Volume 36 Issue 11
Nov.  2021
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SUN Di, LI Yongzhou, LIU Xiaowei, GAN Xiaosong. Influence of transverse variable acceleration on design of insulation structure for solid rocket motor[J]. Journal of Aerospace Power, 2021, 36(11): 2458-2464. doi: 10.13224/j.cnki.jasp.20200435
Citation: SUN Di, LI Yongzhou, LIU Xiaowei, GAN Xiaosong. Influence of transverse variable acceleration on design of insulation structure for solid rocket motor[J]. Journal of Aerospace Power, 2021, 36(11): 2458-2464. doi: 10.13224/j.cnki.jasp.20200435
shu

Influence of transverse variable acceleration on design of insulation structure for solid rocket motor

doi: 10.13224/j.cnki.jasp.20200435
  • 1.

    School of Aircraft Engineering，Nanchang Hangkong University，Nanchang 330063，China

  • 2.

    Xi'an Institute of Aerospace Propulsion Technology，China Aerospace Science and Technology Corporation，Xi'an 710025，China

  • 3.

    School of Aerospace Engineering，Huazhong University of Science and Technology，Wuhan 430074，China

  • Received Date: 2020-10-20
  • Publish Date: 2021-11-28
    Abstract
  • Targeting the high-mobility characteristics of the new generation antiaircraft missiles，the influence of the complex transverse variable acceleration trajectory on the engineering design for the solid rocket motor insulation structure was studied.It considered the instantaneous changes of acceleration value and angle，meshed the insulation structure，and calculated its ablation thickness by programming，and then the design thickness of the heat insulation layer at different positions was obtained according to the safety margin design criterion.Compared with traditional design results，considering the change of transverse acceleration significantly reduced the structural mass of the motor，and improved the overall performance；the heat insulation mass of the motor was reduced by 53.7%，and the total impulse was increased by 6.84%.

     

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    • References(20)
  • [1]
    袁华,简金蕾,任宏滨，等.第4代防空导弹关键技术初探[J].现代防御技术，2007，35（5）:51-54．
    [2]
    陈海建.先进防空导弹关键技术分析及发展启示[J].现代防御技术，2020，48（4）:60-66.
    [3]
    李江,何国强,秦飞,等.高过载条件下绝热层烧蚀实验方法研究（Ⅰ）方案论证及数值模拟[J].推进技术，2003，24（6）:315-318．
    [4]
    张翔宇,高波,甘晓松,等.飞行过载对固体火箭发动机不稳定燃烧的影响[J].宇航学报,2019,40（8）:972-976.
    [5]
    孙迪,马亮,甘晓松,等.嵌金属丝两级药柱掺混燃烧下的内弹道计算[J].火箭推进，2019,45（3）:59-63.
    [6]
    MITANI T,NIILKA T.An analytical and experimental study for solid-propellant combustion in an acceleration[J].Combustion Science and Technology,1973,8（3）:61-66.
    [7]
    BORAAS S.Modeling slag deposition in the space shuttle solid rocket motor[J].Journal of Spacecraft and Rockets,1984,21（1）:47-54.
    [8]
    刘世东.过载对固体火箭发动机影响的研究[J].航空兵器,2006,6:42-44.
    [9]
    田维平,许团委,王建儒.过载下燃烧室粒子特性与绝热层烧蚀研究进展[J].固体火箭技术,2015,38（1）:30-37.
    [10]
    KOVALEV O B.Motor and plume particle size prediction in solid-propellant rocket motors[J].Journal of Propulsion and Power,2002,18（6）:1199-1210．
    [11]
    BAKER K,CROWE C T,WILLOUGHBY P.A photographic and analytic study of composite propellant combustion in an acceleration field[J].Journal of Spacecraft and Rockets,1971，8（4）:310-317.
    [12]
    KING M K.Critical review: modeling of acceleration effects on solid propellant combustion[J].AIAA Journal,1976,14（1）:18-25.
    [13]
    LANGHENRY M T.Acceleration effects in solid propellant rocket motors[R].AIAA 1986-1577,1986.
    [14]
    SABNIS J S,DE JONG F J,GIBELING H J.Calculation of particle trajectories in solid rocket motors with arbitrary acceleration[J].Journal of Propulsion and Power,1992,8（5）:961-967.
    [15]
    DERBIDGE C,POWARS C.Acceleration effects on internal insulation erosion[R].AIAA 1993-1858,1993.
    [16]
    何国强,王国辉,蔡体敏,等.高过载条件下固体发动机内流场及绝热层冲蚀研究[J].固体火箭技术,2001,24（4）:4-8.
    [17]
    刘洋,李江,杨飒,等.过载条件下EPDM绝热材料烧蚀机理和模型研究:Ⅰ 烧蚀机理分析[J].固体火箭技术,2011,34（2）:229-233.
    [18]
    李江,何国强,陈剑,等.高过载条件下绝热层烧蚀实验方法研究:Ⅱ 收缩管聚集法[J].推进技术,2004,25（3）:196-198.
    [19]
    李越森,叶定友,利凤祥.横向加速度对飞行发动机绝热层烧蚀影响的试验研究[J].航空动力学报,2004,19（2）:278-282.
    [20]
    诸毓武.某导弹主动段全程横向过载条件下发动机绝热层安全性分析[J].上海航天，2013,30（2）:56-59.
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