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RDMT-400 X


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A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z RDMT-400 X Part of RDMT engine series NII Mash N2O4/UDMH rocket engine. Developed 1980's. Experimental low-thrust thruster. Carbon combustion chamber. Mass may be chamber only.

Status: Developed 1980's. Thrust: 400 N (80 lbf). Unfuelled mass: 0.13 kg (0.28 lb). Specific impulse: 296 s.

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

Family: Storable liquid. Country: Russia. Propellants: N2O4/UDMH. Agency: NII Mash. Bibliography: 336. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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