Isayev Design Bureau, Russia.
AKA: A M Isayev; OKB2; KB Khimmash Imeni A. M. Isayeva.
More...  Chronology...
Associated Countries
Associated Spacecraft

346 Russian manned rocketplane. 4 flights from 1946. Postwar Soviet version of the German supersonic DFS 8346 rocket reconnaissance aircraft. Abandoned in 1951 after the prototype crashed. More...
Associated Engines

11D416 Isayev N2O4/UDMH rocket engine. 16.4 kN. Study 1968. Three of these engines used for midcourse corrections and soft lunar landing in Block 11 and Block 1V stages of LK700 manned spacecraft. More...

11D458 Isayev N2O4/UDMH rocket engine. 0.392 kN. In Production. Isp=252s. Small attitude control thruster in Briz upper stage propulsion system S5.98M. Total summmary impulse 14,112 kgs. Minimum impulse 4 kgs. Specific impulse also reported as 275 sec. More...

11D49 Isayev Nitric acid/UDMH rocket engine. 157.5 kN. Kosmos3M stage 2. Engine has one main and four steering nozzles. Thrust 157.5 + 4 x 25 kN. Precessor was 11D47 in R14 (derivative ?) stage 2. Isp=303s. First flight 1964. More...

17D58E Isayev N2O4/UDMH rocket engine.13 N. In Production. Isp=247s. Small attitude control thruster used in Briz, BrizM upper stage propulsion system S5.98M. More...

4D10 Isayev N2O4/UDMH rocket engine. 255 kN. R27 / RSM25 (SSN6). Out of Production. 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. More...

DMT600 MMH Isayev N2O4/MMH rocket engine. 0.600 kN. Hermes. In Production. Version of DMT600 using MMH in place of UDMH, adaptation to western market (was discussed for European Hermes space plane project). 6,000 ignitions Isp=305s. More...

DMT600 Isayev N2O4/UDMH rocket engine. 0.600 kN. In Production. Bipropellant hypergolic (selfigniting) engine, pressurefed. 6,000 ignitions Isp=300s. More...

DOK10 Isayev monopropellant rocket engine. 10 N. In Production. Pressurefed monopropellant engine. Thermal decomposition of hydrazine by an iridiumbased catalyst, which heated to increase stability. 40,000 ignitions Isp=229s. More...

DOK50 Isayev monopropellant rocket engine. 0.050 kN. In Production. Pressurefed monopropellant engine. Thermal decomposition of hydrazine by an iridiumbased catalyst, which heated to increase stability. 40,000 ignitions Isp=229s. More...

DOT25 Isayev monopropellant rocket engine. 0.025 kN. In Production. Pressurefed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions Isp=234s. More...

DOT5 Isayev monopropellant rocket engine. 5 N. In Production. Pressurefed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 550,000 ignitions Isp=230s. More...

DST100 Isayev N2O4/UDMH rocket engine. 0.100 kN. In Production. Bipropellant hypergolic (selfigniting) engine, pressurefed. 10,000 ignitions Isp=276s. More...

DST100A Isayev N2O4/UDMH rocket engine. 0.100 kN. In Production. Bipropellant hypergolic engine, pressurefed. Larger nozzle and reduced chamber pressure to increase performance and lifetime in comparison to DST100. 450,0000 ignitions. Isp=304s. More...

DST200 Isayev N2O4/UDMH rocket engine. 0.200 kN. In Production. Bipropellant hypergolic (selfigniting) engine, pressurefed. 10,000 ignitions Isp=280s. More...

DST200A Isayev N2O4/UDMH rocket engine. 0.20 kN. In Production. Bipropellant hypergolic engine, pressurefed. Larger nozzle and reduced chamber pressure to increase performance and lifetime compared to DST200. 100,0000 ignitions. Isp=300s. More...

DST25 Isayev N2O4/UDMH rocket engine. 0.025 kN. In Production. Bipropellant hypergolic (selfigniting) engine, pressurefed. 300,000 ignitions Isp=285s. More...

Isayev R17 Isayev Nitric acid/Kerosene rocket engine. 131.2 kN. R17. Out of production. Designation unknown. First flight 1961. More...

Isayev 218 Isayev Nitric acid/Amine rocket engine. 218 (S25 system). Out of Production. Launch thrust 166 kN. More...

Isayev V750V Isayev Nitric acid/Amine rocket engine. 30.4 kN. SAMmissile V750V. Out of Production. Designation unknown. More...

Isayev P15 Isayev Nitric acid/Amine rocket engine. 11.9 kN. P15 Termit. Out of Production. Designation unknown. Thrust range 11.8955.43 kN. More...

KDU414 Isayev Nitric acid/UDMH rocket engine. 1.961 kN. Molniya 1, Mars 1, Venera 1, Zond 23 maneuvering engine. Out of Production. Spacecraft maneuvering engine. Isp=272s. More...

