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KTDU-425A
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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-425A used on Spacecraft
Bibliography and Further Reading - Glushko, V P (ed), Kosmonavtika Entsiklopedi, Moscow 1985 via Dietrich Haeseler.
- Kudryavtsev, V M, et.al., Osnovy Teorii i Rascheta, Moscow, Vysshaya Shkola, 1993 via Dietrich Haeseler. ISBN: 5060025624. Russian-language textbook on rocket theory; contains some information on Russian rocket engines. More at amazon.com...
- Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
- Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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