RD-191

Manufacturer Name: RD-191. Other Designations: RD-191M. Designer: Glushko. Developed in: 1996-. Application: Angara stage 1. Propellants: Lox/Kerosene. Thrust(vac): 2,079.000 kN (467,377 lbf). Isp: 337 sec. Isp (sea level): 311 sec. Burn time: 150 sec. Mass Engine: 3,230 kg (7,120 lb). Diameter: 2.00 m (6.50 ft). Length: 4.05 m (13.28 ft). Chambers: 1. Chamber Pressure: 257.00 bar. Area Ratio: 37.00. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 64.56. Country: Russia. Status: In development. First Flight: 2003. Flown: 132.

Proposed for stage 1 of the Angara family of ELVs. This is single chamber motor would be 1/4 of the RD-170/171 so would be cheap and fast to develop. It has only reached the draft project stage. Gimbaling +/- 8 degree in two planes.

RD-191 used on Rocket Stages

Used on stage: Angara UM. on launch vehicle: Angara 1.1.

Used on stage: Angara UM. on launch vehicle: Angara 1.2.

Used on stage: Angara UM. on launch vehicle: Angara 3A.

Used on stage: Angara UM. on launch vehicle: Angara 3A.

Used on stage: Angara UM. on launch vehicle: Angara 5A.

Used on stage: Angara UM. on launch vehicle: Angara 5A.

Used on stage: Angara UM. on launch vehicle: KSLV-I.

Used on stage: Angara UM. on launch vehicle: KSLV-II.

Used on stage: Angara UM. on launch vehicle: KSLV-III.

Bibliography and Further Reading

Salmon, Andrew, The Story Of Russian Rocket Engines - Energomash Museum, Commentary by the guide at the Energomash rocket engine museum in Khimki, April 1998 at YSC98..

Novosti kosmonavtiki, Issues. 21-22, 1998 via Dietrich Haeseler.

Klepikov, Katorgin, Chvanov, IAF-Congress Turin, 1997, "The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant ...", IAF-97-S.1.03 via Dietrich Haeseler.

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