Engine,Mfr Name,Govt Designation,Other Name,Type,Designer,Application,Developed in,Chambers,Thrust(vac)-kN,Thrust(sl)-kN,Mass Engine-kg,Diameter-m,Length-m,Chamber Pressure-bar,Area Ratio,Propellant,Isp-sec,Isp (sea level)-sec,Burn time-sec,Oxidizer to Fuel Ratio,Country,References,Notes
11B97,,11B97,,Electric,Korolev,Interorbital Tug project,1986-,1,0.0004494,,,,,,,Xenon,3000,1,57600000,,Russia,"21, 89","Beginning in 1978 the 11B97 nuclear electric engine was studied for use in a reusable interorbital space tug for launch by Energia-Buran.  In 1982, according to the decree of 5 February 1981, NPO Energia developed for the Ministry of Defence the inte"
11D121,,11D121,,Lox/Hydrocarbon,Korolev,N-1 stage 1 (block A) roll control engine,1969-74,1,68.65,,,,,71.6,,GOX/Kerosene,313,273,,,Russia,"342, 344","Gimbaling +/- 45 degree. Propellants are fed from main engine (NK-15, NK-33) turbopumps."
11D423,,11D423,,Storable liquid,Izotov,LK-700S manned lunar spacecraft project ascent stage,1963-67,,134,,,,,,,N2O4/UDMH,326,,,,Russia,"319, 344","Krasniy Oktyabr Joint Stock Company, St. Petersburg, built for ascent stage of Chelomei LK-700S manned lunar project. Engines for UR-100 stage 2 and LK-700 probably identical; maybe had same designation. Gas generator cycle; 2 large turbine exhaust p"
11D428,,11D428,,Storable liquid,Melnikov,Yantar-2K orbital propulsion,,1,0.11,,,,,,,N2O4/UDMH,,,10000,,Russia,69,"Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions."
11D43,,11D43,,Storable liquid,Glushko,UR-500 stage 1 original concept,1960-64,1,1688.45,,,,,,,N2O4/UDMH,308,278,115,,Russia,273,Low-expansion ratio gimbaled variant developed for UR-500 stage 1. In initial configuration 4 x 8D43 would be clustered with 4 x Glushko 11D43. Abandoned in favor of 6 x 11D48 by Glushko.
11D430,,11D430,,Storable liquid,Melnikov,Yantar-2K orbital propulsion,,1,29.43,,,,,9,,N2O4/UDMH,307,,600,,Russia,69,"Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 50 ignitions."
11D431,,11D431,,Storable liquid,Melnikov,Yantar-2K orbital propulsion,,1,0.00588,,,,,,,N2O4/UDMH,,,2000,,Russia,69,"Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 150,000 ignitions."
11D445,,11D445,,Storable liquid,Melnikov,Yantar-2K descent propulsion,,1,0.065,,,,,,,N2O4/UDMH,,,900,,Russia,69,"Propulsion system of the Yantar-2K military satellite descent capsule. Up to 10,000 ignitions. Thrust from 0,065 - 0,012 kN."
11D446,,11D446,,Storable liquid,Melnikov,Yantar-2K orbital propulsion,,4,0.052,,,,,,,N2O4/UDMH,,,4000,,Russia,69,"Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions."
11D458,,,,Storable liquid,Isayev,Rokot-3 Briz; Soyuz-2 Briz; Proton Briz-M vernier,,1,0.392,,,,,,,N2O4/UDMH,252,,3200,2,Russia,409,"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."
11D49,,11D49,S5.23,Storable liquid,Isayev,Kosmos-3M stage 2,1960-64,1 + 4,157.5,51.8,185,1.92,1.78,98.1,103.4,AK27I/UDMH,303,,4305,2.65,Russia,"320, 342",Engine has one main and four steering nozzles. Thrust 157.5 + 4 x 25 kN. Precessor was 11D47 in R-14 (derivative ?) stage 2.
11D51F,,11D51F,,Lox/Hydrocarbon,Kuznetsov,N1F 1965 - A,1965,1,1918,,,,,,,Lox/Kerosene,331,296,,,Russia,283,"As described in N1 improvement study, 1965. Block A engine thrust increased."
11D51M,,11D51M,,Lox/Hydrocarbon,Kuznetsov,N1M 1965 - A,1965,1,2843,,,,,,,Lox/Kerosene,346,,,,Russia,283,"As described in N1 improvement study, 1965. Huge modification of Block A engines - sea level thrust increased from 175 tonnes thrust to 250 tonnes."
11D52F,,11D52F,,Lox/Hydrocarbon,Kuznetsov,N1F 1965 - B,1965,1,1961,,,,,,,Lox/Kerosene,347,,,,Russia,283,"As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t."
11D52M,,11D52M,,Lox/Hydrocarbon,Kuznetsov,N1M 1965 - B,1965,1,2745,,,,,,,Lox/Kerosene,330,296,,,Russia,283,"As per N1 improvement study, 1965. Thrust increased to 280 tonnes per engine."
11D53F,,11D53F,,Lox/Hydrocarbon,Kuznetsov,N1F 1965 - V,1965,1,612,,,,,,,Lox/Kerosene,346,,,,Russia,283,"As per N1 improvement study, 1965. Engine thrust increased and stretched propellant tanks resulting in 20% longer burn time."
11D53M,,11D53M,,Lox/Hydrocarbon,Kuznetsov,N1M 1965 - V,1965,1,735,,,,,,,Lox/Kerosene,347,,,,Russia,283,"As per N1 improvement study, 1965. Further increase in thrust of Block V engines."
11D79,,11D79,,Storable liquid,Stepanov,Blok D SOZ,1964-67,,44,,,,,,,N2O4/UDMH,,,,,Russia,,Thrust 1.1-4.5 tf variable.
15D305,,15D305,,Solid,Tsurilnikov,RT-23 stage I,1976-85,,0.0098,,,,,,,Solid,,,,,Russia,,
15D339,,15D339,,Solid,Tsurilnikov,RT-23 stage II,1976-85,,,,,,,,,Solid,,,,,Russia,,
17D11,,17D11,,Lox/Hydrocarbon,Korolev,Buran OMS and verniers,1976-88,1,86.3,,230,1.17,2.27,79.4,189,Lox/Kerosene,362,,680,2.42,Russia,"95, 315","Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT-200K"
17D12,,17D12,,Lox/Hydrocarbon,Korolev,Buran OMS,1976-88,1,86.3,,230,1.17,2.27,79.4,189,Lox/Kerosene,362,,680,2.42,Russia,"95, 315","Version of RD-58 for Buran orbital propulsion system 17D11. Uses synthetic kerosene ('Sintin') for higher specific impulse. Some data differ for 17D12 in Energia 92 compared to RD-58S (Energia 92): Area Ratio 192, Ivac 362 s, pc 78.5 bar. 15 ignition"
17D15,,17D15,,Lox/Hydrocarbon,Korolev,Buran OMS large verniers.,1976-88,1,4,,,,,,50,GOX/Sintin,295,,10800,,Russia,"95, 315",Large verniers for Buran orbital propulsion system 17D11. Uses synthetic kerosene ('Sintin') for high specific impulse. Oxygen is gaseous in system. Pulse mode up to 8 Hz with 180 s spec. impulse. Area ratio 19.8 - 50.
17D58E,,17D58E,,Storable liquid,Isayev,Rokot-3 Briz; Soyuz-2 Briz; Proton Briz-M vernier,,1,0.0133,,,,,,,N2O4/UDMH,247,,3200,2,Russia,"293, 409",High performance storable liquid engine. Manufactured by Isayev. Small attitude control thruster in Briz upper stage propulsion system S5.98M. Minimum impulse 0.068 kg-s. Specific impulse also reported as 270 sec.
17D61,,17D61,,Storable liquid,Melnikov,Ikar stage 4 for Soyuz-Ikar,,1 + 4 + 4 + 8,29.43,,820,2.72,2.56,9,,N2O4/UDMH,325.5,,600,,Russia,"69, 345, 346","Derived from propulsion module of Yantar spysat, over 30 flights to 1998. Ikar upper stage upgrades the Soyuz LV, replaces Block L; increased versatility due to capability for 50 restarts. Engine thrusts: 1 x 2943 N  +  4 x 110 N  +  4 x 52 N  +  8 x"
293-P,,,,Solid,Kartukov,P-70 Ametist,1959-68,,,,,,,,,Solid,,,,,Russia,,
4D10,,4D10,,Storable liquid,Isayev,R-27 / RSM-25 (SS-N-6),,1 + 4,255,,,,,,,N2O4/UDMH,,,,,Russia,"319, 340, 342",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.
8D415K,,8D415K,,Lox/Hydrocarbon,Kosberg,Concept for N-1,1960-,1,1471,,,,,,,Lox/Kerosene,,,,,Russia,344,Designed for use in N-1. Development canceled when Korolev turned to Kuznetsov for R-9 and N-1 engines after continuous rows with Glushko over performance and propellant types.
8D423,,8D423,,Storable liquid,Izotov,UR-100 stage 2,,1,131,,,,,,,N2O4/UDMH,325,,184,,Russia,293,"Single chamber engine for UR-100 stage 2. Gas generator cycle with two large turbine exhaust pipes. Photos available in Russian Arms Cat. (Gives thrust as 15,200 kgf, Ispvac=326))"
8D43,,8D43,,Storable liquid,Kosberg,UR-500 stage 1 original concept,,1,559,,,,,147,28.5,N2O4/UDMH,316,283.5,115,2.6,Russia,"273, 320",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 + 11D43,,8D43 + 11D43,,Storable liquid,Kosberg,UR-500 stage 1 original concept,,1,2247.45,,,,,,,N2O4/UDMH,310,280,115,,Russia,273,Originally the first stage of the Proton was designed for 4 x fixed 11D43 and 4 x gimballed Kosberg 8D43 (see separate entries for each engine for details of those engines). This configuration was replaced by 6 x 11D48 from Glushko.
8D725,,8D725,,Storable liquid,Glushko,,1963-1970,1,117,,,,,,,N2O4/UDMH,325,,,,Russia,283,10 to 12 tonne thrust engine developed for an unstated military requirement.
8D726,,,,Lox/Hydrocarbon,Korolev,GR-1 stage 3,,1,66.7,,,,,,,Lox/T-1,,,,,Russia,21,Development based on S1.5400.
8D726,,8D726,,Lox/Hydrocarbon,Korolev,"GR-1 Stage 3, N-11GR - V",,1,66,,,,,,,Lox/Kerosene,350,,380,,Russia,,
A6-12,,,,Storable liquid,Dushkin,V-600,1955-62,2,39,,,,,,,,,,,,Russia,,Thrust variable 1500 - 4000 kgf.
Burlak Stage 1,,,,Storable liquid,,Burlak stage 1,,1,360,,,,,,,N2O4/UDMH,320,270,140,,Russia,,"Masses, thrust, specific impulse estimated based on total vehicle mass of 28.5 tonnes and first stage burn time of 140 seconds. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions."
Burlak Stage 2,,,,Storable liquid,,Burlak stage 2,,1,98,,,,,,,N2O4/UDMH,330,230,275,,Russia,,"Masses, thrust, specific impulse estimated based on total vehicle mass of 28.5 tonnes and first stage burn time of 140 seconds. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions."
D-1,,,,Monopropellant,Kosberg,,1955-56,1,39,,,,,35.3,,OT-152,,210,,,Russia,309,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.
D-18T,,,,Turbofan,Lotarev,An-225,,1,229.4,203.9,4500,,,,,Air/Kerosene,9000,8000,3375,,Ukraine,303,
D-7,,,,Monopropellant,Kosberg,Missile by Toropov,1956,1,11.8,,,,,29.4,,OT-152,,200,6,,Russia,309,Intended for air-air missile by I I Toropov. Uncooled thrust chamber.  Sea level thrust 11.8 kN.
DMT-600,,,,Storable liquid,Isayev,,,1,0.6,,4.2,,,9,46.5,N2O4/UDMH,300.8,,5000,1.85,Russia,350,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 6,000 ignitions"
DMT-600 MMH,,,,Storable liquid,Isayev,Hermes,,1,0.6,,4.2,,,9,46.5,N2O4/MMH,305.9,,5000,1.65,Russia,350,"Version of DMT-600 using MMH in place of UDMH, adaptation to western market (was discussed for European Hermes space plane project). 6,000 ignitions"
DOK-10,,,,Monopropellant,Isayev,,,1,0.01,,0.6,,,10,46,Hydrazine,229.4,,1500,,Russia,350,"Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions"
DOK-50,,,,Monopropellant,Isayev,,,1,0.05,,1.1,,,8,42,Hydrazine,229.4,,1500,,Russia,350,"Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions"
DOT-25,,,,Monopropellant,Isayev,,,1,0.025,,1.3,,,4.5,55,Hydrazine,234.5,,25000,,Russia,350,"Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions"
DOT-5,,,,Monopropellant,Isayev,,,1,0.005,,0.9,,,3.8,60,Hydrazine,230,,120000,,Russia,350,"Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 550,000 ignitions"
DST-100,,,,Storable liquid,Isayev,,,1,0.1,,1.1,,,15,43,N2O4/UDMH,276,,10000,1.85,Russia,350,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions"
DST-100A,,,,Storable liquid,Isayev,,,1,0.1,,1.5,,,7.7,100,N2O4/UDMH,304,,50000,1.85,Russia,350,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime in comparison to DST-100. 450,0000 ignitions"
DST-200,,,,Storable liquid,Isayev,,,1,0.2,,1.3,,,15,43,N2O4/UDMH,280,,5000,1.85,Russia,350,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions"
DST-200A,,,,Storable liquid,Isayev,,,1,0.2,,1.7,,,7,100,N2O4/UDMH,300,,10000,1.85,Russia,350,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime in comparison to DST-200. 100,0000 ignitions"
DST-25,,,,Storable liquid,Isayev,,,1,0.025,,0.9,,,8,45,N2O4/UDMH,285,,25000,1.85,Russia,350,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 300,000 ignitions"
Dushkin 3M9,,,,Solid,Dushkin,3M9 Kub,,,,,,,,,,Solid,,,,,Russia,,
EKR Ramjet,,,,Ramjet,Bondaryuk,EKR Stage 2,1953-54,1,6.13,,,,,,,Air/Kerosene,1580,,800,,Russia,21,Study for an experimental winged cruise missile. Not developed but formed basis for Burya and Buran missiles. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point.
Isayev 218,,,,Storable liquid,Isayev,218 (S-25 system),,,,,,,,,,AK27I/TG-02,,,,,Russia,,
Isayev DOS-3/4,,,,Storable liquid,Isayev,DOS-3/4,1972-74,,3.92,,,,,,,AK27I/UDMH,,,,,Russia,,
Isayev P-15,,,,Storable liquid,Isayev,P-15 Termit,1955-60,1,11.9,,,,,,,AK20K/TG-02,,,,,Russia,"342, 344",Designation unknown. Thrust range 11.895-5.43 kN.
Isayev Polet/IS,,,,Storable liquid,Isayev,Polet/IS,1960-63,,3.92,,,,,,,N2O4/UDMH,,,,,Russia,,
Isayev R-17,,,,Storable liquid,Isayev,R-17,1958-64,1,131.2,,120,0.77,1.49,,,AK27I/TM185,,,,,Russia,"342, 344",Designation unknown.
Isayev TKS attitude,,,,Storable liquid,Isayev,"TKS, Almaz",1972-77,,0.39,,,,,,,N2O4/UDMH,,,,,Russia,,
Isayev V-750V,,,,Storable liquid,Isayev,SAM-missile V-750V,1954-57,1,30.4,,43,0.476,0.926,,,AK20K/TG-02,,,,,Russia,"342, 344",Designation unknown.
Izotov LK-700,,,,Storable liquid,Izotov,LK-700,1966-69,1,131,,,,,,,N2O4/UDMH,,,,,Russia,,
Izotov UR-100 stage 2 vernier,,,,Storable liquid,Izotov,UR-100 stage II vernier,1963-67,4,58,,,,,,,N2O4/UDMH,,,,,Russia,,
Kartukov LL,,,,Solid,Kartukov,"LL-1, LL-2, LL-3",1946-48,,14.7,,,,,,,Solid,,,,,Russia,,
Kartukov P-15M,,,,Solid,Kartukov,P-15M,,,,,,,,,,Solid,,,,,Russia,,
Kartukov P-35,,,,Solid,Kartukov,P-35,1956-62,,294,,,,,,,Solid,,,,,Russia,,
Kartukov P-5,,,,Solid,Kartukov,P-5,1954-59,,179,,,,,,,Solid,,,,,Russia,,
Kartukov P-6,,,,Solid,Kartukov,P-6,1956-64,,,,,,,,,Solid,,,,,Russia,,
Kartukov Soyuz SAS,,,,Solid,Kartukov,"Soyuz 7K-OK, Soyuz 7KT-OK, Soyuz 7K-T",1962-66,,785,,,,,,,Solid,,,,,Russia,,Thrust 76 tf at cutout - 80.1tf at ignition.
