A.M. Isayev Chemical Engineering Design Bureau

From Wikipedia, the free encyclopedia

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.

Native name
Конструкторское бюро химического машиностроения имени A.M. Исаева
Chemical Engineering Design Bureau named after A.M. Isayev
FormerlyOKB-2
Company typesubsidiary
Quick facts Native name, Romanized name ...
A.M. Isayev Chemical Engineering Design Bureau
Native name
Конструкторское бюро химического машиностроения имени A.M. Исаева
Chemical Engineering Design Bureau named after A.M. Isayev
FormerlyOKB-2
Company typesubsidiary
Industry
  • Liquid rocket engine manufacturing
  • equipment for heat treatment of meat and fish
  • medical equipment
  • common consumption goods
PredecessorNII-88
Founded1948 Podlipki (Korolyov), Soviet Union
FounderAleksei Mihailovich Isaev
Headquarters12 Bogomolov street, Korolyov (Russian: ул. Богомолова, д. 12, Королёв),
Moscow region
,
Russia
Key people
Igor G. Panin
Products
ParentKhrunichev State Research and Production Space Center
WebsiteOfficial Website
Footnotes / references
[1][2][3][4]
Close

Products

Current engines

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]
  • Propulsion Modules
  • Experimental Engines
    • S5.86.1000-0

Former engines

Engines that are no longer produced.

  • Monopropellant Thrusters[7]
  • Bipropellant Thrusters[7]
    • S5.144: Used on the control module 17D61 of the Ikar.
    • S5.205
  • Orbit Correction Engines
  • Propulsion Modules
    • KDU-414: Pressure-fed liquid rocket engine burning UDMH and RFNA. Used on early soviet deep space probes.
    • KTDU-35: Liquid rocket engine burning UDMH and AK27I in the gas generator cycle. Used on first generation Soyuz, and Progress.[7]
    • KTDU-425: Pump-fed liquid rocket engine. Used on the 4MV bus employed by unmanned Mars and Venus probes.
    • 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
    • S5.1
    • S.5.6.0000.0
    • S5.15
    • S5.33
    • S5.33A S5.33M
    • S5.41
    • S5.44 5D25
    • S5.57
    • S5.44 5D25
    • 5D25N
    • S5.83
  • 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.
    • S5.3: 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.
    • 4D10: 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.
    • 4D10: 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.
    • 4D76: 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.
    • 4D76M: A UDMH/N2O4 burning engine in the gas generator cycle. Development years: 1969-1970 . Improved version of the 4D-76.
    • 4D28: 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.
    • 3D20: A UDMH/N2O4 burning engine in the staged combustion cycle. Development years: 1971-1973 . For use as main engine RSM-27U.
    • 3D20: A UDMH/N2O4 burning engine in the gas generator cycle. Development years: 1971-1973 . For use as steering engine R-27U.
    • 3D41: 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.
    • 3D42: 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.
    • 3D67?: 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.
    • 3D36: A UDMH/N2O4 burning engine in the gas generator cycle. Development years: 1980-1986 . For use on warhead of the R-29RM.
    • 3D38: 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.
    • 3D39: 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.

See also

References

External links

Related Articles

Wikiwand AI