Encyclopedia Astronautica
Isayev


Isayev Design Bureau, Russia.

AKA: A M Isayev; OKB-2; KB Khimmash Imeni A. M. Isayeva.

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Associated Countries
Associated Spacecraft
  • 346 Russian manned rocketplane. 4 flights from 1946. Post-war Soviet version of the German supersonic DFS 8-346 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 LK-700 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 kg-s. Minimum impulse 4 kg-s. Specific impulse also reported as 275 sec. More...
  • 11D49 Isayev Nitric acid/UDMH rocket engine. 157.5 kN. Kosmos-3M stage 2. Engine has one main and four steering nozzles. Thrust 157.5 + 4 x 25 kN. Precessor was 11D47 in R-14 (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, Briz-M upper stage propulsion system S5.98M. More...
  • 4D10 Isayev N2O4/UDMH rocket engine. 255 kN. R-27 / RSM-25 (SS-N-6). 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...
  • DMT-600 MMH Isayev N2O4/MMH rocket engine. 0.600 kN. Hermes. In Production. 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 Isp=305s. More...
  • DMT-600 Isayev N2O4/UDMH rocket engine. 0.600 kN. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 6,000 ignitions Isp=300s. More...
  • DOK-10 Isayev monopropellant rocket engine. 10 N. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions Isp=229s. More...
  • DOK-50 Isayev monopropellant rocket engine. 0.050 kN. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions Isp=229s. More...
  • DOT-25 Isayev monopropellant rocket engine. 0.025 kN. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions Isp=234s. More...
  • DOT-5 Isayev monopropellant rocket engine. 5 N. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 550,000 ignitions Isp=230s. More...
  • DST-100 Isayev N2O4/UDMH rocket engine. 0.100 kN. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions Isp=276s. More...
  • DST-100A Isayev N2O4/UDMH rocket engine. 0.100 kN. In Production. Bi-propellant hypergolic engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime in comparison to DST-100. 450,0000 ignitions. Isp=304s. More...
  • DST-200 Isayev N2O4/UDMH rocket engine. 0.200 kN. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions Isp=280s. More...
  • DST-200A Isayev N2O4/UDMH rocket engine. 0.20 kN. In Production. Bi-propellant hypergolic engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime compared to DST-200. 100,0000 ignitions. Isp=300s. More...
  • DST-25 Isayev N2O4/UDMH rocket engine. 0.025 kN. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 300,000 ignitions Isp=285s. More...
  • Isayev R-17 Isayev Nitric acid/Kerosene rocket engine. 131.2 kN. R-17. Out of production. Designation unknown. First flight 1961. More...
  • Isayev 218 Isayev Nitric acid/Amine rocket engine. 218 (S-25 system). Out of Production. Launch thrust 166 kN. More...
  • Isayev V-750V Isayev Nitric acid/Amine rocket engine. 30.4 kN. SAM-missile V-750V. Out of Production. Designation unknown. More...
  • Isayev P-15 Isayev Nitric acid/Amine rocket engine. 11.9 kN. P-15 Termit. Out of Production. Designation unknown. Thrust range 11.895-5.43 kN. More...
  • KDU-414 Isayev Nitric acid/UDMH rocket engine. 1.961 kN. Molniya 1, Mars 1, Venera 1, Zond 2-3 maneuvering engine. Out of Production. Spacecraft maneuvering engine. Isp=272s. More...
  • KDU-426 Isayev N2O4/UDMH rocket engine. 3.089 kN. Soyuz-T orbital correction engine. In Production. Pressure-fed engine. Used as long duration engine for correction orbits of satellites. Isp=292s. More...
  • KRD-442 Isayev N2O4/UDMH rocket engine. 4.38 / 0.17 kN. Orbital propulsion for FGB-derived modules for Mir and ISS. In Production. Main and low-thrust mode. Operation of turbopump without chamber used to pump propellants into tanks from Progress tankers. More...
  • KRD-61 Isayev N2O4/UDMH rocket engine. 18.8 kN. Luna Ye-8. Out of Production. Spacecraft maneuvering engine for ascent stage of Luna moon sample return missions. Isp=313s. First flight 1969. More...
  • KRD-79 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 KDU-426. Pressure fed engine. More...
  • KTDU-417 Isayev Nitric acid/UDMH rocket engine. 18.920 kN. Luna 15-24 descent stage. Out of Production. Isp=314s. Comprised turbopump-fed high-thrust engine with plus KTDU-417-B low-thrust engine. Eleven ignitions for lunar orbit insertion and orbit corrections. More...
  • KTDU-80 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...
  • KTDU-66 Isayev Nitric acid/UDMH rocket engine. 4.090 kN. Out of Production. Isp=280s. Maneuvering engine for Salyut 1, derivative of KTDU-35. Longer burn time of 1000 s. Comprised single-chamber main engine plus dual-chamber back-up engine. Thrusts 4.09 + 4.03 kN More...
