RD-0124

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RD-0124
Country of origin Russia
Date 2001
Designer KBKhA (Chief designers: Valery Kozelkov, Viktor Gorokhov[1]
Manufacturer TsSKB Progress
Application Upper stage booster
Predecessor RD-0110
Status In use
Liquid-fuel engine
Propellant LOX / RP-1
Cycle Staged Combustion
Performance
Thrust (vac.) 294.3 kN (66,161 lbf)
Chamber pressure 162 bar
Isp (vac.) 359 sec
Isp (SL) 331 sec
Dimensions
Length 1.58 m
Diameter 2.4 m
Dry weight 480 kg

The RD-0124 is a rocket engine burning liquid oxygen and kerosene in a staged combustion cycle. RD-0124 engines are used on the Soyuz-2.1b. A modification of the engine will also be used on the second stage of some rockets in the planned Angara rocket family. RD-0124 is developed by Khimavtomatiki Design Bureau.[2]

Design[edit]

RD-0124 engines use a multi-stage turbopump powered by pre-combustion of the engine propellants in a gas generator. The kerosene fuel is used for regenerative cooling of the engine. Vehicle attitude control during ascent is provided by gimbaling the engine in two planes. The propellant tanks are helium-pressurized.[3] Four combustion chambers are fed by a single turbopump system.[3][4] The engine operates at a high chamber pressure and, for the type of propellants used, achieves a very high specific impulse.

History[edit]

The inaugural flight of a launch vehicle using an RD-0124 engine took place on December 27, 2006.[3] Orbital Sciences considered using the RD-0124 in the High Energy Second Stage (HESS) for their Antares rocket. It would have replaced the Castor 30B second stage.[5]

See also[edit]

References[edit]

  1. ^ ru:Горохов, Виктор Дмитриевич Viktor Gorokhov / ru.wikipedia.org
  2. ^ "Russia's Angara rocket family needs cash injection". Flight International. 2009-05-05. Retrieved 2009-07-25. 
  3. ^ a b c "The Modernized Soyuz". Starsem. 
  4. ^ Arianespace
  5. ^ Bergin, Chris (5 March 2013). "CASTOR 30XL prepares for static fire ahead of providing Antares boost". NASA Spaceflight. Retrieved 22 February 2014.