Kartukov Soyuz T - TM SAS 17k,,,,Solid,Kartukov,"Soyuz T, Soyuz TM",-1979,,171,,,,,,,Solid,,,,,Russia,,Thrust 10 tf at cutout - 17.5 at ignition.
Kartukov Soyuz T - TM SAS 73k,,,,Solid,Kartukov,"Soyuz T, Soyuz TM",-1979,,715,,,,,,,Solid,,,,,Russia,,Thrust 45 tf at cutout - 73 tf at ignition.
KDU-414,KTDU-414,11D414,S5.19,Storable liquid,Isayev,"Molniya 1, Mars 1, Venera 1, Zond 2-3 maneuvering engine",1960-65,1,1.961,,61,0.74,1.02,11.8,,AK20F/UDMH,272,,40,2.6,Russia,"225, 321, 342, 344",Spacecraft maneuvering engine.
KDU-426,KDU-426,11D426,,Storable liquid,Isayev,Soyuz-T orbital correction engine,1968-74,1,3.089,,270,2.1,1.235,8.8,,N2O4/UDMH,292,,570,1.85,Russia,"314, 329, 344",Pressure-fed engine. Used as long duration engine for correction orbits of satellites.
KRD-442,KRD-442,11D442,,Storable liquid,Isayev,"Orbital propulsion engine for Kvant, Kvant-2, Kristall, Spektr, Priroda, FGB",1972-77,1,4.38,,52,0.46,0.729,,,N2O4/UDMH,,,,,Russia,"309, 314, 342, 344","Main and low-thrust mode. Operation of turbopump without chamber made it possible to pump propellants into tanks (e.g. from Progress), Thrust regimes 4.38 kN / 0.17 kN."
KRD-604,KRD-604,,,Storable liquid,Dushkin,,-1941,,,,,,,,,Solid/Liquid,,,,,Russia,,"The KRD-604 engine was developed in the late 1930s by OKB Dushkin. It was a combined (powder+liquid) engine, characterized by a new technical approach."
KRD-61,KRD-61,,S5.61,Storable liquid,Isayev,Luna Ye-8,1968-70,1,18.8,,41.8,0.545,0.714,92.2,,N2O4/UDMH,313,,53,1.84,Russia,"225, 321, 329, 342",Spacecraft maneuvering engine for ascent stage of Luna moon sample return missions.
KRD-79,KRD-79,,S5.79,Storable liquid,Isayev,"Salyut 6, 7and Mir orbital propulsion maneuvering engine",,1,3.09,,38.5,0.84,0.55,,,N2O4/UDMH,,,,,Russia,"342, 344",Probably derived from engine of propulsion system KDU-426. Pressure fed engine.
KRR-300,,,,Storable liquid,Dushkin,G-300,1955-62,3,98,,,,,,,,,,,,Russia,,Thrust variable 0.1 / 3.0 / 10 tf.
KTDU-35,KTDU-35,11D62,S5.35 + S5.60,Storable liquid,Isayev,"Soyuz maneuvering engine, Salyut 4",1962-67,1 + 2,4.09,,305,2.5,1.136,39.2,,AK27I/UDMH,280,,500,1.85,Russia,"314, 321, 342",Spacecraft maneuvering engine. KTDU-53 version in Soyuz L-1 circumlunar spacecraft; KTDU-66 in Salyut 1 space station. Thrusts 4.09 kN main + 4.03 kN secondary.
KTDU-417,KTDU-417,11D417,KRD-417,Storable liquid,Isayev,Luna 15-24 descent stage,,1 + 2,18.92,,80.6,0.73,0.79,83,,AK27I/UDMH,314,,650,1.8,Russia,"225, 321, 329, 342, 344","Comprises turbopump-fed high-thrust engine with data given in this entry, plus low-thrust engine, see entry KTDU-417-B. Eleven ignitions for lunar orbit insertion and orbit corrections. Two different oxidizers named."
KTDU-417-B,KTDU-417-B,11D417B,,Storable liquid,Isayev,Luna 15-24 low thrust engine in system KTDU-417,,2,3.43,,,,,8.9,,N2O4/UDMH,254,,30,2.4,Russia,"321, 329, 342",Pressure-fed engine. Used as low thrust engine in system KTDU-417 for soft-landing. Could be throttled to 2.06 kN/2440 m/s.See entry KTDU-417.
KTDU-425,KTDU-425,11D425,,Storable liquid,Isayev,Mars 2 and 3 maneuver engine,1970-73,1,18.85,,,,,133.2,,N2O4/UDMH,312,,560,1.9,Russia,"329, 344","Pump-fed engine. Could be throttled to 7.05 kN / 9.5 MPa / 2850 m/s. . Chamber pressure 133,2 - 95 bar."
KTDU-425A,KTDU-425A,11D425A,,Storable liquid,Isayev,"Mars 4-7, Venera 9-16, Vega 1-2, and Phobos 1-2 maneuvering engine",1972-75,1,18.89,,70,0.7,0.71,149,,N2O4/UDMH,315,,560,1.9,Russia,"225, 329, 321, 342, 344",Spacecraft maneuvering engine. Could be throttled to 9.86/9.5/2870. Chamber pressure 149 - 95 bar.
KTDU-53,KTDU-53,,S5.53,Storable liquid,Isayev,Zond 4-7 maneuvering engine,1962-67,1,4.089,,,2.5,1.136,39.2,,AK27I/UDMH,280,,,1.85,Russia,321,"Spacecraft maneuvering engine, derivative of KTDU-35 without back-up engine. "
KTDU-5A,KTDU-5A,,"S5.5,  S5.5A",Storable liquid,Isayev,"Luna E-6, Luna E-6LF, Luna E-6LS, Luna E-6M, Luna E-6S",,1 + 3,45.5,,48,1.7,1.908,62.8,43.4,AK271/TG-02,287,117,43,3.6,Russia,"85, 225, 320, 329, 342, 344","1st turbopump engine with surface tension propellant management devices in tanks, allowing re-ignition in Zero-G. 3 fixed steering thrusters using the turbine exhaust gas for attitude control. Thrusts 45,5 + 0,245 kN. System mass 138,2 kg incl. tanks"
KTDU-66,KTDU-66,,S5.66,Storable liquid,Isayev,Salyut 1,1970-71,1 + 2,4.09,,305,2.5,1.136,39.2,,AK27I/UDMH,280,,1000,1.85,Russia,"321, 344","Spacecraft maneuvering engine, derivative of KTDU-35. Longer burn time of 1000 s. Comprises single-chamber main engine plus dual-chamber back-up engine. Thrusts 4.09 + 4.03 kN."
KTDU-80,KTDU-80,,S5.80,Storable liquid,Isayev,"Soyuz TM, Progress M",-1977,1,6.19,,310,2.1,1.204,8.8,153.8,N2O4/UDMH,302,,890,1.85,Russia,"314, 336","Propulsion system includes 4 spherical tanks for a total of 880 kg propellant. Developed from NII Mash experimental thruster, 3 thrust levels by 4 valves: 6000 N, 0.7 N, 0.3 N. Specific impulse 326 - 286 sec."
MIHT-1,,,,Solid,,Start-1,,1,980.6,887.4,,1.61,8.5,,,Solid,263,238,60,,Russia,42,Used in Start-1. Estimated values.
MIHT-2,,,,Solid,,Start-2,,1,490.3,385.3,,1.55,6,,,Solid,280,220,64,,Russia,42,Used in Start-2. Estimated values.
MIHT-3,,,,Solid,,Start-3,,1,245.2,192.6,,1.5,3,,,Solid,280,220,56,,Russia,42,Used in Start-3. Estimated values.
MIHT-4,,,,Solid,,Start-4,,1,9.8,,,1.4,2.5,,,Solid,295,,207,,Russia,42,Used in Start-4. Estimated values.
NII 612 kgf,,,RDMT-XX,Storable liquid,NII Mash,experimental 612.25 kgf / 0.071 tf / 0.031tf,,1,6,,,,,,,N2O4/UDMH,286,,,,Russia,336,"Experimental thruster, 3 thrust levels by 4 valves: 6000 N, 0.7 N, 0.3 N. Specific impulse 326 - 286 sec."
NK-15,NK-15,11D51,,Lox/Hydrocarbon,Kuznetsov,N-1 stage 1 (block A),1962-72,1,1544,1526,1247,1.5,2.7,78.5,,Lox/Kerosene,318,297,,2.52,Russia,341,On the basis of NK-9 the NK-15 was developed for the N-1 launcher. 30 were used on the Block A (Stage 1) of the N-1.
NK-15F,NK-15F,,,Lox/Hydrocarbon,Kuznetsov,N-1 variant stage 1 (block A),,1,2180,,,,,,,Lox/Kerosene,350,290,,,Russia,275,"Improved version of NK-15. 24 NK-15F to be used on the Block A (Stage 1) of a studied variant of N-1. That engine had only a very short nozzle, the 24 engines around the periphery were to expand along a common central plug."
NK-15V,NK-15V,11D52V,,Lox/Hydrocarbon,Kuznetsov,N-1 stage 2 (block B),1962-72,1,1648,,1345,2,2.34,78.5,,Lox/Kerosene,325,,,2.52,Russia,341,"On the basis of the NK-9 the NK-15V was developed for the N-1 launcher. 8 NK-15V engines, featuring high-expansion nozzles, were used on the Block B (stage 2)."
NK-15V-mod,NK-15V-mod,,,Lox/LH2,Kuznetsov,N1 concept,1960s,1,1961,,,,,,,Lox/LH2,,,,,Russia,,
NK-15VM,NK-15VM,11D52VM,,Lox/LH2,Kuznetsov,N-1 stage 2 (block B) replacement,1965,1,1960,,,,,,,Lox/LH2,,,,,Russia,283,"Derivative of NK-15 with kerosene replaced by hydrogen. Canceled before hot-tests. Intended for cryogenic second stage of N-IFV-II,III or N-IMV-II,III launcher versions studied in 1965."
NK-19,NK-19,11D54,NK-9V,Lox/Hydrocarbon,Kuznetsov,N-1 stage 4 (block G),1960-72,1,,,,,,,,Lox/RG-1,,,,,Russia,"306, 319",Based on NK-9 engine. Originally developed for the modernized second stage of the R-9 (abandoned). Also to have been used on GR-1 / 8K713 Stage 2. Proposed for N-II stage 1. Designation 11D54 used also for predecessor of 11D57 LOX/LH2 engine.
NK-21,NK-21,11D53,NK-9V,Lox/Hydrocarbon,Kuznetsov,N-1 stage 3 (block V),1962-72,1,,,,,,,,Lox/Kerosene,318,,,,Russia,"306, 319",Based on NK-9 engine. Propellants kerosene T-1 / LOX. 4 engines used in N-1 stage 3 (block V).
NK-231,NK-231,,,Turbofan,Kuznetsov,Tu-160,,1,226.5,205.9,,,,,,Air/Kerosene,1980,,58000,,Russia,303,Turbofan engine used in Tu-160. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust.
NK-31,NK-31,11D114,,Lox/Hydrocarbon,Kuznetsov,N-1F stage 4 (block G),1969-74,1,402,,722,1.4,,92,124,Lox/Kerosene,353,,1200,2.6,Russia,351,"To have been used in the N-1F fourth (Block G translunar injection) stage. After initial failures of the N-1 Kuznetsov developed modified versions of engines for all four stages, which had multiple ignition capability and increased operational lifeti"
NK-33,NK-33,11D111,,Lox/Hydrocarbon,Kuznetsov,N-1F stage 1 (block A),1970-74,1,1638,1510.2,1222,1.5,3.71,145.7,27,Lox/Kerosene,331,297,600,2.8,Russia,351,"After initial failures of N1 modified engines with multiple ignition capability and increased life were developed.  NK-33 was tested at thrust of up to 204 t, variations of components ratio up to 20% and total burning time up to 1200 sec. Mothballed,"
NK-33 LH2 Mod + 4 x LACE,NK-33 LH2 Mod,,,Air augmented rocket,Kuznetsov,N1-MOK,1974,1,980.7,,,,,,,Air/Lox/LH2,430,,410,,Russia,21,"Ultimate derivative of NK-9. Propellants changed to LH2/LOX, 16 x modified NK-33 engines + 4 Liquid Air Cycle Engine Liquid Air/LH2 boosters.  All figures estimated based on tank volume of Block A and delivery of 90,000 kg payload to 400 kg MKBS orbi"
NK-39,NK-39,11D113,,Lox/Hydrocarbon,Kuznetsov,N-1F stage 3 (block V),1969-74,1,402,,631,1.3,,98,114,Lox/Kerosene,352,,1200,2.6,Russia,351,"After initial failures of the N-1 Kuznetsov developed modified versions of engines for all 3 stages, with multiple ignition capability and increased operational lifetime. These engines were never flown and were mothballed after the cancellation of th"
NK-43,NK-43,11D112,,Lox/Hydrocarbon,Kuznetsov,N-1F stage 2 (block B),1969-74,1,1755,1247.8,1396,2.5,,145.7,70,Lox/Kerosene,346,246,600,2.8,Russia,351,"Version of NK-33 with higher expansion ratio nozzle for operation at altitude. After initial failures of the N-1 the company developed modified versions of engines for all four stages, which had multiple ignition capability and increased operational "
NK-9,NK-9,,,Lox/Hydrocarbon,Kuznetsov,"R-9, GR-1 stage 1",1959-65,1,441.3,,,,,,,Lox/RG-1,327,280,,,Russia,"283, 306, 319","Developed for 1st Stage of the R-9 ICBM, reached phase of stand testing, but then RD-111 selected. Later planned for 1st Stage of GR-1, but that rocket was abandoned. OKB Kuznetsov."
NK-9V,NK-9V,11D53,"NK-19, NK-21",Lox/Hydrocarbon,Kuznetsov,N-1 stage 2 (block V) / N-1 stage 3 (block G) / R-9 Stage 2,1959-65,1,441.3,,,,,,,Lox/RG-1,340,312,,,Russia,"306, 319",Developed for 2nd stage of the R-9 ICBM (alternative to RD-111 engine by OKB-456). NK-9 with increased expansion ratio.
NK-9V-11D53,NK-9V-11D53,11D53,NK-21,Lox/Hydrocarbon,Kuznetsov,N-1 stage 3 (block V),,1,449,,,,,,,Lox/Kerosene,340,312,,,Russia,341,Modification of NK-9 engine for the N-1 lunar rocket. May be identical to NK-21 (stage 3).
NK-9V-11D54,NK-9V-11D54,11D54,NK-19,Lox/Hydrocarbon,Kuznetsov,N-1 stage 4 (block G),,1,392,,,,,,,Lox/Kerosene,340,312,,,Russia,341,Modification of NK-9 engine for the N-1 lunar rocket. May be identical to NK-19 (stage 4).
PRD-15,,,,Solid,Kartukov,Strela,1954-,,392,,,,,,,Solid,,,,,Russia,,
PRD-19M,,,,Solid,Kartukov,KSShch Shchuka,1950s,,,,,,,,,Solid,,,,,Russia,,
PRD-22,,,,Solid,Kartukov,SM-30,1950s,,3.92,,,,,,,Solid,,,,,Russia,,
PRD-36,,,,Solid,Kartukov,V-600,1956-60,,,,,,,,,Solid,,,,,Russia,,
PRD-52,,,,Solid,Kartukov,DBR-1 Yastreb,1956-,,784,,,,,,,Solid,,,,,Russia,,"Thrust 80 tf at ignition, 75 tf at cutout."
PRD-61,,,,Solid,Kartukov,036 Vikhr,1958-,,,,,,,,,Solid,,,,,Russia,,
PRD-70,,,,Solid,Kartukov,400/5V11 stage I,1955-,,,,,,,,,Solid,,,,,Russia,,
R-13,,,,Storable liquid,Dushkin,,1946-,,,,,,,,,Solid/Liquid,,,,,Russia,,"The R-13 engine was developed in the late 1950s by OKB Dushkin. It was a combined (powder+liquid) engine, characterized by a new technical approach conceived by Dushkin in the prewar design of the KRD-604."
R-200,,,,Storable liquid,Dushkin,,,1,9.8,,,,,,,,,,,,Russia,,Thrust variable 0.8 tf -1.0 tf.
