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Engine Model: RDMT-8 X. Designer: NII Mash. Propellants: N2O4/UDMH. Thrust(vac): 8.00 N (1.70 lbf). Isp: 296 sec. Mass Engine: 0.0250 kg (0.0550 lb). Chambers: 1. Chamber Pressure: 30.00 bar. Thrust to Weight Ratio: 32.79. Country: Russia. Status: Developed 1980's.

Experimental low-thrust thruster.

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