Engine Manufacturer Name,Government Designation,Other Designations,Application,Development Organisation,Devel. Period,Comments,No. of Chambers,Thrust (vac) [kN],"Engine Mass [kg]", Diameter [m] , Length [m] ," Chamber Press [bar] ", Area Ratio ,Propellants,Isp-vac [sec],Isp (sea-level) [sec],Burn time [sec],Oxidizer to Fuel Ratio,Country,Reference 4D10,,,R-27 / RSM-25 (SS-N-6),KB-Isayev (now KBKhimMash),,First engine system to be submerged in propellant tank. One main engine chamber plus unknown number (probably 4) of steering thrusters.,1 + 4 (?), 226 + 29 ,,,,,,N2O4/UDMH,,,,,Russia,"FAS, Russ. Arms C., ""Raketi nad Morem""" 8D43,8D43,,UR-500 stage 1 original concept,OKB Kosberg (now KBKhimAvtomatiki),1960-64,Low-expansion ratio gimbaled variant developed for UR-500 stage 1. In initial configuration four 8D43 would be clustered with four Glushko 11D43. Abandoned in favor of six 11D48. The engine 8D43 was further developed into the RD-0208 and RD-0210 engines.,1,559,, , , 147.0 , 28.5 ,N2O4/UDMH,316,283.5,115,2.6,Russia,"Glushko 69, (Nov. Kosmon. 1/98´)" 8D43 + 11D43,8D43 + 11D43,,UR-500 stage 1 original concept,"OKB Kosberg (now KBKhimAvtomatiki) OKB Glushko (now NPO Energomash)",1960-64,In initial concept the first stage of the Proton was designed for 4 fixed 11D43 and 4 gimbaled Kosberg 8D43 (see separate entries for each engine). This configuration was replaced by six 11D48 from Glushko.,1,2247.45,, , , , ,N2O4/UDMH,310,280,115,,Russia,Nov. Kosmon. 1/98 8D415K,8D415K,,concept for N-1,OKB Kosberg (now KBKhimAvtomatiki),1960-,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.,1,1471,, , , , ,LOX/Kerosene,,,,,Russia,"Wade, Siddiqi" 8D423,"8D423, 11D423",,LK-700S manned lunar spacecraft project ascent stage,"Krasnyy Oktyabr Joint Stock Company, St. Peterburg",1963-67,"Produced by the Krasniy Oktyabr Joint Stock Company in St. Petersburg for the ascent stage of the LK-700S manned lunar project, designed by Chelomei.",,134,,,,,,N2O4/UDMH (?),326,,,,Russia,"FAS, Siddiqi" 11B97,11B97,,Interorbital Tug project,RKK Energia,1986-,"Beginning in 1978 the 11B97 nuclear electric engine was studied for use in a reusable interorbital space tug for launch by Energia. From 1982, as per the decree of 5 February 1981, NPO Energia developed this engine.",1,"0,4494 N",, , , , ,Xenon,3000,,57600000,,Russia,"""Energia 46-96""" 11D43,,,UR-500 stage 1 original concept,OKB Glushko (now NPO Energomash),1960-64,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.,1,1688.45,, , , , ,N2O4/UDMH,308,278,115,,Russia,Nov. Kosmon. 1-5/98 11D49,11D49,S5.23,Kosmos-3M stage 1,KB-Isayev (now KBKhimMash),1962-64,Processor was 11D47 in R-14 stage 2. Engine has one main and four steering nozzles.,1 + 4,"157,5 + 4 x 25",185, 1.92 , 1.78 , 98.1 , 103.4 ,AK27I/UDMH,303,0,4305,2.65,Russia,"Russian Arms Cat. (CD-VKS, Glushko 69)" 11D54,11D54,,N-1M stage 2 (block V),,,Designation 11D54 is also stated to be used for NK-19 ?,1,392.3,, , , , ,LOX/LH2,440,0,360,,Russia,"CADB 92, 95, Glushko 69, Varfolomeyev 6" 11D121,11D121,,N-1 stage 1 (block A) roll control engine,OKB Korolyov (now RKK Energia),1969-74,"Gimbaling +/- 45 degree. Propellants are fed from main engine (NK-15, NK-33) turbopumps.",1,68.65,,,, 71.6 ,,GOX/Kerosene,313,273,,,Russia,"Russian Arms Cat., Siddiqi" 11D428,,,"""Yantar-2K"" orbital propulsion","KB Melnikov (KBKhimMash ?)",,"Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions.",1,0.11,,,,, ,N2O4/UDMH,,,10000,,Russia,Nov. Kosm. 17-19/97 (via S. Grahn) 11D430,,,"""Yantar-2K"" orbital propulsion","KB Melnikov (KBKhimMash ?)",,"Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 50 ignitions.",1,2943,,,, 9.0 , ,N2O4/UDMH,307,,600,,Russia,Nov. Kosm. 17-19/97 (via S. Grahn) 11D431,,,"""Yantar-2K"" orbital propulsion","KB Melnikov (KBKhimMash ?)",,"Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 150,000 ignitions.",1,"5,88 N",,,,, ,N2O4/UDMH,,,2000,,Russia,Nov. Kosm. 17-19/97 (via S. Grahn) 11D445,,,"""Yantar-2K"" descent propulsion","KB Melnikov (KBKhimMash ?)",,"Propulsion system of the Yantar-2K military satellite descent capsule. Up to 10,000 ignitions.",1,"0,065 - 0,012",,,,, ,N2O4/UDMH,,,900,,Russia,Nov. Kosm. 17-19/97 (via S. Grahn) 11D446,,,"""Yantar-2K"" orbital propulsion","KB Melnikov (KBKhimMash ?)",,"Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions.",4,0.052,,,,, ,N2O4/UDMH,,,4000,,Russia,Nov. Kosm. 17-19/97 (via S. Grahn) 11D458,,,Rokot-3 Briz; Soyuz-2 Briz; Proton Briz-M vernier,KBKhimMash,,Small attitude control thruster in Briz upper stage propulsion system S5.98M,1,0.392,, , , , ,N2O4/UDMH,252,,3200,2,Russia, 17D11,,,Buran OMS and verniers,RKK Energia,1982-86,"Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT-200K",1,86.3,230, 1.17 , 2.27 , 79.4 , 189.0 ,LOX/Sintin,362,0,680,2.42,Russia,"Energia 92, 95" 17D12,,,Buran OMS,RKK Energia,1982-86,"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 ignitions.",1,86.3,230, 1.17 , 2.27 , 79.4 , 189.0 ,LOX/Sintin,362,0,680,2.42,Russia,"Energia 92, 95" 17D15,,,Buran OMS large verniers,RKK Energia,1982-86,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.,1,4,,,,," 19,8 - 50 ",GOX/Sintin,275 - 295,0,10800,,Russia,"Energia 92, 95" 17D58E,,,Rokot-3 Briz; Soyuz-2 Briz; Proton Briz-M vernier,KBKhimMash,,Small attitude control thruster in Briz upper stage propulsion system S5.98M,1,0.0133,, , , , ,N2O4/UDMH,247,,3200,2,Russia, 17D61,,,"""Ikar"" stage 4 for Soyuz-Ikar","KB Melnikov (KBKhimMash ?)",,"Derived from orbital propulsion module used for military satellites, used over 30 times until 1998. Ikar upper stage is used to upgrade the Soyuz launcher, replacing the Block L stage 4. Main improvement is versatility due to capability for 50 restarts.",1 + 4 + 4 + 8,"2943 + 4 x 0,11 + 4 x 0,052 + 8 x 5,88 N",820, 2.72 , 2.56 , 9.0 , ,N2O4/UDMH,307,,600,,Russia,"Starsem 97 (Starsem 99-2), Nov. Kosm. 17-19/97 (via S. Grahn)" Burlak Stage 1,,,Burlak stage 1,,,"Status: Hardware. 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.",1,360,, , , , ,N2O4/UDMH,320,270,140,,Russia,Wade Burlak Stage 2,,,Burlak stage 2,,,"Status: Hardware. 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.",1,98,, , , , ,N2O4/UDMH,330,230,275,,Russia,Wade DOK-10,,,,KB-Isayev (now KBKhimMash),,"Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions",1,10 N,0.6,,, 10.0 , 46.0 ,N2H4,229.4,,1500,,Russia,CMDB 98 DOK-50,,,,KB-Isayev (now KBKhimMash),,"Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions",1,50 N,1.1,,, 8.0 , 42.0 ,N2H4,229.4,,1500,,Russia,CMDB 98 DOT-5,,,,KB-Isayev (now KBKhimMash),,"Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 550,000 ignitions",1,5 N,0.9,,, 3.8 , 60.0 ,N2H4,230,,120000,,Russia,CMDB 98 DOT-25,,,,KB-Isayev (now KBKhimMash),,"Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions",1,25 N,1.3,,, 4.5 , 55.0 ,N2H4,234.5,,25000,,Russia,CMDB 98 DST-25,,,,KB-Isayev (now KBKhimMash),,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 300,000 ignitions",1,25 N,0.9,,, 8.0 , 45.0 ,N2O4/UDMH,285,,25000,1.85,Russia,CMDB 98 DST-100,,,,KB-Isayev (now KBKhimMash),,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions",1,100 N,1.1,,, 15.0 , 43.0 ,N2O4/UDMH,276,,10000,1.85,Russia,CMDB 98 DST-100A,,,,KB-Isayev (now KBKhimMash),,"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",1,100 N,1.5,,, 7.7 , 100.0 ,N2O4/UDMH,304,,50000,1.85,Russia,CMDB 98 DST-200,,,,KB-Isayev (now KBKhimMash),,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions",1,200 N,1.3,,, 15.0 , 43.0 ,N2O4/UDMH,280,,5000,1.85,Russia,CMDB 98 DST-200A,,,,KB-Isayev (now KBKhimMash),,"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",1,200 N,1.7,,, 7.0 , 100.0 ,N2O4/UDMH,300,,10000,1.85,Russia,CMDB 98 DMT-600,,,,KB-Isayev (now KBKhimMash),,"Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 6,000 ignitions",1,600 N,4.2,,, 9.0 , 46.5 ,N2O4/UDMH,300.8,,5000,1.85,Russia,CMDB 98 DMT-600 MMH,,,,KB-Isayev (now KBKhimMash),,"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",1,600 N,4.2,,, 9.0 , 46.5 ,N2O4/MMH,305.9,,5000,1.65,Russia,CMDB 98 D-1,,,,OKB Kosberg (now KBKhimAvtomatiki),1955-56,Second thrust level at 50%. Explosion of D-1 on test bench in 1956 forced stop of work with mono-propellant OT-152.,1,39 sea-level,,,, 35.3 , ,OT-152 (Isopropylnitrate ?),,210,,,Russia,CADB 95 D-7,,,missile by Toropov,OKB Kosberg (now KBKhimAvtomatiki),1956,Intended for air-air missile by I I Toropov. Uncooled thrust chamber.,1,"11,8 sea-level",,,, 29.4 , ,OT-152 (Isopropylnitrate ?),,200,6,,Russia,CADB 95 EKR Ramjet,,,EKR Stage 2,,1954,Study for an experimental winged rocket (missile) Not developed but formed basis for Burya and Buran missiles,1,6.13,, , , , ,Air/Kerosene,1580,0,800,,Russia,"""Energia 46-96""" Glushko M-41,,,Buran M-41,OKB Glushko,-1957,Canceled in November 1957. Specific impulse estimated.,1,617.8,, , , , ,LOX/Kerosene,290,253,70,,Russia,"""Energia 46-96""" Isayev-1,,,SAM-missile V-750V,KB-Isayev (now KBKhimMash),1954-57,Designation unknown.,1, 30 ,43, 0.48 , 0.93 ,, ,AK20K/TG-02,,,,,Russia,"Russian Arms Cat., Siddiqi" Isayev-2,,,missile P-15,KB-Isayev (now KBKhimMash),1955-60,Designation unknown.,1," 11,895-5,43 ",47, 0.40 , 1.19 ,, ,AK20K/TG-02,,,,,Russia,"Russian Arms Cat., Siddiqi" Isayev-3,,,R-17,KB-Isayev (now KBKhimMash),1958-64,Designation unknown.,1, 131 ,120, 0.77 , 1.49 ,, ,AK27I/TM-185,,,,,Russia,"Russian Arms Cat., Siddiqi" KDU-414,11D414,S5.19,"Molniya 1, Mars 1, Venera 1, Zond 2-3 maneuvering engine",KB-Isayev (now KBKhimMash),1960-65,Spacecraft maneuvering engine.,1,1.961,61, 0.74 , 1.02 , 11.8 , ,AK20F/UDMH,272,0,40,2.6,Russia,"Glushko 85, Russian Arms Cat., Siddiqi" KDU-426,11D426,,Soyuz-T orbital correction engine,KB-Isayev (now KBKhimMash),1968-74,Pressure-fed engine. Used as long duration engine.,1,3.089,270,2.1,1.235, 8.8 , ,N2O4/UDMH,292,,570,1.85,USSR,"Kudryavtsev 93, CMDB 94, Siddiqi" KRD-442,11D442,,"Orbital propulsion engine for Kvant, Kvant-2, Kristall, Spektr, Priroda, FGB",KB-Isayev (now KBKhimMash),1972-77,"Main and low-thrust mode. Operation of turbopump without chamber made it possible to pump propellants into tanks (e.g. from Progress),",1,"4,38 / 0,17",52, 0.46 , 0.73 ,, ,N2O4/UDMH,,,,,Russia,"Russian Arms Cat., CMDB 94, Siddiqi" KRD-61,,S5.61,"ascent stage of Luna 16, 20, 24",KB-Isayev (now KBKhimMash),1968-70,Spacecraft maneuvering engine for ascent