Volume 38 Issue 2
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TIAN Zhongliang, LI Junwei, HE Ye, et al. Influence of dynamic lateral overload on internal ballistics of solid rocket motor[J]. Journal of Aerospace Power, 2023, 38（2）：504-512 doi: 10.13224/j.cnki.jasp.20210442
Citation: TIAN Zhongliang, LI Junwei, HE Ye, et al. Influence of dynamic lateral overload on internal ballistics of solid rocket motor[J]. Journal of Aerospace Power, 2023, 38（2）：504-512 doi: 10.13224/j.cnki.jasp.20210442
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Influence of dynamic lateral overload on internal ballistics of solid rocket motor

doi: 10.13224/j.cnki.jasp.20210442

  • School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China

  • Received Date: 2021-08-12
    Available Online: 2022-09-07
    Abstract

  • In order to study the internal ballistic characteristics of the solid rocket motor（SRM） under dynamic lateral overload, the burning rate measurement of a three-component composite propellant under −50g−50g overload acceleration was carried out, and the overload burning rate model of the propellant was established by combining with the Greatrix multi-parameter model; based on this model, the combustion surface retreat of tubular inner hole combustion grain under lateral overload was carried out, and the internal ballistic calculation model of large aspect ratio SRM under dynamic lateral overload was established. Results showed that there was an angular threshold for the influence of overload on the burning rate, and the influence of negative angular overload was small; an instantaneous lateral overload made the combustion chamber pressure jump, under 100g overload, the pressure increased by about 8%, the overload disappeared and the pressure dropped suddenly; if the time interval of lateral overload was fixed, the pressure change amplitude of maneuvering flight after 100g overload （t=12−15 s） was 1% smaller than that of maneuvering flight first （t=3−6 s）, which was more favorable for flight.

     

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    • References(20)
  • [1]
    唐金兰, 刘佩进. 固体火箭发动机原理[M]. 北京: 国防工业出版社, 2012.
    [2]
    GLICK R L. An analytical study of the effects of radial acceleration upon the combustion mechanism of solid propellant final report [R]. NASA-CR-66218, 1966.
    [3]
    BAKER K L,CROWE C T,WILLOUGHBY P G. A photographic and analytic study of composite propellant combustion in an acceleration field[J]. Journal of Spacecraft and Rockets,1971,8(4): 310-317.
    [4]
    NORTHAM G B. Effects of the acceleration vector on transient burning rate of an aluminized solid propellant[J]. Journal of Spacecraft and Rockets,1971,8(11): 1133-1138. doi: 10.2514/3.30357
    [5]
    FUCHS M D,PERETZ A,TIMANT Y M. Parametric study of acceleration effects on burning rates of metallized solid propellants[J]. Journal of Spacecraft and Rockets,1982,19(6): 539-544. doi: 10.2514/3.62298
    [6]
    GREATRIX D R,GOTTLIEB J. Model for prediction of normal acceleration augmentation of composite propellant combustion[J]. Mental Retardation,1987,7(2): 3-6.
    [7]
    GREATRIX D R. Acceleration-based combustion a-augmentation modelling for noncylindrical grain solid rocket motors[R]. San Diego, US: the 31st Joint Propulsion Conference and Exhibit, 1995
    [8]
    GREATRIX D R. Powered flight the engineering of aerospace propulsion[M]. London, UK: Springer-Verlag, 2012.
    [9]
    GREATRIX D R. A study of combustion and flow behavior in solid propellant rocket motors[R]. University of Tornoto Institute for Aerospace Studies Report No. 280, 1987.
    [10]
    万东,何国强,王占利,等. 低燃速HTPB复合推进剂过载情况下燃烧性能试验研究[J]. 固体火箭技术,2010,33(6): 656-659. doi: 10.3969/j.issn.1006-2793.2010.06.012

    WAN Dong,HE Guoqiang,WANG Zhanli,et al. Study on acceleration-based combustion for low-burning rate HTPB propellant[J]. Journal of Solid Rocket Technology,2010,33(6): 656-659. (in Chinese) doi: 10.3969/j.issn.1006-2793.2010.06.012
    [11]
    张为华,曹泰岳,万章吉. 固体火箭发动机旋转对燃速的影响[J]. 航空动力学报,1994,9(1): 67-70. doi: 10.13224/j.cnki.jasp.1994.01.017

    ZHANG Weihua,CAO Taiyue,WAN Zhangji. The effect of solid rocket motor rotation on burning rate[J]. Journal of Aerospace Power,1994,9(1): 67-70. (in Chinese) doi: 10.13224/j.cnki.jasp.1994.01.017
    [12]
    曹泰岳,张为华,万章吉,等. 旋转固体火箭发动机内弹道理论与试验研究[J]. 宇航学报,1997,18(1): 2-8.

