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RD-0126
RD-0126
RD-0126
Credit: KBKhA
Kosberg LOx/LH2 rocket engine. Space tugs or upper stage for Onega or Yastreb versions of Soyuz. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Design concept 1993. Hot-tests in 1998.

AKA: RO-97. Status: Design concept 1993-. Date: 1993-. Thrust: 39.20 kN (8,813 lbf). Unfuelled mass: 320 kg (700 lb). Specific impulse: 476 s. Height: 2.60 m (8.50 ft).

Engine: 320 kg (700 lb). Chamber Pressure: 71.50 bar. Thrust to Weight Ratio: 12.49. Oxidizer to Fuel Ratio: 6.



Subtopics

RD-0126E Kosberg LOx/LH2 rocket engine. Upper stages. Design concept 1998-. Concept for a cryogenic engine for upper stages. Single annular chamber with straight expansion nozzle, common turbopump.

Country: Russia. Launch Vehicles: Onega. Propellants: Lox/LH2. Agency: Kosberg bureau. Bibliography: 21, 342, 4484.

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