R-3,R-3,,D-2,Lox/Hydrocarbon,Polyarniy,R-3,1947-51,1,1373,,,,,,,Lox/Kerosene,300,360,124,,Russia,194,Engine for 3000 km range IRBM design to study problems of long-range rockets.  Developed from April 1947 until cancellation. Second missile designated R-3 later used the RD-110 engine.
R-31,R-31,,,Turbojet,Lyulka,MiG-25,,1,91.2,82.9,,,,,,Air/Kerosene,2073,,3000,,Russia,303,Used in MiG-25. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust.
R-56 Blok A,,,,Storable liquid,,R-56 Blok A,1961,1,4412,,,,,,,RFNA/Kerosene,320,300,142,,Russia,194,"Notional engines for polyblock R-56, immense booster/ICBM; planned range 16,000 km.  payload 35,000 kg. Tsniimash has 1:10 structural simulation model."
R-56 Blok B,,,,Storable liquid,,R-56 Blok B,1961,1,784,,,,,,,RFNA/Kerosene,330,,205,,Russia,194,"Notional engines for polyblock R-56, immense booster/ICBM; planned range 16,000 km.  payload 35,000 kg. Tsniimash has 1:10 structural simulation model."
R6-117,,,,Storable liquid,Chelomei,LK-1 Blok A,1964-66,,132,,,,,,,N2O4/UDMH,,,,,Russia,,Developed in cooperation with OKB-117 on the basis of the latter's main engine for the UR-100 stage II.
RD-0101,RD-0101,,SK1,Lox/Hydrocarbon,Kosberg,E-50A aircraft by Mikoyan,1954-58,1,39.2,,,,,42.7,,Lox/Alcohol,255,,300,,Russia,"309, 344, 414","Chamber pressure 42,7 - 22,1 bar. Specific impulse 255 - 248,5 sec."
RD-0102,RD-0102,,SK1K,Lox/Hydrocarbon,Kosberg,Yak-27V aircraft by Yakovlev,1954-58,1,39.2,,,,,41.2,,Lox/Kerosene,260,,330,,Russia,"309, 344, 414","Based on RD-0101. Two ignitions possible. Chamber pressure 41,2 - 16,4 bar."
RD-0103,RD-0103,,,Lox/Hydrocarbon,Kosberg,"T-3, P-1 aircraft by Sukhoy",1957,1,34.6,,,,,37.3,,LOX/TS1,277,,,,Russia,309,"Based on RD-0102. Chamber pressure 37,3 - 15,7 bar."
RD-0105,RD-0105,8D714,"RO-5, RD-428",Lox/Hydrocarbon,Kosberg,R-7 8K72 Luna stage 3 (block E-Luna),1957-59,1,49.4,,125,2.56,,45,,Lox/Kerosene,316,,440,,Russia,"174, 307, 344","RD-0105 was developed jointly with OKB-1 on the basis of a steering chamber from RD-107 engine, which was developed by OKB-1. Developed in nine months."
RD-0106,RD-0106,8D715,,Lox/Hydrocarbon,Kosberg,R-9 stage 2,1959-62,4,304,,,,,,,Lox/T-1,330,,140,,Russia,342,Gas generator cycle.
RD-0107,RD-0107,8D715K,"RD-461, RO-9",Lox/Hydrocarbon,Kosberg,"R-9, Molniya 8K78, Voskhod 11A57 stage 3",1958-62,4,297.9,,410,0.64,,68.2,,Lox/T-1,326,,250,,Russia,177,Gas generator cycle.
RD-0108,RD-0108,8D715P,"RD-461, 11D55, 8D715K, RO-8",Lox/Hydrocarbon,Kosberg,"Voskhod 11A57, Molniya 8K78 stage 3",1961-65,4,297.9,,410,0.64,,68.2,,Lox/T-1,326,,250,,Russia,177,
RD-0109,RD-0109,8D719,"RD-448, RO-7",Lox/Hydrocarbon,Kosberg,"8A92 Vostok stage 3, 8K72K stage 3 (block E-Vostok)",1959-60,1,54.52,,121,0.76,1.58,50,79.4,Lox/RG-1,323.5,,430,,Russia,"95, 307, 320",Developed in 15 months.
RD-0110,RD-0110,11D55,RD-461,Lox/Hydrocarbon,Kosberg,"Soyuz 11A511, Molniya-M 8K78M",1964-69,4,297.9,,408,2.24,1.58,68.2,82.2,Lox/RG-1,326,,250,2.2,Russia,"95, 177, 225, 226, 307, 320",Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability.
RD-0110MD,RD-0110MD,,,Lox/Hydrocarbon,Kosberg,,1994-,4,245,,,,,54,82.2,Lox/LNG,,,20,,Russia,403,"Prototype engine for tests with propellants LOX/liquified natural gas. Tests performed from 30 April 1998 on, test duration 20s."
RD-0120,RD-0120,11D122,RO-200,Lox/LH2,Kosberg,Energia core stage,1976-90,1,1961,1517.1,3450,2.42,4.55,218,85.7,Lox/LH2,455,359,600,6,Russia,308,"First operational Russian cryogenic systems.  Starting point was US SSME, resulting in engine of similar size, thrust, and specific impulse. Feed Method: 35,000 rpm dual-stage turbopumps on each chamber. A single pre-burner burns fuel-rich at 527 Cel"
RD-0120-CH,RD-0120-CH,,,Lox/Hydrocarbon,Kosberg,,,1,1576,,2370,,,172.5,,Lox/LCH4,363,,,3.4,Russia,342,Proposed variant of the RD-0120 engine using liquid methane instead of hydrogen as propellant.
RD-0120M,RD-0120M,11D122A,,Lox/LH2,Kosberg,Energia-M core stage.,1987-1991,1,1961,1517.1,3450,2.42,4.55,218,85.7,Lox/LH2,455,372,600,6,Russia,308,"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. The original RD-0120 engines are mothballed at Baikonur."
RD-0120M-CH,RD-0120M-CH,,,Lox/Hydrocarbon,Kosberg,,,1,1720,,2600,,,186,,Lox/LCH4,372,,,3.4,Russia,342,Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant.
RD-0120TD,RD-0120TD,,,Lox/LH2,Kosberg,experimental tri-propellant,,1,1317,,,2.42,4.55,,85.7,Lox/Kerosene/LH2,419,295,,4.13,Russia,310,Experimental tri-propellant (dual-fuel) variant using the RD-0120 engine. Realized by supply of high-pressure kerosene from test bench or adapted existing kerosene pump for tests. Specific impulse 419 / 452 sec.
RD-0122,RD-0122,,,Lox/LH2,Kosberg,Energia-M core stage. Planned for Angara central stage,1990-,1,2313,,,,,,,Lox/LH2,460.5,,,,Russia,309,Based on RD-0120. Upgrade of RD-0120 engine for Energia-M launcher with increased thrust. Prototype from RD-0120 hardware. Currently an upgraded RD-0122 is planned for use in the central stage of Angara heavy launcher.
RD-0124,RD-0124,14D451M,14D23,Lox/Hydrocarbon,Kosberg,Rus Soyuz 2 stage 3,1993-,4,294.3,,480,2.4,1.575,157,,Lox/RG-1,359,331,300,2.6,Russia,"225, 226, 312","Engine to succeed RD-0110 in second stage of  Soyuz-2/Rus LV. Uses staged combustion; chamber pressure increased from 70 to  160 atmospheres, specific impulse from 326 to 359 seconds, payload by 950 kg from current 6900/7200 kg (Plesetsk/Baikonur)."
RD-0124 sea-level,RD-0124 sea-level,14D23,,Lox/Hydrocarbon,Kosberg,Angara stage 2 verniers. Kvant-1 stage 1 vernier,,4,298.64,,,,,173.5,,Lox/Kerosene,331,,300,2.6,Russia,21,Variant of RD-0124 with shortened nozzle for sea-level operation. Proposed for small launcher Kvant-1 by RKK Energia for stage 1 steering engine. Also proposed by RKK Energia in initial studies in 1993 for Angara upper stage.
RD-0124-14D23,RD-0124-14D23,14D23,,Lox/Hydrocarbon,Kosberg,Kvant-1 stage 1 vernier,,4,298.64,,,,,173.5,,Lox/Kerosene,331,,300,2.6,Russia,,Variant of RD-0124 with shortened nozzle for sea-level operation. Proposed for small launcher Kvant-1 by RKK Energia for stage 1 steering engine.
RD-0124M,RD-0124M,,,Lox/Hydrocarbon,Kosberg,,1998-,1,294.3,,360,1.43,2.1,161.9,,Lox/Kerosene,348,,300,,Russia,312,"Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber."
RD-0124M1,RD-0124M1,,,Lox/Hydrocarbon,Kosberg,,1998-,1,294.3,,393,1.5,2.6,157,,Lox/Kerosene,359,,300,,Russia,312,"Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber with larger nozzle extension compared to RD-0124M."
RD-0126,RD-0126,,RO-97,Lox/LH2,Kosberg,upper stage,1993-,1,39.2,,320,,2.6,71.5,,Lox/LH2,476,,,6,Russia,"21, 342","Concept for a cryogenic engine ""Yastreb"" for upper stages. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Hot-tests began 1998."
RD-0126A,RD-0126A,,RO-97A,Lox/LH2,Kosberg,upper stage,1996-,1,98,,340,,2.73,118,,Lox/LH2,476,,,6,Russia,342,"Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump."
RD-0128,RD-0128,,,Lox/LH2,Kosberg,upper stage,1996-,1,98,,370,,4.175,118,,Lox/LH2,474,,,6,Russia,342,"Concept for a cryogenic engine for upper stages. One single chamber with bell nozzle, separate turbopumps."
RD-0129,RD-0129,,,Lox/Hydrocarbon,Kosberg,,1990s,,,,,,,,,Lox/LCH4,,,,,Russia,,
RD-012U,RD-012U,,,Ramjet,Bondaryuk,Burya,,1,76,,,,,,,Air/Kerosene,1500,,8500,,Russia,"192, 300",1.2 m diameter ramjet to be used in Burya cruise missile. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point.
RD-0131,RD-0131,,,Lox/LH2,Kosberg,upper stage,1996-,1,98,,350,,2.2,123,,Lox/LH2,467,,,6,Russia,342,"Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump."
RD-0132,RD-0132,,,Lox/LH2,Kosberg,upper stage,1996-,4,98,,370,,1.38,98,,Lox/LH2,469,,,5.9,Russia,342,"Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump."
RD-0132M,RD-0132M,,,Lox/Hydrocarbon,Kosberg,Vozdushnyy Start stage 2,1998-,4,98,,,,,,,Lox/LNG,,,,,Russia,327,"Proposed variant of RD-0132, replacing hydrogen by liquid natural gas. Initially selected for stage 2 of Vozdushnyy Start project by Kompomash."
RD-0133,RD-0133,,,Lox/LH2,Kosberg,upper stage,1996-,4,98,,390,,1.43,83,,Lox/LH2,467,,,6,Russia,342,"Concept for a cryogenic engine for upper stages. Four chambers with bell nozzles, common turbopump."
RD-0134,RD-0134,,,Lox/Hydrocarbon,Kosberg,stage 1,1998-,1,2038,,1800,,3.5,,,Lox/LNG,358,316.3,,,Russia,403,Proposed engine for LOX/liquid natural gas. Staged combustion cycle variant of RD-0139.
RD-0139,RD-0139,,,Lox/Hydrocarbon,Kosberg,stage 1,1998-,1,2038,,1544,,3.61,,,Lox/LNG,341,301.3,,,Russia,403,Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle.
RD-0140,RD-0140,,,Lox/Hydrocarbon,Kosberg,stage 2,1998-,1,2086,,1689,,5.037,,,Lox/LNG,349,300,,,Russia,403,Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle.
RD-0141,RD-0141,,,Lox/Hydrocarbon,Kosberg,stage 1,1998-,1,2251,,1973,,3.35,,,Lox/LNG,353,323,,,Russia,403,Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle.
RD-0142,RD-0142,,,Lox/Hydrocarbon,Kosberg,stage 2,1998-,1,2353,,2058,,4.51,,,Lox/LNG,369,,,,Russia,403,Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle.
RD-0143,RD-0143,,,Lox/Hydrocarbon,Kosberg,Vozdushnyy Start stage 2,1998-,4,343,,,,,,,Lox/LNG,372,,,,Russia,328,"Proposed variant of RD-0124, replacing kerosene by liquid natural gas. Selected for stage 2 of Vozdushnyy Start project by Kompomash."
RD-0143A,RD-0143A,,,Lox/Hydrocarbon,Kosberg,Vozdushnyy Start stage 1,1998-,1,343,,,,,,,Lox/LNG,370,,,,Russia,328,Proposed single chamber variant of RD-0143. Selected for stage 1 of Vozdushnyy Start project by Kompomash.
RD-0144,RD-0144,,,Lox/Hydrocarbon,Kosberg,upper stage,1998-,1,147,,250,,1.195,,,Lox/LNG,374,,,,Russia,403,Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Radiation cooled nozzle extension.
RD-0145,RD-0145,,,Lox/Hydrocarbon,Kosberg,upper stage,1998-,4,147,,282,,1.42,,,Lox/LNG,374,,,,Russia,403,Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Four-chamber variant of RD-0144.
RD-0146,RD-0146,,,Lox/LH2,Kosberg,Centaur upper stage (Atlas),1998-,1,100,,,,,,,Lox/LH2,470,,,,Russia,352,Proposed Russian version of RL10A-4-1 by Pratt & Whitney. Main modification are new turbopumps. May be derivative of RD-0128 project.
RD-0149,RD-0149,,,Lox/Hydrocarbon,Kosberg,upper stage,1998-,1,49,,150,,1.575,,,Lox/LNG,370,,,,Russia,403,Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Variant of RD-0141 with larger nozzle.
RD-018,RD-018,,,Ramjet,Bondaryuk,"Buran missile, early version.",,1,98,,,,,,,Air/Kerosene,1500,,8500,,Russia,"192, 300",1.8 m diameter ramjet engine initially considered for Buran M-42. RD-020 adpopted later during development. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point.
RD-020,RD-020,,,Ramjet,Bondaryuk,Buran M-42,,1,103,,,,,,,Air/Kerosene,1500,,8500,,Russia,"192, 300","Cancelled November 1957. Ramjet for Buran cruise missile. Boosted by 4 x Glushko-engined boosters.  8,500 km cruise at Mach 3.1 at 18-20 km altitude with 3,500 kg warhead. Wing area 98 square meters; diameter of ramjet 2.0 m. Never reached flight tes"
RD-0200,RD-0200,,RO1-154,Storable liquid,Kosberg,SAM by Lavochkin on stage 2,1957-62,2,58.8,,86,0.3,0.4,66,,AK27I/TG-02,,230,360,,Russia,"95, 307, 342","The first liquid rocket engine of OKB-154, engine was developed on a basis of the S2.1200 engine, developed by Isayev's OKB-2 of GKOT and transferred to OKB-154. Thrust range 59 - 5.9 kN. Sea level specific impulse 230 - 166 sec."
RD-0201,RD-0201,,,Storable liquid,Kosberg,SAM V1100 by Grushin stage 3,1957-60,4,58.06,,120,0.4,0.7,62,,AK27P/TG-02,260,,180,,Russia,"307, 342",Thrust range 59 - 28 kN.
RD-0202,RD-0202,8D45,,Storable liquid,Kosberg,UR-200 stage 1,1961-64,4,2236,,1525,,1.8,,29.8,N2O4/UDMH,311,278,136,2.6,Russia,309,Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0204 for tank pressurization and three RD-0203.
RD-0203,RD-0203,8D44,,Storable liquid,Kosberg,UR-200 stage 1,1961-64,1,559,,381,0.89,1.8,,29.81,N2O4/UDMH,311,278,135.5,2.6,Russia,309,DU consisting of 4 RD-0204 gimballed motors. Staged combustion cycle.
RD-0204,RD-0204,,,Storable liquid,Kosberg,UR-200 stage 1,1961-64,1,559,,381,0.89,1.8,,29.8,N2O4/UDMH,311,278,136,2.6,Russia,309,Diameter is per chamber. Staged combustion cycle. Variant of RD-0203 with additional pressure sensor.
RD-0205,RD-0205,8D46,,Storable liquid,Kosberg,UR-200 stage 2,1961-64,1,606.4,,552,1.47,2.325,,48.07,N2O4/UDMH,322,,150,2.625,Russia,309,Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0206 maine engine and 4 RD-0207 vernier/steering engines. Version of 8D44 and 8D45 with extended nozzle.. Developed 1961.
RD-0206,RD-0206,8D47,,Storable liquid,Kosberg,UR-200 stage 2,1961-64,1,575.5,,,1.47,,147,81.3,N2O4/UDMH,326,,150,2.6,Russia,"309, 320",Staged combustion cycle.
