This page no longer updated from 31 October 2001. Latest version can be found at RDMT-400A

Designer: NII Mash. Propellants: N2O4/UDMH Thrust(vac): 41 kgf. Thrust(vac): 0.40 kN. Isp: 290 sec. Mass Engine: 3 kg. Chambers: 1. Country: Russia. Status: Developed 1980's. References: 336 . Comments: Experimental low-thrust thruster. Niobium combustion chamber with coating.
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 .