Russian manned spacecraft module. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Improved PAO service module derived from Soyuz 7K-S with pressure-fed main engines and unitary RCS/main engine propellant feed system. Equipment-engine section.
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: 2,750 kg (6,060 lb).
Unfuelled mass: 2,050 kg (4,510 lb).
Height: 2.26 m (7.41 ft).
Diameter: 2.15 m (7.05 ft).
Thrust: 3.09 kN (694 lbf).
Specific impulse: 292 s.
Soyuz T Russian manned spacecraft. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Soyuz T had a long gestation, beginning as the Soyuz VI military orbital complex Soyuz in 1967. 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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