RD-8
<templatestyles src="Module:Hatnote/styles.css"></templatestyles>
Lua error in Module:Infobox at line 199: malformed pattern (missing ']').
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
<templatestyles src="Reflist/styles.css" />
Cite error: Invalid <references> tag; parameter "group" is allowed only.
<references />, or <references group="..." />| Liquid fuel |
|
 |
||||||||||||||||||||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Solid fuel |
|
|||||||||||||||||||||||||||||||
| Related articles | ||||||||||||||||||||||||||||||||
<templatestyles src="Asbox/styles.css"></templatestyles>
 |
This rocketry article is a stub. You can help Wikipedia by expanding it. |
