Astronomy:NK-15
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Short description: Soviet rocket engine design
| Country of origin | Soviet Union |
|---|---|
| Date | 1960s |
| Designer | Kuznetsov Design Bureau |
| Application | 1st/2nd-stage engine |
| Successor | NK-33 |
| Liquid-fuel engine | |
| Propellant | LOX / kerosene |
| Cycle | Staged combustion |
| Pumps | Turbopump |
| Performance | |
| Thrust (vac.) | 1,753 kN (394,000 lbf) |
| Thrust (SL) | 1,505 kN (338,000 lbf) |
| Throttle range | 50–105% |
| Thrust-to-weight ratio | 137 |
| Chamber pressure | 14.50 MPa (2,103 psi) |
| Isp (vac.) | 331 seconds (3.25 km/s) |
| Isp (SL) | 297 seconds (2.91 km/s) |
| Dimensions | |
| Length | 3.7 m (12 ft) |
| Diameter | 2 m (6 ft 7 in) |
| Dry weight | 1,247 kg (2,749 lb) |
The NK-15 (GRAU index 11D51) was a rocket engine designed and built in the late 1960s by the Kuznetsov Design Bureau. The NK designation was derived from the initials of chief designer Nikolay Kuznetsov. The NK-15 was among the most powerful LOX/kerosene rocket engines when it was built, with a high specific impulse and low structural mass. It was intended for the ill-fated Soviet N-1 Moon rocket.
History
The engine equipped the N1 rocket - the first two launch attempts failed due to this engine.[1] Its successor the NK-33 was to be used on the N1F, a new version of the N1, but the program was cancelled.
Versions
- NK-15V (GRAU index 11D52): Modified NK-15 optimized for vacuum operation, used on the N1 second stage.
See also
References
- ↑ Chertok, Boris E. (2011). Rockets and people.. Washington, DC: NASA. p. 208,230. ISBN 978-0-16-089559-3. http://www.nasa.gov/pdf/621513main_RocketsPeopleVolume4-ebook.pdf. Retrieved 9 August 2021.
External links
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