KRD-61 home
topic index
Engine Model: KRD-61. Manufacturer Name: KRD-61. Other Designations: S5.61. Designer: Isayev. Developed in: 1968-70. Application: Luna Ye-8. Propellants: N2O4/UDMH. Thrust(vac): 18.800 kN (4,226 lbf). Isp: 313 sec. Burn time: 53 sec. Mass Engine: 42 kg (92 lb). Diameter: 0.55 m (1.79 ft). Length: 0.71 m (2.34 ft). Chambers: 1. Chamber Pressure: 92.20 bar. Oxidizer to Fuel Ratio: 1.84. Thrust to Weight Ratio: 45.88. Country: Russia. Status: Out of Production. First Flight: 1969.

Spacecraft maneuvering engine for ascent stage of Luna moon sample return missions.

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.
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

© Mark Wade, 1997 - 2008 except where otherwise noted.