Encyclopedia Astronautica

Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. N-1 stage 2 / N-1 stage 3 / R-9 Stage 2. Developed for 2nd stage of the R-9 ICBM (alternative to RD-111 engine by OKB-456). NK-9 with increased expansion ratio. Isp=340s. First flight 1965.

Application: N-1 stage 2 (block V) / N-1 stage 3 (block G) / R-9 Stage 2.

Thrust (sl): 360.390 kN (81,019 lbf). Thrust (sl): 36,750 kgf. Propellant Formulation: Lox/RG-1.

AKA: NK-19; NK-21; NK-9V; 11D53.
Thrust: 441.30 kN (99,208 lbf).
Specific impulse: 340 s.
Specific impulse sea level: 312 s.
First Launch: 1959-65.

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • R-9 Russian intercontinental ballistic missile. ICBM developed by Korolev OKB using liquid oxygen/kerosene propellants. The Soviet military favoured storable propellants as advocated by Glushko and implemented by Yangel and Chelomei. Development of the R-9 was protracted and it was deployed in only very limited numbers between 1964 and 1974. More...

Associated Manufacturers and Agencies
  • Kuznetsov Russian manufacturer of rocket engines. Kuznetsov Design Bureau, Russia. More...

Associated Propellants
  • Lox/Kerosene Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...

Associated Stages
  • 8K513 Blok B Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,000/2,100 kg. Thrust 441.00 kN. Vacuum specific impulse 340 seconds. Masses estimated based on total vehicle mass of 117 tonnes. Developed into Molniya/Soyuz second stage. More...

Home - Browse - Contact
© / Conditions for Use