stage of Luna moon sample return missions.,1,18.8,41.8, 0.55 , 0.71 , 92.2 , ,N2O4/UDMH,313,0,53,1.84,Russia,"Kudryavtsev 93, Russian Arms Cat., Glushko 85" KRD-79,,S5.79,"Salyut 6, 7and Mir orbital propulsion maneuvering engine",KB-Isayev (now KBKhimMash),,Probably derived from engine of propulsion system KDU-426. Pressure fed engine.,1,3.09,38.5, 0.84 , 0.55 ,, ,N2O4/UDMH,,,,,Russia,"Russian Arms Cat., Siddiqi" KTDU-35,11D62,S5.35 + S5.60,"Soyuz maneuvering engine, Salyut 4",KB-Isayev (now KBKhimMash),1963-64,Spacecraft maneuvering engine. Comprises main engine S5.35 plus back-up engine S5.60.,1 + 2,"4,09 + 4,03",305, 2.50 , 1.14 , 39.2 , ,AK27I/UDMH,280 / 270,0,500,"1,85 / 1,82",Russia,"CMDB 94, Russian Arms Cat., Glushko 85" KTDU-417,11D417,,Luna 15-24 descent stage,KB-Isayev (now KBKhimMash),1965-69,"Spacecraft maneuvering engine. Comprises of 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.",1,"18,92 - 7,35",80.6, 0.73 , 0.79 , 83.0 , ,N2O4/UDMH,314 - 308,0,650,1.8,Russia,"Glushko 85, Kudryavtsev 93, Russian Arms Cat., Siddiqi" KTDU-417-B,11D417-B,,Luna 15-24 low thrust engine in system KTDU-417,KB-Isayev (now KBKhimMash),1965-69,Pressure-fed engine. Used as low thrust engine in system KTDU-417 for soft-landing. See entry KTDU-417.,2,"3,43 - 2,06",, , , 8.9 , ,N2O4/UDMH,254 - 249,,30,2.4,USSR,"Glushko 85, Kudryavtsev 93, Russian Arms Cat." KTDU-425,11D425,,Mars 2 and 3 maneuver engine,KB-Isayev (now KBKhimMash),1970-73,Pump-fed engine. Could be throttled.,1,"18,85 - 7,05",, , ," 133,2 - 95 ", ,N2O4/UDMH,312 - 290,,560,1.9,USSR,"Kudryavtsev 93, Siddiqi" KTDU-425A,11D425A,,"Mars 4-7, Venera 9-16, Vega 1-2, and Phobos 1-2 maneuvering engine",KB-Isayev (now KBKhimMash),1972-75,Spacecraft maneuvering engine. Could be throttled.,1,"18,89 - 9,856",70,0.7,0.71, 149 - 95 , ,N2O4/UDMH,315 - 293,0,560,1.9,Russia,"Kudryavtsev 93, Glushko 85, Russian Arms Cat., Siddiqi" KTDU-53,,S5.53,Zond 4-7 maneuvering engine,KB-Isayev (now KBKhimMash),1962-67,"Spacecraft maneuvering engine, derivative of KTDU-35 without back-up engine. ",1,4.089,, 2.50 , 1.14 , 39.2 , ,AK27I/UDMH,280,0,,1.85,Russia,Glushko 85 KTDU-5A,,S5.5,Luna 4-14 maneuvering engine,KB-Isayev (now KBKhimMash),1962-63,"Spacecraft maneuvering engine. First turbopump engine with surface tension propellant management devices in tanks, allowing re-ignition in weightlessness. Three fixed steering thrusters using the turbine exhaust gas for attitude control.",1 + 3,"45,5 + 0,245","48; 138,2 incl. tanks",1.7,1.908, 62.8 , 43.4 ,AK27I/TG-02,278 (main chamber 287),(main chamber 117),43,"3,2 (main chamber 3.6)",Russia,"Kudryavtsev 93, Glushko 69, 85, Russian Arms Cat., Siddiqi" KTDU-66,,S5.66,Salyut 1 maneuvering engine,KB-Isayev (now KBKhimMash),1962-67,"Spacecraft maneuvering engine, derivative of KTDU-35. Longer burn time of 1000 s. Comprises single-chamber main engine plus dual-chamber back-up engine.",1 + 2,"4,09 + 4,03",305, 2.50 , 1.14 , 39.2 , ,AK27I/UDMH,280 / 270,0,1000,"1,85 / 1,82",Russia,"Glushko 85, Siddiqi" NK-15,11D51,,N-1 stage 1 (block A),KB Kuznetsov,1964-72,On the basis of NK-9 OKB-276 developed NK-15 and NK-15V. 30 NK-15 were used on the Block A (Stage 1) of the N-1.,1,1544,1247, 1.50 , 2.70 , 78.5 , ,LOX/Kerosene,318,297,,2.52,Russia,"""Rakety Nositeli""" NK-15V,11D52,,N-1 stage 2 (block B),KB Kuznetsov,1964-72,"On the basis of NK-9 OKB-276 developed NK-15 and NK-15V. 8 NK-15V (11D52) engines, featuring high-expansion nozzle, were used on the Block B (stage 2).",1,1648,1345, 2.00 , 2.34 , 78.5 , ,LOX/Kerosene,325,,,2.52,Russia,"""Rakety Nositeli""" NK-15V H2,11D52,,N-1 stage 2 (block B) replacement,KB Kuznetsov,1965,"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.",1,ca. 1960,,,,, ,LOX/LH2,,,,,Russia,Vetrov 98 NK-19,11D54 (?),NK-9V,N-1 stage 4 (block G),KB Kuznetsov,1964-72,Based on NK-9 engine. Designation 11D54 used also for predecessor of 11D57 LOX/LH2 engine.,1,,, , , , ,LOX/Kerosene,,,,,Russia,"AIAA-97-2680, FAS" NK-21,11D53,NK-9V,N-1 stage 3 (block V),KB Kuznetsov,1964-72,Based on NK-9 engine. Propellants kerosene T-1 / LOX. 4 engines used in N-1 stage 3 (block V).,1,,, , , , ,LOX/Kerosene,,,,,Russia,"AIAA-97-2680, FAS" NK-31,11D114,,N-1F stage 4 (block G),KB Kuznetsov,,"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 lifetime.",1,402,722, 1.40 , , 92.0 , 124.0 ,LOX/Kerosene,353,0,1200,2.6,Russia,Data shets NPO Trud NK-33,11D111,,N-1F stage 1 (block A),KB Kuznetsov,,"To have been used in N-1F. 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 lifetime.",1,1638,1222, 1.50 , 3.71 , 145.7 , 27.0 ,LOX/Kerosene,331,297,600,2.8,Russia,Data shets NPO Trud NK-33 LH2 Mod + 4 x LACE,,,N1-MOK,KB Kuznetsov,1974,"Study 1974. Ultimate derivative of N1 Block A. Propellants changed to LH2/LOX, 16 modified NK-33 engines + 4 Liquid Air Cycle Engine boosters. All figures estimated based on tank volume of Block A and delivery of 90000 kg payload to 400 km MKBS orbit.",1,980.7,, , , , ,Air/LOX/LH2,430,875,410,,Russia,"""Energia 46-96""" NK-39,11D113,,N-1F stage 3 (block V),KB Kuznetsov,,"After initial failures of the N-1 Kuznetsov developed modified versions of engines for all three stages, which had multiple ignition capability and increased operational lifetime. These engines were never flown.",1,402,631, 1.30 , , 98.0 , 114.0 ,LOX/Kerosene,352,0,1200,2.6,Russia,Data shets NPO Trud NK-43,11D112,,N-1F stage 2 (block B),KB Kuznetsov,,"Version of NK-33 with larger nozzle for operation at altitude. After initial failures of the N-1 company developed modified versions of engines for all four stages, which had multiple ignition capability and increased operational lifetime. Never flown.",1,1755,1396, 2.50 , , 145.7 , 70.0 ,LOX/Kerosene,346,,600,2.8,Russia,Data shets NPO Trud NK-9,8D726,,"R-9, GR-1 stage 1",KB Kuznetsov,1959-65,"Developed as alternative to RD-111 engine by OKB-456. NK-9 reached phase of stand testing, but RD-111 was selected. Later NK-9 was planned for stage 1 of GR-1 Global Rocket, but that rocket was abandoned.",1,441.3,, , , , ,LOX/Kerosene,,,,,Russia,"AIAA-97-2680, FAS, Vetrov 98" NK-9V,,,GR-1 stage 2,KB Kuznetsov,1959-65,Developed as alternative to RD-111 engine by OKB-456. NK-9 with increased expansion ratio. Isp estimated.,1,441.3,, , , , ,LOX/Kerosene,340,,,,Russia,"AIAA-97-2680, FAS" NK-9V,11D53,NK-21,N-1 stage 3 (block V),KB Kuznetsov,,Modification of NK-9 engine for the N-1 lunar rocket. May be identical to NK-21 (stage 3).,1,449,, , , , ,LOX/Kerosene,312,0,,,Russia,"""Rakety Nositeli""" NK-9V,11D54,NK-19,N-1 stage 4 (block G),KB Kuznetsov,,Modification of NK-9 engine for the N-1 lunar rocket. May be identical to NK-19 (stage 4).,1,392,, , , , ,LOX/Kerosene,,0,,,Russia,"""Rakety Nositeli""" R-26 Stage 2,,,R-26 stage 2,,,Orevo has sectioned hardware. TsNIIMash has 1:10 structural simulation model. All figures accurate except empty mass estimated.,1,428.06,, , , , ,RFNA/UDMH,308,252,160,,Russia,"TsNIIMash, Orevo" R-3,,D-2,R-3,NII-1 (ITs Keldysh),1949,Engine for 3000 km range IRBM design to study problems of long-range rockets. Developed April 1947 to 1949 before cancellation. R-3 missile later used the RD-110 engine.,1,"1373, 1180",, , , , ,LOX/Kerosene,300,360,124,,Russia,Russian Space Agency Placard R-56 Block A,,,R-56 block A,,1961,"Engines for immense booster/ICBM; planned range 16,000 km, payload 35,000 kg. TsNIIMash has 1:10 structural simulation model.",1,4413,, , , , ,RFNA/Kerosene,320,300,142,,Russia,TsNIIMash (via Wade) R-56 Block B,,,Used in R-56 block B,,1961,"Engines for immense booster/ICBM; planned range 16,000 km, payload 35,000 kg. TsNIIMash has 1:10 structural simulation model.",1,785,, , , , ,RFNA/Kerosene,330,,205,,Russia,TsNIIMash (via Wade) RD-0101,,SK1,E-50A aircraft by Mikoyan,OKB Kosberg (now KBKhimAvtomatiki),1956-57,,1,"39,2 - 19,6",,,," 42,7 - 22,1 ", ,LOX/ethanol,"255 - 248,5",,300,,Russia,"CADB 95, Siddiqi" RD-0102,,SK1K,Yak-27V aircraft by Yakovlev,OKB Kosberg (now KBKhimAvtomatiki),1957,Based on RD-0101. Two ignitions possible.,1,"39,2 - 14,7",,,," 41,2 - 16,4 ", ,LOX/kerosene,260,,330,,Russia,"CADB 95, Siddiqi" RD-0103,,,"T-3, P-1 aircraft by Sukhoy",OKB Kosberg (now KBKhimAvtomatiki),1957,Based on RD-0102.,1,"34,6 - 13,7",,,," 37,3 - 15,7 ", ,LOX/kerosene TS1,277,,,,Russia,CADB 95 RD-0105,8D714,"RO-5, RD-428",R-7 8K72 Luna stage 3 (block E-Luna),OKB Kosberg (now KBKhimAvtomatiki),1958-59,"Developed in nine months. RO-5 was developed jointly with OKB-1 on a basis of a steering chamber from RD-107 engine, which was developed by OKB-1. Propellants kerosene T-1 / LOX.",1,49.4,125, 2.56 , , 45.0 , ,LOX/Kerosene,316,,440,,Russia,"CADB 92, Varfolomeyev 2, Siddiqi" RD-0106,8D715,,R-9 stage 2,OKB Kosberg (now KBKhimAvtomatiki),1959-62,Propellants kerosene T-1 / LOX. Gas generator cycle. ,4,304,, , , , ,LOX/Kerosene,330,,140,,Russia,Russian Arms Cat. RD-0107,8D715K,"RD-461, RO-9","R-9, Molniya 8K78, Voskhod 11A57 stage 3",OKB Kosberg (now KBKhimAvtomatiki),1958-62,Propellants kerosene T-1 / LOX. Gas generator cycle.,4,297.9,410, 0.64 , , 68.2 , ,LOX/Kerosene,326,0,250,,Russia,Varfolomeyev 6 RD-0108,8D715P,"RD-461, RO-9","Voskhod 11A57, Molniya 8K78 stage 3",OKB Kosberg (now KBKhimAvtomatiki),1961-65,Propellants kerosene T-1 / LOX.,4,297.9,410, 0.64 , , 68.2 , ,LOX/Kerosene,326,0,250,,Russia,Varfolomeyev 6 RD-0109,8D719,"RD-448, RO-7","8A92 Vostok stage 3, 8K72K stage 3 (block E-Vostok)",OKB Kosberg (now KBKhimAvtomatiki),1959-60,Developed in 15 months. Propellants kerosene RG-1 / LOX. ,1,54.52,121, 0.76 , 1.58 , 50.0 , 79.4 ,LOX/Kerosene,323.5,0,430,,Russia,"CADB 92, 95, Glushko 69" RD-0110,11D55,RD-461,"Soyuz 11A511, Molniya-M 8K78M, R-9 stage 3 (Block I)",OKB Kosberg (now KBKhimAvtomatiki),1964-69,Propellants kerosene T-1 / LOX. Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability.,4,297.9,408, 2.24 , 1.58 , 68.2 , 82.2 ,LOX/Kerosene,326,0,250,2.2,Russia,"CADB 92, 95, Glushko 69, Varfolomeyev 6" RD-0120,11D122,RO-200,Energia core stage,KBKhimAvtomatiki,1976-88,"Energia's four single chamber core engines are the first operational Russian cryogenic systems. Starting point was US SSME, resulting in engine of similar size, thrust, and specific impulse. Four engines per core stage; proposed for Energia-M core.",1,1961,3450, 2.42 , 4.55 , 218.0 , 85.7 ,LOX/LH2,455,359,600,6,Russia,CADB 93 RD-0120M,11D122A,,Energia-M core stage.,KBKhimAvtomatiki,1987-,Upgrade of the 11D122 (RD-0120) engine for Energia-M launcher by including the possibility to throttle the engine down to 28% thrust. The original RD-0120 engines are mothballed at Baikonur.,1,1961,3450, 2.42 , 4.55 , 218.0 , 85.7 ,LOX/LH2,455,359,600,6,Russia,CADB 93 RD-0120-Methan,,,,KBKhimAvtomatiki,,Proposed variant of the RD-0120 engine using liquid methane instead of hydrogen as propellant.,1,1576,2370,,, 172.5 ,,LOX/LCH4,363,,,3.4,Russia,Russian Arms Cat. RD-0120M-Methan,,,,KBKhimAvtomatiki,,Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant.,1,1720,2600,,, 186.0 ,,LOX/LCH4,372,,,3.4,Russia,Russian Arms Cat. RD-0120TD,,,experimental tri-propellant,KBKhimAvtomatiki,,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.,1,1317 / 775,, 2.42 , 4.55 ,, 85.7 ,LOX/LH2-kerosene,419 / 452,295 / -,,"4,13 / 5,85",Russia,CADB+AJ 95 "RD-0122 (RD-0122M)",,,Energia-M core stage. Planned for Angara central stage,KBKhimAvtomatiki,1990-,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.,1,2313,,,,,,LOX/LH2,460.5,,,,Russia,CADB 95 RD-0124,14D451M,,Rus Soyuz 2 stage 3,KBKhimAvtomatiki,1993-,Propellants kerosene RG-1 / LOX. Engine with increased performances to succeed RD-0110. Uses staged combustion to increase chamber pressure.,4,294.3,480, 2.40 , 1.58 , 157.0 , ,LOX/Kerosene,359,0,300,2.6,Russia,CADB ILA98 (RD-0124 sea-level),14D23,,Kvant-1 stage 1 vernier,KBKhimAvtomatiki,,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.,4,298.64,,,, 173.5 , ,LOX/Kerosene,331,,300,2.6,Russia, RD-0124M,,,,KBKhimAvtomatiki,1998-,"Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber.",1,294.3,360, 1.43 , 2.10 , 161.9 , ,LOX/Kerosene,348,0,300,,Russia,CADB ILA98 RD-0124M1,,,,KBKhimAvtomatiki,1998-,"Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber with larger nozzle extension compared to RD-0124M.",1,294.3,393, 1.50 , 2.60 , 157.0 , ,LOX/Kerosene,359,0,300,,Russia,CADB ILA98 RD-0126,,R 097,upper stage,KBKhimAvtomatiki,1993-,"Concept for a cryogenic engine ""Yastreb"" for upper stages. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Hot-tests began 1998.",1,39.2,320,, 2.60 , 71.5 ,,LOX/LH2,476,0,,6.0,Russia,"Russian Arms Cat., ""Energia 46-96""" RD-0126A,,,upper stage,KBKhimAvtomatiki,1996-,"Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.",1,98,340,, 2.73 , 118.0 ,,LOX/LH2,476,0,,6.0,Russia,Russian Arms Cat. RD-0128,,,upper stage,KBKhimAvtomatiki,1996-,"Concept for a cryogenic engine for upper stages. One single chamber with bell nozzle, separate turbopumps.",1,98,370,, 4.18 , 118.0 ,,LOX/LH2,474,0,,6.0,Russia,Russian Arms Cat. RD-0131,,,upper stage,KBKhimAvtomatiki,1996-,"Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.",1,98,350,, 2.20 , 123.0 ,,LOX/LH2,467,0,,6.0,Russia,Russian Arms Cat. RD-0132,,,upper stage,KBKhimAvtomatiki,1996-,"Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump.",4,98,370,, 1.38 , 98.0 ,,LOX/LH2,469,0,,5.9,Russia,Russian Arms Cat. RD-0132M,,,Vozdushnyy Start stage 2,KBKhimAvtomatiki,1998-,"Proposed variant of RD-0132, replacing hydrogen by liquid natural gas. Initially selected for stage 2 of Vozdushnyy Start project by Kompomash.",4,98,,,,,,LOX/LNG,,,,,Russia,Kompomash 98-1 RD-0133,,,upper stage,KBKhimAvtomatiki,1996-,"Concept for a cryogenic engine for upper stages. Four chambers with bell nozzles, common turbopump.",4,98,390,, 1.43 , 83.0 ,,LOX/LH2,467,0,,6.0,Russia,Russian Arms Cat. RD-0143,,,Vozdushnyy Start stage 2,KBKhimAvtomatiki,1998-,"Proposed variant of RD-0124, replacing kerosene by liquid natural gas. Selected for stage 2 of Vozdushnyy Start project by Kompomash.",1,ca. 220,,,,, ,LOX/LNG,,,,,Russia,Kompomash 98-2 RD-0143A,,,Vozdushnyy Start stage 1,KBKhimAvtomatiki,1998-,Proposed single chamber variant of RD-0143. Selected for stage 1 of Vozdushnyy Start project by Kompomash.,1,ca. 220,,,,, ,LOX/LNG,,,,,Russia,Kompomash 98-2 RD-0146,,,Centaur upper stage (Atlas),KBKhimAvtomatiki+ Pratt & Whitney,1998-,Proposed Russian version of RL10A-4-1 by Pratt & Whitney. Main modification are new turbopumps. May be derivative of RD-0128 project.,1,ca. 100,,,,, ,LOX/LH2,ca. 470 (?),0,,,Russia,Nov Kosm. 21-22/98 RD-0200,,,SAM 5V11 by Lavochkin stage 2,OKB Kosberg (now KBKhimAvtomatiki),1957-62,"RO-1, 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.",2,"58,8 - 5.9 sea-level",86, 0.30 , 0.40 , 66.0 , ,AK-27I/TG-02,,230 - 166,360,,Russia,"CADB 92, 95, Russian Arms Cat." RD-0201,,,SAM V1100 by Grushin stage 3,OKB Kosberg (now KBKhimAvtomatiki),1959-60,Thrust range 59 - 28 kN.,4,"58,06 - 28",120, 0.40 , 0.70 , 62.0 , ,AK-27P/TG-02,260,,180,,Russia,"CADB 92, Russian Arms Cat." RD-0202,8D45,,UR-200 stage 1,OKB Kosberg (now KBKhimAvtomatiki),1961-63,Engine unit consisting of one RD-0204 and three RD-0203.,4,2236,1525, , 1.80 , , 29.8 ,N2O4/UDMH,311,278,136,2.6,Russia,CADB 95 RD-0203,8D44,,UR-200 stage 1,OKB Kosberg (now KBKhimAvtomatiki),1961-63,Staged combustion cycle. ,1,559,381, 0.89 , 1.80 , , 29.8 ,N2O4/UDMH,311,278,135.5,2.6,Russia,CADB 95 RD-0204,,,UR-200 stage 1,OKB Kosberg (now KBKhimAvtomatiki),1961-63,Staged combustion cycle. Variant of RD-0203 with additional pressure sensor.,1,559,381, 0.89 , 1.80 , , 29.8 ,N2O4/UDMH,311,278,136,2.6,Russia,CADB 95 RD-0205,8D46,,UR-200 stage 2,OKB Kosberg (now KBKhimAvtomatiki),1961-63,Engine unit consisting of RD-0206 main engine and RD-0207 vernier/steering engine.,1,606.4,552, 1.47 , 2.33 , ,,N2O4/UDMH,322,,150,2.625,Russia,CADB 95 RD-0206,8D46,,UR-200 stage 2,OKB Kosberg (now KBKhimAvtomatiki),1961-63,Staged combustion cycle.,1,575.5,, 1.47 , , 147.0 , 81.3 ,N2O4/UDMH,326,,150,2.6,Russia,"Glushko 69, CADB 95" RD-0207,8D67,,UR-200 stage 2 vernier,OKB Kosberg (now KBKhimAvtomatiki),1961-63,Gas generator cycle. Four vernier thrusters.,4,30.9,, 0.16 , , 53.0 , 43.3 ,N2O4/UDMH,297,,133,1.8,Russia,"Glushko 69, CADB 95" RD-0208,,,UR-200 stage 1,OKB Kosberg (now KBKhimAvtomatiki),1962-65,Stage 1 had three RD-0208 plus one RD-0209. Further developed into RD-0210.,1,,, , , , ,N2O4/UDMH,,,,,Russia,CADB 95 RD-0209,,,UR-200 stage 1,OKB Kosberg (now KBKhimAvtomatiki),1962-65,Modification of RD-0208 with tank pressurization. Further developed into RD--0211.,1,,, , , , ,N2O4/UDMH,,,,,Russia, RD-0210,8D411K,RD-465,Proton stage 2,OKB Kosberg (now KBKhimAvtomatiki),1962-65,Four similar engines used in stage: three RD-0210 plus one RD-0211 providing tank pressurization. Staged combustion cycle.,1,582.1,566, 1.47 , 2.33 , 147.0 , 81.3 ,N2O4/UDMH,326.5,0,230,,Russia,"CADB 92, 95" RD-0210-Kerosene,,,,KBKhimAvtomatiki,,Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants.,1,592,570,,, 147.0 ,,LOX/Kerosene,342,,,2.6,Russia,Russian Arms Cat. RD-0211,8D412K,RD-468,Proton stage 2,OKB Kosberg (now KBKhimAvtomatiki),1962-65,Variant of RD-0210 providing tank pressurization. Staged combustion cycle.,1,582.1,566, 1.47 , 2.33 , 147.0 , 81.3 ,N2O4/UDMH,326.5,0,230,,Russia,"CADB 92, 95" RD-0212,8D49,,Proton stage 3,OKB Kosberg (now KBKhimAvtomatiki),1962-65,Engine unit consisting of RD-0213 main engine and RD-0214 vernier/steering engine.,1 + 4,613,, , , , ,N2O4/UDMH,324.6,0,230,,Russia,CADB 92 RD-0213,8D48,RD-473,Proton stage 3,OKB Kosberg (now KBKhimAvtomatiki),1962-65,Modification of RD-0210 for stage 3. Staged combustion cycle.,1,582.1,, 4.15 , , 147.0 , 81.3 ,N2O4/UDMH,326.5,0,230,,Russia,CADB 92 RD-0214,"8D811 (= 8D611 ?)",,Proton stage 3 vernier,OKB Kosberg (now KBKhimAvtomatiki),1962-65,Based on RD-0207. Steering engine with four thrusters in system RD-0212.,4,30.98,, , , 53.0 , ,N2O4/UDMH,293,0,,,Russia,CADB 92 RD-0215,,,Planned heavy launcher (UR-700 ?) stage 1,OKB Kosberg (now KBKhimAvtomatiki),1962-65,"Intended for stage 1 of heavy launcher by Chelomei. Development stopped, hardware not hot-tested. Staged combustion cycle with ox.-rich gas generator.",?,2450,, ca. 2 , , , ,N2O4/UDMH,,,,,Russia,CADB 95 RD-0216,15D2,,"UR-100, UR-100K / RS-10 (SS-11) stage 1",OKB Kosberg (now KBKhimAvtomatiki),1963-66,"Staged combustion cycle. Includes tank pressurization system (RD-0217 without tank press.). Manufacturing until 1974, operational use until 1991.",1,ca. 220,, , , ca. 147 , ,N2O4/UDMH,313,,,,Russia,"Russian Arms Cat., CADB 98, Siddiqi" RD-0217,15D2,,"UR-100, UR-100K / RS-10 (SS-11) stage 1",OKB Kosberg (now KBKhimAvtomatiki),1963-66,"Staged combustion cycle. Version of RD-0216 without tank pressurization system. Manufacturing until 1974, operational use until 1991.",1,ca. 220,, , , ca. 147 , ,N2O4/UDMH,313,,,,Russia,"Russian Arms Cat., CADB 98, Siddiqi" RD-0221,,,upper stage of unnamed missile by Mishin.,OKB Kosberg (now KBKhimAvtomatiki),1965-70,,1 + 2,78,150," ca 0,8 ","ca. 1,6", 122.6 ,,N2O4/UDMH,330,,800,,Russia,CADB 92 RD-0225,11D24,,Almaz space station orbital maneuvering,OKB Kosberg (now KBKhimAvtomatiki),1966-71,"Two engines used on Almaz space station for orbital maneuvering, Pressure fed. ",1,3.923,23, 0.46 ,0.996, 8.8 , 64.0 ,N2O4/UDMH,287,0,1200,1.85,Russia,"CADB 92, 95" RD-0228,,,R-36M / RS-20A (SS-18 mod-1) stage 2,OKB Kosberg (now KBKhimAvtomatiki),1967-74,Comprises of single-chamber main engine RD-0229 plus four-chamber steering engine RD-0230. Further developed to RD-0255.,1 + 4,755,, , , , ,N2O4/UDMH,,,,,Russia,"Russian Arms Cat., Lardier 94" RD-0229,,,R-36M / RS-20A (SS-18 mod-1) stage 2,OKB Kosberg (now KBKhimAvtomatiki),1967-75,Main engine. Staged combustion cycle. ,1,,, , , , ,N2O4/UDMH,,,,,Russia, RD-0229M,,,Vozdushnyy Start stage 1,KBKhimAvtomatiki,1997,Derivative of RD-0229 for the propellants LOX and liquid natural gas (methane). Initial candidate for stage 1 propulsion of Vozdushnyy Start project by Kompomash.,1,883,, , , , ,LOX/LNG,,,,,Russia,Kompomash 98-1 RD-0230,,,R-36M / RS-20A (SS-18 mod-1) stage 2 vernier,OKB Kosberg (now KBKhimAvtomatiki),1967-75,Vernier engine. Gas generator cycle.,4,,, , , , ,N2O4/UDMH,,,,,Russia, RD-0231,,,Granit spacecraft,OKB Kosberg (now KBKhimAvtomatiki),1968-70,Staged combustion cycle. ,1,29,28, 0.15 , 0.60 , 123.0 , ,N2O4/UDMH,275,,16,,Russia,CADB 92 RD-0233,,,UR-100N / RS-18 (SS-19) stage 1,OKB Kosberg (now KBKhimAvtomatiki),1969-74,Staged combustion cycle. ,1,520,, , , 205.0 , ,N2O4/UDMH,310,285,121,,Russia,"Pavutn. 96, Eurockot 98" RD-0234,,,UR-100N / RS-18 (SS-19) stage 1,OKB Kosberg (now KBKhimAvtomatiki),1969-74,Staged combustion cycle. Modification of RD-0233 including tank pressurization system.,1,520,, , , 205.0 , ,N2O4/UDMH,310,285,121,,Russia,"Pavutn. 