KDU426 Isayev N2O4/UDMH rocket engine. 3.089 kN. SoyuzT orbital correction engine. In Production. Pressurefed engine. Used as long duration engine for correction orbits of satellites. Isp=292s. More...

KRD442 Isayev N2O4/UDMH rocket engine. 4.38 / 0.17 kN. Orbital propulsion for FGBderived modules for Mir and ISS. In Production. Main and lowthrust mode. Operation of turbopump without chamber used to pump propellants into tanks from Progress tankers. More...

KRD61 Isayev N2O4/UDMH rocket engine. 18.8 kN. Luna Ye8. Out of Production. Spacecraft maneuvering engine for ascent stage of Luna moon sample return missions. Isp=313s. First flight 1969. More...

KRD79 Isayev N2O4/UDMH rocket engine. 3.090 kN. Salyut 6, 7and Mir orbital propulsion maneuvering engine. In Production. Probably derived from engine of propulsion system KDU426. Pressure fed engine. More...

KTDU417 Isayev Nitric acid/UDMH rocket engine. 18.920 kN. Luna 1524 descent stage. Out of Production. Isp=314s. Comprised turbopumpfed highthrust engine with plus KTDU417B lowthrust engine. Eleven ignitions for lunar orbit insertion and orbit corrections. More...

KTDU80 Isayev N2O4/UDMH rocket engine. 6.190 kN. Soyuz TM, Progress M. In Production. Isp=326s. Propulsion system included 4 spherical tanks for a total of 880 kg propellant. Developed from NII Mash experimental thruster. 3 thrust levels by 4 valves. More...

KTDU66 Isayev Nitric acid/UDMH rocket engine. 4.090 kN. Out of Production. Isp=280s. Maneuvering engine for Salyut 1, derivative of KTDU35. Longer burn time of 1000 s. Comprised singlechamber main engine plus dualchamber backup engine. Thrusts 4.09 + 4.03 kN More...

KTDU5A Isayev Nitric acid/Amine rocket engine. 45.5 kN. Used on Luna E6 probes. Out of Production. Isp=287s. First turbopump engine with surface tension propellant management devices in tanks, allowing reignition in zeroG. More...

KTDU53 Isayev Nitric acid/UDMH rocket engine. 4.089 kN. Zond 47 maneuvering engine. Out of Production. Spacecraft maneuvering engine, derivative of KTDU35 without backup engine. Isp=280s. More...

KTDU425A Isayev N2O4/UDMH rocket engine. 18.890 kN. Mars 47, Venera 916, Vega 12, and Phobos 12 maneuvering engine. Out of Production. Could be throttled to 9.86/9.5/2870. Chamber pressure 149  95 bar. Isp=315s. First flight 1973. More...

KTDU417B Isayev N2O4/UDMH rocket engine. 3.430 kN. Luna 1524 used this low thrust engine in system KTDU417 for softlanding on the moon. Out of Production. Isp=254s. Pressurefed engine; could be throttled to 2.06 kN. More...

KTDU35 Isayev Nitric acid/UDMH rocket engine. 4.09 kN. Out of Production. Isp=280s. Soyuz, Salyut 4 maneuvering engine. KTDU53 version in L1 circumlunar spacecraft; KTDU66 in Salyut 1 space station. Thrusts 4.09 kN main + 4.03 kN secondary. First flight 1966. More...

KTDU425 Isayev N2O4/UDMH rocket engine. 18.850 kN. Mars 2 and 3 maneuver engine. Out of Production. Pumpfed engine. Could be throttled to 7.05 kN / 9.5 MPa / 2850 m/s. . Chamber pressure 133,2  95 bar. Isp=312s. More...

R101B.360000 Isayev Nitric acid/Amine rocket engine. R101B/R108 SAM. Developed 195051. Launch thrust 83.3 kN. Single chamber engine designed for use in the R101B and R108 (derivative of German Wasserfall). More...

RD56 Isayev lox/lh2 rocket engine. 69.6 kN. N1 block R. Development ended 1971. Oxygenhydrogen engine for cryogenic upper stage. Developed but never flown. Design sold to India in 1990's for GSLV. Isp=462s. More...

RD56M Isayev lox/lh2 rocket engine. 73.580 kN. Proton and Angara upper stage KVRB, 12KRB upper stage for GSLV (India). In development. Isp=461s. First flight 2001. More...

RD56M LNG Isayev Lox/LNG rocket engine. 73.5 kN. Vozdushnyy Start stage 2. Developed 1996. Variant of RD56M using liquid natural gas in place of hydrogen. First engine tests performed in 1998. More...

S09.29 Isayev Nitric acid/Amine rocket engine. 88 kN. V300/V303 (S25 system). Out of Production. More...

