There are 2 images added on 11 September 2008
Initial Operational Capability (IOC): September 2008
Total Production: ?
Origin: Russia
Corporations: NPO Energomash
Parent System: RD-191
Initial Operational Capability (IOC): September 2008
Total Production: ?
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Description: The RD-191 is a liquid fuel rocket engine developed by Energomash between 1999 and 2008 for the Angara family of space launch vehicles and Baikal reusable booster. Its design is based on the RD-170/171 engines developed to power Energia and Zenit rockets. The new engine burns a mixture of liquid oxygen (LOx) and kerosene with a limited amount of hydrogen in a single combustion chamber. The RD-191 design has been arranged to achieve simultaneous and stable combustion of all the three components. The first test burn of RD-191 engine was held in July 2001. Through August 2006, the RD-191 had logged more than 35 engine tests with more than 4,500 seconds of burning time. The engine development was completed in early September 2008. The next phase of the RD-191 program will see the engine tested with the Angara rocket.

The RD-191 rocket engine is a highly versatile design to power the first and second stages of Angara space launch vehicle family. It will develop between 196 and 213 tons of thrust for 310.7 to 337 seconds. Besides, the engine will be powering the Baikal reusable booster which is slated for use with heavyweight versions of the Angara complex. The new engine has been developed as a reuseable one. When existing liquid-fueled rocket engines are used, the burnt-out stages fall down to Earth, posing a serious threat both to the ecology of the impact areas and people's lives. The environmentally friendly reusable engine avoids this scenario. Besides, the RD-191's recoverability and repeated use is aimed at cutting payload deployment costs several times over.

RD-191 Applications

Propulsion Systems Baikal RD-181 Space Systems Angara 1.1 Angara 1.2PP Angara A3 Angara A5 Angara A5V Angara A7 Delta Epsilon Gamma

RD-191 Specifications

Combustion Chambers: 1
Diameter: 1,450 millimeter (57 inch)
Length: 4,000 millimeter (157 inch)
Combustion Chamber Pressure: 263 kg/cm2 (3,747 psi)
Burn Time: 337 second (5.62 minute)
Dry Weight: 2,200 kilogram (4,850 pound)
Thrust: 213 ton (469,577 pound)
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)

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