A.M. Isayev Chemical Engineering Design Bureau

AM Isayev Chemical Engineering Design Bureau
Native name	Конструкторское бюро химического машиностроения имени A.M. Исаева
Romanized name	Chemical Engineering Design Bureau named after AM Isayev
Formerly called	OKB-2
Type	Unitary enterprise
Industry	Liquid rocket engine manufacturing equipment for heat treatment of meat and fish medical equipment common consumption goods
Predecessor	NII-88
Founded	1948 Podlipki, Soviet Union
Founder	Aleksei Mihailovich Isaev
Headquarters	12 Bogomolov, Korolev Королёв (Russian: ул. Богомолова, д. 12), Moscow, Russia
Key people	Igor G. Panin
Products	S5.92 KTDU-80 S5.142
Parent	Khrunichev State Research and Production Space Center
Website	Official 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, Moscow Oblast. It started as the OKB-2 division of the NII-88 research institute, where Isayev directed the development of liquid rocket engines for ballistic 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]
- 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^[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.

References

↑ "Краткая история нашего предприятия" [A brief history of our company] (in Russian). KB KhIMMASH. Retrieved 2015-07-30.
↑ "Руководство" [Leadership] (in Russian). KB KhIMMASH. Retrieved 2015-07-30.
↑ "Основные направления деятельности" [Main Activities] (in Russian). KB KhIMMASH. Retrieved 2015-07-30.
↑ "Этапы истории КБхиммаш им. А.М. Исаева" [Milestones KBhimmash then AM Isayev] (in Russian). KB KhIMMASH. Retrieved 2015-07-30.
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. Retrieved 2015-07-25.
↑ "Двигатели тягой от 250 кгс до 50 тс" [Engines with thrust of 250 kg to 50 tonnes] (in Russian). KB KhIMMASH. Retrieved 2015-07-25.
1 2 3 4 5 6 Ponomarenko, Alexander. "Основные двигатели разработки КБХМ" [The main engines produced by KbKhA]. LPRE.DE (in Russian). Retrieved 2015-07-25.
↑ Brügge, Norbert. "Spacecraft-propulsion blocks (KDU) from Isayev's design bureau (now Khimmash)". B14643.de. Retrieved 2015-07-30.
↑ "Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные" [Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry] (PDF) (in Russian). p. 75-81. Retrieved 2015-07-25.
1 2 "Isayev". Encyclopedia Astronautica. Retrieved 2015-07-30.
1 2 Brügge, Norbert. "Some identified rocket-engines from Isayev's Design Bureau (now KB Khimmash)". B14643.de. Retrieved 2015-07-30.

External links

KB KhIMMASH Official Page

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