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Research and Development Institute of Mechanical Engineering

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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.

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]

Products

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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

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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

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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

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References

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  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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