S09.502 Isayev Nitric acid/Amine rocket engine. R101 SAM. Developed 194950. Launch thrust 78.4 kN. Four chamber engine designed for use in the R101 (derivative of German Wasserfall). Abandoned by 1950 in favour of singlechamber engine. More...

S2.1100 Isayev rocket engine. V1000. Out of Production. OKB2 transferred work on the S2.1100 to OKB117 in 195859. OKB117 completed development. More...

S2.1150 Isayev Nitric acid/Amine rocket engine. 671.2 kN. Burya booster. Out of production. Isp=250s. First flight 1957. Engines developed from R11 S2.253 engine. More...

S2.1200 Isayev rocket engine. Developed 1950s middle. OKB2 transferred work on the S2.1200 to OKB154 in 1957. The latter used the designation RO1 for the engine. More...

S2.145 Isayev rocket engine. 88 kN. Developed 1950s early. More...

S2.253 Isayev Nitric acid/Kerosene rocket engine. 93.3 kN. R11 (Scud B) 8A61. Thrust 8300 kgf at sea level. Fuel Kerosene T1, chemical ignition by TG02. Isp=251s. First flight 1953. More...

S2.253 derivative Isayev Lox/Kerosene rocket engine. 93.2 kN. EKR (experimental winged missile). Study 1953. Derivative of S2.253 was proposed for use in EKR Stage 1 (project for an experimental winged missile). Isp=250s. More...

S2.253A Isayev Nitric acid/Kerosene rocket engine. 93 kN. R11FM. Out of Production. Used in R11FM submarine version of Scud B. Fuel Kerosene T1, chemical ignition by TG02. Mixture ratio derived from tank content. 81 kN sealevel. More...

S2.721V Isayev Nitric acid/Amine rocket engine. 11.8 kN. KSR. Developed 1956. More...

S2.713 Isayev Nitric acid/Amine rocket engine. 252.2 kN. R13 (SSN4). Out of Production. First engine to employ gas generator on main propellants. One main and four vernier thrusters. (Mixture derived ratio from tank content.) More...

S2.720 Isayev Nitric acid/Amine rocket engine. 34.3 kN. Engine for SAMmissile V755. Out of Production. Pumpfed engine. Used in engine unit of a special apparatus. Pumpfed engine. 20,4 kN sea level. More...

S5.1 Isayev Nitric acid/Amine rocket engine. 167 kN. SAMmissiles 217M and 218. Out of Production. Designation unknown. More...

S5.3M Isayev Nitric acid/Amine rocket engine. 396.7 kN. R9 (SS8) missile stage 1. Out of Production. Proposed for R9 missile stage 1. Four engines per stage. 396,7 kN sealevel. More...

S5.3 Isayev Nitric acid/Amine rocket engine. 392 kN. R21 (SSN5). Out of Production. First engine to start underwater. 392 kN sealevel. More...

S5.4 Isayev Nitric acid/Amine rocket engine. 15.830 kN. Vostok/Voskhod retorfire engine; spacecraft maneuvering engine. . Out of Production. Includes 4 small lateral steering nozzles. Isp=266s. More...

S5.44 Isayev Nitric acid/Amine rocket engine. 177 kN. SAMmissile 5Ya24. Out of Production. Could be throttled. 17749 kN sealevel. Area ratio 118  44. More...

S5.45 Isayev Nitric acid/UDMH rocket engine. 1961 kN. correction engine for Zond1, Venera28, and others. Out of Production. Pressurefed engine. Used as correction engine for spacecraft Zond1, Vernera8, and others. Isp=267s. More...

S5.51 Isayev N2O4/UDMH rocket engine. 33.196 kN. Hardware 1969. Isp=314s. 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. Verniers included for midcourse corrections. More...

S5.80.11000 Isayev Lox/Kerosene rocket engine. 2.940 kN. Soyuz2 Blok LM. Developed 1990s. Thrust chamber from KTDU80 / S5.80 converted to burn Lox/Kerosene. More...

S5.92 Isayev N2O4/UDMH rocket engine. 19.6 kN. Phobos propulsion module, later adapted as Fregat upper stage. In production. Isp=327s. Gas generator cycle. Nominal and lowthrust thrust levels. More...

S5.98M Isayev N2O4/UDMH rocket engine. 19.62 kN. Used on Briz and BrizM upper stages. Isp=325s. Engine system consists of: main engine (2000 kgf, Isp=325.5s) + 4x11D458 (40 kgf, Isp=252s) + 12x17D58E (1.36 kgf, Isp=247s). 8 restarts. First flight 1990. More...

U1250 Isayev rocket engine. 12.7 kN. Developed 194546. Isp=208s. More...

U2000 Isayev rocket engine. 19.6 kN. for SAM. Out of Production. More...

U4002 Isayev Nitric acid/Amine rocket engine. Shchuka. Out of Production. More...

U40010 Isayev rocket engine. 3.920 kN. Samolet 5. Developed 194647. More...
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