This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Other Designations: S5.92. Designer: Isayev. Developed in: 1966-1987. Application: Phobos propulsion module. Used on stages: Fregat. Used on launch vehicles: Soyuz 11A511U / Fregat, Soyuz ST / Fregat. Used on spacecraft: Fobos 1F. Propellants: N2O4/UDMH Thrust(vac): 2,000 kgf. Thrust(vac): 19.60 kN. Isp: 327 sec. Burn time: 2,000 sec. Mass Engine: 75 kg. Diameter: 0.8 m. Length: 1.0 m. Chambers: 1. Chamber Pressure: 97.00 bar. Area Ratio: 153.80. Oxidizer to Fuel Ratio: 2.00. Country: Russia. Status: Out of Production. References: 293 . Comments: 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.
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .