RDMT-400 X (original) (raw)

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RDMT-400 X

Part of RDMT engine series

NII Mash N2O4/UDMH rocket engine. Developed 1980's. Experimental low-thrust thruster. Carbon combustion chamber. Mass may be chamber only.

Status: Developed 1980's. Thrust: 400 N (80 lbf). Unfuelled mass: 0.13 kg (0.28 lb). Specific impulse: 296 s.

Engine: 0.13 kg (0.28 lb). Chamber Pressure: 30.00 bar. Thrust to Weight Ratio: 328.

Family: Storable liquid. Country: Russia. Propellants: N2O4/UDMH. Agency: NII Mash. Bibliography: 336.

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