96, CADB 95 Eurockot 98" RD-0234-Kerosene,,,,KBKhimAvtomatiki,1996-,Proposed variant of RD-0234 engine using LOX-kerosene instead of N2O4/UDMH as propellants.,1,516,390,,, 196.0 ,,LOX/Kerosene,331,,,2.6,Russia,Russian Arms Cat. RD-0234-Methan,,,,KBKhimAvtomatiki,1996-,Proposed variant of RD-0234 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.,1,442,390,,, 176.0 ,,LOX/LCH4,343,,,3.4,Russia,Russian Arms Cat. RD-0235,,,UR-100N / RS-18 (SS-19) stage 2,OKB Kosberg (now KBKhimAvtomatiki),1969-74,Main engine based on RD-0217 with larger nozzle for altitude operation. Staged combustion cycle. ,1,240,, , , 175.0 , ,N2O4/UDMH,320,,,,Russia,"Pavutn. 96, Eurockot 98" RD-0236,,,UR-100N / RS-18 (SS-19) stage 2 vernier,OKB Kosberg (now KBKhimAvtomatiki),1969-74,Development problems not solved until 1978. Vernier engines. Gas generator cycle. ,4,15.76,, , , , ,N2O4/UDMH,293,,,,Russia,"CADB 95, Eurockot 98" RD-0237,,,UR-100N / RS-18 (SS-19) stage 3,OKB Kosberg (now KBKhimAvtomatiki),1969-74,"Analogous to RD-0225, pressure fed. Steering engine for space vehicles gimbaling +/- 45 degree.",1,4.9,, , , , ,N2O4/UDMH,,,,,Russia,"CADB 95, Euro. 99, M.Wade (PBV 500)" RD-0242,,,sea-based missile booster stage (Burlak ?),OKB Kosberg (now KBKhimAvtomatiki),1977-83,"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.",1,123.6,120, 0.27 , 0.88 , 196.2 ,,N2O4/UDMH,302.6,,60,,Russia,"CADB ILA97, 95, Russian Arms Cat." RD-0242-Kerosene,,,,KBKhimAvtomatiki,1998-,Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants.,1,125,120,,, 196.2 ,,LOX/Kerosene,312,,,2.6,Russia,Russian Arms Cat. RD-0242M,,,,KBKhimAvtomatiki,1998-,Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market ?). Reusable for 6 ignitions total. Throttling to 80%. 15 ignitions tested with one single engine.,1,98.1,185, 0.80 , 1.60 , 153.0 ,,N2O4/MMH,335.6,,600,,Russia,CADB ILA98 RD-0242M1,,,,KBKhimAvtomatiki,1998-,Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market ?). Reusable for 6 ignitions total. Throttling to 80%.,1,98.1,229, 1.25 , 2.34 , 153.0 ,,N2O4/MMH,343,,600,,Russia,CADB ILA98 RD-0243,,,R-29RM / RSM-54 (SS-N-23) stage 1,OKB Kosberg (now KBKhimAvtomatiki),1977-85,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.,1 + 4,825.8,852.8, 2.27 , 1.90 , , ,N2O4/UDMH,300,,79,,Russia,"CADB 95, 96, ILA98" RD-0244,,,R-29RM / RSM-54 (SS-N-23) stage 1,OKB Kosberg (now KBKhimAvtomatiki),1977-85,Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank.,1,682,, , , ca. 275 , ca. 22 ,N2O4/UDMH,ca. 310,ca. 280,74,"ca. 2,6",Russia,"CADB 95, 96, ILA98" RD-0244-Kerosene,,,,KBKhimAvtomatiki,,Proposed variant of RD-0244 engine using LOX-kerosene instead of N2O4/UDMH as propellants.,1,690,540,,, 230.0 ,,LOX/Kerosene,332,,,2.7,Russia,Russian Arms Cat. RD-0245,,,R-29RM / RSM-54 (SS-N-23) stage 1 vernier,OKB Kosberg (now KBKhimAvtomatiki),1977-85,Four-chamber steering engine in system RD-0243 driven by turbine exhaust gas.,4,211,, , , ca. 147 , ca. 14 ,N2O4/UDMH,ca. 300,ca. 280,79,"ca. 2,6",Russia,"CADB 95, 96, ILA98" RD-0245-Kerosene,,,,KBKhimAvtomatiki,,Proposed variant of RD-0245 engine using LOX-kerosene instead of N2O4/UDMH as propellants.,1,214,290,,, 142.0 ,,LOX/Kerosene,320,,,2.3,Russia,Russian Arms Cat. RD-0246,,,,OKB Kosberg (now KBKhimAvtomatiki),,Project for further development of RD-0243.,1 + 4,,,,, , ,N2O4/UDMH,,,,,Russia,CADB 95 RD-0250,,,Modif. of Tchelomey-launcher stage 2 (?),OKB Kosberg (now KBKhimAvtomatiki),,Further development of RD-0235 main engine for projected modification of launcher by Chelomei. Development ceased during study phase. Staged combustion cycle. ,1,,, , ,, ,N2O4/UDMH,,,,,Russia,CADB 95 RD-0251,,,Modif. of Tchelomey-launcher stage 2 (?),OKB Kosberg (now KBKhimAvtomatiki),,Further development of RD-0236 steering engine for projected modification of launcher by Chelomei. Development ceased during study phase. Gas generator cycle. ,4,,, , , , ,N2O4/UDMH,,,,,Russia,CADB 95 RD-0255,,,R-36M2 / RS-20V (SS-18 Mod-4) stage 2,OKB Kosberg (now KBKhimAvtomatiki),1983-89,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%.,1 + 4,755,, , , , ,N2O4/UDMH,,,,,Russia,"Russian Arms Cat., Lardier 94, CADB 95" RD-0256,,,R-36M2 / RS-20V (SS-18 Mod-4) stage 2,OKB Kosberg (now KBKhimAvtomatiki),1983-89,Main engine of system RD-0255. Staged combustion cycle.,1,,, , , , ,N2O4/UDMH,,,,,Russia,CADB 95 RD-0256-Kerosene,,,,KBKhimAvtomatiki,1996-,Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants.,1,820,770,,, 172.0 ,,LOX/Kerosene,344,,,2.6,Russia,Russian Arms Cat. RD-0256-Methan,,,,KBKhimAvtomatiki,1996-,Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.,1,836,770,,, 176.0 ,,LOX/LCH4,353,,,3.4,Russia,Russian Arms Cat. RD-0257,,,R-36M2 / RS-20V (SS-18 Mod-4) stage 2 vernier,OKB Kosberg (now KBKhimAvtomatiki),1983-89,Steering engine of system RD-0255. Gas generator cycle.,1,,, , , , ,N2O4/UDMH,,,,,Russia,CADb 95 RD-0410,11B91,,experimental nuclear engine,OKB Kosberg (now KBKhimAvtomatiki),1967-94,"To be used on Nuclear rocket. Tested at Semipalatinsk test range in 1980s and is ""the only operational nuclear engine in the USSR"".",1,35.3,2000, 1.60 , 3.50 , , ,Nuclear/LH2,910,,3600,,Russia,"CADB 95, 98" RD-0411,,,full-size nuclear thermal engine,OKB Kosberg (now KBKhimAvtomatiki),1968-94,Planned full-size nuclear thermal engine for Mars expeditions. Never progressed beyond study stage.,1,392,, , , , ,Nuclear/LH2,900,,,,Russia,"CADB 92, 95" RD-0750,,,alternative for Angara central stage,KBKhimAvtomatiki,1998-,Derivative of RD-0120 for tri-propellants LOX / LH2-Kerosene. Some components tested in RD-0120TD technology demonstration in cooperation with Aerojet. Two modes: LOX/LH2-Ker. and LOX/LH2.,1,1720 / 780,,,, 190 / 85 , ,LOX/LH2-Kerosene,418 / 451,,,"4,0 / 6,0",Russia,"Russian Arms Cat., Nov. Kosm. 21-22/98" RD-1,,,"take-off acelleration of Pe-2, La-7, Yak-3, Su-6 airplanes",OKB Glushko (now NPO Energomash),1941-45,The RD-1 was the first Russian liquid propellant rocket engine. Production 1944-45. Ignition was by an ethane-air mixture.,1, 3 ,56,,, 20.0 , ,HNO3/Kerosene,200,,,,Russia,Russian Arms Cat. RD-2,,,experimental,OKB Glushko (now NPO Energomash),1945-47,The RD-2 was based on the RD-1 engine. Used chemical ignition.,1, 2 - 6 ,71,,, 20.6 , ,HNO3/Kerosene,200,,,,Russia,Russian Arms Cat. RD-3,,,experimental,OKB Glushko (now NPO Energomash),,The RD-3 was a cluster of three RD-1 engines with a new common turbopump. Ignition was by an ethane-air mixture.,3, 1 - 9 ,190,,, 22.0 , ,HNO3/Kerosene,190,,,,Russia,Russian Arms Cat. RD-100,,,"R-1, V-1A",OKB Glushko (now NPO Energomash),1946-50,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.,1,304,885, 1.65 , 3.70 , 15.9 , ,LOX/ethanol-75%,237,203,65,1.28,Russia,"Energomash 92, Russian Arms Cat, Glushko 85" RD-101,,,R-2 and V-2A,OKB Glushko (now NPO Energomash),1947-51,"The RD-101 was developed simultaneously with the RD-100 but with no German involvement (for security). It was more compact, had increased thrust, increased pressure and an increased alcohol concentration.",1,404,888, 1.65 , 3.35 , 21.2 , ,LOX/ethanol-92%,237,210,,1.45,Russia,"Energomash 92, Russian Arms Cat." RD-102?,,RD-3A,R-3A,OKB Glushko (now NPO Energomash),ca. 1959,Project for R-3A experimental missile. Stopped in favor of RD-103.,1,390 sea-level,885, , 3.12 , , ,LOX/ethanol-96%,,214,,,Russia,Vetrov 98 RD-103,8D52,,R-5,OKB Glushko (now NPO Energomash),1947-53,,1,500,870, 1.65 , 3.12 , 23.9 , ,LOX/ethanol-96%,243,216,,,Russia,FAS RD-103M,8D52,,R-5M 8K51,OKB Glushko (now NPO Energomash),1952-55,,1,500.1,867, 1.65 , 3.22 , 23.9 , ,LOX/ethanol-92%,248,220,120,1.44,Russia,Glushko 69 RD-105,8D71,,R-7 ICBM stage 1 (strap-on) initial project,OKB Glushko (now NPO Energomash),1952-54,Intended for R-7 strap-ons in first project versions. Subsequently replaced by RD-107,1,627.6,782, 1.20 , 4.45 , 58.8 , 14.2 ,LOX/Kerosene,302,260,130,2.7,Russia,"Glushko 69, Varfolomeyev 1" RD-106,,,R-7 ICBM stage 2 (core) initial project,OKB Glushko (now NPO Energomash),1952-54,Intended for R-7 sustainer in first project versions. Version of RD-105 with larger nozzle. Subsequently replaced by RD-108.,1,645.3,802, 1.40 , 4.75 , 58.8 , 20.4 ,LOX/Kerosene,310,250,330,2.7,Russia,Glushko 69 RD-107,8D74,,8K71 stage 1,OKB Glushko (now NPO Energomash),1954-57,Glushko had developed the RD-110 with a cylindrical burner but it suffered combustion instabilities. He returned to his experiments from the 30's with cylindrical burners - combining his ideas with German ones.,4 + 2,971,1155, 2.58 , 2.87 , 58.5 , ,LOX/Kerosene,306,250,140,,Russia,Varfolomeyev 1 RD-107,8D74PS,,8K71PS stage 1,OKB Glushko (now NPO Energomash),1956-57,Propellants kerosene T-1 / LOX.,4 + 2,971,1155, 2.58 , 2.87 , 60.0 , 18.9 ,LOX/Kerosene,306,250,146,,Russia,Varfolomeyev 1 RD-107,8D76,,8A91 stage 1,OKB Glushko (now NPO Energomash),1956-57,Propellants kerosene T-1 / LOX.,4 + 2,971,1155, 2.58 , 2.87 , 56.9 , 18.9 ,LOX/Kerosene,310,252,150,,Russia,Varfolomeyev 1 RD-107,8D74-1958,,"8K71, 8K72 Luna, R-7 stage 1",OKB Glushko (now NPO Energomash),1958-59,Propellants kerosene T-1 / LOX.,4 + 2,991,1155, 2.58 , 2.87 , 58.4 , 18.9 ,LOX/Kerosene,312,254,120,2.47,Russia,Varfolomeyev 2 RD-107,8D74-1959,,8K72K stage 1,OKB Glushko (now NPO Energomash),1958-59,"Further development of 8D74-1958, OKB Glushko. Propellants kerosene T-1 / LOX.",4 + 2,996,1155, 2.58 , 2.87 , 58.6 , 18.9 ,LOX/Kerosene,313,256,120,2.47,Russia,Varfolomeyev 5 RD-107,8D74K,,"8K78 R-7A, early Molniya stage 1",OKB Glushko (now NPO Energomash),1957-60,Propellants kerosene T-1 / LOX.,4 + 2,996,1145, 2.58 , 2.87 , 59.7 , 18.9 ,LOX/Kerosene,313,256,119,,Russia,Varfolomeyev 1 RD-107,8D728,,Molniya 8K78M and 11A57 stage 1,OKB Glushko (now NPO Energomash),1962-63,Propellants kerosene RG-1 or T-1 / LOX.,4 + 2,996,1145, 2.58 , 2.87 , 58.6 , ,LOX/Kerosene,314,257,120,,Russia,Varfolomeyev 5 RD-107,11D511,,Soyuz 11A511 stage 1,OKB Glushko (now NPO Energomash),,Propellants kerosene RG-1 / LOX.,4 + 2,995,1150, 2.58 , 2.87 , 58.5 , ,LOX/Kerosene,311,254,118,,Russia,Energia 1994 RD-107,11D511P,,Soyuz 11A511U2 stage 1,OKB Glushko (now NPO Energomash),,Propellants kerosene RG-1 / LOX.,4 + 2,996.4,, , , , ,LOX/Kerosene,314,257,140,,Russia,Energia 1994 RD-108,8D75,,8K71 R-7 stage 