RD-0124 engines use a multi-stage turbopump powered by pre-combustion of the engine propellants in the preburner. 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.[7] Four combustion chambers are fed by a single turbopump system.[7][8] The engine operates at a high chamber pressure and, for the type of propellants used, achieves a very high specific impulse of nearly 360 seconds in vacuum.
HistoryEdit
The inaugural flight of a launch vehicle using an RD-0124 engine took place on December 27, 2006, on the inaugural launch of the Soyuz-2.1b[7]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.[9]
VersionsEdit
This upper stage engine has been adapted to two different launch vehicles, the Soyuz-2-1b/v and the Angara family. As such, there are different versions:
RD-0124 (GRAU Index 14D23). It is the version for the Soyuz-2-1b and Soyuz-2-1v Blok-I. It is the first liquid rocket engine designed in Russia after the Soviet period.[3][citation needed]
RD-0124A It is the version that powers the Angara URM-2, both the 1.2 and the bigger 5 versions. It differs on the base model in having an extended burn time of 424 seconds and, at 548 kg (1,208 lb), being 24 kg (53 lb) lighter.[3]
RD-0124DR Version developed between 2008 and 2013 for the Soyuz-2-3 project. It would differ from the base version in the implementation of a throttled point of 176.6 kN (39,700 lbf) with a reduced chamber pressure of 9.5 MPa (1,380 psi) and a specific impulse of 347s. The throttling capability meant a redesign of the preburner and the combustion chamber.[10]
RD-0125A Single nozzle version of the RD-0124A, it is planned as an upgrade for the Angara URM-2. It would enable the use of dual engines, which would enhance performance and reduce launch cost. Probably only planned for the Angara-5 URM-2, which is larger than that of the Angara-1.2.[11]
RD-0124MS A new Russian rocket engine with a thrust of 60 tons (533 kN), powered by naphthyl–liquid oxygen propellants. The engine consists of two blocks located on a common frame and a heat shield. Each consists of two diagonally located combustion chambers. The engine provides steering of the chambers in two planes, as well as able to work when one of the blocks is turned off. In development as of 2020 to power second stage of Soyuz-5 rocket.[12]
^ abc. Starsem. Archived from the original on 8 May 2001.
^. Arianespace. Archived from the original on 27 November 2015.
^Bergin, Chris (2013-03-05). "CASTOR 30XL prepares for static fire ahead of providing Antares boost". NASA Spaceflight. Retrieved 2015-07-22.
^ [Engine RD0124DR (throttleable)] (in Russian). KBKhA. Archived from the original on 4 December 2013.
^ [Engine RD0125A] (in Russian). KBKhA. Archived from the original on 4 December 2013.
^"Russian designers have started creating an engine for the Sunkar rocket (In Russian)". TASS. 7 April 2017.
October 19, 2023
0124, grau, index, 14d23, rocket, engine, burning, liquid, oxygen, kerosene, oxygen, rich, staged, combustion, cycle, developed, chemical, automatics, design, bureau, voronezh, engines, used, soyuz, soyuz, variant, engine, used, angara, rocket, family, upper, . The RD 0124 GRAU Index 14D23 is a rocket engine burning liquid oxygen and kerosene in an oxygen rich staged combustion cycle developed by the Chemical Automatics Design Bureau in Voronezh 3 RD 0124 engines are used on the Soyuz 2 1b and Soyuz 2 1v A variant of the engine the RD 0124A is used on the Angara rocket family s URM 2 upper stage RD 0124 14D23 Country of originRussiaDate1993 2006First flight2006 12 27DesignerKBKhA Chief designers Valery Kozelkov Viktor Gorokhov ru 1 ManufacturerKBKhA in house 2 ApplicationUpper StageAssociated LVSoyuz 2 Angara Soyuz 5PredecessorRD 0110StatusIn ProductionLiquid fuel enginePropellantLOX RP 1CycleStaged CombustionConfigurationChamber4PerformanceThrust vacuum294 3 kN 66 200 lbf Thrust to weight ratio52 5Chamber pressure15 7 MPa 2 280 psi Specific impulse vacuum359 s 3 52 km s Burn time300 sDimensionsLength1 