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Used in Soyuz M-3. Two versions available in differing expansion ratios: 19.25/18.75. Dry Mass: 141/119 kg. Length: 2205/1700 mm. Maximum Diameter: 1020/780 mm. Engine Cycle: closed gas generator. Oxidizer: LOX. Fuel: Kerosene. Mixture Ratio: (O/F) 2:6. Feed Method: turbopump. Thrust: 19.9/19.6 kN vacuum. Isp: 365/360 sec vacuum. Chamber Pressure: 116.1 atm. Burn Time: 900 sec maximum. Developed 1988-on.

Manufacturer Name: RD-161. Propellants: Lox/Kerosene. Thrust(vac): 2,029 kgf. Thrust(vac): 19.90 kN. Isp: 365 sec. Burn time: 900 sec. Mass Engine: 119 kg. Diameter: 1.0 m. Length: 2.2 m. Chambers: 1. Chamber Pressure: 116.10 bar. Area Ratio: 19.25. Country: Russia. Status: Hardware. First Flight: 1999.


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Last update 25 April 1999.
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© Mark Wade, 1999 .