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Engine Model: KTDU-425. Manufacturer Name: KTDU-425. Government Designation: 11D425. Designer: Isayev. Developed in: 1970-73. Application: Mars 2 and 3 maneuver engine. Propellants: N2O4/UDMH. Thrust(vac): 18.850 kN (4,238 lbf). Throttled thrust(vac): 7.050 kN (1,585 lbf). Isp: 312 sec. Burn time: 560 sec. Chambers: 1. Chamber Pressure: 133.20 bar. Oxidizer to Fuel Ratio: 1.90. Country: Russia. Status: Out of Production.

Pump-fed engine. Could be throttled to 7.05 kN / 9.5 MPa / 2850 m/s. . Chamber pressure 133,2 - 95 bar.

Engine Model: KTDU-425A. Manufacturer Name: KTDU-425A. Government Designation: 11D425A. Designer: Isayev. Developed in: 1972-75. Application: Mars 4-7, Venera 9-16, Vega 1-2, and Phobos 1-2 maneuvering engine. Propellants: N2O4/UDMH. Thrust(vac): 18.890 kN (4,247 lbf). Throttled thrust(vac): 9.856 kN (2,216 lbf). Isp: 315 sec. Burn time: 560 sec. Mass Engine: 70 kg (154 lb). Diameter: 0.70 m (2.29 ft). Length: 0.71 m (2.32 ft). Chambers: 1. Chamber Pressure: 149.00 bar. Oxidizer to Fuel Ratio: 1.90. Thrust to Weight Ratio: 27.54. Country: Russia. Status: Out of Production. First Flight: 1973.

Spacecraft maneuvering engine. Could be throttled to 9.86/9.5/2870. Chamber pressure 149 - 95 bar.

KTDU-425 used on Spacecraft
Bibliography:

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
  • Kudryavtsev, V M, et.al., Osnovy Teorii i Rascheta, Moscow, Vysshaya Shkola, 1993 via Dietrich Haeseler.
  • Glushko, V P (ed), Kosmonavtika Entsiklopedi, Moscow 1985 via Dietrich Haeseler.
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
  • Siddiqi, Asif A, Soviet Space Web Page, 1999 via Dietrich Haeseler. Web Address when accessed: http://home.earthlink.net/~cliched/main_space.html.
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