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RD-0242
RD-0242
RD-0242
Credit: KBKhA
Kosberg N2O4/UDMH rocket engine. sea-based missile booster stage developed 1977-83 (Burlak). First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. Single ignition, 297 development tests. 50 engines for sale.

Status: Developed 1977-83. Date: 1977-83. Thrust: 123.60 kN (27,786 lbf). Unfuelled mass: 120 kg (260 lb). Specific impulse: 303 s. Burn time: 60 s. Height: 0.88 m (2.89 ft). Diameter: 0.27 m (0.89 ft).

Max. duration 420 s.

Engine: 120 kg (260 lb). Chamber Pressure: 196.20 bar. Thrust to Weight Ratio: 105.03.



Subtopics

RD-0242-HC Kosberg LOx/Kerosene rocket engine. Developed 1998-. Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

RD-0242M Kosberg N2O4/MMH rocket engine. Design concept 1998-. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH. Reusable for 6 ignitions total. Throttling to 80%.

RD-0242M1 Kosberg N2O4/MMH rocket engine. Design concept 1998-. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market). Reusable for 6 ignitions total. Throttling to 80%.

Family: Storable liquid. Country: Russia. Propellants: N2O4/UDMH. Agency: Kosberg bureau. Bibliography: 312, 342, 95.

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