RD-0207,RD-0207,8D67,,Storable liquid,Kosberg,UR-200 stage 2 vernier,1961-64,4,30.9,,,0.163,,53,43.3,N2O4/UDMH,297,,133,1.8,Russia,"309, 320",Gas generator cycle. Four vernier thrusters.
RD-0208,RD-0208,,,Storable liquid,Kosberg,UR-200 stage 1,1961-65,1,,,,,,,,N2O4/UDMH,,,,,Russia,309,Stage 1 had three RD-0208 plus one RD-0209. Further developed into RD-0210.
RD-0209,RD-0209,,,Storable liquid,Kosberg,UR-200 stage 1,1961-65,1,,,,,,,,N2O4/UDMH,,,,,Russia,293,Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0211 for tank pressurization and three RD-0210. Modification of RD-0208 with tank pressurization. Further developed into RD--0211.
RD-0210,RD-0210,8D411K,"RD-465, 8D49",Storable liquid,Kosberg,Proton stage 2,1962-65,1,582.1,,566,1.47,2.33,147,81.3,N2O4/UDMH,326.5,,230,,Russia,"95, 307",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 (Oxidizer pre-burner gas routed to main chamber after driving turbine).
RD-0210-HC,RD-0210-HC,,,Lox/Hydrocarbon,Kosberg,,,1,592,,570,,,147,,Lox/Kerosene,342,,,2.6,Russia,342,Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
RD-0211,RD-0211,8D412K,RD-468,Storable liquid,Kosberg,Proton stage 2,1962-65,1,582.1,421.9,566,1.47,2.33,147,81.3,N2O4/UDMH,326.5,,230,,Russia,"95, 307",Variant of RD-0210 providing tank pressurization. Staged combustion cycle.
RD-0212,RD-0212,8D49,RD-473,Storable liquid,Kosberg,Proton stage 3,1962-68,1 + 4,613,,,,,,,N2O4/UDMH,324.6,,230,,Russia,307,Engine unit (DU) consisting of 1 RD-0213 maine engine and 4 RD-0214 vernier/steering engines. 8D48 is essentially similar to 8D411 and 8D412 and has the same combustion chamber.
RD-0213,RD-0213,8D48,RD-473,Storable liquid,Kosberg,Proton stage 3,1962-68,4,582.1,446,,4.15,,147,81.3,N2O4/UDMH,326.5,,230,,Russia,307,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.
RD-0214,RD-0214,8D811,,Storable liquid,Kosberg,Proton stage 3 vernier,1962-68,4,30.98,,,,,53,,N2O4/UDMH,293,,,,Russia,307,Based on RD-0207. Four used as steering engines for Proton Stage 3 in system RD-0212.
RD-0215,RD-0215,,,Storable liquid,Kosberg,Planned heavy launcher (UR-700 ?) stage 1,1962-65,?,2450,,,2,,,,N2O4/UDMH,310,280,102,,Russia,309,"Engine unit (DU) consisting of 1 RD-0217 for tank pressurization and three RD-0216. Intended for stage 1 of heavy launcher by Chelomei. Development stopped, hardware not hot-tested. Staged combustion cycle with ox.-rich gas generator."
RD-0216,RD-0216,15D2,,Storable liquid,Kosberg,"UR-100, UR-100K / RS-10 (SS-11)  stage 1",1963-66,1,219,,,,,147,,N2O4/UDMH,313,,,,Russia,"313, 342, 344","Date is that of the authorizing Decree. Actual development earlier, since first launch occured November  1963.. Staged combustion cycle. Includes tank pressurization system (RD-0217 without tank press.). Manufacturing until 1974, operational until 19"
RD-0217,RD-0217,15D2,,Storable liquid,Kosberg,"UR-100, UR-100K / RS-10 (SS-11)  stage 1",1963-66,1,219,,,,,147,,N2O4/UDMH,313,,,,Russia,"313, 342, 344","Staged combustion cycle. Version of RD-0216 without tank pressurization system. Manufacturing until 1974, operational use until 1991."
RD-0221,RD-0221,,,Storable liquid,Kosberg,upper stage of unnamed missile by Mishin.,1965-70,1 + 2,78,,150,0.8,1.6,122.6,,N2O4/UDMH,330,300,800,,Russia,307,
RD-0225,RD-0225,11D24,,Storable liquid,Kosberg,Almaz space station orbital maneuvering,1966-71,1,3.923,,23,0.46,0.996,8.8,64,N2O4/UDMH,287,,1200,1.85,Russia,"95, 307","Originally designed for UR-100 follow-ons spaceships. Two engines used on Almaz space station for orbital maneuvering, Pressure fed."
RD-0228,RD-0228,,,Storable liquid,Kosberg,R-36M / RS-20A (SS-18 mod-1) stage 2,1967-75,1 + 4,755,,,,,,,N2O4/UDMH,,,,,Russia,"330, 342",Comprises single-chamber main engine RD-0229 plus four-chamber steering engine RD-0230. Further developed to RD-0255.
RD-0229,RD-0229,,,Storable liquid,Kosberg,R-36M / RS-20A (SS-18 mod-1) stage 2,1967-75,1,,,,,,,,N2O4/UDMH,,,,,Russia,293,Main engine. Staged combustion cycle.
RD-0229M,RD-0229M,,,Lox/Hydrocarbon,Kosberg,Vozdushnyy Start stage 1,1997,1,883,,,,,,,Lox/LNG,,,,,Russia,327,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.
RD-0230,RD-0230,,,Storable liquid,Kosberg,R-36M / RS-20A (SS-18 mod-1) stage 2 vernier,1967-75,4,,,,,,,,N2O4/UDMH,,,,,Russia,293,Vernier engine. Gas generator cycle.
RD-0231,RD-0231,,,Storable liquid,Kosberg,P-700 Granit,1968-70,1,29,,28,0.15,0.6,123,,N2O4/UDMH,275,,16,,Russia,307,Staged combustion cycle.
RD-0232,RD-0232?,,,Storable liquid,Kosberg,UR-100N / RS-18 / (SS-19) Stage 1,,1,,,,,,,,N2O4/UDMH,,,,,Russia,293,Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0234 for tank pressurization and three RD-0233.
RD-0233,RD-0233,,,Storable liquid,Kosberg,UR-100N / RS-18 (SS-19) stage 1,1969-74,1,520,,,,,205,,N2O4/UDMH,310,285,121,,Russia,"339, 353",Staged combustion cycle.
RD-0234,RD-0234,,,Storable liquid,Kosberg,UR-100N / RS-18 (SS-19) stage 1,1969-74,1,520,,,,,205,,N2O4/UDMH,310,285,121,,Russia,"339, 309, 353",Staged combustion cycle. Modification of RD-0233 including tank pressurization system.
RD-0234-CH,RD-0234-CH,,,Lox/Hydrocarbon,Kosberg,,1996-,1,442,,390,,,176,,Lox/LCH4,343,310,,3.4,Russia,342,Proposed variant of RD-0234 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.
RD-0234-HC,RD-0234-HC,,,Lox/Hydrocarbon,Kosberg,,1996-,1,516,,390,,,196,,Lox/Kerosene,331,310,,2.6,Russia,342,Proposed variant of RD-0234 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
RD-0235,RD-0235,,,Storable liquid,Kosberg,UR-100N / RS-18 (SS-19) stage 2,1969-74,1,240,,,,,175,,N2O4/UDMH,320,,,,Russia,"339, 353",Main engine based on RD-0217 with larger nozzle for altitude operation. Staged combustion cycle.
RD-0236,RD-0236,,,Storable liquid,Kosberg,UR-100N / RS-18 (SS-19) stage 2 vernier,1969-74,4,15.76,,,,,,,N2O4/UDMH,293,17.5,,,Russia,"309, 353",Developed in 1969-1974 / problems not solved until 1978. Vernier engines. Gas generator cycle.
RD-0237,RD-0237,,,Storable liquid,Kosberg,UR-100N / RS-18 (SS-19) stage 3,1969-74,1,4.9,,,,,,,N2O4/UDMH,200,,150,,Russia,"309, 353","MIRV service block. Open cycle. Analogous to RD-0225, pressure fed. Steering engine for space vehicles gimbaling +/- 45 degree."
RD-0242,RD-0242,,,Storable liquid,Kosberg,sea-based missile booster stage (Burlak ?),1977-83,1,123.6,,120,0.272,0.882,196.2,,N2O4/UDMH,302.6,,60,,Russia,"95, 312, 342","First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. 50 engines ready for sale. Single ignition, 297 development tests, max. duration 420 s."
RD-0242-HC,RD-0242-HC,,,Lox/Hydrocarbon,Kosberg,,1998-,1,125,,120,,,196.2,,Lox/Kerosene,312,,,2.6,Russia,342,Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
RD-0242M,RD-0242M,,,Storable liquid,Kosberg,,1998-,1,98.1,,185,0.798,1.597,153,,N2O4/MMH,335.6,,600,,Russia,312,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%. 15 ignitions tested with one single engine.
RD-0242M1,RD-0242M1,,,Storable liquid,Kosberg,,1998-,1,98.1,,229,1.25,2.337,153,,N2O4/MMH,343,,600,,Russia,312,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%.
RD-0243,RD-0243,,,Storable liquid,Kosberg,R-29RM / RSM-54 (SS-N-23) stage 1,1977-85,1 + 4,825.8,,852.8,2.267,1.9,,,N2O4/UDMH,300,,79,,Russia,"96, 309, 312",Comprises of single-chamber main engine RD-0244 plus four-chamber steering engines RD-0245 driven by turbine exhaust gas. Engine submerged in propellant tank.
RD-0244,RD-0244,,,Storable liquid,Kosberg,R-29RM / RSM-54 (SS-N-23) stage 1,1977-85,1,682,,,,,275,2,N2O4/UDMH,310,280,74,2.6,Russia,"96, 309, 312",Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank.
RD-0244-HC,RD-0244-HC,,,Lox/Hydrocarbon,Kosberg,,,1,690,,540,,,230,,Lox/Kerosene,332,,,2.7,Russia,342,Proposed variant of RD-0244 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
RD-0245,RD-0245,,,Storable liquid,Kosberg,R-29RM / RSM-54 (SS-N-23) stage 1 vernier,1977-85,4,211,,,,,147,14,N2O4/UDMH,300,280,79,2.6,Russia,"96, 309, 312",Four-chamber steering engine in system RD-0243 driven by turbine exhaust gas.
RD-0245-HC,RD-0245-HC,,,Lox/Hydrocarbon,Kosberg,,,4,214,,290,,,142,,Lox/Kerosene,320,,,2.3,Russia,342,Proposed variant of RD-0245 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
RD-0246,RD-0246,,,Storable liquid,Kosberg,,,1 + 4,,,,,,,,N2O4/UDMH,,,,,Russia,309,Project for further development of RD-0243.
RD-0250,RD-0250,,,Storable liquid,Kosberg,Modif. of Chelomei-launcher stage 2 (?),,1,,,,,,,,N2O4/UDMH,,,,,Russia,309,Further development of RD-0235 main engine for projected modification of launcher by Chelomei. Development ceased during study phase. Staged combustion cycle. 
RD-0251,RD-0251,,,Storable liquid,Kosberg,Modif. of Chelomei-launcher stage 2 (?),,4,,,,,,,,N2O4/UDMH,,,,,Russia,309,Further development of RD-0236 steering engine for projected modification of launcher by Chelomei. Development ceased during study phase. Gas generator cycle. 
RD-0255,RD-0255,,,Storable liquid,Kosberg,R-36M2 / RS-20V (SS-18 Mod-4) stage 2,1983-89,1 + 4,755,,,,,,,N2O4/UDMH,,,,,Russia,"342, 309, 330",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%.
RD-0256,RD-0256,,,Storable liquid,Kosberg,R-36M2 / RS-20V (SS-18 Mod-4) stage 2,1983-89,1,,,,,,,,N2O4/UDMH,,,,,Russia,309,Main engine of system RD-0255. Staged combustion cycle.
RD-0256-HC,RD-0256-HC,,,Lox/Hydrocarbon,Kosberg,,1996-,1,820,,770,,,172,,Lox/Kerosene,344,,,2.6,Russia,342,Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
RD-0256-Methane,RD-0256-Methan,,,Lox/Hydrocarbon,Kosberg,,1996-,1,836,,770,,,176,,Lox/LCH4,353,,,3.4,Russia,342,Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.
RD-0257,RD-0257,,,Storable liquid,Kosberg,R-36M2 / RS-20V (SS-18 Mod-4) stage 2 vernier,1983-89,4,,,,,,,,N2O4/UDMH,,,,,Russia,309,Steering engine of system RD-0255. Gas generator cycle.
RD-0410,RD-0410,11B91,,Nuclear,Kosberg,Experimental nuclear engine,1965-94,1,35.3,,2000,1.6,3.5,,,Nuclear/LH2,910,,3600,,Russia,"98, 309","Nuclear thermal rocket engine. Propellant LH2. Developed from 1965 through 1980s. Tested at Semipalatinsk test range in 1980s and was ""the only operational nuclear engine in the USSR""."
RD-0411,RD-0411,,,Nuclear,Kosberg,Full-size nuclear thermal engine,1965-94,1,392,,,,,,,Nuclear/LH2,900,,,,Russia,"95, 307",Planned full-size nuclear thermal engine for Mars expeditions. Never progressed beyond study stage.
RD-0600,RD-0600,,,Laser,Kosberg,"Space station ""Skif""",1970-85,,,,750,,0.9,,,Gas Dynamic Laser/CO+Air+N2+C2H5OH,,,,,Russia,"309, 342",Gas dynamic laser. Working medium gaseous carbon monoxide + air + nitrogen + ethanol. Flow rate up to 100 kg/s. Tests were performed at NII TP. Beam power up to 600 kW. A second variant for dicianatethylen + nitrogen oxide was developed and tested at
RD-0750,RD-0750,,RD-0650TF,Lox/LH2,Kosberg,Alternative for Angara central stage,1997-,1,1720,,,,,190,,Lox/Kerosene/LH2,451,,,4,Russia,"342, 352",Tripropellant derivative of RD-0120. Some components tested in RD-0120TD technology demonstration in cooperation with Aerojet. Two modes: LOX/LH2-Ker. and LOX/LH2. Chamber pressure 190 / 85 bar. Specific impulse 418 / 451 sec. O:F ratio 4.0 / 6.0.
RD-1,RD-1,,,Storable liquid,Glushko,"Take-off acelleration of Pe-2, La-7, Yak-3, Su-6 airplanes",1941-45,1,2.94,,56,,,20,,Nitric acid/Kerosene,200,,,,Russia,342,The RD-1 was the first Russian liquid propellant rocket engine. Production 1944-45. Ignition was by an ethane-air mixture.
RD-100,RD-100,,,Lox/Hydrocarbon,Glushko,"R-1, V-1A",1946-50,1,304,267,885,1.65,3.7,15.9,,Lox/Alcohol-75%,237,203,65,1.28,Russia,"225, 287, 317, 321, 342",The RD-100 was a Russian copy of the V-2 engine using Russian materials - which made it very difficult! German rocket scientists assisted in its realization. German salaries and conditions were good - the chief of the German team receiving the second
RD-101,RD-101,,,Lox/Hydrocarbon,Glushko,R-2 and V-2A,1946-51,1,404,363,888,1.65,3.35,21.2,,Lox/Alcohol-96%,237,210,,1.45,Russia,"287, 317, 342","The RD-101 was developed simultaneously with the RD-100 but with no German involvement (for security). It was more compact, had increased thrust (37,000 kgf), increased pressure and an increased alcohol concentration. They were nicknamed drunk engine"
RD-102,RD-102,,RD-3A,Lox/Hydrocarbon,Glushko,R-3A,,1,428,,,,,,,Lox/Alcohol-96%,235,214,83,,Russia,283,Project for R-3A experimental missile. Stopped in favor of RD-103.
