NK-9
From Wikipedia, the free encyclopedia
| Country of origin | Soviet Union |
|---|---|
| Date | 1959 |
| Designer | Kuznetsov Design Bureau |
| Application | 1st/2nd-stage engine |
| Successor | NK-15 |
| Liquid-fuel engine | |
| Propellant | LOX / RG-1 |
| Cycle | Oxidiser-rich Staged combustion |
| Pumps | Turbopump |
| Performance | |
| Thrust, vacuum | 441 kN (99,000 lbf) |
| Thrust, sea-level | 360 kN (81,000 lbf) |
| Chamber pressure | 10.9 MPa (1,580 psi) |
| Specific impulse, vacuum | 327 s (3.21 km/s) |
| Specific impulse, sea-level | 280 s (2.7 km/s) |
| References | |
| References | [1] [2] |
The NK-9 was a rocket engine designed and built in 1959 by the Kuznetsov Design Bureau.[3] The NK designation was derived from the initials of chief designer Nikolay Kuznetsov. It was intended for the R-9 Desna, but lost this bid to the RD-111. It was the world's first oxygen-kerosene engine in the 1 MN+ thrust class to use a closed-cycle design with staged combustion of generator gas in the combustion chamber. For the second stage of this missile, the NK-9V engine was developed, with testing starting in September 1962. In the early 1960s, the NK-19 was created, for use on an upgraded R-9 first stage, along with the NK-21. Both were cancelled. It was later developed into the NK-31, which was intended to be used on variants of the N-1, which were also cancelled.
