RDMT-400 X

Engine · Russia

Original archive entry. The text, images and links below are kept as they were written.

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

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

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