2,OKB Glushko (now NPO Energomash),1954-55,Propellants kerosene RG-1 / LOX.,4 + 4,912,1278, 1.95 , 2.87 , 51.0 , 18.9 ,LOX/Kerosene,308,241,340,2.39,Russia,Varfolomeyev 1 RD-108,8D75PS,,Sputnik 1 8K71PS stage 2,OKB Glushko (now NPO Energomash),1956-57,Propellants kerosene RG-1 / LOX.,4 + 4,912,1250, 1.95 , 2.87 , 53.0 , 18.9 ,LOX/Kerosene,308,241,340,,Russia,Varfolomeyev 1 RD-108,8D77,,Sputnik 3 8A91 stage 2,OKB Glushko (now NPO Energomash),1956-57,Propellants kerosene T-1 / LOX.,4 + 4,804,1250, 1.95 , 2.87 , 39.2 , 18.9 ,LOX/Kerosene,315,246,370,,Russia,Varfolomeyev 1 RD-108,8D75-1958,,"8K71, 8K72 Luna, R-7A stage 2",OKB Glushko (now NPO Energomash),1957-58,Propellants kerosene T-1 / LOX.,4 + 4,937,1250, 1.95 , 2.87 , 51.0 , 18.9 ,LOX/Kerosene,315,246,340,2.39,Russia,Varfolomeyev 2 RD-108,8D75-1959,,8K72K stage 2,OKB Glushko (now NPO Energomash),1958-59,Further development of 8D74-1958. Propellants kerosene T-1 / LOX.,4 + 4,941,1250, 1.95 , 2.87 , 51.0 , 18.9 ,LOX/Kerosene,315,248,340,2.39,Russia,Varfolomeyev 5 RD-108,8D75K,,Vostok R-7A stage 2,OKB Glushko (now NPO Energomash),1957-60,,4 + 4,941,1252, 1.95 , 2.87 , 51.0 , 18.9 ,LOX/Kerosene,315,248,340,,Russia,Varfolomeyev 1 RD-108,8D727,"8D727K, 8D727P","Molniya 8K78, 8K78M and 11A57 stage 2",OKB Glushko (now NPO Energomash),1962-63,Propellants kerosene RG-1 or T-1 / LOX.,4 + 4,977,1230, 1.95 , 2.87 , 53.6 , ,LOX/Kerosene,316,251,290,2.39,Russia,Varfolomeyev 5 RD-108,11D512,,Soyuz 11A511 stage 2,OKB Glushko (now NPO Energomash),,Propellants kerosene RG-1 / LOX.,4 + 4,981,1250, 2.58 , 2.87 , 51.0 , ,LOX/Kerosene,314,250,286,,Russia,Energia 1994 RD-108,11D512P,,Soyuz 11A511U2 stage 2,OKB Glushko (now NPO Energomash),,Propellants synthetic kerosene / LOX. A 1-2 second specific impulse increase was realized by the use of synthetic fuel Sintin and a modified mixing head. This was a very complicated modification.,4 + 4,1011,, , , , ,LOX/Sintin,319,252,290,,Russia,Energia 1994 RD-109,8D711,,8K73 stage 2.,OKB Glushko (now NPO Energomash),1957-60,The project was abandoned. Later used to develop RD-119.,1,101.6,210, 1.02 , 2.28 , 77.5 , 58.5 ,LOX/UDMH,334,0,330,1.49,Russia,"Varfolomeyev 2,7,8, Glushko 69" RD-110,,,R-3 ?,OKB Glushko (now NPO Energomash),1947-51,Glushko developed the RD-110 with a cylindrical burner but it suffered combustion instabilities. Never put into production.,1,1374,, 1.80 , 5.20 , 58.8 , ,LOX/Kerosene,285,243.6,,2.65,Russia,Energomash 92 RD-111,8D716,,R-9 stage 1,OKB Glushko (now NPO Energomash),1959-62,Propellants kerosene RG-1 / LOX. It had special flexible pipelines and gimbals (simpler than bellows). Pre-launch pressurization should be simple and quick for a military missile but the LOX on the R-9 missile took two hours to load.,4,1628,1492, 1.67 , 2.10 , 78.5 , 18.0 ,LOX/Kerosene,317,275,110,2.39,Russia,"Energomash 92, Glushko 69" RD-112,,,ICBM stage 1 (stage 2 was RD-113),OKB Glushko (now NPO Energomash),1960,,1,1089,790, 1.29 , 2.60 , 147.0 , 31.8 ,LOX/UDMH,344,304,,1.704,Russia,Glushko 69 RD-113,,,ICBM stage 2 (stage 1 was RD-112),OKB Glushko (now NPO Energomash),1960,Upper stage version of RD-112 with larger nozzle.,1,1138,1100, 2.48 , 4.20 , 147.0 , 119.8 ,LOX/UDMH,360,0,,1.704,Russia,Glushko 69 RD-114,,,Used in ICBM stage 1 (stage 2 was RD-115),OKB Glushko (now NPO Energomash),1961-65,,1,1653,990, 1.46 , 2.60 , 147.0 , 26.4 ,LOX/UDMH,341,307,120,1.77,Russia,Glushko 69 RD-115,,,ICBM stage 2 (stage 1 was RD-114),OKB Glushko (now NPO Energomash),1961-65,Upper stage version of RD-114 with larger nozzle.,1,1726,1250, 3.27 , 5.00 , 147.0 , 86.2 ,LOX/UDMH,357,0,130,1.77,Russia,Glushko 69 RD-117,,,unmanned Soyuz-launcher stage 1,NPO Energomash,,Update of RD-107. Probably version using Sintin instead of kerosene.,4,,,,,,,LOX/Sintin,,,,,Russia,Energomash 93 RD-117PF,11D511PF,,manned Soyuz-launcher stage 1,NPO Energomash,,Update of RD-107. Probably version using Sintin instead of kerosene.,4,,,,,,,LOX/Sintin,,,,,Russia,Energomash 93 RD-118,,,manned and unmanned Soyuz-launcher stage 2,NPO Energomash,,Update of RD-108. Probably version using Sintin instead of kerosene.,4,,,,,,,LOX/Sintin,,,,,Russia,Energomash 93 RD-119,8D710,,Kosmos 1 stage 2,NPO Energomash,1958-63,Based on RD-109.,1,105.5,168, 1.02 , 2.17 , 78.9 , 102.0 ,LOX/UDMH,352,0,260,1.5,Russia,"Glushko 69, Varfolomeyev 2" RD-120,11D123,,Zenit stage 2,NPO Energomash,1978-85,The RD-120 is a high altitude engine. It was the first batch produced Russian engine to be test fired in the United States (3 test burns were made).,1,833,1125, 1.95 , 3.87 , 162.8 , 106.7 ,LOX/Kerosene,350,0,315,2.6,Russia,Sutton 91 RD-120K,,,"Soyuz M stage 1, 2. Proposed for X-34.",NPO Energomash,,"Sea-level variant of RD-120 engine. Thrust range 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.",1,794 - 873,1433, 1.50 , 2.80 , 163 - 172 ,,LOX/Kerosene,334 - 336,295 - 298,,2.6,Russia,IAF-97-S.1.03 RD-134,,,upper stage,NPO Energomash,,"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.",4,343,540, 2.40 , 1.60 , 167.0 ,,LOX/Kerosene,357,0,,2.6,Russia,IAF-97-S.1.03 RD-135,,,upper stage,NPO Energomash,prior 1976,Experimental cryogenic engine. (Ref. May be not correct.),,,,,,,,LOX/LH2,,,,,Russia,Gubanov 91 RD-160,,,upper stage,NPO Energomash,,"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.",1,19.6,129, 0.76 , 1.70 , 117.7 , 351.6 ,LOX/Kerosene,380.6,0,900,3.69,Russia,IAF-97-S.1.03 RD-161 (1),,,Soyuz M stage 3,NPO Energomash,1993-,"Basic version of upper stage kerosene engine. Gimbaling +/- 6 degree in two planes. Status 1996 was project, development estimated for four years. Nozzle expansion ratio is 120/0.05=2400.",1,19.6,124, 0.76 , 1.70 , 117.7 , 351.6 ,LOX/Kerosene,360,0,900,2.6,Russia,"Energomash 93, IAF-97-S.1.03" RD-161 (2),,,Soyuz M stage 3 (block LM),NPO Energomash,1993-,Version with uncooled nozzle extension,1,19.9,141, 1.02 , 2.21 , 117.7 , 370.6 ,LOX/Kerosene,365,0,900,2.6,Russia,Energomash 93 RD-161P,,,Soyuz M stage 3 (block LM),NPO Energomash,1993-,Version for H2O2 fuel. Two thrust levels. H2O2 concentration 96-98%.,1,"24,5 / 14,7",105, 1.24 , 1.45 , 117.7 , 265.0 ,H2O2/Kerosene,319,0,900,5.9,Russia,Energomash 93 RD-167,,,upper stage,NPO Energomash,,"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.",4,353,570, 2.40 , 1.60 , 167.0 ,,LOX/LCH4,379,0,,3.4,Russia,IAF-97-S.1.03 RD-169,,,Riksha-0 stage 1,NPO Energomash,,"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.",1,167,215, 0.50 , 1.70 , 147.0 ,,LOX/LCH4,351,309,,3.4,Russia,IAF-97-S.1.03 RD-170,11D520,,Energia strap-on,NPO Energomash,1981-93,"The RD-170 and RD-171 with 4 chambers, 1 turbo-pump and 2 gas generators were developed simultaneously, the difference being two-plane gimbaling in the RD-170 used in the Energia launch vehicle strap-ons versus one-plane gimbaling in the RD-171.",4,7903,9750 (12054), 4.02 , 3.78 , 245.0 ,36.87,LOX/Kerosene,337,309,150,2.6,Russia,"Energomash 92, Sutton 91, Russian Arms Cat. (Pratt&Whitney 1/95)" RD-171,11D521,,Zenit stage 1,NPO Energomash,1976-86,"The RD-170 and RD-171 with 4 chambers, 1 turbo-pump and 2 gas generators were developed simultaneously, the difference being two-plane gimbaling in the RD-170 used in the Energia launch vehicle strap-ons versus one-plane gimbaling in the RD-171.",4,7903,",", 4.02 , 3.78 , 245.0 ,36.87,LOX/Kerosene,337,309,150,2.63,Russia,"Energomash 92, Russian Arms Cat." RD-172,,,Zenit-3 stage 1 (?),NPO Energomash,-1994,Uprated version of RD-171. To be qualified for flight 1994.,4,8354,11703, 4.00 , 3.78 , 258.9 ,36.87,LOX/Kerosene,337,311,,2.6,Russia,Pratt&Whitney 1/95 RD-173,,,Zenit-3 stage 1 (?),NPO Energomash,,"Uprated version of RD-171 with 4 chambers, 1 turbo-pump and 2 gas generators. Intended for uprated Zenit named Zenit 3",4,8181,," ca. 4,015 "," ca. 3,78 ", 255.0 ,"36,87 (?)",LOX/Kerosene,337,311,,2.63,Russia,Isakowitz 2 RD-180,,,AtlasIIAR stage 1,NPO Energomash under RD-AMROSS,1993-99,"Russian engine for U.S. Atlas III launcher. This is double chamber motor is 1/2 of the RD-173 so is cheap and fast to develop, 70% of the parts come directly fromRD-170, main new development is turbopump. Throttle range 40-100%.",2,4152,5393, 3.20 , 3.76 , 257.0 , 36.9 ,LOX/Kerosene,337.8,311.3,150,2.72,Russia,"Pratt&Whitney 5/97, Russian Arms Cat." RD-182,,RD-120M,"Riksha (-1, -2) stage 1",NPO Energomash,1994-,"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.",1,814 - 902,1500, 1.50 , 2.80 , 163 - 172 ,,LOX/LCH4,351 - 353,311 - 316,,3.4,Russia,"IAF-97-S.1.03, Kompomash 98-1" RD-182M,,,Vozdushnyy Start stage 1,NPO Energomash,1998-,Variant of RD-182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash.,1,882,,,,,,LOX/LNG,,,,,Russia,Kompomash 98-1 RD-183,,,"Riksha (-0, -1, -2) apogee stage",NPO Energomash,1996-,"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.",1,9.8,60, 0.31 , 1.15 , 73.5 ,,LOX/LCH4,360,0,,3.4,Russia,IAF-97-S.1.03 RD-185,,,Riksha-0 stage 2,NPO Energomash,1996-,"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.",1,179,415, 1.50 , 3.30 , 147.0 ,,LOX/LCH4,378,0,,3.4,Russia,IAF-97-S.1.03 RD-190,,,Riksha-0 stage 1,NPO Energomash,1996-,The RD-190 consists of 6 RD-169 engines. Each chamber can be gimbaled individually in two planes by +/- 8 degree.,6,1000,1470, 2.40 , 1.70 , 147.0 ,,LOX/LCH4,351,309,,3.4,Russia,IAF-97-S.1.03 RD-191,,RD-191M,Angara stage 1,NPO Energomash,1996-,Energomash proposes the RD-191 for stage 1 of the Angara family of medium and heavy ELVs. This is single chamber motor would be 1/4 of the RD-170/171 so would be cheap and fast to develop. Gimbaling +/- 8 degree in two planes.,1,2079,3230, 2.00 , 4.05 , 257.0 ,,LOX/Kerosene,337,311,,2.6,Russia,"IAF-97-S.1.03, Nov. Kosm. 21-22/98 and 2/99" RD-192,,,,NPO Energomash,1996-,"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.",1,2138,3300, 2.00 , 4.05 , 257.0 ,,LOX/LCH4,356,330,,3.5,Russia,IAF-97-S.1.03 RD-1KhZ,,,"take-off acelleration of Pe-2R, La-7R, Yak-3, Su-6, Su-7, La-120R airplanes",OKB Glushko (now NPO Energomash),1941-46,The RD-1KhZ was a variant of the RD-1 engine with chemical ignition. Production 1944-45.,1, 3 ,60,,, 22.0 , ,HNO3/Kerosene,200,,,,Russia,Russian Arms Cat. RD-200,,,vertical sounding rocket,OKB Glushko (now NPO Energomash),-1951,,,98.508,218, 0.53 , 0.51 , 23.5 , 4.0 ,HNO3/TM-114,234,210,605,3.76,Russia,Glushko 69 RD-210,,,vertical sounding rocket,OKB Glushko (now NPO