RD-0126A
RD-0126E
Credit - KBKhA
Manufacturer Name: RD-0126A. Other Designations: RO-97A. Designer: Kosberg. Developed in: 1996-. Application: Upper stages. Propellants: Lox/LH2. Thrust(vac): 98.000 kN (22,031 lbf). Isp: 476 sec. Mass Engine: 340 kg (740 lb). Length: 2.73 m (8.95 ft). Chambers: 1. Chamber Pressure: 118.00 bar. Oxidizer to Fuel Ratio: 6.00. Thrust to Weight Ratio: 29.41. Country: Russia. Status: Design concept 1996-.

Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.

Bibliography and Further Reading
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
 
 
 
 
 
 
 
 
 
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