to RD303 and predecessor to RD301. Staged combustion cycle. Isp=405s. More...

RD303 Glushko exotic LF2/Ammonia rocket engine. Developed 196065. Predecessor to RD302 and RD301. More...

RD350 Glushko exotic LF2/LH2 rocket engine. 98 kN. Design concept 1963. Studied by Glushko as engine concept with highenergy propellants. Isp=464s. More...

RD410 Glushko nuclear/lh2 rocket engine. 68 kN. UR700M concept. Developed 1960s. More...

RD502 Glushko H2O2/Pentaborane rocket engine. 98.1 kN. Experimental upper stage engine. Developed 196066. Isp=380s. Experimental upper stage engine. Program stopped due to toxicity of propellants. Intended for Proton upper stage. First flight 1966. More...

RD510 Glushko H2O2/CxHy rocket engine. Developed 196575. First flight 1975. More...

RD510T Glushko H2O2/CxHy rocket engine. Developed 196575. First flight 1975. More...

RD511 Glushko H2O2/CxHy rocket engine. Developed 196575. First flight 1975. More...

RD550 Glushko exotic rocket engine. 98.060 kN. Experimental upper stage engine. Developed 196370. Isp=400s. Propellants Lox/30% Beryllium+Pentaborane in 70% Hydrazine. More...

RD600 Glushko nuclear/lh2 rocket engine. 1960 kN. Isp=2000s. Gas core nuclear engine worked developed 19621970 for use in second stage of twostage interplanetary rockets. More...

RD701 Glushko lox/lh2/kerosene tripropellant rocket engine for airlaunched MAKS spaceplane. 4003 kN. Development ended 1988. Isp=415 / 460s. First flight 2001. More...

RD704 Glushko Lox/Kerosene/LH2 tripropellant engine. 1966 kN. Developed 1990's. Isp=407 / 452 s. Tripropellant engine, single chamber, derived from RD701 project. Chamber pressure 294 / 124 bar. First flight 1999. More...

RKDS100 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...

RLA600 Glushko Lox/Kerosene rocket engine. 6370 kN. Design 1972. Twochamber version of RLA300. Proposed for the RLA series launch vehicles and the UR700M Mars booster. More...

RLA1200 Glushko Lox/Kerosene rocket engine. 12,700 kN. Design 1974. Proposed engines for the RLA series launch vehicles. This version would use four chambers. 'Downsized' to 200 tonnes thrust for Energia. More...

RLA300 Glushko Lox/Kerosene rocket engine. 3187 kN. Design 1974. Proposed for the RLA series launch vehicles and the UR700M Mars booster. Following rejection of RLA, design 'downsized' to 200 tonnes thrust for Energia and Zenit. More...

U102000 Glushko Nitric acid/UDMH rocket engine. 468 kN. R26 stage 2. Out of production. Isp=307s. More...

YaRD OKB456 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

R8 Russian intercontinental ballistic missile. Glushko project 1956 for multistage 650t ICBM powered by Lox/UDMH. More...

R10 Russian heavylift orbital launch vehicle. Glushko booster  1500t, Korolev I evo delo p. 307 More...

R20 Russian orbital launch vehicle. Glushko booster  2000t, Korolev I evo delo p. 307 More...
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