RD-171  
Initial Operational Capability (IOC): 2006
Total Production: ?
Also Known As: RD-171M and RD-171MV
Origin: Russia
Corporations: NPO Energomash
Parent System: RD-170
Initial Operational Capability (IOC): 1988
Maiden Flight: 13 April 1985
Total Production: ?
Family Members: RD-170
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Description: The RD-171 is a derivative of the RD-170 liquid fuel rocket engine keeping the four combustion chambers used on the RD-170 engine. The RD-171M engine variant development was completed in 2006. The RD-171MV variant has been selected to power the first stage of the Soyuz-5 medium-weight space launch system. The RD-171MV burns a mixture of liquefied natural gas (LNG) and liquefied Oxygen (LOx).

RD-171 Applications


Space Systems Soyuz-5

RD-171 Specifications

Combustion Chambers: 4
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

RD-171 News

There are 3 news between
14 Jan 2016 and 22 Jul 2018
Sunday, July 22, 2018Russia Starts Development of Soyuz-5 Space Launch System
Wednesday, February 22, 2017Russia Developing Two Version of Federatsiya Spaceship and New Super Heavy Rocket
Thursday, January 14, 2016Russia Developing New Futuristic Methane-Powered Rocket Propulsion System

Operators & Related Equipment


OperatorsItems

Grand Total ?1
 
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