Engine Model: S5.92. Other Designations: S5.92. Designer: Isayev. Developed in: 1966-1987. Application: Phobos propulsion module. Propellants: N2O4/UDMH. Thrust(vac): 19.600 kN (4,406 lbf). Throttled thrust(vac): 13.700 kN (3,080 lbf). Isp: 327 sec. Burn time: 2,000 sec. Mass Engine: 75 kg (165 lb). Diameter: 0.84 m (2.75 ft). Length: 1.03 m (3.37 ft). Chambers: 1. Chamber Pressure: 97.00 bar. Area Ratio: 153.80. Oxidizer to Fuel Ratio: 2.00. Thrust to Weight Ratio: 26.66. Country: Russia. Status: In production. Gas generator cycle. Nominal and low-thrust thrust levels. 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.
S5.92 used on Rocket Stages
Bibliography:- Haeseler, Dietrich, "Personal communication", 1998 December..