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RD-0124


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RD-0124
Credit: KBKhA Kosberg LOx/Kerosene rocket engine. In development. Engine to succeed RD-0110 in second stage of Soyuz. Used staged combustion; chamber pressure increased from 70 to 160 bar, specific impulse from 326 to 359 seconds. First flight 2001. Proposed for small launcher Kvant-1 by RKK Energia for stage 1 steering engine. Also proposed by RKK Energia in initial studies in 1993 for Angara upper stage.

AKA: 14D23;14D451M. Status: In development. Date: 1993-. Number: 19 . Thrust: 294.30 kN (66,161 lbf). Unfuelled mass: 480 kg (1,050 lb). Specific impulse: 359 s. Specific impulse sea level: 331 s. Burn time: 300 s. Height: 1.58 m (5.17 ft). Diameter: 2.40 m (7.80 ft).

Payload increase by 950 kg from current 6900 / 7200 kg from Plesetsk / Baikonur.

Chambers: 4. Engine: 480 kg (1,050 lb). Chamber Pressure: 162.00 bar. Propellant Formulation: Lox/RG-1. Thrust to Weight Ratio: 62.5. Oxidizer to Fuel Ratio: 2.6.

Country: Russia. Launch Vehicles: Soyuz M, Soyuz-ST-B. Propellants: Lox/Kerosene. Stages: Angara A-2, Soyuz ST-2. Agency: Kosberg bureau. Bibliography: 225, 226, 312, 7469. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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