575 mm 62 0 in Diameter2 400 mm 94 in Dry weight572 kg 1 261 lb Used inSoyuz 2 1b and Soyuz 2 1v Block IReferencesReferences 3 4 5 6 Contents 1 Design 2 History 3 Versions 4 See also 5 ReferencesDesign EditRD 0124 engines use a multi stage turbopump powered by pre combustion of the engine propellants in the preburner 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 7 Four combustion chambers are fed by a single turbopump system 7 8 The engine operates at a high chamber pressure and for the type of propellants used achieves a very high specific impulse of nearly 360 seconds in vacuum History EditThe inaugural flight of a launch vehicle using an RD 0124 engine took place on December 27 2006 on the inaugural launch of the Soyuz 2 1b 7 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 9 Versions EditThis upper stage engine has been adapted to two different launch vehicles the Soyuz 2 1b v and the Angara family As such there are different versions RD 0124 GRAU Index 14D23 It is the version for the Soyuz 2 1b and Soyuz 2 1v Blok I It is the first liquid rocket engine designed in Russia after the Soviet period 3 citation needed RD 0124A It is the version that powers the Angara URM 2 both the 1 2 and the bigger 5 versions It differs on the base model in having an extended burn time of 424 seconds and at 548 kg 1 208 lb being 24 kg 53 lb lighter 3 RD 0124DR Version developed between 2008 and 2013 for the Soyuz 2 3 project It would differ from the base version in the implementation of a throttled point of 176 6 kN 39 700 lbf with a reduced chamber pressure of 9 5 MPa 1 380 psi and a specific impulse of 347s The throttling capability meant a redesign of the preburner and the combustion chamber 10 RD 0125A Single nozzle version of the RD 0124A it is planned as an upgrade for the Angara URM 2 It would enable the use of dual engines which would enhance performance and reduce launch cost Probably only planned for the Angara 5 URM 2 which is larger than that of the Angara 1 2 11 RD 0124MS A new Russian rocket engine with a thrust of 60 tons 533 kN powered by naphthyl liquid oxygen propellants The engine consists of two blocks located on a common frame and a heat shield Each consists of two diagonally located combustion chambers The engine provides steering of the chambers in two planes as well as able to work when one of the blocks is turned off In development as of 2020 to power second stage of Soyuz 5 rocket 12 See also EditRD 0110 previous engine Soyuz 2 1b first launch vehicle to use it Soyuz 2 1v second launch vehicle to use it Angara third launch vehicle to use it Comparison of orbital rocket enginesReferences Edit ru Gorohov Viktor Dmitrievich Viktor Gorokhov ru wikipedia org Lyudi i raketnye dvigateli People and Rocket Engines Official History of KBKhA in Russian p 262 a b c d RD0124 14D23 Launch vehicle Soyuz 2 1b RD0124A Angara launch vehicle KBKhA Archived from the original on 15 August 2015 Turbopumps for Gas Generator and Staged Combustion Cycle Rocket Engines PDF AIAA July 2005 Retrieved 2015 07 22 Zhidkostnyj raketnyj dvigatel RD 0124A Liquid rocket engine RD 0124A in Russian Khrunichev Archived from the original on 22 July 2015 Zak Anatoly RD 0110 russianspaceweb com Retrieved 2015 07 22 a b c The Modernized Soyuz Starsem Archived from the original on 8 May 2001 Soyuz Overview Arianespace Archived from the original on 27 November 2015 Bergin Chris 2013 03 05 CASTOR 30XL prepares for static fire ahead of providing Antares boost NASA Spaceflight Retrieved 2015 07 22 Dvigatel RD0124DR drosselirovannyj Engine RD0124DR throttleable in Russian KBKhA Archived from the original on 4 December 2013 Dvigatel RD0125A Engine RD0125A in Russian KBKhA Archived from the original on 4 December 2013 Russian designers have started creating an engine for the Sunkar rocket In Russian TASS 7 April 2017 Retrieved from https en wikipedia org w index php title RD 0124 amp oldid 1153091344, wikipedia, wiki, book, books, library,
