Research and Development Institute of Mechanical Engineering

NIIMash
Native name
ФГУП «Научно-исследовательский институт машиностроения»
FSUE “Research and Development Institute of Mechanical Engineering”
FormerlyOKB-2
Company typeFederal State Unitary Enterprise
Industry
  • Liquid rocket engine manufacturing
  • Development, production and operation of the bench test equipment
  • production of air separation products and liquefied natural gas
PredecessorNII-1 of Moscow
FoundedSeptember 1, 1958 (1958-09-01) in Soviet Union
FounderMikhail G. Mironov
HeadquartersBuilders Street 72 (Russian: ул. Строителей, 72),
Nizhnyaya Salda, Sverdlovsk Oblast
,
Russia
Key people
Anatoly Long, Director of the Institute
Adolf I. Razzhigaev Chief Engineer
Products
ParentRoscosmos[1]
WebsiteOfficial Website
Footnotes / references
[2][3][4][5]

FSUE Research and Development Institute of Mechanical Engineering (Russian: ФГУП Научно-исследовательский институт машиностроения), also known as NIIMash, is a Russian rocket engine design and manufacturing company specialized in small thrusters. It is located in the city of Nizhnyaya Salda, Sverdlovsk Oblast. It started as the B-175 factory of the NII-1 research institute, where Mikhail G. Mironov directed the development of liquid rocket engines research and testing.

Products

NIIMash has an extensive experience in design of testing stands, measurement and control as well as certifications. They also have a line of custom built air separation plants. They also have extensive experience in rotational forming of metals. The list of space rated products is extensive and is the following:

Current propulsion products

Engines in current production:[6][7]

  • Propulsion
    • Experimental Reactive Control System Module
    • KDU 11D414NS
    • Fobos-Grunt Sample Return Spacecraft Propulsion System
    • Fobos-Grunt Spacecraft Thruster Modules
  • Thrusters
    • MD5 (a.k.a. RDMT-5): Cold gas thruster.
    • MD08 (a.k.a. RDMT-8): Cold gas thrusters used on the Ekspress satellite series.
    • MD08-02 (a.k.a. RDMT-8-02): Cold gas thruster: Used on the Fobos-Grunt Sample Return Spacecraft.
    • 11D428A-16 (a.k.a. RDMT-135M): 135 N (30 lbf) N2O4/UDMH thruster. Used on the KTDU-80.
    • 11D428AF-16: N2O4/UDMH thrusters used by the Fobos-Grunt space mission.
    • 11D457: 53.9 N (12.1 lbf) N2O4/UDMH thrusters used by the Resurs-DK No.1.
    • 11D457F: 54 N (12 lbf) N2O4/UDMH thrusters used by the Fobos-Grunt space mission.
    • 11D458 (a.k.a. RDMT-400): 392 N (88 lbf) N2O4/UDMH thrusters used by the Functional Cargo Block based modules and the Briz upper stage.[8]
    • 11D458F (a.k.a. RDMT-400F): 382 N (86 lbf) N2O4/UDMH thrusters used by the Fobos-Grunt space mission.
    • 11D458M (a.k.a. RDMT-400M): 392.4 N (88.2 lbf) N2O4/UDMH thrusters used by the Briz-M upper stage.
    • 17D16 (a.k.a. RDMT-200K): 200 N (45 lbf) GOX/Kerosene thruster. Used the Buran DO thrusters.
    • 17D58E: N2O4/UDMH thrusters used by the Briz-M upper stage.
    • 17D58EF: N2O4/UDMH thrusters used by the Fobos-Grunt space mission.
  • Experimental thursters
    • RDMT2600: 2.6 kN (580 lbf) Ethanol/GOX thruster designed attitude control when the air density is so low that the control surfaces are ineffective.
    • RDMT10: 12 N (2.7 lbf) thruster designed for space applications.
  • Propellant tanks & high pressure gas vessels
    • Composite high pressure Xenon storage tank: Xenon storage unit for electric propulsion spacecraft.
    • Composite Vessel: General high pressure vessel used on the Fobos-Grunt mission.
    • Monopropellant Tank with Stiff-Plastic Separation Device (Diaphragm): Monopropellant storage unit used on the Fobos-Grunt mission.
    • Bipropellant Tank with Stiff-Plastic Separation Devices (Diaphragms): Bipropellant storage unit used on communications satellites.
  • Solenoid Valves
    • RT.200:
    • 18RT.200:
    • 16RT.200:
    • 12RT.200:
    • 6RT.200:
  • Flow stabilizers
    • CP1: 2.43 g (0.086 oz) per second of hypergolic propellant flow.
    • CP2: 23.5 g (0.83 oz) per second of hypergolic propellant flow.
    • CP3: 63 g (2.2 oz)/87 g (3.1 oz)/345 g (12.2 oz)/470 g (17 oz) per second of hypergolic propellant flow.
    • CP4: 60 g (2.1 oz) per second of air/nitrogen/oxygen/hydrogen flow.

Former Propulsion Products

Engines that are no longer produced.[9]

  • RDMT-0.4X: N2O4/UDMH rocket engine.
  • RDMT-0.8: Nitrogen and helium cold gas thruster.
  • RDMT-12: N2O4/UDMH rocket engine.
  • RDMT-50: N2O4/UDMH rocket engine.
  • RDMT-100: N2O4/UDMH rocket engine.
  • RDMT-135 (a.k.a. 11D428A): 135 N (30 lbf) N2O4/UDMH rocket engine. Used on the Soyuz 7K-S, KTDU-426 and initial KTDU-80.
  • RDMT-200: 200 N (45 lbf) N2O4/UDMH thruster used on the Almaz space stations.[10]
  • RDMT-400A: Experimental version of the RDMT-200 with Niobium combustion chamber.[11]
  • RDMT-400X: Experimental version of the RDMT-200 with Carbon combustion chamber.[12]

See also

References

  1. ^ "О мерах по созданию Государственной корпорации по космической деятельности "Роскосмос"". Официальный интернет-портал правовой информации. Retrieved 15 April 2017.
  2. ^ "История" [History] (in Russian). Keldysh Research Center. Retrieved 2015-07-30.
  3. ^ "История" [History] (in Russian). NIIMash. Retrieved 2015-07-30.
  4. ^ "Руководители" [Leaders] (in Russian). NIIMash. Retrieved 2015-07-30.
  5. ^ "Находящиеся в ведении Роскосмоса" [Administered by the Russian Federal Space Agency] (in Russian). Roscosmos. Retrieved 2015-07-30.
  6. ^ "Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные" [Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry] (PDF) (in Russian). pp. 140–144. Retrieved 2015-07-25.
  7. ^ "Products". NIIMash. Retrieved 2015-07-30.
  8. ^ "RDMT-400". Encyclopedia Astronautica. Retrieved 2015-07-30.
  9. ^ "NII Mash". Encyclopedia Astronautica. Archived from the original on September 18, 2010. Retrieved 2015-07-30.
  10. ^ "RDMT-200". Encyclopedia Astronautica. Archived from the original on May 6, 2002. Retrieved 2015-07-30.
  11. ^ "RDMT-400A". Encyclopedia Astronautica. Archived from the original on May 6, 2002. Retrieved 2015-07-30.
  12. ^ "RDMT-400X". Encyclopedia Astronautica. Retrieved 2023-01-19.

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