Encyclopedia Astronautica
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.

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

Application: Soyuz TM, Progress M.

Characteristics

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.

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

More... - Chronology...


Associated Countries
Associated Spacecraft
  • Soyuz TM Russian manned spacecraft. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34). More...
  • 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...
  • 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...
  • Soyuz TMA PAO 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. More...

See also
Associated Manufacturers and Agencies
Associated Propellants
  • 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...

Bibliography
  • Haeseler, Dietrich, Visit to the museum of Chemical Machining Design Bureau, Kalinin 1994 via Dietrich Haeseler.
  • Haeseler, Dietrich, Datasheets from NII Mashinostroeniye, Nishnaya Salda, 1992 via Dietrich Haeseler.

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