This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com

astronautix.com DOK-50


Designer: Isayev. Propellants: Hydrazine Thrust(vac): 5 kgf. Thrust(vac): 0.05 kN. Isp: 229 sec. Burn time: 1,500 sec. Mass Engine: 1 kg. Chambers: 1. Chamber Pressure: 8.00 bar. Area Ratio: 42.00. Country: Russia. Status: In Production. References: 350 . Comments: Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 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 .