Russian manned spacecraft module. Operational. First launch 2002.10.30. Further improvement of Soyuz T PAO service module with pressure-fed main engines and unitary RCS/main engine propellant feed system. Equipment-engine section.
The new KTDU-80 propulsion system, developed from a NII Mash experimental thruster, included four spherical tanks with a total of 880 kg propellant. The variable thrust engine could achieve three different thrust levels through adjustment of four valves: 6000 N, 0.7 N, 0.3 N. Specific impulse varied from 326 - 286 sec according to setting.
RCS Coarse No x Thrust: 16 X 98 N. RCS Fine No x Thrust: 8 X 98 N. RCS Coarse Backup No x Thrust: No separate backup translation engines.. Electric System: 0.60 average kW.
AKA: Priborno-agregatniy otsek.
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Gross mass: 2,900 kg (6,300 lb).
Unfuelled mass: 2,020 kg (4,450 lb).
Height: 2.26 m (7.41 ft).
Diameter: 2.15 m (7.05 ft).
Thrust: 6.20 kN (1,393 lbf).
Specific impulse: 302 s.
Soyuz TMA Russian three-crew manned spacecraft. Operational, first launch 2002.10.30. Designed for use as a lifeboat for the International Space Station. After the retirement of the US shuttle in 2011, Soyuz TMA was the only conveying crews to the ISS. Except for the Chinese Shenzhou, it became mankind's sole means of access to space. More...
KTDU-80 Isayev N2O4/UDMH rocket engine. 6.190 kN. Soyuz TM, Progress M. In Production. Isp=326s. 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. More...
N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
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