NK-43

Manufacturer Name: NK-43. Government Designation: 11D112. Designer: Kuznetsov. Developed in: 1969-74. Application: N-1F stage 2 (block B). Propellants: Lox/Kerosene. Thrust(vac): 1,755.000 kN (394,539 lbf). Thrust(sl): 1,247.800 kN (280,517 lbf). Isp: 346 sec. Isp (sea level): 246 sec. Burn time: 600 sec. Mass Engine: 1,396 kg (3,077 lb). Diameter: 2.50 m (8.20 ft). Chambers: 1. Chamber Pressure: 145.70 bar. Area Ratio: 70.00. Oxidizer to Fuel Ratio: 2.80. Thrust to Weight Ratio: 128.22. Country: Russia. Status: Design 1975.

Version of NK-33 with higher expansion ratio nozzle for operation at altitude. After initial failures of the N-1 the company developed modified versions of engines for all four stages, which had multiple ignition capability and increased operational lifetime. Never flown, they were mothballed and selected by Kistler 20 years later for the second stage of their commercial launch vehicle.

NK-43 used on Rocket Stages

Used on stage: Kistler Stage 2. on launch vehicle: Kistler K-1.

Used on stage: N1F Block B. on launch vehicle: N1F.

Used on stage: N1F Block B. on launch vehicle: N1F Sr.

Used on stage: N1F Block B. on launch vehicle: N1F-L3M.

Used on stage: UR-500MK-2. on launch vehicle: UR-500MK.

Bibliography and Further Reading

Data sheets NPO Trud 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 - 2007 except where otherwise noted.

Encyclopedia Astronautica
topic index
0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z