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RD-0126
Credit - KBKhA
Engine Model: RD-0126. Manufacturer Name: RD-0126. Other Designations: RO-97. Designer: Kosberg. Developed in: 1993-. Application: Upper stages, such as a space tug or injection stage for the Onega upgraded version of the Soyuz launch vehicle. Propellants: Lox/LH2. Thrust(vac): 39.200 kN (8,813 lbf). Isp: 476 sec. Mass Engine: 320 kg (700 lb). Length: 2.60 m (8.50 ft). Chambers: 1. Chamber Pressure: 71.50 bar. Oxidizer to Fuel Ratio: 6.00. Thrust to Weight Ratio: 12.49. Country: Russia. Status: Design concept 1993-.

Concept for a cryogenic engine "Yastreb" for upper stages. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Hot-tests began 1998.

Engine Model: RD-0126A. 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.

Engine Model: RD-0126E. Manufacturer Name: RD-0126E. Other Designations: RO-97E. Designer: Kosberg. Developed in: 1998-. Application: Upper stages. Propellants: Lox/LH2. Thrust(vac): 39.200 kN (8,813 lbf). Isp: 472 sec. Mass Engine: 234 kg (515 lb). Chambers: 1. Chamber Pressure: 70.00 bar. Country: Russia. Status: Design concept 1998-.

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

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