RD-103,RD-103,8D52,8D71,Lox/Hydrocarbon,Glushko,R-5,1947-53,1,500,432,870,1.65,3.12,23.9,,Lox/Alcohol-92%,243,216,120,,Russia,"225, 319",
RD-103M,RD-103M,8D52M,,Lox/Hydrocarbon,Glushko,R-5M 8K51,1950-55,1,500.1,432,867,1.65,3.221,23.9,,Lox/Alcohol-96%,248,220,120,1.44,Russia,"225, 320",
RD-103RD,RD-103RD,,,Lox/Hydrocarbon,Glushko,M5RD,1954-56,1,,,,,,,,Lox/Alcohol,,,,,Russia,,
RD-105,RD-105,8D71,,Lox/Hydrocarbon,Glushko,R-7 ICBM stage 1 (strap-on) initial project,1952-54,1,627.6,,782,1.2,4.45,58.8,14.2,Lox/Kerosene,302,260,130,2.7,Russia,"173, 320",Intended for R-7 strap-ons in first project versions. Subsequently replaced by RD-107
RD-106,RD-106,8D72?,,Lox/Hydrocarbon,Glushko,R-7 ICBM stage 2 (core) initial project,1952-54,1,645.3,,802,1.4,4.75,58.8,20.4,Lox/Kerosene,310,250,330,2.7,Russia,320,Intended for R-7 sustainer in first project versions. Version of RD-105 with larger nozzle. Subsequently replaced by RD-108.
RD-107-11D511,RD-107,11D511,,Lox/Hydrocarbon,Glushko,"Soyuz 11A511-0, Soyuz 11A511U-0",,4,992,205.4,1200,0.67,2.86,58.5,,Lox/Kerosene,314,257,118,2.47,Russia,225,Diameter is per chamber.
RD-107-11D511P,RD-107,11D511P,,Lox/Hydrocarbon,Glushko,Soyuz 11A511U2-0,,4,996.4,192.2,,,,,,Lox/Kerosene,314,257,140,,Russia,173,OKB Glushko. Used on 11A511U2 Stage 0. Propellants kerosene (RG-1) / Lox. Diameter is per chamber.
RD-107-8D728,RD-107,8D728,,Lox/Hydrocarbon,Glushko,"Molniya 0, Molniya 8K78M-0",,4,996,204.7,1145,0.67,2.86,58.6,,Lox/Kerosene,314,257,120,,Russia,173,OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber.
RD-107-8D74,RD-107,8D74,,Lox/Hydrocarbon,Glushko,"R-7 8K71-0, Vostok 8K72-0, Vostok 8K72K-0",,4,971,198.3,1155,0.67,2.86,58.5,,Lox/Kerosene,306,250,140,,Russia,287,"Glushko decided that an ICBM using German ideas was impossible. He had developed the RD-110 with a cylindrical burner but it suffered combustion instabilities, the engine equivalent of flutter when breaking the sound barrier. Glushko returned to his "
RD-107-8D74-1958,RD-107,8D74-1958,,Lox/Hydrocarbon,Glushko,Luna 8K72-0,,4,996,201.6,1155,0.67,2.86,58.4,18.9,Lox/Kerosene,312,254,120,2.47,Russia,173,Diameter is per chamber.
RD-107-8D74-1959,RD-107,8D74-1959,,Lox/Hydrocarbon,Glushko,,,4,996,,1155,0.67,2.86,58.6,18.9,Lox/Kerosene,313,256,120,2.47,Russia,173,Diameter is per chamber.
RD-107-8D74K,RD-107,8D74K,,Lox/Hydrocarbon,Glushko,"Molniya 8K78-0, R-7A 8K74-0, Voskhod 11A57-0, Vostok 8A92-0, Vostok 8A92M-0",,4,996,203.5,1145,0.67,2.86,59.7,18.9,Lox/Kerosene,313,256,119,,Russia,173,"OKB Glushko. Used on R-7A 8K74 Production Stage 0, Early Molniya stage 0. Developed in 1957-1960. Propellants kerosene (T-1/RG-1) / Lox. Diameter is per chamber."
RD-107-8D74PS,RD-107,8D74PS,,Lox/Hydrocarbon,Glushko,Sputnik 8K71PS-0,,4,971,198.3,1155,0.67,2.86,60,18.9,Lox/Kerosene,306,250,146,,Russia,173,OKB Glushko. Used on 8K71PS Stage 0. Developed in 1956-1957. Propellants kerosene (RG-1) / Lox. Diameter is per chamber.
RD-107-8D76,RD-107,8D76,,Lox/Hydrocarbon,Glushko,Sputnik 8A91-0,,4,971,197.3,1155,0.67,2.86,56.9,18.9,Lox/Kerosene,310,252,150,,Russia,173,OKB Glushko. Used on 8A91 Stage 0. Developed in 1956-1957. Propellants kerosene (RG-1) / Lox. Diameter is per chamber.
RD-108-11D512,RD-108,11D512,,Lox/Hydrocarbon,Glushko,"Soyuz 11A511-1, Soyuz 11A511U-1",,4,997,186.6,1400,0.67,2.86,51,,Lox/Kerosene,315,248,286,,Russia,21,Diameter is per chamber.
RD-108-11D512P,RD-108,11D512P,,Lox/Hydrocarbon,Glushko,Soyuz 11A511U2-1,,4,1011,197.1,,,,,,Lox/Kerosene,319,252,290,,Russia,21, A 1-2 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. This was a very complicated modification. Diameter is per chamber.
RD-108-8D727,RD-108,8D727,"8D727K, 8D727P",Lox/Hydrocarbon,Glushko,"Molniya 1, Molniya 8K78M-1",,4,977,,1230,0.7475,2.86,53.6,,Lox/Kerosene,316,251,290,2.39,Russia,225,"OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber."
RD-108-8D727K,RD-108,8D727K,,Lox/Hydrocarbon,Glushko,Molniya 8K78-3,-1962,4,976,,,,,,,Lox/RG-1/T-1,316,,,,Russia,,
RD-108-8D75,RD-108,8D75,,Lox/Hydrocarbon,Glushko,"R-7 8K71-1, Vostok 8K72-1, Vostok 8K72K-1",,4,912,178.4,1278,0.67,2.86,51,18.9,Lox/Kerosene,308,241,340,2.39,Russia,173,OKB Glushko. Used on 8K71 R-7 Stage 1. Developed in 1954-1955. Propellants kerosene (RG-1) / Lox. Diameter is per chamber.
RD-108-8D75-1958,RD-108,8D75-1958,,Lox/Hydrocarbon,Glushko,Luna 8K72-1,,4,941,182.8,1250,0.67,2.86,51,18.9,Lox/Kerosene,315,246,340,2.39,Russia,173,Diameter is per chamber.
RD-108-8D75-1959,RD-108,8D75-1959,,Lox/Hydrocarbon,Glushko,,,4,941,,1250,0.67,2.86,51,18.9,Lox/Kerosene,315,248,340,2.39,Russia,173,"Further development of 8D74-1958, 1958-1959. Diameter is per chamber."
RD-108-8D75K,RD-108,8D75K,,Lox/Hydrocarbon,Glushko,"Molniya 8K78-1, R-7A 8K74-1, Voskhod 11A57-1, Vostok 8A92-1, Vostok 8A92M-1",,4,941,185.1,1252,0.67,2.86,51,18.9,Lox/Kerosene,315,248,340,,Russia,173,Diameter is per chamber.
RD-108-8D75PS,RD-108,8D75PS,,Lox/Hydrocarbon,Glushko,Sputnik 8K71PS-1,,4,912,178.4,1250,0.67,2.86,53,18.9,Lox/Kerosene,308,241,340,,Russia,173,Diameter is per chamber.
RD-108-8D77,RD-108,8D77,,Lox/Hydrocarbon,Glushko,Sputnik 8A91-1,,4,804,157,1250,0.67,2.86,39.2,18.9,Lox/Kerosene,315,246,370,,Russia,173,Diameter is per chamber.
RD-109,RD-109,8D711,GDU-10,Lox/UDMH,Glushko,8K73 stage 2.,1957-60,1,101.6,,210,1.024,2.28,77.5,58.5,Lox/UDMH,334,,330,1.49,Russia,"7, 8, 174, 320",The project was abandoned. Later used to develop RD-119.
RD-110,RD-110,,,Lox/Hydrocarbon,Glushko,R-3 ?,1947-51,1,1374,1176,,1.8,5.2,58.8,,Lox/Kerosene,285,243.6,,2.65,Russia,"287, 317","Glushko developed the RD-110 with a cylindrical burner but it suffered combustion instabilities, the engine equivalent of flutter when breaking the sound barrier. Never put into production."
RD-111,RD-111,8D716,,Lox/Hydrocarbon,Glushko,R-9 stage 1,1959-62,4,1628,692.5,1492,1.67,2.1,78.5,18,Lox/RG-1,317,275,110,2.39,Russia,"225, 287, 317, 320","The 121-140,000 kgf RD-111 was developed for combat missiles. It had special flexible pipelines and gimbals (simpler than bellows). You’d expect pre-launch pressurisation to be simple and quick with a military missile but the LOX on the R-9 missile t"
RD-112,RD-112,,,Lox/UDMH,Glushko,ICBM stage 1 (stage 2 was RD-113),1960,1,1089,,790,1.29,2.6,147,31.8,Lox/UDMH,344,304,,1.704,Russia,320,
RD-113,RD-113,,,Lox/UDMH,Glushko,ICBM stage 2 (stage 1 was RD-112),1960,1,1138,,1100,2.48,4.2,147,119.8,Lox/UDMH,360,,,1.704,Russia,320,Upper stage version of RD-112 with larger nozzle.
RD-114,RD-114,,,Lox/UDMH,Glushko,Used in ICBM stage 1 (stage 2 was RD-115),1961-65,1,1653,,990,1.462,2.6,147,26.4,Lox/UDMH,341,307,120,1.77,Russia,320,
RD-115,RD-115,,,Lox/UDMH,Glushko,ICBM stage 2 (stage 1 was RD-114),1961-65,1,1726,,1250,3.265,5,147,86.2,Lox/UDMH,357,,130,1.77,Russia,320,Upper stage version of RD-114 with larger nozzle.
RD-117,RD-117,,,Lox/Hydrocarbon,Glushko,unmanned Soyuz-launcher stage 1,,4,,,,,,,,Lox/Kerosene,,,,,Russia,318,Update of RD-107. Probably version using Sintin instead of kerosene.
RD-117PF,RD-117PF,11D511PF,,Lox/Hydrocarbon,Glushko,manned Soyuz-launcher stage 1,,4,,,,,,,,Lox/Kerosene,,,,,Russia,318,Update of RD-107. Probably version using Sintin instead of kerosene.
RD-118,RD-118,,,Lox/Hydrocarbon,Glushko,manned and unmanned Soyuz-launcher stage 2,,4,,,,,,,,Lox/Kerosene,,,,,Russia,318,Update of RD-108. Probably version using Sintin instead of kerosene.
RD-119,RD-119,8D710,,Lox/UDMH,Glushko,Kosmos 1 stage 2,1958-63,1,105.5,65.6,168,1.02,2.17,78.94,102,Lox/UDMH,352,220,260,1.5,Russia,"225, 174, 320",Based on RD-109.
RD-120,RD-120,11D123,,Lox/Hydrocarbon,Glushko,Zenit stage 2,1976-85,1,833,,1125,1.945,3.872,162.8,106.7,Lox/Kerosene,350,,315,2.6,Russia,"287, 347",The RD-120 is a high altitude engine used in the Zenit second stage. It was the first batch produced Russian engine to be test fired in the United States (3 test burns were made). Mass is wet mass.
RD-120.01,RD-120.01,,,Lox/Hydrocarbon,Glushko,,,1,784,,,,,,,Lox/Kerosene,329,,,,Russia,,
RD-120.03,RD-120.03,,,Lox/Hydrocarbon,Glushko,,,1,882,,,,,,,Lox/Kerosene,353,,,,Russia,,
RD-120K,RD-120K,,RD-123,Lox/Hydrocarbon,Glushko,"Soyuz M stage 1, 2. Proposed for X-34.",,1,873,866.9,1433,1.5,2.8,172,,Lox/Kerosene,336,298,305,2.6,Russia,325,"Sea-level variant of RD-120. Thrust and Isp range due to throat diam. and chamber pressure. Gimbaling +/- 6 degree in two planes. Status 1996 was RD-120 prototype with 1.8 m diam., development estimated for three years. Chamber pressure 163 - 172 bar"
RD-120M,RD-120M,,,Lox/Hydrocarbon,Glushko,PacAstro-2 stage 1,1995,1,850.4,,1080,1.4,2.435,176.3,4.96,Lox/Kerosene,330.5,304.4,,2.6,Russia,412,"Sea-level variant of RD-120 engine, similar to RD-120K. Gimbaling +/- 6 degree in two planes."
RD-134,RD-134,,,Lox/Hydrocarbon,Glushko,upper stage,,4,343,,540,2.4,1.6,167,,Lox/Kerosene,357,,,2.6,Russia,325,"Proposed upper stage kerosene engine. Gimbaling +/- 3 degree in two planes. Status 1996 was project, development estimated for four years. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400."
RD-134R,RD-134R,11D123,RD-123,Lox/Hydrocarbon,Glushko,Angara stage 2 vernier,1993,4 (?),343,,,,,,,Lox/Kerosene,,,,,Russia,21,Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG-1.
RD-135,RD-135,,,Lox/LH2,Glushko,upper stage,-1976,,,,,,,,,Lox/LH2,,,,,Russia,324,Experimental cryogenic engine. (Ref. May be not correct.)
RD-146,RD-146,11D123,RD-123,Lox/Hydrocarbon,Glushko,Angara stage 2,1993,1,883,,,,,,,Lox/Kerosene,,,,,Russia,21,Sea-level variant of RD-120 engine. Proposed in initial study for Angara by RKK Energia in1993. Kerosene RG-1.
RD-160,RD-160,,,Lox/Hydrocarbon,Glushko,upper stage,,1,19.6,,129,0.764,1.7,117.7,351.6,Lox/LCH4,380.6,,900,3.69,Russia,325,"Methane version of upper stage engine RD-161 (1). Gimbaling +/- 6 degree in two planes. Status 1996 was RD-161 prototype, development estimated for four years. Nozzle expansion ratio is 120/0.05=2400."
RD-160,,,,Lox/Hydrocarbon,Glushko,Upper stage,1993-,1,19.6,,129,0.764,1.7,,,Lox/LCH4,380.6,,,,Russia,325,Methane version of RD-161 engine. Gimbaling +/- 6 degree in two planes. In 1996 development estimated to take  four years. Prototype was RD-161.
RD-161-1,RD-161 (1),,,Lox/Hydrocarbon,Glushko,,,1,19.6,,119,0.78,1.7,117.7,351.6,Lox/Kerosene,360,,900,2.6,Russia,318,Proposed for use on Soyuz M-3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump.
RD-161-2,RD-161 (2),,,Lox/Hydrocarbon,Glushko,,,1,19.9,,141,1.02,2.21,117.7,370.6,Lox/Kerosene,365,,900,2.6,Russia,318,Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump.
RD-161P,RD-161P,,,Lox/Hydrocarbon,Glushko,Soyuz M stage 3 (block LM),1993-,1,24.5,,105,1.24,1.45,117.7,265,H2O2/Kerosene,319,,900,5.9,Russia,318,"Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%."
RD-167,RD-167,,,Lox/Hydrocarbon,Glushko,upper stage,,4,353,,570,2.4,1.6,167,,Lox/LCH4,379,,,3.4,Russia,325,"Proposed upper stage engine, obviously a methane variant of RD-134. Gimbaling +/- 3 degree in two planes. Status 1996 was project, development estimated for four years. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400"
RD-169,RD-169,,,Lox/Hydrocarbon,Glushko,Riksha-0 stage 1,,1,167,,215,0.5,1.7,147,,Lox/LCH4,351,309,,3.4,Russia,325,"LOX/Methane engine derived from RD-120. Gimbaling +/- 8 degree in two planes. Status 1996 was project, development estimated for four years. Nozzle expansion ratio is 150/0.51=294."
RD-170,RD-170,11D520,,Lox/Hydrocarbon,Glushko,Energia strap-on,1981-93,4,7903,1887.5,9750,4.015,3.78,245,36.87,Lox/Kerosene,337,309,150,2.6,Russia,"225, 287, 317, 342, 347","The RD-170 and RD-171 engines consisted of 4 chambers, 1 turbo-pump and 2 gas generators were developed simultaneously, the difference being one-plane gimballing in the RD-170 used in the Energia launch vehicle strap-ons versus two-plane gimablling i"
RD-171,RD-171,11D521,,Lox/Hydrocarbon,Glushko,Zenit stage 1,1976-86,4,7903,1887.5,9500,4.015,3.78,245,36.87,Lox/Kerosene,337,309,150,2.63,Russia,"287, 317, 342","The RD-170 and RD-171 engines consisted of 4 chambers, 1 turbo-pump and 2 gas generators were developed simultaneously, the difference being one-plane gimballing in the RD-170 used in the Energia launch vehicle strap-ons versus two-plane gimablling i"
RD-172,RD-172,,,Lox/Hydrocarbon,Glushko,Zenit-3 stage 1 (?),-1994,4,8354,,11703,4,3.78,258.9,36.87,Lox/Kerosene,337,311,,2.6,Russia,354,Uprated version of RD-171. To have been qualified for flight 1994.
