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
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]

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.

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

  1. ↑ "Краткая история нашего предприятия" [A brief history of our company] (in Russian). KB KhimMash. Archived from the original on 19 August 2011.
  2. ↑ "Руководство" [Leadership] (in Russian). KB KhimMash. Archived from the original on 23 April 2013.
  3. ↑ "Основные направления деятельности" [Main Activities] (in Russian). KB KhimMash. Archived from the original on 19 August 2011.
  4. ↑ "Этапы истории КБХМ им. А.М. Исаева" [Milestones A.M. Isayev KBKhM] (in Russian). KB KhimMash. Archived from the original on 23 April 2013.
  5. 1 2 "ЖРДМТ от 0,5 кгс до 250 кгс" [Small thrust jet engine from 0.5 kgf to 250 kgf] (in Russian). KB KhimMash. Archived from the original on 23 April 2013.
  6. ↑ "Двигатели тягой от 250 кгс до 50 тс" [Engines with thrust of 250 kg to 50 tonnes] (in Russian). KB KhimMash. Archived from the original on 23 April 2013.
  7. 1 2 3 4 5 6 Ponomarenko, Alexander. "Основные двигатели разработки КБХМ" [The main engines produced by KBKhM]. LPRE.DE (in Russian). Retrieved 2015-07-25.
  8. ↑ Brügge, Norbert. "Spacecraft-propulsion blocks (KDU) from Isayev's design bureau (now KB KhimMash)". B14643.de. Archived from the original on 2015-06-02. Retrieved 2015-07-30.
  9. ↑ "Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные" [Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry] (PDF) (in Russian). pp. 75–81. Retrieved 2015-07-25.
  10. 1 2 "Isayev". Encyclopedia Astronautica. Archived from the original on 2016-08-08. Retrieved 2015-07-30.
  11. 1 2 Brügge, Norbert. "Some identified rocket-engines from Isayev's Design Bureau (now KB KhimMash)". B14643.de. Archived from the original on 2015-10-17. Retrieved 2015-07-30.
This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.