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Engine Model: RD-0132. Manufacturer Name: RD-0132. Designer: Kosberg. Developed in: 1996-. Application: upper stage. Propellants: Lox/LH2. Thrust(vac): 98.000 kN (22,031 lbf). Isp: 469 sec. Mass Engine: 370 kg (810 lb). Length: 1.38 m (4.52 ft). Chambers: 4. Chamber Pressure: 98.00 bar. Oxidizer to Fuel Ratio: 5.90. Thrust to Weight Ratio: 27.02. Country: Russia. Status: Design concept 1996-.

Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump.

Engine Model: RD-0132M. Manufacturer Name: RD-0132M. Designer: Kosberg. Developed in: 1998-. Application: Vozdushnyy Start stage 2. Propellants: Lox/LNG. Thrust(vac): 98.000 kN (22,031 lbf). Chambers: 4. Country: Russia. Status: Design concept 1998-.

Proposed variant of RD-0132, replacing hydrogen by liquid natural gas. Initially selected for stage 2 of Vozdushnyy Start project by Kompomash.

Bibliography:

  • Polovnikov S P; Karpov, A S, Vestnik Aviatsii i Kosmonavtiki, "Projekt 'Vozdushnyy Start'", Moscow, 1-2/98 via Dietrich Haeseler.
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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