RD-8: Difference between revisions
Content deleted Content added
m No longer unreferenced. using AWB |
m r2.7.2+) (Robot: Adding uk:РД-8 |
||
| Line 47: | Line 47: | ||
[[ja:RD-8]] |
[[ja:RD-8]] |
||
[[uk:РД-8]] |
|||
Revision as of 22:07, 8 June 2012
 | This article needs additional citations for verification. (December 2009) |
| Country of origin | USSR/Russia |
|---|---|
| Manufacturer | Yuzhnoye Design Bureau |
| Application | upper stage vernier |
| Status | Operational |
| Liquid-fuel engine | |
| Propellant | LOX / rocket grade kerosine |
| Cycle | staged combustion |
| Performance | |
| Thrust, vacuum | 78.5 kilonewtons (17,600 lbf)[1] |
| Chamber pressure | 7.8 megapascals (1,130 psi)[1] |
| Specific impulse, vacuum | 342 s |
| Dimensions | |
| Dry weight | 380 kilograms (840 lb) |
| Used in | |
| Zenit-2, Zenit-3SL upper stage | |
For the Dominican Republic national highway #8 see DR-8
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 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. |