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RD-0126A
Part of RD-0131 Family
RD-0126E
RD-0126E
Credit: KBKhA
Kosberg LOx/LH2 rocket engine. Upper stages. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.

AKA: RO-97A. Status: Design concept 1996-. Date: 1996-. Thrust: 98.00 kN (22,031 lbf). Unfuelled mass: 340 kg (740 lb). Specific impulse: 476 s. Height: 2.73 m (8.95 ft).

Engine: 340 kg (740 lb). Chamber Pressure: 118.00 bar. Thrust to Weight Ratio: 29.41. Oxidizer to Fuel Ratio: 6.



Country: Russia. Propellants: Lox/LH2. Agency: Kosberg bureau.

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