This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Designer: Isayev. Propellants: Hydrazine Thrust(vac): 3 kgf. Thrust(vac): 0.03 kN. Isp: 235 sec. Burn time: 25,000 sec. Mass Engine: 1 kg. Chambers: 1. Chamber Pressure: 4.50 bar. Area Ratio: 55.00. Country: Russia. Status: In Production. References: 350 . Comments: Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions.
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 .