Russian manned spacecraft module. Operational, first launch 1989.08.23 (Progress M-1). 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: 2,950 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.
Progress M Russian logistics spacecraft. Operational, first launch 1989.08.23 (Progress M-1). Progress M was an upgraded version of the original Progress. New service module and rendezvous and docking systems were adopted from Soyuz T. More...
Progress M-SO Russian docking and airlock module for the International Space Station. First launch 2001.09.14. Delivered to the station by the Progress service module, which was jettisoned after docking. 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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