Engine Model: 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.