RDMT-8 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.

Engine: 0.0250 kg (0.0550 lb). Chamber Pressure: 30.00 bar. Thrust to Weight Ratio: 32.79.

Related