The A.M. Isayev Chemical Engineering Design Bureau (Russian: ), 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 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 S5.86.1000-0

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 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. 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. 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 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 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

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

External links KBKhM Official Page