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Contents

   



(Top)
 


1 History  





2 Versions  





3 See also  





4 References  





5 External links  














RD-864






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RD-864 (РД-864)
Country of originSoviet Union
Date1976-1978
First flightOctober 31, 1977
DesignerYuzhnoye Design Bureau
ManufacturerYuzhmash
ApplicationUpper stage
Associated LVR-36M UTTKh and Dnepr
SuccessorRD-869
StatusIn service
Liquid-fuel engine
PropellantN2O4 / UDMH
Mixture ratio1.8
CycleGas generator
Configuration
Chamber4
Performance
Thrust
  • High thrust mode: 20.2 kN (4,500 lbf)
  • Low thrust mode: 8.45 kN (1,900 lbf)
  • Chamber pressure
    • High thrust mode: 4.1 MPa (590 psi)
  • Low thrust mode: 1.7 MPa (250 psi)
  • Specific impulse
    • High thrust mode: 309 seconds
  • Low thrust mode: 298 seconds
  • Burn timeUp to 600 s
    Restarts25
    Gimbal range±55°
    Dimensions
    Length4,020 mm (158 in)
    Diameter1,420 mm (56 in)
    Dry weight199 kg (439 lb)
    Used in
    R-36M UTTKh and Dnepr third stage
    References
    References[1][2][3][4][5][6][7][8][9]
    RD-869 (РД-869)
    Country of originSoviet Union
    Date1983-1985
    First flightMarch 1986
    DesignerYuzhnoye Design Bureau
    ManufacturerYuzhmash
    ApplicationUpper Stage
    Associated LVR-36M2
    PredecessorRD-864
    StatusIn service
    Liquid-fuel engine
    PropellantN2O4 / UDMH
    Mixture ratio1.8
    CycleGas generator
    Configuration
    Chamber4
    Performance
    Thrust
    • High thrust mode: 20.47 kN (4,600 lbf)
  • Low thrust mode: 8.58 kN (1,930 lbf)
  • Chamber pressure
    • High thrust mode: 4.1 MPa (590 psi)
  • Low thrust mode: 1.7 MPa (250 psi)
  • Specific impulse
    • High thrust mode: 313 seconds
  • Low thrust mode: 302.3 seconds
  • Burn timeUp to 700 s
    Restarts50
    Gimbal range±55°
    Dimensions
    Length4,020 mm (158 in)
    Diameter1,420 mm (56 in)
    Dry weight196 kg (432 lb)
    Used in
    R-36M2 third stage
    References
    References[1][5][6][10]

    The RD-864 (GRAU: 15D177) is a Soviet liquid propellant rocket engine burning UDMH and nitrogen tetroxide in a gas generator combustion cycle.[1] It has a four combustion chambers that provide thrust vector controlbygimbaling each nozzle in a single axis ±55°. It is used on the third stage of the R-36M UTTKh (GRAU: 15A18) and Dnepr.[5] For the R-36M2 (GRAU: 15A18M), an improved version, the RD-869 (GRAU: 15D300) was developed.[1][6][10][11]

    History[edit]

    When the Soviet military developed an improved version of the R-36M ICBM, Yangel's OKB-586 developed a new engine for the third stage, the RD-864. Developed between 1976 and 1978 it flew for the first time on October 31, 1977. With the START I and START II the some 150 R-36M and R-36M UTTKh were retired and to be destroyed by 2007.[1][4] So, a civilian application was looked for and during the 1990s, Yuzhnoe Design Bureau (the R-36M designer) successfully developed the Dnepr launch vehicle.[3] It flew for the first time on April 21, 1999 and as of June 2016 it is still operational.[12] So, while the production of the RD-864 has long since been finished, the engine is still to this day operational.[12][13]

    The RD-869 was an improved version for the most powerful Soviet ICBM ever, the R-36M2 (15A18M). It had improved efficiency, restart capability and burn life over the RD-864.[1][10] As of January 2016 there are still 46 operational R-36M2 (RS-20V, SS-18) and thus the RD-869 is still in service, if out of production.[13]

    Versions[edit]

    There are two versions of this engine:

    See also[edit]

    References[edit]

    1. ^ a b c d e f g h "Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные" [Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry] (PDF) (in Russian). pp. 341–342. Retrieved 2016-07-07.
  • ^ Brügge, Norbert. "Dnepr Propulsion". B14643.de. Retrieved 2015-08-06.
  • ^ a b Wade, Mark. "Dnepr". Encyclopedia Astronautica. Archived from the original on October 15, 2002. Retrieved 2016-07-07.
  • ^ a b Wade, Mark. "R-36MU 15A18". Encyclopedia Astronautica. Archived from the original on November 29, 2010. Retrieved 2016-07-07.
  • ^ a b c d Wade, Mark. "RD-864". Encyclopedia Astronautica. Archived from the original on June 26, 2002. Retrieved 2016-07-07.
  • ^ a b c d Wade, Mark. "RD-869". Encyclopedia Astronautica. Archived from the original on May 6, 2002. Retrieved 2016-07-07.
  • ^ Pillet, Nicolas. "Le troisième étage de Dniepr" [The Dnepr third stage] (in French). Kosmonavtika.com. Retrieved 2016-07-07.
  • ^ "Dnepr". Yuzhnoye. Archived from the original on 28 October 2014.
  • ^ "Dnepr Launch Vehicle". Yuzhmash. Archived from the original on 15 December 2012.
  • ^ a b c Wade, Mark. "R-36M2 15A18M". Encyclopedia Astronautica. Archived from the original on September 10, 2010. Retrieved 2016-07-07.
  • ^ Pal'kov, V. A.; Timchenko, A. Ju.; Stecenko, A. Ja. (2014). Tkachenko, V. D. (ed.). Шестьдесят лет в ракетостроении и космонавтике. 1954-2014 [Sixty years in rocketry and astronautics. 1954-2014] (in Russian). Yuzhnoye SDO. pp. 183–185. ISBN 978-966-348-349-8.
  • ^ a b Krebs, Gunter Dirk (2016-06-13). "Dnepr". Gunter's Space Page. Retrieved 2016-07-07.
  • ^ a b "Strategic Rocket Forces". January 2016. Retrieved 2016-07-07.
  • External links[edit]


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  • Retrieved from "https://en.wikipedia.org/w/index.php?title=RD-864&oldid=1181052073"

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    Yuzhmash rocket engines
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