Energomash),-1954,,,29.85,80.6, 0.40 , 1.40 , 23.5 , 4.2 ,HNO3/TM-114,241,214,60,4.12,Russia,Glushko 69 RD-211,,,long-distance missile,OKB Glushko (now NPO Energomash),-1955,,,642.3,635.2, 1.65 , 2.70 , 39.2 , 9.5 ,AK20/TM-185,261.8,223.6,122,4.05,Russia,Glushko 69 RD-212,,,winged rocket M-40 (1),OKB Glushko (now NPO Energomash),-1956,Two thrust levels. Ignition with propellant TG-02.,4,437 / 623,642, 1.48 , 2.50 ," 28,4 / 39,2 ", 7.2 ,AK27I/TM-185,253,227,100,3.97,Russia,"Glushko 69, Siddiqi" RD-213,,,winged rocket M-40 (2),OKB Glushko (now NPO Energomash),-1957,Two thrust levels. Ignition with propellant TG-02.,4,549 / 755,625, 1.48 , 2.50 ," 33,8 / 46,6 ", 7.2 ,AK27I/TM-185,255 / 254,223 / 231,110,3.97,Russia,"Glushko 69, Siddiqi" RD-214,,,"Kosmos B-1, (SS-4 Sandal) stage 1",OKB Glushko (now NPO Energomash),1955-59,First Orbital Flight : March 1962. Number Flown: 144 on orbital missions. Engine Cycle: Open. Feed Method: single turbopump driven by H2O2 gas generator. Ignition with propellant TG-02.,4,730,655, 2.38 , 1.48 , 43.6 , 9.4 ,AK27I/TM-185,264,230,140,3.97,Russia,"Energomash 92, Glushko 69" RD-215,,,"R-14, Kosmos 11K63 stage 1",OKB Glushko (now NPO Energomash),1958-60,Two RD-215 clustered to make RD-216.,2,864,675, , , 73.6 , 18.8 ,AK27I/UDMH,291.4,247.7,146,2.5,Russia,Glushko 69 RD-216,11D614,,"R-14, Kosmos 11K63 stage 1",OKB Glushko (now NPO Energomash),1958-60,RD-216 is a block of two RD-215. Beginning with this engine Glushko cut the previous 3 to 5 year development time for new engines to 2 years.,4,1728,1350, 2.26 , 2.20 , 73.6 , 18.8 ,AK27I/UDMH,291.4,247.7,146,2.5,Russia,"Energomash 92, Glushko 69, Isakowitz 2" RD-217,8D515,,R-16 stage 1,OKB Glushko (now NPO Energomash),1958-61,Three RD-217 clustered to make RD-218.,2,1296,980, , , 73.6 , 18.8 ,AK27I/UDMH,289,246,,2.5,Russia,Glushko 69 RD-218,"8D712; 11D69",,R-16 stage 1,OKB Glushko (now NPO Energomash),1958-61,The RD-218 consists of three RD-217. 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.,6,2592,1960, 2.79 , 2.19 , 73.6 , 18.8 ,AK27I/UDMH,289,246,,2.5,Russia,"Energomash 92, Glushko 69, Johnson 94" RD-219,"8D713; 11D26",,R-16 stage 2,OKB Glushko (now NPO Energomash),1958-61,Two-chamber high altitude engine. 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.,2,883,760, 2.16 , 2.03 , 73.6 , 25.8 ,AK27I/UDMH,293,0,125,2.5,Russia,"Energomash 92, Glushko 69" RD-220,,,missile stage 1 (stage 2 used RD-221).,OKB Glushko (now NPO Energomash),1960,,1,1074,760, 1.29 , 2.60 , 147.0 , 31.8 ,AK27P/UDMH,306,270,,2.8,Russia,Glushko 69 RD-221,,,missile stage 2 (stage 1 used RD-220).,OKB Glushko (now NPO Energomash),1960,,1,1118,1070, 2.40 , 4.20 , 147.0 , 119.8 ,AK27P/UDMH,318,0,,2.8,Russia,Glushko 69 RD-222,,,missile stage 1 (stage 2 used RD-223),OKB Glushko (now NPO Energomash),1960-61,Precursor to RD-253.,1,1634,980, 1.46 , 3.47 , 147.0 , 26.3 ,AK27P/UDMH,302,272,,2.92,Russia,Glushko 69 RD-223,,,missile stage 2 (stage 1 used RD-222),OKB Glushko (now NPO Energomash),1960-61,Precursor to RD-253.,1,1697,1240, 2.59 , 5.05 , 147.0 , 86.2 ,AK27P/UDMH,314,0,,2.92,Russia,Glushko 69 RD-224,8D721,,R-26 stage 1,OKB Glushko (now NPO Energomash),1960-62,RD-224 is a block of 2 RD-225s. An upper stage thrust chamber was developed under designation U102-000.,4,1778,1250, 2.27 , 2.00 , 83.4 , 21.0 ,AK27P/UDMH,294,251,100,2.5,Russia,Glushko 69 RD-225,,,R-26 stage 1,OKB Glushko (now NPO Energomash),1960-62,Two clustered together to make RD-224.,2,889,, , , 83.4 , 21.0 ,AK27P/UDMH,294,251,100,2.5,Russia,Glushko 69 RD-250,8D723,,"R-36-0 stage 1, Tsyklon 2 stage 1",OKB Glushko (now NPO Energomash),1961-65,Assembly of 3 RD-250 units make RD-251.,2,881,576,, 1.76 , 83.3 , 14.7 ,N2O4/UDMH,301,269,120,2.6,Russia,Glushko 98 RD-251,8D723,,"R-36-0 stage 1, Tsyklon 2 stage 1",OKB Glushko (now NPO Energomash),1961-65,Assembly of 3 RD-250 units.,6,2643,1729, 2.52 , 1.76 , 83.3 , 14.7 ,N2O4/UDMH,301,269,120,2.6,Russia,"Energomash 92, Russian Arms Cat., Isakowitz 2" RD-252,,,R-36-0 stage 2; Tsyklon 2 stage 2,OKB Glushko (now NPO Energomash),1961-66,Uses modified chamber from RD-219.,2,940.5,715, 2.59 , 2.19 , 89.5 , 46.1 ,N2O4/UDMH,317,0,160,2.6,Russia,"Energomash 92, Yuzhnoe 97, Russian Arms Catal." RD-253,11D48,,UR-500 Proton stage 1,OKB Glushko (now NPO Energomash),1961-65,Six gimbaled single chamber RD-253 in stage. Development went rather quickly but there were problems transitioning to production. ,1,1635,1280, 1.50 , 2.72 , 147.0 , 26.0 ,N2O4/UDMH,316,285,130,2.67,Russia,"Energomash 92, Glushko 87,98" RD-253,14D14,RD-275 (?),Proton KM stage 1,OKB Glushko (now NPO Energomash),1990s,RD-253 version incl. additional gas generator for tank pressurization. This uprated version is obviously designated RD-275 (Glushko 98),1,1746,1300," ca. 1,50 "," ca. 2,72 ", 157.0 , ,N2O4/UDMH,316,287,108,,Russia,Mishin 96 RD-254,,,"N-1 upper stage, UR-700 stage 3",OKB Glushko (now NPO Energomash),1963-66,High altitude version of RD-253 for 2nd stages.,1,1716,, , , , ,N2O4/UDMH,,,,,Russia,Glushko 98 RD-261,,,Tsyklon 3 stage 1,OKB Glushko (now NPO Energomash),1967-69,Based on RD-251,6,3032,1764, 0.75 , 1.76 , 83.0 , 14.7 ,N2O4/UDMH,301.4,269.6,120,2.6,Russia,"Yuzhnoe 97, Russian Arms Cat., Siddiqi" RD-262,,,Tsyklon 3 stage 2,OKB Glushko (now NPO Energomash),1967-69,Based on RD-252,2,941,728, 1.28 , 2.19 , 89.5 , 46.1 ,N2O4/UDMH,317.6,0,160,2.6,Russia,"Yuzhnoe 97, Russian Arms Cat., Siddiqi" RD-263,,,R-36M / RS-20A (SS-18 Mod 1) stage 1,OKB Glushko (now NPO Energomash),1969-73,Four RD-263 engines combined into RD-264 system.,1,1155,,,, 206.0 , ,N2O4/UDMH,318,293,,2.67,Russia,Glushko 98 RD-263F,,,,OKB Glushko (now NPO Energomash),1980,Project to upgrade RD-263. Upgrade was realized in RD-273 engine.,1,,,,,, ,N2O4/UDMH,,,,,Russia,Glushko 98 RD-264,11D119,,R-36M / RS-20A (SS-18 Mod 1) stage 1,OKB Glushko (now NPO Energomash),1969-73,Consists of four RD-263 engines.,4,4521,3600, 3.03 , 2.15 , 206.0 , ,N2O4/UDMH,318,293,,2.67,Russia,"Russian Arms Cat., Glushko 98, Energia 92" RD-268,,,MR-UR-100 / RS-16 (SS-17) stage 1,OKB Glushko (now NPO Energomash),-1976,First flight 1976.Modification of RD-263 engine.,1,1236,770, 1.08 , 2.15 , 226.0 , ,N2O4/UDMH,319,296,,2.67,Russia,Russian Arms Catal. RD-270,8D420,,"UR-700, R-56 stage 1",OKB Glushko (now NPO Energomash),1962-71,RD-270 was the same thrust class as 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 and/or Yangel's R-56 monster. Development tests were only partial success.,1,6713,4470, 3.30 , 4.85 , 261.0 , ,N2O4/UDMH,322,301,,2.67,Russia, RD-270M,8D420M,,,OKB Glushko (now NPO Energomash),1962-70,Glushko studied use of Pentaborane 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.,1,7159,, , , , ,N2O4/B5H9,365,340,,,Russia,Vetrov 98 RD-273,,,,OKB Glushko (now NPO Energomash),1982,Upgrade of RD-263 in 1982 based on RD-263F project.,1,1238,,,, 226.0 , ,N2O4/UDMH,,296,,,Russia,Glushko 98 RD-274,,,,OKB Glushko (now NPO Energomash),1982-85,"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.",4,4952,,,, 226.0 , ,N2O4/UDMH,,296,,,Russia,Glushko 98 RD-275,,,Proton stage 1,OKB Glushko (now NPO Energomash),1980th,Uprated version of RD-253.,1,1745,1280, 1.50 , 2.72 , 157.0 , 26.0 ,N2O4/UDMH,317,285,130,2.67,Russia,"Glushko 87,98" RD-280,,,Experimental engine,OKB Glushko (now NPO Energomash),1963-65,Experimental engine using Aerozine 50 (50% UDMH + 50% hydrazine) as fuel.,1,117.6,174, 1.27 , 2.20 , 147.0 ,,N2O4/AZ50,350,0,,1.718,Russia,Energomash 92 RD-301,,8D21,Proton K stage 4,OKB Glushko (now NPO Energomash),1965-68,"Planned for use in high energy upper stage, e.g. Proton. Motor tested but never flown.",1,96.67,183, 0.98 , 1.89 , 117.6 , 108.7 ,LF2/NH3,400,0,750,2.7,Russia,"Energomash 92, Sergienko 96" RD-302,,11D130F,,OKB Glushko (now NPO Energomash),1960-65,Successor to RD-303 and predecessor to RD-301. Staged combustion cycle.,1,98,,,, 117.6 ,,LF2/NH3,405,,,,Russia,"Glushko 98, Siddiqi" RD-303,,11D14,,OKB Glushko (now NPO Energomash),1960-65,Predecessor to RD-302 and RD-301.,1,,,,,,,LF2/NH3,,,,,Russia,"Glushko 98, Siddiqi" RD-350,,,,OKB Glushko (now NPO Energomash),1963,Studied by Glushko as engine concept with high-energy propellants.,,98,,,,,,LF2/LH2,464,,,,Russia,Vetrov 98 RD-502,,,Experimental upper stage engine,OKB Glushko (now NPO Energomash),1960-66,"Proposed by Glushko for N-1 around Sept. 1960. Intended later for upper stages, e.g. Proton. Program stopped due to toxicity of propellant pentaborane.",1,98.1,132, 1.18 , 2.51 , 147.0 , ,H2O2/B5H9,380,0,,,Russia,"Energomash 92, Wade" RD-510,,,,OKB Glushko (now NPO Energomash),1965-75,"(mentioned on FAS-site, no original reference found)",1,,, , , , ,H2O2/CxHy,,,,,Russia,"FAS, Vetrov" RD-510T,,,,OKB Glushko (now NPO Energomash),1965-75,"(mentioned on FAS-site, no original reference found)",1,,, , , , ,H2O2/CxHy,,,,,Russia,"FAS, Vetrov" RD-511,,,,OKB Glushko (now NPO Energomash),1965-75,"(mentioned on FAS-site, no original reference found)",1,,, , , , ,H2O2/CxHy,,,,,Russia,"FAS, Vetrov" RD-550,,,experimental upper stage engine,OKB Glushko (now NPO Energomash),1963-70,Toxic exotic propellant engine studied by Glushko.,1,98.06,, , , , ,H2O2 / 70% N2H4 + 30% Beryllium,400,,,,Russia,Vetrov 98 RD-56,11D56,KVD-1,N1 block R,OKB Isayev (now KBKhimMash),1960-77,Oxygen-hydrogen engine for cryogenic upper stage. ,1,69.6,282, 1.56 , 2.14 , 55.9 , 198.7 ,LOX/LH2,462,0,800,6,Russia,"CMDB 93, Siddiqi" RD-56M,11D56M,KVD-1M,"Proton and Angara upper stage KVRB, 12KRB upper stage for GSLV (India)",OKB Isayev (now KBKhimMash),1994-,Oxygen-hydrogen 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.,1,73.58,, , , , ,LOX/LH2,461,0,,,Russia,Russian Arms Cat. RD-56M LNG,,KVD-1M,Vozdushnyy Start stage 2,KBKhimMash,1996-,Variant of RD-56M using liquid natural gas in place of hydrogen. First engine tests performed in 1998.,1,"ca. 73,5",, , , , ,LOX/LNG,,,,,Russia,Kopmpomash 98-1 RD-57,11D57,,N1 Block S (N-1M),OKB Lyulka (NPO Saturn),1960-74,To be used in N1 Block S (N-1M). Engine system includes roll control thruster with 1.29 kN thrust.,1,392,840, 1.86 , 3.66 , 111.0 , 142.3 ,LOX/LH2,456.5,0,800,5.8,Russia,Lyulka 92 RD-57M,11D57M,,,OKB Lyulka (NPO Saturn),1960-74,Version with extendible nozzle. Ref. Lyulka 94 has higher mass at 911 kg and higher fixed nozzle area ratio at 100,1,397 / 303,874, 2.00 , 4.06 / 2.61 , 115.0 ," 170 / 