Engine Model: RDMT-400 X. Designer: NII Mash. Propellants: N2O4/UDMH. Thrust(vac): 400 N (80 lbf). Isp: 296 sec. Mass Engine: 0.13 kg (0.28 lb). Chambers: 1. Chamber Pressure: 30.00 bar. Thrust to Weight Ratio: 328.00. Country: Russia. Status: Developed 1980's. Experimental low-thrust thruster. Carbon combustion chamber. Mass may be chamber only.