  • KTDU-5A Isayev Nitric acid/Amine rocket engine. 45.5 kN. Used on Luna E-6 probes. Out of Production. Isp=287s. First turbopump engine with surface tension propellant management devices in tanks, allowing re-ignition in zero-G. More...
  • KTDU-53 Isayev Nitric acid/UDMH rocket engine. 4.089 kN. Zond 4-7 maneuvering engine. Out of Production. Spacecraft maneuvering engine, derivative of KTDU-35 without back-up engine. Isp=280s. More...
  • KTDU-425A Isayev N2O4/UDMH rocket engine. 18.890 kN. Mars 4-7, Venera 9-16, Vega 1-2, and Phobos 1-2 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...
  • KTDU-417-B Isayev N2O4/UDMH rocket engine. 3.430 kN. Luna 15-24 used this low thrust engine in system KTDU-417 for soft-landing on the moon. Out of Production. Isp=254s. Pressure-fed engine; could be throttled to 2.06 kN. More...
  • KTDU-35 Isayev Nitric acid/UDMH rocket engine. 4.09 kN. Out of Production. Isp=280s. Soyuz, Salyut 4 maneuvering engine. KTDU-53 version in L-1 circumlunar spacecraft; KTDU-66 in Salyut 1 space station. Thrusts 4.09 kN main + 4.03 kN secondary. First flight 1966. More...
  • KTDU-425 Isayev N2O4/UDMH rocket engine. 18.850 kN. Mars 2 and 3 maneuver engine. Out of Production. Pump-fed engine. Could be throttled to 7.05 kN / 9.5 MPa / 2850 m/s. . Chamber pressure 133,2 - 95 bar. Isp=312s. More...
  • R-101B.36000-0 Isayev Nitric acid/Amine rocket engine. R-101B/R-108 SAM. Developed 1950-51. Launch thrust 83.3 kN. Single chamber engine designed for use in the R-101B and R-108 (derivative of German Wasserfall). More...
  • RD-56 Isayev lox/lh2 rocket engine. 69.6 kN. N1 block R. Development ended 1971. Oxygen-hydrogen engine for cryogenic upper stage. Developed but never flown. Design sold to India in 1990's for GSLV. Isp=462s. More...
  • RD-56M 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...
  • RD-56M LNG Isayev Lox/LNG rocket engine. 73.5 kN. Vozdushnyy Start stage 2. Developed 1996-. Variant of RD-56M 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. V-300/V-303 (S-25 system). Out of Production. More...
  • S09.502 Isayev Nitric acid/Amine rocket engine. R-101 SAM. Developed 1949-50. Launch thrust 78.4 kN. Four chamber engine designed for use in the R-101 (derivative of German Wasserfall). Abandoned by 1950 in favour of single-chamber engine. More...
  • S2.1100 Isayev rocket engine. V-1000. Out of Production. OKB-2 transferred work on the S2.1100 to OKB-117 in 1958-59. OKB-117 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 R-11 S2.253 engine. More...
  • S2.1200 Isayev rocket engine. Developed 1950s middle. OKB-2 transferred work on the S2.1200 to OKB-154 in 1957. The latter used the designation RO-1 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. R-11 (Scud B) 8A61. Thrust 8300 kgf at sea level. Fuel Kerosene T-1, chemical ignition by TG-02. 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. R-11FM. Out of Production. Used in R-11FM submarine version of Scud B. Fuel Kerosene T-1, chemical ignition by TG-02. Mixture ratio derived from tank content. 81 kN sea-level. 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. R-13 (SS-N-4). 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 SAM-missile V-755. Out of Production. Pump-fed engine. Used in engine unit of a special apparatus. Pump-fed engine. 20,4 kN sea level. More...
  • S5.1 Isayev Nitric acid/Amine rocket engine. 167 kN. SAM-missiles 217M and 218. Out of Production. Designation unknown. More...
  • S5.3M Isayev Nitric acid/Amine rocket engine. 396.7 kN. R-9 (SS-8) missile stage 1. Out of Production. Proposed for R-9 missile stage 1. Four engines per stage. 396,7 kN sea-level. More...
  • S5.3 Isayev Nitric acid/Amine rocket engine. 392 kN. R-21 (SS-N-5). Out of Production. First engine to start underwater. 392 kN sea-level. 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. SAM-missile 5Ya24. Out of Production. Could be throttled. 177-49 kN sea-level. Area ratio 118 - 44. More...
  • S5.45 Isayev Nitric acid/UDMH rocket engine. 1961 kN. correction engine for Zond-1, Venera-2-8, and others. Out of Production. Pressure-fed engine. Used as correction engine for spacecraft Zond-1, Vernera-8, 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...
  • S5.80.1100-0 Isayev Lox/Kerosene rocket engine. 2.940 kN. Soyuz-2 Blok LM. Developed 1990s. Thrust chamber from KTDU-80 / 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 low-thrust thrust levels. More...
  • S5.98M Isayev N2O4/UDMH rocket engine. 19.62 kN. Used on Briz and Briz-M 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...
  • U-1250 Isayev rocket engine. 12.7 kN. Developed 1945-46. Isp=208s. More...
  • U-2000 Isayev rocket engine. 19.6 kN. for SAM. Out of Production. More...
  • U-400-2 Isayev Nitric acid/Amine rocket engine. Shchuka. Out of Production. More...
  • U-400-10 Isayev rocket engine. 3.920 kN. Samolet 5. Developed 1946-47. More...

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