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S5.92
Isayev N2O4/UDMH rocket engine. Phobos propulsion module, later adapted as Fregat upper stage. In production. Gas generator cycle. Nominal and low-thrust thrust levels.

Status: In production. Date: 1966-1987. Thrust: 19.60 kN (4,406 lbf). Unfuelled mass: 75 kg (165 lb). Specific impulse: 327 s. Burn time: 2,000 s. Height: 1.03 m (3.37 ft). Diameter: 0.84 m (2.75 ft).

Low thrust version with 1400 kgf, chamber diameter of 0.68 m, chamber pressure of 67 bar, specific impulse 316 seconds. Chamber pressure 97 / 67. Specific impulse 327 / 316 sec.

Throttled thrust(vac): 13.700 kN (3,080 lbf). Engine: 75 kg (165 lb). Chamber Pressure: 97.00 bar. Area Ratio: 153.8. Thrust to Weight Ratio: 26.66. Oxidizer to Fuel Ratio: 2.



Family: Storable liquid. Country: Russia. Launch Vehicles: Soyuz 11A511U / Fregat, Soyuz ST / Fregat ST. Propellants: N2O4/UDMH. Stages: Fregat. Agency: Isayev bureau. Bibliography: 293.

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