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Engine Model: KTDU-417. 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.

Engine Model: KTDU-417-B. Manufacturer Name: KTDU-417-B. Government Designation: 11D417B. Designer: Isayev. Application: Luna 15-24 low thrust engine in system KTDU-417. Propellants: N2O4/UDMH. Thrust(vac): 3.430 kN (771 lbf). Throttled thrust(vac): 2.060 kN (463 lbf). Isp: 254 sec. Burn time: 30 sec. Chambers: 2. Chamber Pressure: 8.90 bar. Oxidizer to Fuel Ratio: 2.40. Country: Russia. Status: Out of Production.

Pressure-fed engine. Used as low thrust engine in system KTDU-417 for soft-landing. Could be throttled to 2.06 kN/2440 m/s.See entry KTDU-417.

KTDU-417 used on Spacecraft
Bibliography:

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
  • 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.
  • 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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