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RD-0204
Part of RD-0202 Family
Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Hardware. Diameter is per chamber. Staged combustion cycle. Variant of RD-0203 with additional pressure sensor. First flight 1964.

Status: Hardware. Date: 1961-64. Thrust: 559.00 kN (125,668 lbf). Gross mass: 1,961 kg (4,323 lb). Unfuelled mass: 1,524 kg (3,359 lb). Specific impulse: 311 s. Specific impulse sea level: 278 s. Burn time: 136 s. Height: 1.80 m (5.90 ft). Diameter: 0.89 m (2.91 ft).

Thrust (sl): 500.000 kN (112,400 lbf). Thrust (sl): 51,000 kgf. Engine: 381 kg (839 lb). Area Ratio: 29.8. Thrust to Weight Ratio: 149.5. Oxidizer to Fuel Ratio: 2.6.



Family: Storable liquid. Country: Russia. Propellants: N2O4/UDMH. Stages: UR-200-1. Agency: Kosberg bureau. Bibliography: 309, 7473.

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