RD-173,RD-173,,,Lox/Hydrocarbon,Glushko,Zenit-3 stage 1 (?),,4,8181,,,4.015,3.78,255,36.87,Lox/Kerosene,337,311,,2.63,Russia,42,"Uprated version of RD-171 with 4 chambers, 1 turbo-pump and 2 gas generators. Intended for uprated Zenit named Zenit 3"
RD-174,RD-174,,,Lox/Hydrocarbon,Glushko,Angara stage I,1995-,4,7905,,,,,,,Lox/Kerosene,,,,,Russia,,
RD-182,RD-182,,RD-120M,Lox/Hydrocarbon,Glushko,"Riksha (-1, -2) stage 1",1994-,1,902,,1500,1.5,2.8,172,,Lox/LCH4,353,316,,3.4,Russia,325,"Methane variant of RD-120K engine. Thrust range and Isp range due to throat diam. and chamber pressure. Gimbaling +/- 6 degree in two planes. Status 1996 was RD-120K, development estimated for three years. Chamber pressure 163 - 172."
RD-182M,RD-182M,,,Lox/Hydrocarbon,Glushko,Vozdushnyy Start stage 1,1998-,1,882,,,,,,,Lox/LNG,,,,,Russia,327,Variant of RD-182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash.
RD-183,RD-183,,,Lox/Hydrocarbon,Glushko,"Riksha (-0, -1, -2) apogee stage",1996-,1,9.8,,60,0.31,1.15,73.5,,Lox/LCH4,360,,,3.4,Russia,325,"Main engine for apogee stage of Riksha-1 launcher project. Gimbaling +/- 10 degree in two planes. Status 1996 was project, development estimated for four years. Nozzle expansion ratio is 75/0.055=1364."
RD-184,RD-184,,,Lox/Hydrocarbon,Glushko,"Riksha (-0, -1, -2) apogee stage",1996-,1,,,,0.065,0.24,2,,Lox/LCH4,322,,,2.5,Russia,402,"Probably attitude correction engine for apogee stage of Riksha-1 launcher project (together with RD-183). Gimbaling +/- 20 degree in two planes. Status 1996 was project, development estimated to take four years."
RD-185,RD-185,,,Lox/Hydrocarbon,Glushko,Riksha-0 stage 2,1996-,1,179,,415,1.5,3.3,147,,Lox/LCH4,378,,,3.4,Russia,325,"Upper stage version of RD-169 with larger nozzle. Gimbaling +/- 4 degree in two planes. Status 1996 was project, development estimated for four years. Nozzle expansion ratio is 150/0.036=4167."
RD-190,RD-190,,,Lox/Hydrocarbon,Glushko,Riksha-0 stage 1,1996-,6,1000,,1470,2.4,1.7,147,,Lox/LCH4,351,309,,3.4,Russia,325,The RD-190 consists of 6 RD-169 engines. Each chamber can be gimbaled individually in two planes by +/- 8 degree.
RD-191,RD-191,,RD-191M,Lox/Hydrocarbon,Glushko,Angara stage 1,1996-,1,2079,,3230,2,4.05,257,37,Lox/Kerosene,337,311,150,2.6,Russia,"287, 325, 352",Proposed for stage 1 of the Angara family of ELVs. This is single chamber motor would be 1/4 of the RD-170/171 so would be cheap and fast to develop. It has only reached the draft project stage. Gimbaling +/- 8 degree in two planes.
RD-191M ,RD-191M ,,,Lox/Hydrocarbon,Glushko,Angara stage I,1996-,1,1976,,,,,,,Lox/RG-1,337.5,,,,Russia,,Single chamber version of the RD-170 / RD-171.
RD-192,RD-192,,,Lox/Hydrocarbon,Glushko,,1996-,1,2138,,3300,2,4.05,257,,Lox/LCH4,356,330,,3.5,Russia,325,"Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. Status 1996 was project based on RD-191 prototype, development estimated for four years. Nozzle expansion ratio is 262/0.75=349."
RD-192.2,RD-192.2,,,Lox/Hydrocarbon,Glushko,,1996-,1,1942,,,1.45,3.62,196,,Lox/LCH4,354,325,,3.5,Russia,402,"Proposed variant of RD-192. Staged combustion cycle with fuel-rich gas generator. Gimbaling +/- 8 degree in two planes. Status 1998 was project based on RD-191 protoype, development estimated to take four years."
RD-192.3,RD-192.3,,,Lox/Hydrocarbon,Glushko,,1996-,1,2089,,,1.45,3.62,245,,Lox/LCH4,341,311,,3,Russia,402,"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."
RD-192S,RD-192S,,,Lox/Hydrocarbon,Glushko,,1996-,1,2128,,,2.4,4.82,196,,Lox/LCH4,371.5,,,3.5,Russia,402,"Proposed variant of RD-192. Staged combustion cycle with oxidizer-rich gas generator. Gimbaling +/- 8 degree in two planes. Status 1998  project based on RD-191 protoype, development estimated for four years."
RD-1KhZ,RD-1KhZ,,,Storable liquid,Glushko,"take-off acelleration of Pe-2R, La-7R, Yak-3, Su-6, Su-7, La-120R airplanes",1941-46,1,2.94,,60,,,22,,Nitric acid/Kerosene,200,,,,Russia,342,The RD-1KhZ was a variant of the RD-1 engine with chemical ignition. Production 1944-45.
RD-2,RD-2,,,Storable liquid,Glushko,experimental,1945-47,1,6,,71,,,20.6,,Nitric acid/Kerosene,200,,,,Russia,342,The RD-2 was based on the RD-1 engine. Used chemical ignition.
RD-200,RD-200,,,Storable liquid,Glushko,vertical sounding rocket,-1951,,98.508,,218,0.53,0.505,23.5,4,HNO3/TM-114,234,210,605,3.76,Russia,320,
RD-210,RD-210,,,Storable liquid,Glushko,vertical sounding rocket,-1954,,29.85,,80.6,0.4,1.4,23.5,4.16,HNO3/TM-114,241,214,60,4.12,Russia,320,
RD-211,RD-211,,,Storable liquid,Glushko,long-distance missile,1952-55,,642.3,,635.2,1.65,2.7,39.2,9.52,AK20/TM-185,261.8,223.6,122,4.05,Russia,320,
RD-212,RD-212,,,Storable liquid,Glushko,winged rocket M-40 (1),1952-56,4,623,,642,1.48,2.5,39.2,7.2,AK27I/TM-185,253,227,100,3.97,Russia,"320, 344","Intended for acceleration of winged rocket, development to 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 28,4 / 39,2 bar."
RD-213,RD-213,,,Storable liquid,Glushko,Winged rocket M-40 (2),1956-57,4,755,,625,1.48,2.503,46.6,7.21,AK27I/TM-185,254,231,110,3.97,Russia,"320, 344","Two thrust levels. Ignition with propellant TG-02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level."
RD-214,RD-214,,,Storable liquid,Glushko,"Kosmos B-1, (SS-4 Sandal) stage 1",1955-59,4,730,158.8,655,2.38,1.48,43.6,9.42,AK27I/TM-185,264,230,140,3.97,Russia,"225, 317, 320","Engine Cycle: Open. Feed Method: single turbopump driven by H2O2 gas generator feeding four fixed chambers.  Ignition with propellant TG-02. Chamber Internal Diameter . 480 mm, throat diameter 176 mm. Diameter is per chamber."
RD-215,RD-215,,,Storable liquid,Glushko,"R-14, Kosmos 11K63 stage 1",1958-60,2,864,,675,,,73.6,18.8,RFNA/UDMH,291.4,247.7,146,2.5,Russia,320,Original intended use unknown. Two RD-215 clustered to make RD-216.
RD-216,RD-216,11D614,,Storable liquid,Glushko,"R-14, Kosmos 11K63 stage 1",1958-60,4,1728,367.3,1350,2.26,2.195,73.6,18.8,AK27I/UDMH,291.4,247.7,146,2.5,Russia,"225, 287, 42, 317, 320",RD-216 is a block of 2 RD-215's.  The RD-216 had 2 combustion chambers and 2 turbines. Two sets of these were used in the first stage of the R-14 missile and Kosmos 11K63 series launch vehicles. Beginning with this engine Glushko cut the previous 3 t
RD-216M,RD-216M,,,Storable liquid,Glushko,Kosmos-3M stage I,1960s,4,,,,,,,,AK27I/UDMH,,,,,Russia,,
RD-217,RD-217,8D515,,Storable liquid,Glushko,R-16 stage 1,1958-61,2,865,,980,,,73.6,18.8,AK27I/UDMH,289,246,,2.5,Russia,320,Original intended use unknown. Three RD-217 clustered to make RD-218.
RD-218,RD-218,8D712,11D69,Storable liquid,Glushko,R-16 stage 1,1958-61,6,2592,555,1960,2.789,2.188,73.6,18.8,AK27I/UDMH,289,246,,2.5,Russia,"119, 287, 317, 320",Consisted of three RD-217; had 6 combustion chambers and 3 turbines The RD-218 powered the R-16 ICBM that was referred to by Khrushchev at the UN when he claimed the USSR was producing missiles like sausages. Both the engines and the R-16 were built 
RD-219,RD-219,8D713,11D26,Storable liquid,Glushko,R-16 stage 2,1958-61,2,883,,760,2.16,2.03,73.6,25.8,AK27I/UDMH,293,,125,2.5,Russia,"225, 317. 320","RD-219 is a derivative of RD-217 with a truss and some piping changes. Despite higher expansion ratio the engine is shorter than first stage engines. The result is relatively low performance, with Isp just 3 sec more than that of 1st stage in vacuum."
RD-220,RD-220,,,Storable liquid,Glushko,missile stage 1 (stage 2 used RD-221).,1960-,1,1074,,760,1.29,2.6,147,31.8,AK27P/UDMH,306,270,,2.8,Russia,320,
RD-221,RD-221,,,Storable liquid,Glushko,missile stage 2 (stage 1 used RD-220).,1960-,1,1118,,1070,2.4,4.2,147,119.8,AK27P/UDMH,318,,,2.8,Russia,320,
RD-222,RD-222,,,Storable liquid,Glushko,missile stage 1 (stage 2 used RD-223),1960-61,1,1634,,980,1.46,3.47,147,26.3,AK27P/UDMH,302,272,,2.92,Russia,320,Precursor to RD-253.
RD-223,RD-223,,,Storable liquid,Glushko,missile stage 2 (stage 1 used RD-222),1960-61,1,1697,,1240,2.59,5.05,147,86.2,AK27P/UDMH,314,,,2.92,Russia,320,Precursor to RD-253.
RD-224,RD-224,8D721,,Storable liquid,Glushko,R-26 stage 1,1960-62,4,1778,,1250,2.27,2,83.4,21,AK27P/UDMH,294,251,100,2.5,Russia,320,RD-224 is a block of 2 RD-225s. An upper stage thrust chamber was developed under designation U102-000.
RD-225,RD-225,,,Storable liquid,Glushko,R-26 stage 1,1960-62,2,889,,,,,83.4,21,AK27P/UDMH,294,251,100,2.5,Russia,320,Two clustered together to make RD-224.
RD-250,RD-250,8D723,,Storable liquid,Glushko,"R-36-0 stage 1, Tsyklon 2 stage 1",1960-65,2,881,,576,,1.762,83.3,14.7,N2O4/UDMH,301,269,120,2.6,Russia,323,Assembly of 3 RD-250 units make RD-251.
RD-251,RD-251,8D723,,Storable liquid,Glushko,"R-36-0 stage 1, Tsyklon 2 stage 1",1961-65,6,2643,410.2,1729,2.52,1.762,83.3,14.7,N2O4/UDMH,301,269,120,2.6,Russia,"42, 317, 342",Assembly of 3 RD-250-type units.
RD-252,RD-252,,,Storable liquid,Glushko,R-36-0 stage 2; Tsyklon 2 stage 2,1961-66,2,940.5,342.3,715,2.59,2.186,89.5,46.1,N2O4/UDMH,317,,160,2.6,Russia,"317, 342, 349","Used modified chamber from RD-219, nozzle is conventional, so performance is higher."
RD-253,RD-275,,RD-253,Storable liquid,Glushko,,-1986,1,1745,,,,,,,N2O4/UDMH,,,,,Russia,"225, 335",Version of RD-253 with thrust increased by 7%. Includes an additional gas generator for tank pressurization. This enhancement is accomplished with only a minor modification to the propellant flow control valves. This modification first flew as a miss
RD-253-11D48,RD-253,11D48,,Storable liquid,Glushko,"Proton K-1, UR700-3",,1,1635,1474,1280,1.5,2.72,147,26,N2O4/UDMH,316,285,130,2.67,Russia,"219, 273, 287",Six gimballed single chamber RD-253 provide the first stage power for the UR-500 Proton launch vehicle. Development went rather quickly but there were problems transitioning to production. After development is completed in Russia production moves to 
RD-253-14D14,RD-253,14D14,,Storable liquid,Glushko,Proton KM-1,1990-99,1,1746,1578.2,1300,1.233333333,,157,,N2O4/UDMH,317,285,108,,Russia,219,Developed in 1990s.
RD-253-UR-700,RD-253,,,Storable liquid,Glushko,,,1,1745,,,,,,,N2O4/UDMH,,,,,Russia,"225, 335",UR-700 Stage 3.  Development of RD-253 with increased expansion ratio for upper stage use.
RD-254,RD-254,,,Storable liquid,Glushko,"N-1 upper stage, UR-700 stage 3",1962-66,1,1716,,,,,,,N2O4/UDMH,,,,,Russia,323,Proposed for use in N-1. High altitude version of RD-253 for 2nd stages.
RD-261,RD-261,,,Storable liquid,Glushko,Tsyklon 3 stage 1,1967-69,6,3032,,1764,0.745,1.762,83,14.7,N2O4/UDMH,301.4,269.6,120,2.6,Russia,"342, 344, 349",Based on RD-251
RD-262,RD-262,,,Storable liquid,Glushko,Tsyklon 3 stage 2,1967-69,2,941,,728,1.279,2.186,89.5,46.1,N2O4/UDMH,317.6,,160,2.6,Russia,"342, 344, 349",Based on RD-252
RD-263,RD-263,,,Storable liquid,Glushko,R-36M / RS-20A (SS-18 Mod 1) stage 1,1969-73,1,1155,,,,,206,,N2O4/UDMH,318,293,,2.67,Russia,323,Four RD-263 engines combined into RD-264 system.
RD-263F,RD-263F,,,Storable liquid,Glushko,,1980,1,,,,,,,,N2O4/UDMH,,,,,Russia,323,Project to upgrade RD-263. Upgrade was realized in RD-273 engine.
RD-264,RD-264,11D119,,Storable liquid,Glushko,R-36M / RS-20A (SS-18 Mod 1) stage 1,1969-73,4,4521,,3600,3.025,2.15,206,,N2O4/UDMH,318,293,,2.67,Russia,"315, 323, 342",Consists of four RD-263 engines.
RD-268,RD-268,,,Storable liquid,Glushko,MR-UR-100 / RS-16 (SS-17) stage 1,1969-76,1,1236,,770,1.083,2.15,226,,N2O4/UDMH,319,296,,2.67,Russia,342,First flight 1976. Modification of RD-263 engine.
RD-270,RD-270,8D420,,Storable liquid,Glushko,"UR-700, R-56 stage 1",1962-71,1,6713,6272,4470,3.3,4.85,261,,N2O4/UDMH,322,301,,2.67,Russia,287,"Authorized for development in the 1962-1971 period, the RD-270 was Glushko's answer to the US F-1 rocket engine and was the largest rocket engine ever built in the Soviet Union. It was to be used on Chelomei's UR-700 lunar vehicle or Yangel's R-56 mo"
RD-270M,RD-270M,8D420M,,Exotic,Glushko,,1962-70,1,7159,,,,,,,N2O4/Pentaborane,365,340,,,Russia,283,In 1962-1970 Glushko studied use of Pentaborane 'zip' propellants in his monster RD-270 engine. This would have created immense toxicity problems but increased the specific impulse of the engine by 42 seconds.
RD-273,RD-273,,,Storable liquid,Glushko,,1975-82,1,1238,,,,,226,,N2O4/UDMH,,296,,,Russia,323,Upgrade of RD-263 in 1982 based on RD-263F project.
RD-274,RD-274,,,Storable liquid,Glushko,,1975-85,4,4952,,,,,226,,N2O4/UDMH,,296,,,Russia,323,"Upgrade of RD-264 engine with increased chamber pressure and thrust. Development stopped due to problems, e.g. turbopump shaft balance. Consists of four RD-273 engines."
