A.M. Isayev Chemical Engineering Design Bureau
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(Redirected from KBKhM)
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Native name
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Конструкторское бюро химического машиностроения имени A.M. Исаева |
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Romanized name
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Chemical Engineering Design Bureau named after A.M. Isayev |
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Formerly called
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OKB-2 |
| Unitary enterprise | |
| Industry |
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| Predecessor | NII-88 |
| Founded | 1948 Podlipki, Soviet Union |
| Founder | Aleksei Mihailovich Isaev |
| Headquarters | 12 Bogomolov street, Korolyov (Russian: ул. Богомолова, д. 12, Королёв), Moscow region, Russia |
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Key people
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Igor G. Panin |
| Products | |
| Parent | Khrunichev State Research and Production Space Center |
| Website | Official Website |
| Footnotes / references [1][2][3][4] |
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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
- С5.86.1000-0
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
- 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
- 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.
See also
- Isayev — Founder and director of the company until 1975.
- NII-88 — The research institute where KB KhimMash started as OKB-2 division.
- Khrunichev State Research and Production Space Center — The corporate parent of KBKhM.
- United Rocket and Space Corporation — The government owned corporate entity that will encompass all aerospace corporations in Russia.
References
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