|
RD-161-1
|
|
Manufacturer Name: RD-161 (1). Designer: Glushko. Propellants: Lox/Kerosene. Thrust(vac): 19.600 kN (4,406 lbf). Isp: 360 sec. Burn time: 900 sec. Mass Engine: 119 kg (262 lb). Diameter: 0.78 m (2.55 ft). Length: 1.70 m (5.50 ft). Chambers: 1. Chamber Pressure: 117.70 bar. Area Ratio: 351.60. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 16.80. Country: Russia. Status: Development ended 2000. Proposed for use on Soyuz M-3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump.
RD-161-1 used on Rocket Stages
Bibliography and Further Reading - Haeseler, Dietrich, NPO Energomash exhibit at Moscow Airshow MAKS 93, Moscow, 1993 via Dietrich Haeseler.
|
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2007 except where otherwise noted.
|
|
|
|