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A.M. Isayev Chemical Engineering Design Bureau

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Formerly called
  
OKB-2

Predecessor
  
NII-88

Founded
  
1948

Type
  
Unitary enterprise

Headquarters
  
Korolyov, Moscow Oblast

Native name
  
Конструкторское бюро химического машиностроения имени A.M. Исаева

Romanized name
  
Chemical Engineering Design Bureau named after A.M. Isayev

Industry
  
Liquid rocket engine manufacturingequipment for heat treatment of meat and fishmedical equipmentcommon consumption goods

Parent organization
  
Khrunichev State Research and Production Space Center

The A.M. Isayev Chemical Engineering Design Bureau (Russian: Конструкторское бюро химического машиностроения имени A.M. Исаева), also known as KB KhimMash or just KBKhM, is a Russian rocket engine design and manufacturing company. It is located in the city of Korolyov. It started as the OKB-2 division of the NII-88 research institute, where A.Isaev directed the development of liquid rocket engines for ballistic missile submarines.

Contents

Current engines

Engines in current production:

  • Monopropellant Thrusters
  • DOT-5
  • DOT-25
  • MLC-10
  • MLC-50
  • Bipropellant Thrusters
  • 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
  • S5.80
  • S5.92
  • S5.98
  • KVD-1
  • Propulsion Modules
  • KTDU-80
  • Experimental Engines
  • С5.86.1000-0

    • Former engines

    Engines that are no longer produced.

  • Monopropellant Thrusters
  • S5.70: Used on Phobos 1 spacecraft.
  • S5.70: Used on Phobos 1 spacecraft.
  • Bipropellant Thrusters
  • 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.
  • 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.
  • Propulsion Modules
  • KTDU-35: Liquid rocket engine burning UDMH and AK27I in the gas generator cycle. Used on first generation Soyuz, and Progress.
  • KTDU-426: Spacecraft version of the S5.79. Used on the Soyuz-T.
  • Military Missiles
  • 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.
  • S2.1150: An improved version of the S2.1100. Development years: 1958-1960. For use in the booster module of the Burya project.
  • 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
  • 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.

    • References

    A.M. Isayev Chemical Engineering Design Bureau Wikipedia
    (Text) CC BY-SA


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