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KTDU-417
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Manufacturer Name: KTDU-417. Government Designation: 11D417. Other Designations: KRD-417. Designer: Isayev. Application: Luna 15-24 descent stage. Propellants: Nitric acid/UDMH. Thrust(vac): 18.920 kN (4,253 lbf). Throttled thrust(vac): 7.350 kN (1,652 lbf). Isp: 314 sec. Burn time: 650 sec. Mass Engine: 81 kg (178 lb). Diameter: 0.73 m (2.39 ft). Length: 0.79 m (2.59 ft). Chambers: 1 + 2. Chamber Pressure: 83.00 bar. Oxidizer to Fuel Ratio: 1.80. Thrust to Weight Ratio: 23.93. Country: Russia. Status: Out of Production. Comprises turbopump-fed high-thrust engine with data given in this entry, plus low-thrust engine, see entry KTDU-417-B. Eleven ignitions for lunar orbit insertion and orbit corrections. Two different oxidizers named.
KTDU-417 used on Spacecraft
Bibliography and Further Reading - 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...
- Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
- Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
- Glushko, V P (ed), Kosmonavtika Entsiklopedi, Moscow 1985 via Dietrich Haeseler.
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