title: Research and Development Institute of Mechanical Engineering
text: # Research and Development Institute of Mechanical Engineering
  
  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:
  
  * 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) $N_2O_4/UDMH$ thruster. Used on the KTDU-80.
     * 11D428AF-16: $N_2O_4/UDMH$ thrusters used by the Fobos-Grunt space mission.
     * 11D457: 53.9 N (12.1 lbf) $N_2O_4/UDMH$ thrusters used by the Resurs-DK No.1.
     * 11D457F: 54 N (12 lbf) $N_2O_4/UDMH$ thrusters used by the Fobos-Grunt space mission.
     * 11D458 (a.k.a. RDMT-400): 392 N (88 lbf) $N_2O_4/UDMH$ thrusters used by the Functional Cargo Block based modules and the Briz upper stage.
     * 11D458F (a.k.a. RDMT-400F): 382 N (86 lbf) $N_2O_4/UDMH$ thrusters used by the Fobos-Grunt space mission.
     * 11D458M (a.k.a. RDMT-400M): 392.4 N (88.2 lbf) $N_2O_4/UDMH$ 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: $N_2O_4/UDMH$ thrusters used by the Briz-M upper stage.
     * 17D58EF: $N_2O_4/UDMH$ 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.
  
  * RDMT-0.4X: $N_2O_4/UDMH$ rocket engine.
  * RDMT-0.8: Nitrogen and helium cold gas thruster.
  * RDMT-12: $N_2O_4/UDMH$ rocket engine.
  * RDMT-50: $N_2O_4/UDMH$ rocket engine.
  * RDMT-100: $N_2O_4/UDMH$ rocket engine.
  * RDMT-135 (a.k.a. 11D428A): 135 N (30 lbf) $N_2O_4/UDMH$ rocket engine. Used on the Soyuz 7K-S, KTDU-426 and initial KTDU-80.
  * RDMT-200: 200 N (45 lbf) $N_2O_4/UDMH$ thruster used on the Almaz space stations.
  * RDMT-400A: Experimental version of the RDMT-200 with Niobium combustion chamber.
  * RDMT-400X: Experimental version of the RDMT-200 with Carbon combustion chamber.
  