RD-8: Difference between revisions
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|cycle = [[Staged combustion]] |
|cycle = [[Staged combustion]] |
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|thrust(Vac) = {{convert|78.5|kN|lbf}}<ref name="whatever">[http://www.nkau.gov.ua/nsau/productnsau2.nsf/09e578a9237d8923c2256f9700336d37/3e2b55cce321c673c2256faf005ca84d!OpenDocument RD-8 rocket engine]</ref> |
|thrust(Vac) = {{convert|78.5|kN|lbf}}<ref name="whatever">[http://www.nkau.gov.ua/nsau/productnsau2.nsf/09e578a9237d8923c2256f9700336d37/3e2b55cce321c673c2256faf005ca84d!OpenDocument RD-8 rocket engine]</ref> |
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|specific_impulse_vacuum = {convert|342|isp}} |
|specific_impulse_vacuum = {{convert|342|isp}} |
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|operating_time = 1100 seconds |
|operating_time = 1100 seconds |
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|chamber_pressure = {{convert|7.8|MPa|psi}}<ref name="whatever" /> |
|chamber_pressure = {{convert|7.8|MPa|psi}}<ref name="whatever" /> |
Revision as of 20:46, 15 December 2013
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 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]