NIIMash

Native name	ФГУП «Научно-исследовательский институт машиностроения»
Romanized name	FSUE “Research and Development Institute of Mechanical Engineering”
Formerly	OKB-2
Company type	Federal 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
Predecessor	NII-1 of Moscow
Founded	September 1, 1958 (1958-09-01) in Soviet Union
Founder	Mikhail G. Mironov
Headquarters	Builders 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	11D428A-16 17D58E 17D16
Parent	Roscosmos[1]
Website	Official 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]