RD-8: Difference between revisions
Content deleted Content added
removed Category:Rocket engines; added Category:Rocket engines of Russia using HotCat |
No edit summary |
||
| Line 6: | Line 6: | ||
|image_size = 225 |
|image_size = 225 |
||
|caption = Photo of rocket engine ''RD-8''. |
|caption = Photo of rocket engine ''RD-8''. |
||
|country_of_origin = [[USSR]]/[[ |
|country_of_origin = [[USSR]]/[[Ukraine]] |
||
|date = |
|date = |
||
|manufacturer = [[Yuzhnoye Design Bureau]] |
|manufacturer = [[Yuzhnoye Design Bureau]] |
||
Revision as of 18:15, 10 May 2015
 | This article needs additional citations for verification. (December 2009) |
| Country of origin | USSR/Ukraine |
|---|---|
| Manufacturer | Yuzhnoye Design Bureau |
| Application | Upper stage vernier |
| Status | Operational |
| Liquid-fuel engine | |
| Propellant | LOX / rocket grade kerosene |
| Performance | |
| Thrust, vacuum | 78.5 kilonewtons (17,600 lbf)[1] |
| Chamber pressure | 7.8 megapascals (1,130 psi)[1] |
| Specific impulse, vacuum | 342 seconds (3.35 km/s) |
| Dimensions | |
| Dry weight | 380 kilograms (840 lb) |
| Used in | |
| Zenit-2, Zenit-3SL upper stage | |
The RD-8 engine was developed by Yuzhnoye Design Bureau for the second stage of the Zenit rocket. It has four hinged chambers and a single turbopump unit. The fuel pair is LOX/kerosene. Vacuum thrust is 78.5 kN and its specific impulse in vacuum is 342 seconds (3.35 km/s).[2]
The engine was designed for long service life (up to 4000 seconds), high reliability, and is the first smaller upper stage engine to use the staged combustion cycle.[2]
References
| Liquid fuel |
|  | ||||||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Solid fuel |
| |||||||||||||||||
| ||||||||||||||||||
 | This rocketry article is a stub. You can help Wikipedia by expanding it. |