A.M. Isayev Chemical Engineering Design Bureau

Engines in current production:

• Monopropellant Thrusters[5]
  • DOT-5
  • DOT-25
  • MLC-10
  • MLC-50
• Bipropellant Thrusters[5]
  • S5.142 (DST-25)
  • DST-50
  • DST-100
  • DST-100A
  • DST-200
  • DST-200A
  • DMT-6
  • DMT-500
  • DMT-600
  • DMT-1000
  • DMT-2200
• Main propulsion[6]
  • S5.80
  • S5.92
  • S5.98
  • KVD-1
• Propulsion Modules
  • KTDU-80
• Experimental Engines
  • С5.86.1000-0

Engines that are no longer produced.

• Monopropellant Thrusters[7]
  • S5.70: Used on Phobos 1 spacecraft.
  • S5.70: Used on Phobos 1 spacecraft.
• Bipropellant Thrusters[7]
  • S5.144: Used on the control module 17D61 of the Ikar.
  • S5.205
• Orbit Correction Engines
  • S5.4: Liquid engine burning TG-02 and AK20F in the gas generator cycle. Used to deorbit Vostok, Voskhod and Zenit.[8]
  • S5.35: Backup engine of the KTDU-35.
  • S5.53: Orbital correction engine for the lunar version of the Soyuz.
  • S5.60: Main engine of the KTDU-35.
  • S5.66: Maneuvering engine version for the Salyut 1 and Salyut 4 stations. Also was composed of primary and secondary engines.
  • S5.79: Pressure-fed rocket engine burning N₂O₄/UDMH. Used as the main orbital engine of Salyut-6, Salyut-7, Mir Core Module and Zvezda.[7]
• Propulsion Modules
  • KTDU-35: Liquid rocket engine burning UDMH and AK27I in the gas generator cycle. Used on first generation Soyuz, and Progress.[7]
  • KTDU-426: Spacecraft version of the S5.79. Used on the Soyuz-T.[9]
• Military Missiles[7]
  • RD-1
  • RD-1M
  • Y-1250
  • U-400-10
  • PT 45-2
  • SU-1500
  • Y-2000
  • S09.19A?
  • S09.29A S09.29.0-0
  • S09.29D
  • S09.29B
  • S09.29.0-OV?
  • S09.29.0-OV?
  • S2.145
  • S2.145
  • S2.168A
  • S2.168B
  • S2.219
  • S.911.0100 S2.219?
  • S2.244
  • S2.258
  • S2.260
  • S2.268
  • S2.514
  • S2.711
  • S2.711V S2.711V1
  • S2.720
  • S2.720.A2
  • S2.720M
  • S2.721 S2.721V
  • S2.722
  • S2.722V
  • S2.726
  • S2.727
  • S2.751V?
  • S2.1100: A TG-02/AK20K burning engine. Development years: 1955–1958. For use in the booster module of the Burya intercontinental cruise missile project.[10][11]
  • S2.1150: An improved version of the S2.1100. Development years: 1958–1960. For use in the booster module of the Burya project.[10][11]
  • S2.1200
  • C5.1
  • S.5.6.0000.0
  • S5.15
  • C5.33
  • C5.33A C5.33M
  • S5.41
  • S5.44 5D25
  • S5.57
  • S5.44 5D25
  • 5D25N
  • C5.83
• Rocket engines for ICBM and SLBM[7]
  • S2.253 (8D511): A kerosene/AK20 burning engine in the pressure fed cycle. Development years: 1951-1955 . For use in first versions of Scud-A. Ignition by hypergolic start fuel TG-02.
  • S2.253A: A kerosene/AK-20 burning engine in the pressure fed cycle. Development years: 1953-1959 . For use in the RSM-11FM. Ignition by hypergolic start fuel TG-02.
  • S2.713: A TG-02/AK27I burning engine in the gas generator cycle. Development years: 1956-1961 . For use in the R-13. It included a fixed nozzle and four verniers.
  • S5.2 (9D21): A TM-185/AK-27I burning engine in the gas generator cycle. Development years: 1959-1962 . For use in the R-17.
  • C5.3: A TG-02/AK-27I burning engine in the gas generator cycle. Development years: 1958-1963 . For use in the R-21.
  • S5.3M: A TG-02/AK-27I burning engine in the gas generator cycle. Development years: 1960. Project for the ICBM R-9B.
  • 4D-10: A UDMH/N₂O₄ burning engine in the staged combustion cycle. Development years: 1962-1968 . For use as main engine of the first stage of R-27. First engine submerged in the propellant tank.
  • 4D-10: A UDMH/N₂O₄ burning engine in the gas generator cycle. Development years: 1963-1968 . For use as the steering engine of the first stage of the R-27. Submerged in the propellant tank.
  • 4D-76: A UDMH/N₂O₄ burning engine in the gas generator cycle. Development years: 1964-1971 . For use as main engine of the second stage of R-29. Submerged in the propellant tank.
  • 4D-76M: A UDMH/N₂O₄ burning engine in the gas generator cycle. Development years: 1969-1970 . Improved version of the 4D-76.
  • 4D-28: A UDMH/N₂O₄ burning engine in the gas generator cycle. Development years: 1968-1970 . For use on the second stage of the rocket RSM-27K.
  • 3D-20: A UDMH/N₂O₄ burning engine in the staged combustion cycle. Development years: 1971-1973 . For use as main engine RSM-27U.
  • 3D-20: A UDMH/N₂O₄ burning engine in the gas generator cycle. Development years: 1971-1973 . For use as steering engine R-27U.
  • 3D-41: A UDMH/N₂O₄ burning engine in the gas generator cycle. Development years: 1973-1975 . For use on the second stage of R-29R. Submerged in the propellant tank.
  • 3D-42: A UDMH/N₂O₄ burning engine in the gas generator cycle. Development years: 1973-1975 . For use on warhead of the R-29R . Four fixed main combustion chambers and four verniers.
  • 3D-67?: A UDMH/N₂O₄ burning engine in the gas generator cycle. Development years: 1976-1980 . For use on warhead of the R-39. Dual-mode rocket engine with multiple regimen.
  • 3D-36: A UDMH/N₂O₄ burning engine in the gas generator cycle. Development years: 1980-1986 . For use on warhead of the R-29RM.
  • ZD-38: A UDMH/N₂O₄ burning engine in the staged combustion cycle. Development years: 1980-1986 . For use on the second stage R-29RM. Submerged in the propellant tank.
  • 3D-39: A UDMH/N₂O₄ burning engine in the staged combustion cycle. Development years: 1980-1986 . For use on the third stage R-29RM. Submerged in the propellant tank.