RD-275,RD-275,,,Storable liquid,Glushko,Proton stage 1,1980's,1,1745,,1280,1.5,2.72,157,26,N2O4/UDMH,317,285,130,2.67,Russia,"98, 322","Uprated version of RD-253, developed in the 1980's."
RD-280,RD-280,,,Storable liquid,Glushko,Experimental engine,1963-65,1,117.6,,174,1.266,2.2,147,,N2O4/Aerozine-50,350,,,1.718,Russia,317,Experimental engine using Aerozine 50 (50% UDMH + 50% hydrazine) as fuel.
RD-2MZV,RD-2MZV,,,Storable liquid,Dushkin,I-270,1944-47,2,13.7,,,,,,,Nitric acid/Kerosene,,,,,Russia,,Thrust variable 0.1-0.3 tf  / 0.35-1.4 tf.
RD-2MZV-F,RD-2MZV-F,,,Storable liquid,Dushkin,Samolet 5,1946,,19.6,,,,,,,Nitric acid/Kerosene,,,,,Russia,,
RD-3,RD-3,,,Storable liquid,Glushko,experimental,,3,9,,190,,,22,,Nitric acid/Kerosene,190,,,,Russia,342,The RD-3 was a cluster of three RD-1 engines with a new common turbopump. Ignition was by an ethane-air mixture.
RD-301,RD-301,8D21,8D21,Exotic,Glushko,Proton K stage 4,1965-77,1,96.67,19.6,183,0.98,1.89,117.6,108.7,LF2/Ammonia,400,,750,2.7,Russia,"225, 317, 343",Developed by Glushko beginning in 1965. Planned for use in Proton K-4H high energy upper stage.  Motor tested but never flown.
RD-302,RD-302,11D130F,11D130F,Exotic,Glushko,,1960-69,1,98,,,,,117.6,,LF2/Ammonia,405,,,,Russia,"323, 344",Successor to RD-303 and predecessor to RD-301. Staged combustion cycle.
RD-303,RD-303,11D14,11D14,Exotic,Glushko,,1960-65,1,,,,,,,,LF2/Ammonia,,,,,Russia,"323, 344",Predecessor to RD-302 and RD-301.
RD-350,RD-350,,,Exotic,Glushko,,1963-,,98,,,,,,,LF2/LH2,464,,,,Russia,283,Studied by Glushko as engine concept with high-energy propellants.
RD-36-41,RD-36-41,,,Turbojet,Lyulka,T-4,,1,158.4,144,,,,,,Air/Kerosene,1980,,5400,,Russia,303,Used in Sukhoi March 3 aircraft. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust.
RD-3A,RD-3A,,RD-102?,Lox/Hydrocarbon,Glushko,R-3A,1951-53,1,,390,885,,3.121,,,Lox/Alcohol-96%,,214,,0,Russia,"21, 283",Project for R-3A experimental missile. Stopped in favour of RD-103.
RD-410,RD-410,,,Nuclear,Glushko,UR-700M concept,1960s,1,68,,,,,,,Nuclear/LH2,,,,,Russia,,
RD-502,RD-502,,,Storable liquid,Glushko,Experimental upper stage engine,1960-66,1,98.1,,132,1.18,2.51,147,,H2O2/Pentaborane,380,,,,Russia,317,"Developed 1960-1966. Experimental upper stage engine. Program stopped due to toxicity of propellants. Proposed by Glushko for N-1 around Sept. 1960. Intended later for upper stages, e.g. Proton."
RD-510,RD-510,,,Storable liquid,Glushko,,1965-75,1,,,,,,,,H2O2/CxHy,,,,,Russia,319,
RD-510T,RD-510T,,,Storable liquid,Glushko,,1965-75,1,,,,,,,,H2O2/CxHy,,,,,Russia,319,
RD-511,RD-511,,,Storable liquid,Glushko,,1965-75,1,,,,,,,,H2O2/CxHy,,,,,Russia,319,
RD-54,D-54,11D54,,Lox/LH2,Lyulka,N1 concept stage III,1960-75,1,392,,,,,,,Lox/LH2,440,,360,,Russia,"95, 177, 307, 320",
RD-550,RD-550,,,Exotic,Glushko,experimental upper stage engine,1963-70,1,98.06,,,,,,,Lox/30% Beryllium+Pentaborane in 70% Hydrazine,400,,,,Russia,283,Toxic exotic propellant engine studied by Glushko in 1963-1970.
RD-56,RD-56,11D56,"KVD-1, D-56",Lox/LH2,Isayev,N1 block R,1960-77,1,69.6,,282,1.56,2.14,55.9,198.7,Lox/LH2,462,,800,6,Russia,"225, 227, 93, 314, 344",Oxygen-hydrogen engine for cryogenic upper stage. Developed but never flown. Design sold to India in 1990's for GSLV.
RD-56M,RD-56M,11D56M,KVD-1M,Lox/LH2,Isayev,"Proton and Angara upper stage KVRB, 12KRB upper stage for GSLV (India)",1994-,1,73.58,,,,,,,Lox/LH2,461,,,,Russia,"89, 342",Engine for KVRB cryogenic kick stage. Was to be completed by the end of 1995 (Competing against motor by CADB). Currently no decision taken. Also used in 12KRB cryogenic upper stage for the Indian GSLV launcher.
RD-56M LNG,RD-56M LNG,,KVD-1M LNG,Lox/Hydrocarbon,Isayev,Vozdushnyy Start stage 2,1996-,1,73.5,,,,,,,Lox/LNG,,,,,Russia,327,Variant of RD-56M using liquid natural gas in place of hydrogen. First engine tests performed in 1998.
RD-57,RD-57,11D57,D-57,Lox/LH2,Lyulka,N1 Block S (N-1M),1960-77,1,392,,840,1.86,3.66,111,142.3,Lox/LH2,456.5,,800,5.8,Russia,"89, 331","One to have been used in N1 Block S. In fixed chamber version, 3 to 6 to have been used in N1 Block V-III. Engine system includes roll control thruster with 1.29 kN thrust."
RD-57A-1,RD-57A-1,,,Lox/LH2,Lyulka,,1995-98,1,395,,550,1.85,3.148,,143,Lox/LH2,460,,,5.8,Russia,332,"New version of RD-57M for SSTO-demonstrator proposed by Aerojet. Optimized nozzle contour for performance increase, new chamber material for weight reduction. First launch was planned for 3rd quarter 1998 in 1994, but not performed until 1999."
RD-57M,RD-57M,11D57M,,Lox/LH2,Lyulka,Vulkan Blok V,1960-74,1,397,,874,2,4.06,115,170,Lox/LH2,461,,,6.2,Russia,"89, 94, 331",Version with extendible nozzle. Ref. Lyulka 94 has higher mass at 911 kg and higher fixed nozzle area ratio at 100. Length 4.06 / 2.61 m. Specific impulse 461 / 448 sec. Area ratio 170 / 87.6.
RD-58,RD-58,11D58,,Lox/Hydrocarbon,Korolev,N-1 stage 5; Proton 8K82K / 11S824 stage 4 (block D),1964-68,1,83.4,,300,1.17,,78,189,Lox/RG-1,349,,600,,Russia,21,Kerosene changed from T-1 to RG-1 to achieve sufficient chamber cooling.
RD-58M,RD-58M,11D58M,,Lox/Hydrocarbon,Korolev,Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM),1970-74,1,83.4,,230,1.17,2.27,77.5,189,Lox/Kerosene,353,,680,2.48,Russia,"42, 315",
RD-58MF,RD-58MF,11D58MF,,Lox/Hydrocarbon,Korolev,"Zenit stage 3 (block DM-SL), upper stage projects N12RA, Proryv, LM, 315GK for Zenit, Angara, Energia-M",,1,83.4,,230,1.17,2.27,77.5,189,Lox/Kerosene,353,,660,0,Russia,"21, 404",Multi-function variant of RD-58 for uprated upper stages for future applications. Block-DM-SL for Sea-Launch may have used RD-58M.
RD-58S,RD-58S,11D58S,,Lox/Hydrocarbon,Korolev,Proton 8K82K / 11S861-01 stage 4 (block DM). Version 17D12 for Buran OMS.,1982-86,1,86.3,,230,1.17,2.27,79.4,189,Lox/Kerosene,361,,680,2.42,Russia,"42, 315",Version uses synthetic kerosene ('Sintin') for higher specific impulse.
RD-58Z,RD-58Z,11D58Z,,Lox/Hydrocarbon,Korolev,Zenit stage 3,,1,71,,300,2.9,,78,189,Lox/Kerosene,361,,660,,Russia,42,
RD-600,RD-600,,,Nuclear,Glushko,interplanetary launchers stage 2,1962-70,1,1960,,,,,,,Nuclear/LH2,2000,,,,Russia,"283, 287",Gas core nuclear engine worked on by Glushko 1962-1970. For use in second stage of two-stage interplanetary rockets. This gas phase nuclear reactor was designed by Energomash for a Venus station/Mars flight. It would be launched from orbit. Work stop
RD-701,RD-701,,,Lox/LH2,Glushko,MAKS spaceplane,1988-,2,4003,1406.1,3670,2.3,5.7,294,133.8,Lox/Kerosene/LH2,415,330,440,6,Russia,"287, 317, 334","The RD-701 was developed for the 22 tonne MAKS spaceplane, which was to have been launched at an altitude of 8 kilometres from the back of a behemoth An-225 Mriya transport. It was planned for 15 re-uses and featured both first and second stage engin"
RD-704,RD-704,,,Lox/LH2,Glushko,,1990's,1,1966,1720.1,2422,1.77,3.81,294,,Lox/Kerosene/LH2,407,356,,,Russia,319,"Tripropellant engine. Mass excluding sensors, gimbal actuators and heat shield. Single chamber derived from RD-701 project. Mass excluding sensors, gimbal actuators and heat shield.  Chamber pressure 294 / 124 bar. Specific impulse 407 / 452 sec."
RD-8,RD-8,11D513,,Storable liquid,Yangel,Zenit stage 2 attitude control engine,1976-85,4,78.4,,380,4,1.67,76.5,,N2O4/UDMH,342,,1100,2.4,Ukraine,"348, 357",Development since 1976.
RD-851,RD-851,8D63,,Storable liquid,Yangel,R-16 (SS-7) stage 1 attitude control engine ,1958-63,4,32.48,,403,3.54,1.7,66.2,,AK27/UDMH,279,243,115,2.45,Ukraine,"348, 344",Four thrusters are each gimbaled in one single axis.
RD-852,RD-852,,,Storable liquid,Yangel,R-16 (SS-7) stage 2 attitude control engine,1958-63,4,48.25,,133,2.95,2.4,66.2,,AK27/UDMH,255,,143,2.4,Ukraine,348,Four thrusters are each gimbaled in one single axis.
RD-853,RD-853,,,Storable liquid,Yangel,"Stage 2, no application",1960-63,1 + 4,467.6,,485,1.296,3.277,83.6,,AK27/UDMH,300.7,,134,2.41,Ukraine,348,"Designed for second stage, no application. Two thrust levels. Thrust 467.6 kN + 11.8 kN / 7.65 kN."
RD-854,RD-854,,,Storable liquid,Yangel,R-36orb (SS-X-10) orbital stage,1962-67,1 + 4,75.5,,100,1.53,1.505,85.3,,N2O4/UDMH,312.2,,70,2.02,Ukraine,348,Thrust vector control by 4 nozzles fed from gas generator.
RD-855,RD-855,,D-68M,Storable liquid,Yangel,Tsyklon stage 1 attitude control engine,1962-67,4,285.4,,320,3.808,1.741,65.7,,N2O4/UDMH,292,254,127,1.97,Ukraine,348,285.4 kN sea-level thrust.
RD-856,RD-856,,D-69M,Storable liquid,Yangel,Tsyklon stage 2 attitude control engine,1962-67,4,54.23,,112.5,3.654,1.122,71.6,,N2O4/UDMH,280.5,,163,1.98,Ukraine,348,
RD-857,RD-857,15D12,,Storable liquid,Yangel,Combined missile (RT-20P) stage 2,1963-67,1,13.73,,190,0.926,2.1,127.5,,N2O4/UDMH,329.5,,215,2.6,Ukraine,"323, 344, 348","Designed for second stage of combined missile, only flight tests. Thrust vector control by secondary gas injection into nozzle. Second thrust level at 12.75 kN."
RD-858,RD-858,,,Storable liquid,Yangel,LK lunar lander main engine,1964-72,1,20.1,,53,1.102,1.09,78.5,,N2O4/UDMH,315,,470,2.03,Ukraine,348,"The LK used a propulsion system designed by the Yangel Design Bureau. This consisted of the main engine RD-858 and the back-up
engine RD-859:
<PRE>
Engine                      RD-858                   RD-859
No of chambers:                1      "
RD-859,RD-859,,,Storable liquid,Yangel,LK lunar lander reserve engine,1964-72,2,20.05,,57,1.102,1.09,78.5,,N2O4/UDMH,312,,400,2,Ukraine,348,"The LK used a propulsion system designed by the Yangel Design Bureau. This consisted of the main engine RD-858 and the back-up
engine RD-859:
<PRE>
Engine                      RD-858                   RD-859
No of chambers:                1      "
RD-861,RD-861,11D25,"S5.23, D-25",Storable liquid,Yangel,Tsyklon 2 and 3 stage 3; Ikar,1968-72,1 + 4 + 2,78.71,,123,1.53,1.56,88.8,112.4,N2O4/UDMH,317,,130,2.1,Ukraine,"42, 348",Based on RD-854. Thrust vector control by 4 nozzles (thrust 98 N each) fed from gas generator. Mass given in ref. IAF-97-S.1.04 is 162 kg instead of 123 kg.
RD-862,RD-862,15D169,,Storable liquid,Yangel,MR-UR-100 / RS-16 (SS-17) stage 2,1969-72,1,142.63,,192,0.926,1.675,132.4,,N2O4/UDMH,331,,195,2.55,Ukraine,348,Based on RD-857. Thrust vector control by secondary gas injection into nozzle.
RD-863,RD-863,,,Storable liquid,Yangel,MR-UR-100 / RS-16 (SS-17) stage 1 attitude control engine,1970-73,4,276.84,,310,2.08,1.88,88.6,,N2O4/UDMH,301,259,130,2.15,Ukraine,348,
RD-864,RD-864,,,Storable liquid,Yangel,R-36M UTTKh / RS-20B (SS-18 Mod 2) vehicle bus,1976-78,4,20.2,,199,3,1.42,41,,N2O4/UDMH,309,,600,1.8,Ukraine,348,"Two thrust levels. The four thruster swing out of the stage housing before use. Chamber pressure 41 / 17 bar. Diameter 3,0 / 4,02 m. Specific impulse 309 / 298 sec."
RD-866,RD-866,3D65,,Storable liquid,Yangel,RT-23 / RS-22 (SS-24) MIRV-bus,1980-83,1 + 16,5.2,,125.4,1.98,1.186,40.7,,N2O4/UDMH,305.5,,330,2.03,Ukraine,"97, 330, 344, 348","One main and 16 control thrusters. 5,20 kN + 16 x 116 N. Chamber pressure 40,7 / 5,56 bar. Specific impulse 305,5 / 245 sec. Burn time 330 / 1200 sec. Oxidizer to fuel ratio 2,03 / 1,85"
RD-868,RD-868,,,Storable liquid,Yangel,Apogee stage,1983-,1 + x,23.25,,203,2.35,1.1,91.5,,N2O4/UDMH,325,,1600,2.2,Ukraine,348,"Still in development in 1996. One main and an unknown number of control thrusters. 23,25 + 0,03 kN.  Chamber pressure 91,5 / 6,9 bar. Specific impulse 325 / 230 sec. Burn time 1600 / 7200 sec. Oxidizer to fuel ratio 2,2 / 1,6"
RD-869,RD-869,,,Storable liquid,Yangel,R-36M2 / RS-20V (SS-18 Mod 4) vehicle bus,1983-85,1,8.58,,196,3,1.42,41,,N2O4/UDMH,313,,700,1.8,Ukraine,348,"Based on RD-864. Two thrust levels. The four thruster swing out of the stage housing before use.  Chamber pressure 41 / 17 bar. Diameter 3,0 / 4,02 m."
RDKS-1,,,,Storable liquid,,,End 40's,,,,,,,,,,,,,,Russia,415,Single chamber with turbopump propellant feed.