87,6 ",LOX/LH2,461 / 448,0,,6.2,Russia,"Lyulka 92, 94" RD-57A-1,,,,NPO Saturn + Aerojet,1995(-98),"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.",1,ca. 395,550, 1.85 , 3.15 ,, 143.0 ,LOX/LH2,460,,,"5,8 (?)",Russia,Lyulka 94 RD-58,11D58,,N-1 stage 5; Proton 8K82K / 11S824 stage 4 (block D),RKK Energia,1970-73,Propellants kerosene RG-1 / LOX.,1,83.4,300, 1.17 , , 78.0 , 189.0 ,LOX/Kerosene,348,0,600,,Russia, RD-58M,11D58M,,Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM),RKK Energia,1970-73,,1,83.4,230, 1.17 , 2.27 , 77.5 , 189.0 ,LOX/Kerosene,353,0,680,2.48,Russia,"Energia 92, Isakowitz 2" RD-58S,11D58S,,Proton 8K82K / 11S861-01 stage 4 (block DM). Version 17D12 for Buran OMS.,RKK Energia,1982-86,Version uses synthetic kerosene ('Sintin') for higher specific impulse.,1,86.3,230, 1.17 , 2.27 , 79.4 , 189.0 ,LOX/Sintin,361,0,680,2.42,Russia,"Energia 92, Isakowitz 2" RD-58Z,11D58Z,,Zenit stage 3,RKK Energia,,,1,71,300, 2.90 , , 78.0 , 189.0 ,LOX/Kerosene,361,,660,,Russia, RD-600,,,interplanetary launchers stage 2,OKB Glushko (now NPO Energomash),1962-70,Gas core nuclear engine. For use in second stage of two-stage interplanetary rockets. This gas phase nuclear reactor was designed for a Venus station/Mars flight. It would be launched from orbit. Work stopped in the USSR.,,1960,,,,,,Nuclear/LH2,2000,,,,Russia,Vetrov 98 RD-701,,,MAKS spaceplane,NPO Energomash,1988-,"The RD-701 was proposed for the 22 tonne MAKS spaceplane, to be launched at an altitude of 8 kilometers from the back of a AN-225 Mriya transport aircraft. It was planned for 15 re-uses. Two identical engines with common booster pump set.",2,4003 / 1588,3670, 2.30 , 5.70 , 294 / 124 , 133.8 ,LOX/Kerosene+LH2,415 / 460,330,440,? / 6,Russia,"Energomash 92, MAKS 95" RD-704,,,,NPO Energomash,1990's,"Proposed tripropellant engine. Single chamber derived from RD-701 project. Mass excluding sensors, gimbal actuators and heat shield.",1,1966 / 782,2422, 1.77 , 3.81 , 294 / 121 , ,LOX/Kerosene+LH2,407 / 452,356,,,Russia,FAS RD-8,11D513,,Zenit stage 2 attitude control engine,GKB Yuzhnoe,1976-,Development since 1976.,4,78.4,380, 4.00 , 1.67 , 76.5 ,,N2O4/UDMH,342,0,1100,2.4,Ukraine,"Yuzhnoe 96 Nov. Kosm. 11/97" RD-851,8D63,,R-16 (SS-7) stage 1 attitude control engine ,GKB Yuzhnoe,1958-63,Four thrusters are each gimbaled in one single axis.,4,324.8,403, 3.54 , 1.70 , 66.2 ,,AK27/UDMH,279,243,115,2.45,Ukraine,"Yuzhnoe 96, Siddiqi" RD-852,,,R-16 (SS-7) stage 2 attitude control engine,GKB Yuzhnoe,1958-63,Four thrusters are each gimbaled in one single axis.,4,48.25,133, 2.95 , 2.40 , 66.2 ,,AK27/UDMH,255,0,143,2.4,Ukraine,Yuzhnoe 96 RD-853,,,"stage 2, no application",GKB Yuzhnoe,1960-63,"Designed for second stage, no application. Two thrust levels.",1 + 4,"467,6 + 11,8 / 7,65",485, 1.30 , 3.28 , 83.6 ,,AK27/UDMH,300.7,0,134,2.41,Ukraine,Yuzhnoe 96 RD-854,,,R-36orb (SS-X-10) orbital stage,GKB Yuzhnoe,1962-67,Thrust vector control by 4 nozzles fed from gas generator.,1 + 4,75.5,100, 1.53 , 1.51 , 85.3 ,,N2O4/UDMH,312.2,0,70,2.02,Ukraine,Yuzhnoe 96 RD-855,,D-68M,Tsyklon stage 1 attitude control engine,GKB Yuzhnoe,1962-65,,4,"285,4 sea-level",320, 3.81 , 1.74 , 65.7 ,,N2O4/UDMH,292,254,127,1.97,Ukraine,Yuzhnoe 96 RD-856,,D-69M,Tsyklon stage 2 attitude control engine,GKB Yuzhnoe,1962-65,,4,54.23,112.5, 3.65 , 1.12 , 71.6 ,,N2O4/UDMH,280.5,0,163,1.98,Ukraine,Yuzhnoe 96 RD-857,15D12,,combined missile (RT-20P) stage 2,GKB Yuzhnoe,1963-67,"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.",1,13.73,190, 0.93 , 2.10 , 127.5 ,,N2O4/UDMH,329.5,0,215,2.6,Ukraine,"Yuzhnoe 96, Glushko 98, Siddiqi" RD-858,,,LK lunar lander main engine,GKB Yuzhnoe,1965-72,Main landing engine for LK lunar lander. Throttling capability for soft landing.,1,"20,1 / 8,414",53, 1.10 , 1.09 ," 78,5 / 33,1 ",,N2O4/UDMH,315 / 285,0,up to 470,"2,03 / 1,6",Ukraine,Yuzhnoe 96 RD-859,,,LK lunar lander reserve engine,GKB Yuzhnoe,1965-72,Reserve engine of LK lunar lander for emergency return to lunar orbit.,2,20.05,57,,, 78.5 ,,N2O4/UDMH,312,0,up to 400,2,Ukraine,Yuzhnoe 96 RD-861,11D25,S5.23,Tsyklon 2 and 3 stage 3; Ikar,GKB Yuzhnoe,1968-72,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.,1 + 4 + 2,78.71,123, 1.53 , 1.56 , 88.8 , 112.4 ,N2O4/UDMH,317,0,130,2.1,Ukraine,"Yuzhnoe 96, Isakowitz " RD-861G,,,Vega upper stage,GKB Yuzhnoe + Fiat Avio,1996-,"Proposed uprate of RD-861 engine. Thrust vector control by gimbal, roll control by 4 nozzles (thrust 29 N each) and new arrangement of turbine exhaust lines for improved performance.",1 + 4 + 2,76.453,185,, 1.66 , 88.8 , 112.4 ,N2O4/UDMH,325,0,400,2.41,Ukraine + Italy,IAF-97-S.1.04 RD-862,15D169,,MR-UR-100 / RS-16 (SS-17) stage 2,GKB Yuzhnoe,1969-72,Based on RD-857. Thrust vector control by secondary gas injection into nozzle.,1,142.63,192, 0.93 , 1.68 , 132.4 ,,N2O4/UDMH,331,0,195,2.55,Ukraine,Yuzhnoe 96 RD-863,,,MR-UR-100 / RS-16 (SS-17) stage 1 attitude control engine,GKB Yuzhnoe,1970-73,,4,276.84,310, 2.08 , 1.88 , 88.6 ,,N2O4/UDMH,301,259,130,2.15,Ukraine,Yuzhnoe 96 RD-864,,,R-36M UTTKh / RS-20B (SS-18 Mod 2) vehicle bus,GKB Yuzhnoe,1976-78,Two thrust levels. The four thruster swing out of the stage housing before use.,4,"20,20 / 8,45",199," 3,0 / 4,02 ", 1.42 , 41 / 17 ,,N2O4/UDMH,309 / 298,0,600,1.8,Ukraine,Yuzhnoe 96 RD-866,3D65,,RT-23 / RS-22 (SS-24) MIRV-bus,GKB Yuzhnoe,1980-83,One main and 16 control thrusters.,1 + 16,"5,20 + 16 x 116",125.4, 1.98 , 1.19 ," 40,7 / 5,56 ",,N2O4/UDMH,"305,5 / 245",0,330 / 1200,"2,03 / 1,85",Ukraine,"Yuzhnoe 96, 97, Lardier 94, Siddiqi" RD-868,,,apogee stage,GKB Yuzhnoe,1983-,Still in development in 1996. One main and an unknown number of control thrusters,1 + x,"23,25 + 0,03",203, 2.35 , 1.10 ," 91,5 / 6,9 ",,N2O4/UDMH,325 / 230,0,1600 / 7200,"2,2 / 1,6",Ukraine,Yuzhnoe 96 RD-869,,,R-36M2 / RS-20V (SS-18 Mod 4) vehicle bus,GKB Yuzhnoe,1983-85,Based on RD-864. Two thrust levels. The four thruster swing out of the stage housing before use.,1,"2,47 / 8,58",196," 3,0 / 4,02 ", 1.42 , 41 / 17 ,,N2O4/UDMH,"313 / 302,3",0,700,1.8,Ukraine,Yuzhnoe 96 RDMT-0.4 X,,,,NII Mash,,Experimental low-thrust thruster. Chamber from niobium alloy.,1,"0,4 N",0.1,,,,,N2O4/UDMH,ca. 290,,,,Russia,NII Mash 92 RDMT-0.8,,,Kosmos satellites,NII Mash,,Low-thrust cold-gas thruster.,1,0.8 N,0.1,,,,,N2 / He,70 / 160,,,,Russia,NII Mash 92 RDMT-5,,,MMK,NII Mash,,Low-thrust cold-gas thruster.,1,5 N,0.35,,,,,Air,70,,,,Russia,NII Mash 92 RDMT-8 X,,,,NII Mash,,Experimental low-thrust thruster.,1,8 N,0.025,,, 30 (?) ,,N2O4/UDMH,296,,,,Russia,NII Mash 92 RDMT-12,,,"Almaz, Kvant, Kristall, Spektr, Priroda",NII Mash,,Low-thrust attitude control thruster.,1,12 N,0.55,,, ca. 9 ,,N2O4/UDMH,279,,,,Russia,NII Mash 92 RDMT-50,,,Kosmos satellites,NII Mash,,Low-thrust attitude control thruster.,1,50 N,1,,, ca. 9 ,,N2O4/UDMH,255,,,,Russia,NII Mash 92 RDMT-100,,,"Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites",NII Mash,,Low-thrust attitude control thruster.,1,100 N,1.2,,, ca. 9 ,,N2O4/UDMH,260,,,,Russia,NII Mash 92 RDMT-135,,,"Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites",NII Mash,,Low-thrust attitude control thruster.,1,135 N,1.2,,, ca. 9 ,,N2O4/UDMH,260,,,,Russia,NII Mash 92 RDMT-200,,,Almaz,NII Mash,,Low-thrust attitude control thruster.,1,200 N,2,,, ca. 9 ,,N2O4/UDMH,255,,,,Russia,NII Mash 92 RDMT-200K,,,Buran,NII Mash,,Low-thrust attitude control thruster. Mass in ref. NIIMash 95 given as only 2.5 kg.,1,200 N,5.5,,,,,GOX/Kerosene,265,,,,Russia,NII Mash 92 RDMT-400,,,"Almaz, Kvant, Kristall, Spektr, Priroda",NII Mash,,Low-thrust attitude control thruster.,1,400 N,2.5,,, ca. 9 ,,N2O4/UDMH,255,,,,Russia,NII Mash 92 RDMT-400 X,,,,NII Mash,,Experimental low-thrust thruster. Carbon combustion chamber. Mass may be chamber only.,1,400 N,0.125,,, 30.0 ,,N2O4/UDMH,296,,,,Russia,NII Mash 92 RDMT-400A,,,,NII Mash,,Experimental low-thrust thruster. Niobium combustion chamber with coating.,1,400 N,2.8,,,,,N2O4/UDMH,290,,,,Russia,NII Mash 92 RDMT-2600,,,,NII Mash,,Experimental low-thrust thruster.,1,2.6,5,,,,,GOX/ethanol,ca. 270,,,,Russia,NII Mash 92 RDMT-XX,,,,NII Mash,,"Experimental thruster, 3 thrust levels by 4 valves.",1,"6000 N, 0.7 N, 0.3 N",,,,,,N2O4/UDMH,326 - 286,,,,Russia,NII Mash 92 S1.5400,,,Molniya 8K78 stage 4 (block L),OKB Korolev,1958-60,Propellants kerosene T-1 / LOX. Began a series of engines leading to the Block D for the N1 and Proton (e.g. 8D726 for GR-1),1,63.8,153, , , 53.0 , ,LOX/Kerosene,338.5,0,250,,Russia,Varfolomeyev 6 S1.5400A,11D33,,R-9M stage 2 / 8K78 stage 4 (block L),design OKB Korolev; production OKB Isayev,,Propellants kerosene RG-1 / LOX. Began a series of engines leading to the Block D for the N1 and Proton.,1,66.7,153, , , 53.5 , ,LOX/Kerosene,340,0,207,,Russia,Varfolomeyev 6 S1.5400A,11D33M,,Molniya 8K78M stage 4 (block L),NPO Lavochkin,1984-85,Based on S1.5400A. Propellants kerosene RG-1 / LOX.,1,67.3,148.3, , , 54.0 , ,LOX/Kerosene,342,0,200,,Russia,Varfolomeyev 6 S2.1150,,,Burya booster,KB-Isayev (now KBKhimMash),1953-59,Booster for Burya missile. Two used to boost ramjet second stage to ignition conditions. Engines developed from R-11 S2.253 engine. Early Buryas had S2.1100 engine. Two thrust levels.,4,"671,20 / 477 sea-level",650, 1.21 , 1.87 , 53.0 , ,AK27I/TG-02,250,218,70,,Russia,"Russian Arms Cat., Siddiqi" S2.253,,,R-11 (Scud B) 8A61,KB-Isayev (now KBKhimMash),1949-53,"Fuel Kerosene T-1, chemical ignition by TG-02.",1,93.3,, 0.96 , , , ,AK20I/Kerosene,251,219,95,,Russia,"""Energia 46-96"", Siddiqi" S2.253 derivative,,,EKR (experimental winged missile),KB-Isayev (now KBKhimMash),,Used in EKR (project for an experimental winged missile). Derivative of S2.253.,1,93.2,, , , , ,LOX/Kerosene,250,217,127,,Russia, S2.253A,,,R-11FM,KB-Isayev (now KBKhimMash),1953-56,"Used in R-11FM submarine version. Fuel Kerosene T-1, chemical ignition by TG-02. Mixture ratio derived from tank content.",1,81 sea-level,,, , , ,AK20I/Kerosene T-1,,218,,3.76,Russia,"""Energia 46-96"", ""Raketi nad Morem"", Siddiqi" S2.713,,,R-13 (SS-N-4),KB-Isayev (now KBKhimMash),1956-61,First engine to employ gas generator on main propellants. One main and four vernier thrusters. (Mixture derived ratio from tank content.),1 + 4,"252,2 kN",, , ,, ,AK27I/TG-02,,,,3.48,Russia,"FAS, ""Rakety nad Morem"", Siddiqi" S2.720,,,Engine for SAM-missile V-755,KB-Isayev (now KBKhimMash),,Pump-fed engine.,1,"34,3-20,4 sea level",47.5, 0.48 , 0.95 , 64.0 , ,AK20K/TG-02,,233,55,3.23,Russia,"Russian Arms Cat., Kudryavtsev 93, ""Raketi nad Morem""" S5.1,,,SAM-missiles 217M and 218,KB-Isayev (now KBKhimMash),late 1950s,Designation unknown.,1, 167-49 ,122, 0.62 , 1.02 ,, ,AK27I/TG-02,,,,,Russia,"Russian Arms Cat., Siddiqi" S5.3,,,R-21 (SS-N-5),KB-Isayev (now KBKhimMash),1958-63,First engine to start underwater.,4,392 sea-level,, , ,,,AK27I/TG-02,,,,,USSR,"FAS, Siddiqi" S5.3M,,,R-9 (SS-8) missile stage 1,KB-Isayev (now KBKhimMash),1959-60,Proposed for R-9 missile stage 1. Four engines per stage.,4,"396,7 sea-level",433, , , 66.0 , 9.6 ,AK27I/TG-02,,241.3,,"3,6 chamber",USSR,"Sergienko 96, Glushko 69" S5.4,,TDU-1,Vostok/Voskhod retorfire engine; spacecraft maneuvering engine. ,KB-Isayev (now KBKhimMash),1959,Includes 4 small lateral steering nozzles.,1 + 4,15.83,98, 0.95 , 1.13 , 55.5 , ,AK20F/TG-02,266,0,44.6,3.07,Russia,"Kudryavtsev 93, Glushko 85" S5.44,5D25,,SAM-missile 5Ya24,KB-Isayev (now KBKhimMash),1964-65,Could be throttled. ,1, 177-49 sea-level ,124, 0.54 , 1.71 ,, 118 - 44 ,AK27I/TG-02,,251 (?),,,Russia,"Russian Arms Cat., Glushko 69, Hindley 96" S5.45,,,"correction engine for Zond-1, Venera-2-8, and others.",KB-Isayev (now KBKhimMash),,Pressure-fed engine. ,1,1961,52, , , 11.8 , 16.0 ,AK20F/UDMH,267,,53,2.6,USSR,"Glushko 69, Russian Arms Cat." S5.51,11D68,,Soyuz LOK lunar orbiter,KB-Isayev (now KBKhimMash),-1967,"This engine was used to maneuver the Soyuz to a rendezvous with the LK lander in lunar orbit, propel the LOK out of lunar orbit towards the earth (large engine), and for midcourse corrections (small engine). Propulsion system includes a large spherical t",2 + 1,"33,196 / 4,089",480, , 2.77 , , ,N2O4/UDMH,314,,700 + 300,"1,85 / 1,76",USSR,CMDB 94 S5.80,,KDU- ?,Soyuz-TM orbital propulsion,KB-Isayev (now KBKhimMash),-1977,Propulsion system includes 4 spherical tanks for a total of 880 kg propellant.,1,2.942,310, 2.10 , 1.20 , 8.8 , 153.8 ,N2O4/UDMH,302,0,ca. 890,1.85,USSR,CMDB 94 S5.92,,,Phobos propulsion module,KB-Isayev (now KBKhimMash),,Gas generator cycle. Nominal and low-thrust thrust levels.,1,"19,6/ 13,7",75," 0,84 x 0,68 ", 1.03 , 97 / 67 , 153.8 ,N2O4/UDMH,327 / 316,0,2000,2,USSR, S5.98M,14D30,,Rokot-3 Briz; Soyuz-2 Briz; Proton Briz-M,KBKhimMash,,High performance storable liquid engine. Engine system consists of main engine plus four 11D458 plus twelve 17D58E vernier thrusters.,1,"19,62 + 4 x 0,392 + 12 x 0,0133",95, , , , ,N2O4/UDMH,"325,5 252 247",,3200,2,Russia,", Nov. Kosm. 2/99" U102-000,,RD-226 ?,R-26 stage 2,OKB Glushko (now NPO Energomash),1960-62,"This is only the thrust chamber, probably based on RD-224 chamber. Other components like turbopumps, etc. were obviously the same as RD-224.",1,468,198 chamber, 1.35 , 2.24 , 83.6 , 48.4 ,AK27P/UDMH,307,0,,2.76,Russia,Glushko 69 YaRD OKB-456,,,nuclear launcher,OKB Glushko,1958-,Korolev's OKB-1 began work on these nuclear launchers beginning on 30 June 1958. Competing engine designs were in development by Glushko's OKB-456 and Bondaryuk's OKB-670.,1,1373,, , , , ,Nuclear/NH3,470,430,500,,Russia,"""Energia 46-96""" YaRD OKB-670,,,nuclear launcher,OKB Bondaryuk,1958-,Korolev's OKB-1 began work on these nuclear launchers beginning on 30 June 1958. Competing engine designs were in development by Glushko's OKB-456 and Bondaryuk's OKB-670.,1,1667,, , , , ,"Nuclear/NH3+Alcohol (""Spirt"" is C2H5OH)",470,430,500,,Russia,"""Energia 46-96""" YaRD Type A,,,nuclear ICBM,,,"Design considered in N1 nuclear upper stage studies. Outgrowth of work by Bondaryuk and Glushko on nuclear engines (YaRD) for ICBMs, but using liquid hydrogen as propellant.",1,177,4800, , , , ,Nuclear/LH2,900,,700,,Russia,Vetrov 98 YaRD Type AF,,,nuclear ICBM,,,"Design considered in N1 nuclear upper stage studies. Outgrowth of work by Bondaryuk and Glushko on nuclear engines (YaRD) for ICBMs, but using liquid hydrogen as propellant.",1,196,3250, , , , ,Nuclear/LH2,950,,700,,Russia,Vetrov 98 YaRD Type V,,,nuclear ICBM,,,"Design considered in N1 nuclear upper stage studies. Outgrowth of work by Bondaryuk and Glushko on nuclear engines (YaRD) for ICBMs, but using liquid hydrogen as propellant.",1,392,18000, , , , ,Nuclear/LH2,900,,700,,Russia,Vetrov 98 YaRD Type V-B,,,nuclear ICBM,,,"Design considered in N1 nuclear upper stage studies. This version had 7,000 kg bioshield for manned missions. Outgrowth of work by Bondaryuk and Glushko on nuclear engines (YaRD) for ICBM's, but using liquid hydrogen as propellant.",1,392,25000, , , , ,Nuclear/LH2,900,,700,,Russia,Vetrov 98 REFERENCES:,,,,,,,,,,,,,,,,,,,, "AIAA-97-2680: Anisimov V.S./Kuznetsov, T.C.Lacefield/Aerojet, J.Andrews/Kistler: ""Evolution of the NK-33 and NK-43 reusable LOX/kerosene engines"", AIAA Joint Propulsion Conference July 1997",,,,,,,,,,,,,,,,,,,, "CADB 92: Visit to the museum of Chemical Automatics Design Bureau, Voronezh 1992" "CADB 93: Information from Chemical Automatics Design Bureau, Voronezh 1993" "CADB 95: ""KB KhimAvtomatiki - Stranitsy Istorii"", A.A. Golubev (ed.), Vol. 1, Voronezh 1995" "CADB+AJ 95: Gontcharov, Orlov, Rachuk, Rudis, Shostak, McIllwain, Starke, Hulka: ""Tripropellant Liquid Rocket Engine Technology Using a Fuel-Rich Closed Power Cycle"", ONERA, June 1995" "CADB 96: Rachuk V.: ""Best Rocket Engines from Voronezh"", Aerospace Journal, Moscow, Nov-Dec. 1996 " "CADB ILA98: CADB-information leaflets, International Aerospace Show Berlin 1998 (ILA 98)" "CADB 98: Discussion with Rubinski, OTN, Dec. 1998" "CMDB 94: Visit to the museum of Chemical Machining Design Bureau, Kalinin 1994" """Energia 46-96"": ""RKK Energia 1946-96"", Korolyov 1996" "Energia 92: Information from NPO Energia museum exhibit, Nov. 1992" "Energia 94: S P Korolev Space Corporation Energia, English-Russian book, 1994." "Energia 95: Semyonov, Yu.P.: ""Mnogorazovyy Orbitalnyy Korabl Buran"", Moscow 1995" "Energomash 92: Information from NPO Energomash museum exhibit, Nov. 1992" "Energomash 93: NPO Energomash exhibit at Moscow Airshow MAKS 93, Moscow, 1993" "Eurockot 98: ""ROCKOT Users Guide"", issue 2 rev. 0, Eurockot Launch Services, Bremen 1998" FAS: Federation of American Scentists internet pages at URL www.fas.org/spp/civil/russia/ "Glushko 69: Glushko V.P.: ""Albom Konstruktsiy ZhRD"" (Album of Liquid Rocket Engine Developments), Vol. 1 1968, Vol. 3 & 4 1969", "Glushko 85: Glushko V.P. (ed.): ""Kosmonavtika Entsiklopedia"", Moscow 1985", "Glushko 87: Glushko V.P.: ""Razvitie Raketostroeniya i Kosmonavtiki v SSSR"", Moscow 1987", "Glushko 98: ""Odnazhdy i Navsegda - Kniga o V.P. Glushko"", V.F. Rakhmanin (ed.), NPO Energomash, Moscow 1998", "Gubanov 91: Gubanov B.I.: ""USSR Main Engines For Heavy-Lift Launch Vehicles: Status and Direction"" AIAA-91-2510, AIAA-Joint Propulsion Conference, Sacramento June 1991", "IAF-97-S.1.03: Klepikov, Katorgin, Chvanov: ""The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant ... "", NPO Energomash, IAF-Congress Turin, 1997, IAF-97-S.1.03", "IAF-97-S.1.04: Shnyakin, Klimov, Shulga: ""Uprated Main Liquid Propellant Rocket Engine For CYCLONE LV Third Stage"", Yuzhnoe State Design Office, IAF-Congress Turin, 1997, IAF-97-S.1.04", "Isakowitz 2: Isakowitz Steven J.: ""International Reference Guide to Space Launch Systems"", 2nd edition, AIAA, Reston 1995", "Johnson 94: Johnson N.L, D.M. Rodvold: ""Europe and Asia in Space 1993-1994"", USAF Phillips Laboratory, 1995", "Kompomash 98-1: Polovnikov S.P., A.S. Karpov: ""Projekt 'Vozdushnyy Start'"", Vestnik Aviatsii i Ksmonavtiki, Moscow, 1-2/98", "Kompomash 98-2: ""Air-Launch aerospace complex"", info leaflet by Kompomash and Polyot Aviation Company, ILA 97", "Kudryavtsev 93: Kudryavtsev V.M. et.al.: ""Osnovy Teorii i Rascheta ZhRD"", Moscow, Vysshaya Shkola, 1993 ", "Lardier 94: Lardier C.: ""SS-18"", Air et Cosmos, 2 Sept. 1994", "Lyulka 92: Prsentation of demonstrator concept, 1992", "Lyulka 94: Andreeyev, Chepkin/Lyulka-Saturn Inc. and Fanciullo/Aerojet: ""The Development of the D-57 Advanced Staged Combustion Engine for Upper stages"", AIAA-94, AIAA Joint Prop. Conf., June 1994", and: ,"Fanciullo, Lacefield: ""High Performance Russian D-57 LH2/LOX Rocket Engine"", AIAA-94-3398, AIAA Joint Prop. Conf., June 1994" "MAKS 95: Catalogue and datasheets at Moscow Aerospace Exhibition, Moscow-Shukovski, 1995" "Mishin 98: Mishin V.P., N.I. Panitskiy: ""Osnovy Aviatsionnoy i Raketno-Kosmicheskoy Tekhniki"", MAI Moscow, 1998" "NIIMash 92: Information from NII Mashinostroeniye, Nishnaya Salda, 1992" "NIIMash 95: Information from NII Mashinostroeniye in internet: www.conveyor.com/space_russia/niimash/ltre.htm (Moscow represent. Max Larin), Nishnaya Salda, 1995" "Nov. Kosm. nn/yy: ""Novosti Kosmonavtiki"" magazine, Moscow. Number / year" "Pavutn. 96: Pavutniskiy Yu.M., V.A. Mazarchenko, M.V. Shilenkov, A.B. Gerasimov: ""Otechestvennye Rakety-Nositeli"", St.Peterburg (State Marine-Technol. Univ.), 1996" """Raketi nad Morem"": Shirokorad A.: ""Rakety nad Morem"", 2nd edition, in: 'Tekhnika I Vooruzhenie', Moscow 11-12, 1997" """Rakety Nositeli"": Kobelyev V.N., A.G. Milovanov: ""Rakety Nositeli"", Moscow State Aviation Techology University, 1993 " "Russian Arms Cat.: Russian Arms Catalogue, Vol. 6 & 4, Military Parade, Moscow" "Sergienko 96: Sergienko A., V. Chervakov: ""Russian Rocket Engines Design"", paper 5.3, 5th Symposium Propulsion in Space Transportation, Paris, May 1996" "Siddiqi : Information from Asif Siddiqi on his web page, April 1999" "Starsem 97: Starsem: ""Soyuz Launcher User manual"", issue 2 rev. 0, Starsem Paris 1997" "Starsem 99-2: Starsem: ""Launch Kit Flight 02"", Starsem Paris 1999 (http://www.starsem.com/newsst_kit.html)" "Sutton 91: Sutton G.: ""Rocket Propulsion Elements"", 3rd edition 1991. Data supplied by NPO Energomash" "Varfolomeyev: Varfolomyev T.: ""Soviet Rocketry that Conquered Space - Parts 1-8"", Spaceflight, London 1995-98" "Vetrov 98: Vetrov G.S.: ""Korolev I Ego Delo"", 1998" "Wade: Mark Wade: ""Encyclopedia Astronautica"", internet http://solar.rtd.utk.edu/~mwade/engines/engindex.htm" "Yuzhnoe 96: Shnyakin V.N.: ""Shidkostnye Raketye Dvigateli - Opisanie i Osnovnye Tekhnicheskie Dannye"", GKB Yuzhnoe ""Yangel"", Dnepropetrovsk 1996" "Yuzhnoe 97: GKB Yuzhnoe ""Yangel"", Data sheets Paris Airshow 1997"