    CAO Taiyue,ZHANG Weihua,WAN Zhangji,et al. Theoretical and experimental research on interior ballistics of swirling solid rocket motors[J]. Journal of Astronautics,1997,18(1): 2-8. (in Chinese)
    [13]
    李桢,王中伟,张为华,等. 横向过载下固体火箭发动机内弹道仿真[J]. 弹箭与制导学报,2005,25(4): 726-728,732. doi: 10.3969/j.issn.1673-9728.2005.04.237

    LI Zhen,WANG Zhongwei,ZHANG Weihua,et al. Internal ballistics simulation of solid rocket motor with lateral overload[J]. Journal of Projectiles, Rockets, Missiles and Guidance,2005,25(4): 726-728,732. (in Chinese) doi: 10.3969/j.issn.1673-9728.2005.04.237
    [14]
    曹军,郭颜红,邢强. 高过载条件下固体火箭发动机工作稳定性研究[J]. 航空兵器,2014,51(1): 33-36. doi: 10.3969/j.issn.1673-5048.2014.01.008

    CAO Jun,GUO Yanhong,XING Qiang. Research on the working stabilization of solid rocket motor under high overload[J]. Aero Weaponry,2014,51(1): 33-36. (in Chinese) doi: 10.3969/j.issn.1673-5048.2014.01.008
    [15]
    郭颜红,梁晓庚,陈斌. 大过载下固体火箭发动机内弹道计算[J]. 航空动力学报,2008,23(10): 1944-1948.

    GUO Yanhong,LIANG Xiaogeng,CHEN Bin. Internal ballistics calculation of solid rocket motors under high overload[J]. Journal of Aerospace Power,2008,23(10): 1944-1948. (in Chinese)
    [16]
    郭颜红,梁晓庚,陈斌. 大过载下固体火箭发动机工作过程仿真的数学模型[J]. 航空兵器,2008,45(1): 21-25.

    GUO Yanhong,LIANG Xiaogeng,CHEN Bin. Working process simulation of solid rocket motor with high acceleration load[J]. Aero Weaponry,2008,45(1): 21-25. (in Chinese)
    [17]
    檀叶,何景轩,孙展鹏. 过载条件下固体火箭发动机燃烧稳定性分析[J]. 弹箭与制导学报,2015,35(3): 113-116. doi: 10.15892/j.cnki.djzdxb.2015.03.029

    TAN Ye,HE Jingxuan,SUN Zhanpeng. Combustion stability analysis for solid rocket motor under overload.[J]. Journal of Projectiles, Rockets, Missiles and Guidance,2015,35(3): 113-116. (in Chinese) doi: 10.15892/j.cnki.djzdxb.2015.03.029
    [18]
    刘中兵,郜伟伟,张飞. 飞行过载对固体发动机内弹道的影响[J]. 固体火箭技术,2018,41(2): 169-175.

    LIU Zhongbing,GAO Weiwei,ZHANG Fei. Influence of acceleration on internal ballistics of solid motors[J]. Journal of Solid Rocket Technology,2018,41(2): 169-175. (in Chinese)
    [19]
    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. doi: 10.3873/j.issn.1000-1328.2019.08.014

    ZHANG Xiangyu,GAO Bo,GAN Xiaosong,et al. Impacts of flight acceleration on combustion instability of solid rocket motors[J]. Journal of Astronautics,2019,40(8): 972-976. (in Chinese) doi: 10.3873/j.issn.1000-1328.2019.08.014
    [20]
    贺业, 李军伟, 田忠亮, 等. 过载条件下高铝粉含量丁羟复合推进剂燃烧性能试验研究[C]//中国宇航学会固体火箭推进专业委员会第38届学术年会论文集. 贵州 遵义: 中国宇航学会, 2021: 494-500.
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