Research and Development Institute of Mechanical Engineering

Short description: Subsidiary of Roscosmos

NIIMash

Native name

| ФГУП «Научно-исследовательский институт машиностроения»

Romanized name

| FSUE “Research and Development Institute of Mechanical Engineering”
Formerly| OKB-2
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.

## Contents

* 1 Products
* 1.1 Current propulsion products
* 1.2 Former Propulsion Products
* 2 See also
* 3 References
* 4 External links

## 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

* NII-1 -- The research institute where NIIMash started.
* Russian Federal Space Agency -- The corporate parent of KB KhIMMASH.

## References

1. ↑ "О мерах по созданию Государственной корпорации по космической деятельности "Роскосмос"". Официальный интернет-портал правовой информации. http://pravo.gov.ru/proxy/ips/?docbody=&nd=102397340&rdk=&backlink=1. Retrieved 15 April 2017.
2. ↑ "История" (in Russian). Keldysh Research Center. http://kerc.msk.ru/predpijatie/история. Retrieved 2015-07-30.
3. ↑ "История" (in Russian). NIIMash. http://niimashspace.ru/index.php/2010-07-16-10-53-23/hiistory. Retrieved 2015-07-30.
4. ↑ "Руководители" (in Russian). NIIMash. http://niimashspace.ru/index.php/2010-07-16-10-53-23/management3. Retrieved 2015-07-30.
5. ↑ "Находящиеся в ведении Роскосмоса" (in Russian). Roscosmos. http://www.federalspace.ru/1446/. Retrieved 2015-07-30.
6. ↑ "Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные" (in Russian) (PDF). pp. 140–144. https://www.scribd.com/doc/46957813/Aviadvigatel. Retrieved 2015-07-25.
7. ↑ "Products". NIIMash. http://niimashspace.ru/eng/index.php/production/rocket-technology. Retrieved 2015-07-30.
8. ↑ "RDMT-400". Encyclopedia Astronautica. http://www.astronautix.com/r/rdmt-400.html. Retrieved 2015-07-30.
9. ↑ "NII Mash". Encyclopedia Astronautica. http://www.astronautix.com/mfrs/niimash.htm. Retrieved 2015-07-30.
10. ↑ "RDMT-200". Encyclopedia Astronautica. http://www.astronautix.com/engines/rdmt200.htm. Retrieved 2015-07-30.
11. ↑ "RDMT-400A". Encyclopedia Astronautica. http://www.astronautix.com/engines/rdmt400a.htm. Retrieved 2015-07-30.
12. ↑ "RDMT-400X". Encyclopedia Astronautica. http://www.astronautix.com/r/rdmt-400x.html. Retrieved 2023-01-19.

## External links

* NIIMash Official Page

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