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{{Infobox rocket engine |
{{Infobox rocket engine |
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|name = RD-8 (РД-8) |
|name = RD-8 (РД-8) |
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|image = |
|image = |
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|image_size = 225 |
|image_size = 225 |
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|caption = Photo of rocket engine ''RD-8''. |
|caption = Photo of rocket engine ''RD-8''. |
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Revision as of 02:24, 11 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
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| Solid fuel |
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