RD-8
RD-8 (РД-8)Country of origin |
USSR |
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Manufacturer |
Yuzhnoye Design Bureau |
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Application |
Upper stage vernier |
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Status |
Operational |
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Liquid-fuel engine |
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Propellant |
LOX / rocket grade kerosene |
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Performance |
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Thrust (vac.) |
78.5 kilonewtons (17,600 lbf)[1] |
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Chamber pressure |
7.8 megapascals (1,130 psi)[1] |
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Isp (vac.) |
342 seconds (3.35 km/s) |
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Dimensions |
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Dry weight |
380 kilograms (840 lb) |
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Used in |
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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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| Liquid fuel | | US | |
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| Semi-cryogenic (Other) | |
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| Solid fuel | US | |
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Russian and former Soviet military designation sequences for radar, missile and rocket systems |
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| Radar systems | Land-based | |
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| Missiles | ICBM | |
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| Unguided rockets | Air-launched | |
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| Surface-launched | |
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| Engines | |
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