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KTDU-80
Isayev N2O4/UDMH rocket engine. Soyuz TM, Progress M. In Production. Propulsion system included 4 spherical tanks for a total of 880 kg propellant. Developed from NII Mash experimental thruster. 3 thrust levels by 4 valves.

AKA: S5.80. Status: In Production. Date: -1977. Thrust: 6.19 kN (1,392 lbf). Unfuelled mass: 310 kg (680 lb). Specific impulse: 302 s. Burn time: 890 s. Height: 1.20 m (3.95 ft). Diameter: 2.10 m (6.80 ft).

Three thrust levels by 4 valves: 6000 N, 0.7 N, 0.3 N. Specific impulse 326 - 286 sec.

Engine: 310 kg (680 lb). Chamber Pressure: 8.80 bar. Area Ratio: 153.8. Thrust to Weight Ratio: 2.03. Oxidizer to Fuel Ratio: 1.85.



Family: Storable liquid. Country: Russia. Spacecraft: Soyuz TM, Progress M, Soyuz TMA, Soyuz TMA PAO. Propellants: N2O4/UDMH. Agency: Isayev bureau. Bibliography: 314, 336, 7439.

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