|
RDMT-0.4 X
|
|
Designer: NII Mash. Propellants: N2O4/UDMH. Thrust(vac): 0.40 N (0.08 lbf). Isp: 290 sec. Mass Engine: 0.10 kg (0.22 lb). Chambers: 1. Chamber Pressure: 41.00 bar. Thrust to Weight Ratio: 0.40. Country: Russia. Status: In Production. Experimental low-thrust thruster. Chamber from niobium alloy. Chamber pressure 41 / 17 bar. Specific impulse 313 / 302,3 sec.
Bibliography and Further Reading - Haeseler, Dietrich, Datasheets from NII Mashinostroeniye, Nishnaya Salda,
1992 via Dietrich Haeseler.
|
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2007 except where otherwise noted.
|
|
|
|