RDKS-100,,,,Lox/Hydrocarbon,Dushkin,Sanger,1946-51,1,980,,,,,,,Lox/Kerosene,285,,,,Russia,,
RDMT-0.4 X,,,,Storable liquid,NII Mash,,,1,0.0004,,0.1,,,,,N2O4/UDMH,290,,,,Russia,336,"Experimental low-thrust thruster. Chamber from niobium alloy.  Chamber pressure 41 / 17 bar. Specific impulse 313 / 302,3 sec."
RDMT-0.8,,,,Cold Gas,NII Mash,Kosmos satellites,,1,0.0008,,0.1,,,,,Nitrogen+Helium,70,,,,Russia,336,Low-thrust cold-gas thruster. Specific impulse 70 / 160 sec.
RDMT-100,,,,Storable liquid,NII Mash,"Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites",,1,0.1,,1.2,,,9,,N2O4/UDMH,260,,,,Russia,336,Low-thrust attitude control thruster.
RDMT-12,,17D58E,,Storable liquid,NII Mash,"Almaz, Kvant, Kristall, Spektr, Priroda",,1,0.012,,0.55,,,9,,N2O4/UDMH,279,,,,Russia,336,Low-thrust attitude control thruster. Predecessor was RDMT-400. Used in Isayev 17D58E engine.
RDMT-135,,,,Storable liquid,NII Mash,"Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites",,1,0.135,,1.2,,,9,,N2O4/UDMH,260,,,,Russia,336,Low-thrust attitude control thruster.
RDMT-200,,,,Storable liquid,NII Mash,Almaz,,1,0.2,,2,,,9,,N2O4/UDMH,255,,,,Russia,336,Low-thrust attitude control thruster.
RDMT-200K,,,,Lox/Hydrocarbon,NII Mash,Buran,,1,0.2,,5.5,,,,,GOX/Kerosene,265,,,,Russia,336,Low-thrust attitude control thruster. Mass in ref. NIIMash 95 given as only 2.5 kg.
RDMT-2600,,,,Lox/Hydrocarbon,NII Mash,,,1,2.6,,5,,,,,GOX/Alcohol,270,,,,Russia,336,Experimental low-thrust thruster.
RDMT-400,,11D458,,Storable liquid,NII Mash,"Almaz, Kvant, Kristall, Spektr, Priroda",,1,0.4,,2.5,,,9,,N2O4/UDMH,255,,,,Russia,336,Low-thrust attitude control thruster. Used in Isayev 11D458 engine.
RDMT-400 X,,,,Storable liquid,NII Mash,,,1,0.4,,0.125,,,30,,N2O4/UDMH,296,,,,Russia,336,Experimental low-thrust thruster. Carbon combustion chamber. Mass may be chamber only.
RDMT-400A,,,,Storable liquid,NII Mash,,,1,0.4,,2.8,,,,,N2O4/UDMH,290,,,,Russia,336,Experimental low-thrust thruster. Niobium combustion chamber with coating.
RDMT-5,,,,Cold Gas,NII Mash,MMK,,1,0.005,,0.35,,,,,Air,70,,,,Russia,336,Low-thrust cold-gas thruster.
RDMT-50,,,,Storable liquid,NII Mash,Kosmos satellites,,1,0.05,,1,,,9,,N2O4/UDMH,255,,,,Russia,336,Low-thrust attitude control thruster.
RDMT-8 X,,,,Storable liquid,NII Mash,,,1,0.008,,0.025,,,30,,N2O4/UDMH,296,,,,Russia,336,Experimental low-thrust thruster.
RPD-04,,,,,Dushkin,,,,,,,,,,,,,,,,Russia,,
RU-013,,,,Storable liquid,Dushkin,,1955-57,,31,,,,,,,Liquid propellants,,,,,Russia,,
S-155,,,,Storable liquid,Dushkin,E-50,1955-56,,39,,,,,,,Liquid propellants,,,,,Russia,,Thrust variable 2000 - 4000 kgf.
S-3-20M5A,,,,Storable liquid,Dushkin,U-21,-1959,,,,,,,,,Nitric acid/Kerosene,,,,,Russia,,
S09.29,S09.29,,,Storable liquid,Isayev,V-300/V-303 (S-25 system),1950-55,4,88,,,,,,,Nitric acid/Amine,,,,,Russia,,
S1.35800,,,S1.35800,Lox/Hydrocarbon,Korolev,R-7 verniers,1954-57,,30,,,,,,,Lox/Kerosene,,,,,Russia,,Thrust variable 2.5-3.1 tf
S1.5400,,11D33,S1.5400,Lox/Hydrocarbon,Korolev,Molniya 8K78-3,1958-60,1,66.7,,153,,,53.5,,Lox/Kerosene,340,,207,,Russia,177,Originally designed by Korolev; passed to Isayev for production. Began a series of engines leading through the 8D726 for GR-1 to the Block D for the N1 and Proton. Earliest versions with 6380 kgf and 338.5 sec specific impulse.
S1.5400A,,11D33M,S1.5400A,Lox/Hydrocarbon,Korolev,Molniya 8K78M-3,1961-64,1,67.3,,148.3,,,54,,Lox/RG-1,342,,200,,Russia,64,
S2.1100,,,S2.1100,Storable liquid,Isayev,V-1000,1955-60,4,,,,,,,,,,,,,Russia,,OKB-2 transferred work on the S2.1100 to OKB-117 in 1958-59. OKB-117 completed development.
S2.1150,,,S2.1150,Storable liquid,Isayev,Burya booster,1953-59,4,671.2,,650,1.206,1.87,53,,Nitric acid/Amine,250,218,70,,Russia,"342, 344","Booster engine for Burya missile. Two used to boost ramjet second stage to ignition conditions. Engines developed by Isayev from R-11 S2.253 engine.  Early Buryas had S2.1100 engine. Two thrust levels.  671,20 / 477 kN sea-level."
S2.1200,RO-1,,S2.1200,Storable liquid,Isayev,,1950s middle,,,,,,,,,,,,,,Russia,,OKB-2 transferred work on the S2.1200 to OKB-154 in 1957. The latter used the designation RO-1 for the engine.
S2.145,,,S2.145,Storable liquid,Isayev,,1950s early,,88,,,,,,,,,,,,Russia,,
S2.253,,,S2.253,Storable liquid,Isayev,R-11 (Scud B) 8A61,1949-55,1,93.3,71,,0.96,,,,AK20I/T-1,251,219,95,,Russia,"21, 344","Thrust 8300 kgf at sea level. Fuel Kerosene T-1, chemical ignition by TG-02."
S2.253 derivative,,,S2.253 derivative,Lox/Hydrocarbon,Isayev,EKR (experimental winged missile),,1,93.2,,,,,,,Lox/Kerosene,250,217,127,,Russia,21,Derivative of S2.253 was proposed for use in EKR Stage 1 (project for an experimental winged missile).
S2.253A,,,S2.253A,Storable liquid,Isayev,R-11FM,1953-59,1,93,,,,,,,AK20I/T-1,,218,,3.76,Russia,"21, 340, 344","Used in R-11FM submarine version of Scud B. Fuel Kerosene T-1, chemical ignition by TG-02. Mixture ratio derived from tank content. 81 kN sea-level."
S2.713,,,S2.713,Storable liquid,Isayev,R-13 (SS-N-4),1956-61,1 + 4,252.2,,,,,,,AK27I/TG-02,,,,3.48,Russia,"319, 340, 344",First engine to employ gas generator on main propellants. One main and four vernier thrusters. (Mixture derived ratio from tank content.)
S2.720,,,S2.720,Storable liquid,Isayev,Engine for SAM-missile V-755,,1,34.3,34.3,47.5,0.476,0.945,64,,AK20K/TG-02,,233,55,3.23,Russia,"225, 329, 340, 342","Pump-fed engine. Used in engine unit of a special apparatus. Pump-fed engine. 20,4 kN sea level."
S2.721V,,,S2.721V,Storable liquid,Isayev,KSR,1956-,2,11.8,,,,,,,AK20F/TG-02,,,,,Russia,,
S3.42A,,,S3.42A,Storable liquid,Sevruk,217,1954-,,166,,,,,,,,,,,,Russia,,
S5.1,,,S5.1,Storable liquid,Isayev,SAM-missiles 217M and 218,1950s late,1,167,,122,0.624,1.016,,,AK27I/TG-02,,,,,Russia,"342, 344",Designation unknown.
S5.3,,,S5.3,Storable liquid,Isayev,R-21 (SS-N-5),1958-63,4,392,,,,,,,AK27I/TG-02,,,,,Russia,"319, 344",First engine to start underwater. 392 kN sea-level.
S5.3M,,,S5.3M,Storable liquid,Isayev,R-9 (SS-8) missile stage 1,"1959-60, 1958-60",4,396.7,,433,,,66,9.55,AK27I/TG-02,,241.3,,3.6,Russia,"320, 343","Proposed for R-9 missile stage 1. Four engines per stage. 396,7 kN sea-level."
S5.4,TDU-1,,S5.4,Storable liquid,Isayev,Vostok/Voskhod retorfire engine; spacecraft maneuvering engine. ,1959,1 + 4,15.83,,98,0.95,1.126,55.5,,AK20F/TG-02,266,,44.6,3.07,Russia,"225, 321, 329",Includes 4 small lateral steering nozzles.
S5.44,,5D25,S5.44,Storable liquid,Isayev,SAM-missile 5Ya24,1964-65,1,177,,124,0.54,1.713,,118,AK27I/TG-02,,251,,,Russia,"320, 342",Could be throttled. 177-49 kN sea-level. Area ratio 118 - 44.
S5.45,,,S5.45,Storable liquid,Isayev,"correction engine for Zond-1, Venera-2-8, and others.",,1,1961,,52,,,11.8,16,AK20F/UDMH,267,,53,2.6,Russia,"225, 320, 342","Pressure-fed engine. Used as correction engine for spacecraft Zond-1, Vernera-8, and others."
S5.51,,11D68,S5.51,Storable liquid,Isayev,Soyuz LOK lunar orbiter,1964-72,2 + 1,33.196,,480,,2.77,,,N2O4/UDMH,314,,700,1.85,Russia,"89, 314","Complex engine used to maneuver the LOK to a rendezvous with the LK lander in lunar orbit, then propel the LOK out of lunar orbit (large engine), and for midcourse corrections  (small engine). Burn time 700 + 300 sec. Oxidizer to fuel ratio 1,85 / 1,"
S5.80.1100-0,,,S5.80.1100-0,Lox/Hydrocarbon,Isayev,Soyuz-2 Blok LM,1990s,1,2.94,,,,,,,Lox/Kerosene,,,,,Russia,,Thrust chamber from KTDU-80 / S5.80 converted to burn Lox/Kerosene.
S5.92,,,S5.92,Storable liquid,Isayev,Phobos propulsion module,,1,19.6,,75,0.84,1.03,97,153.8,N2O4/UDMH,327,,2000,2,Russia,293,"Gas generator cycle. Nominal and low-thrust thrust levels. Low thrust version with 1400 kgf, chamber diameter of 0.68 m, chamber pressure of 67 bar, specific impulse 316 seconds. Chamber pressure 97 / 67. Specific impulse 327 / 316 sec."
S5.98M,,14D30,S5.98M,Storable liquid,Isayev,Rokot-3 Briz; Soyuz-2 Briz; Proton Briz-M,,1,19.62,,95,,,,,N2O4/UDMH,325.5,,3200,2,Russia,"359, 409","High performance storable liquid engine. Engine system consists of: main engine (2000 kgf, Isp=325.5 s) + 4 11D458 (40 kgf, Isp=252 s) + 12 17D58E  (1.36 kgf, Isp=247 s). Main engine: Derivative of S5.92. Capable of 8 restarts. Total deliverable impu"
SPRD-15,,,,Solid,Kartukov,"S-2 Strela, Sopka",1950s,,402,,,,,,,Solid,,,,,Russia,,Thrust 27 tf at cutout - 41at ignition.
SPRD-30,,,,Solid,Kartukov,P-15 Termit,1950s,,294,,,,,,,Solid,,,,,Russia,,Thrust 28 tf at cutout - 30 tf at ignition.
SPRD-99,,,,Solid,Kartukov,MiG-21PFM,,,24.5,,,,,,,Solid,,,,,Russia,,
SPT-100,,,,Solid,Stechkin,"Meteor, Gals",-1984,,0.196,,,,,,,,2500,800,,,Russia,,Thrust variable 2 to 20 kgf
SPT-100-SEP,,,,Solid,Stechkin,,,,,,,,,,,,2200,,,,Russia,,The French company SEP is developing this uprated version of the SPT-100 in cooperation with OKB Fakel.
SPT-140,,,,Solid,Stechkin,,,,,,,,,,,,,,,,Russia,,
SPT-200,,,,Solid,Stechkin,,,,0.78,,,,,,,,3000,800,,,Russia,,Thrust variable 8 to 80 kgf
SPT-290,,,,Solid,Stechkin,,,,,,,,,,,,,,,,Russia,,
SPT-50,,,,Solid,Stechkin,Meteor-Priroda,1972-78,,,,,,,,,,,,,,Russia,,
SPT-70,,,,Solid,Stechkin,Yamal,-1982,,0.098,,,,,,,,2500,800,,,Russia,,Thrust variable 1 to 10 kgf
Stepanov IS/US 1 kgf,,,,Storable liquid,Stepanov,IS/US,1960-63,,0.0098,,,,,,,N2O4/UDMH,,,,,Russia,,
Stepanov IS/US 16 kgf,,,,Storable liquid,Stepanov,IS/US,1960-63,,0.157,,,,,,,N2O4/UDMH,,,,,Russia,,
Stepanov LK/LOK 10 kgf,,,,Storable liquid,Stepanov,LK/LOK attitude,1965-72,,0.098,,,,,,,N2O4/UDMH,,,,,Russia,,
Stepanov LK/LOK 40 kgf,,,,Storable liquid,Stepanov,LK/LOK attitude,1965-72,,0.39,,,,,,,N2O4/UDMH,,,,,Russia,,
U-1250,,,,Storable liquid,Isayev,,1945-46,,12.7,,,,,,,,208,,,,Russia,,
U-2000,,,,Storable liquid,Isayev,for SAM,1940s late,,19.6,,,,,,,,,,,,Russia,,
U-400-10,,,,Storable liquid,Isayev,Samolet 5,1946-47,,3.92,,,,,,,,,,,,Russia,,
U-400-2,,,,Storable liquid,Isayev,Shchuka,1940s late,,,,,,,,,AK20K/TG-02,,,,,Russia,,
U102-000,,,RD-226 ?,Storable liquid,Glushko,R-26 stage 2,1960-62,1,468,,,1.353,2.238,83.6,48.4,AK27P/UDMH,307,,160,2.76,Russia,"193, 194, 320","Orevo has sectioned hardware. This is only the thrust chamber, probably based on RD-224 chamber. Other components like turbopumps, etc. were obviously the same as RD-224. Mass chamber only 198 kg."
YaERD-2200,,,,Nuclear,Korolev,,1962-69,,81,,,,,,,Nuclear/LH2,,,,,Russia,,
YaRD OKB-456,,,,Nuclear,Glushko,nuclear launcher,1958-,1,1373,,,,,,,Nuclear/Ammonia,470,430,500,,Russia,"21, 89","Korolev began work on 3 nuclear launchers on 30 June 1958. Competing engine design was by Bondaryuk. Used  nuclear reactor in cylindrical housing, operating at 3000 deg K. Propellant heated in the reactor and exhausted through four expansion nozzles."
YaRD OKB-670,,,,Nuclear,Bondaryuk,nuclear launcher,1958-,1,1667,,,,,,,Nuclear/NH3+Alcohol (C2H5OH),470,430,500,,Russia,"21, 89","Korolev began work on 3 nuclear launchers on 30 June 1958. Competing engine design was by Glushko. Used  nuclear reactor in cylindrical housings, operating at 3000 deg K. Propellant was heated in the reactor and exhausted through four expansion nozzl"
YaRD Type A,,,,Nuclear,Korolev,nuclear ICBM,,1,177,,4800,,,,,Nuclear/LH2,900,,700,,Russia,283,"Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant."
YaRD Type AF,,,,Nuclear,Korolev,nuclear ICBM,,1,196,,3250,,,,,Nuclear/LH2,950,,700,,Russia,283,"Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant."
YaRD Type V,,,,Nuclear,Korolev,nuclear ICBM,,1,392,,18000,,,,,Nuclear/LH2,900,,700,,Russia,283,"Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant."
YaRD Type V-B,,,,Nuclear,Korolev,nuclear ICBM,,1,392,,25000,,,,,Nuclear/LH2,900,,700,,Russia,283,"Design considered in N1 nuclear upper stage studies. This version had 7,000 kg bioshield for manned missions. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant."