Russian manned spacecraft module. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34). 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.
More... - Chronology...
Gross mass: 2,950 kg (6,500 lb).
Unfuelled mass: 2,070 kg (4,560 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 TM Russian manned spacecraft. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34). 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...
Home - Browse - Contact
© / Conditions for Use