RD-8: Difference between revisions

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|cycle = [[Staged combustion]]
|cycle = [[Staged combustion]]
|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>
|specific_impulse_vacuum = 342 [[second|s]]
|specific_impulse_vacuum = {convert|342|isp}}
|operating_time = 1100 seconds
|operating_time = 1100 seconds
|chamber_pressure = {{convert|7.8|MPa|psi}}<ref name="whatever" />
|chamber_pressure = {{convert|7.8|MPa|psi}}<ref name="whatever" />
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}}
}}


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&nbsp;[[Newton (unit)|kN]] and its specific impulse in vacuum is 342&nbsp;s.<ref name="yuzzi">[http://www.yuzhnoye.com/?id=156&lang=en&path=Aerospace%20Technology/Rocket%20Propulsion/Liquid%20Engines/Vernier%20Engines/RD-8/RD-8_e Yuzhnoye SDO - RD-8 Engine]</ref>
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&nbsp;[[Newton (unit)|kN]] and its specific impulse in vacuum is {{convert|342|isp}}.<ref name="yuzzi">[http://www.yuzhnoye.com/?id=156&lang=en&path=Aerospace%20Technology/Rocket%20Propulsion/Liquid%20Engines/Vernier%20Engines/RD-8/RD-8_e Yuzhnoye SDO - RD-8 Engine]</ref>


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.<ref name="yuzzi" />
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.<ref name="yuzzi" />

Revision as of 20:45, 15 December 2013

For the Dominican Republic national highway #8, see DR-8.
RD-8 (РД-8)
Country of originUSSR/Russia
ManufacturerYuzhnoye Design Bureau
ApplicationUpper stage vernier
StatusOperational
Liquid-fuel engine
PropellantLOX / rocket grade kerosene
Performance
Thrust, vacuum78.5 kilonewtons (17,600 lbf)[1]
Specific impulse, vacuum{convert
 |operating_time    = 1100 seconds
 |chamber_pressure  = 7.8 megapascals (1,130 psi)[1]
 |thrust_to_weight  =
 |length            =
 |diameter          =
 |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

  1. ^ a b RD-8 rocket engine
  2. ^ a b Yuzhnoye SDO - RD-8 Engine
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