固体运载器发动机内弹道设计方法
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摘要
为研究对固体运载器总体性能提升有利的发动机内弹道设计方法,建立了发动机内弹道计算模型,并选取两个燃面设计参数表征内弹道曲线构型。针对某三级固体运载器进行了仿真分析,分别以发动机冲质比最大及运载器射程最大为目标对发动机的内弹道曲线构型进行优化设计,并对这两种设计方法进行对比研究。研究结果表明,发动机性能最优并不一定会实现运载器总体性能最优,以运载器射程最大为目标,对发动机内弹道曲线构型进行优化设计,可显著提高运载器总体性能。研究成果可应用于固体运载器总体方案初步论证阶段,提升固体运载器的性能水平及方案论证效率,使固体运载器总体设计方案更具时效性和竞争性。
To research the interior ballistic design method for improving the overall performance of the solid launch vehicle motor,a calculation model for the motor interior ballistic is established,and two parameters of burning surface design are selected to represent the configuration of the interior ballistic curve.Simulation analysis of a three-stage solid launch vehicle is carried out.The interior ballistic curve configuration of the motor is optimized,with the objectives of the maximum impulse to mass ratio and of the maximum range of launch vehicle.A comparison of the two design methods shows that the optimal performance of the motor does not necessarily mean the best overall performance of the launch vehicle.With the maximum range of the launch vehicle as the objective of the optimal design of the interior ballistic of the motor,the overall performance of the launch vehicle can be significantly improved.The results can be applied to the preliminary demonstration stage of the overall scheme of the design of the solid launch vehicle,enhancing the performance level of the solid launch vehicle and the efficiency of scheme demonstration.The overall design scheme of the solid launch vehicle can thus be more timely and competitive.
To research the interior ballistic design method for improving the overall performance of the solid launch vehicle motor,a calculation model for the motor interior ballistic is established,and two parameters of burning surface design are selected to represent the configuration of the interior ballistic curve.Simulation analysis of a three-stage solid launch vehicle is carried out.The interior ballistic curve configuration of the motor is optimized,with the objectives of the maximum impulse to mass ratio and of the maximum range of launch vehicle.A comparison of the two design methods shows that the optimal performance of the motor does not necessarily mean the best overall performance of the launch vehicle.With the maximum range of the launch vehicle as the objective of the optimal design of the interior ballistic of the motor,the overall performance of the launch vehicle can be significantly improved.The results can be applied to the preliminary demonstration stage of the overall scheme of the design of the solid launch vehicle,enhancing the performance level of the solid launch vehicle and the efficiency of scheme demonstration.The overall design scheme of the solid launch vehicle can thus be more timely and competitive.
引文
[1]KAMRAN A,LIANG G.An integrated approach for optimization of solid rocket motor[J].Aerospace Science&Technology,2012,17(1):50-64.
[2]何允钦,梁国柱.基于蚁群算法的固体火箭发动机总体参数优化[J].推进技术,2010,31(1):5-11.HE Y Q,LIANG G Z.System parameter optimization of solid propellant rocket motors based on ant colony algorithm[J].Journal of Propulsion Technology,2010,31(1):5-11(in Chinese).
[3]刘竹生,张博戎.运载火箭总体设计多学科优化方法发展及展望[J].宇航总体技术,2017,1(2):1-6.LIU Z S,ZHANG B R.An overview of multidisciplinary optimization method in launch vehicle design[J].Astronautical Systems Engineering Technology,2017,1(2):1-6(in Chinese).
[4]郑安波,马汉东,罗小云.战术导弹多目标多学科设计优化[J].航空学报,2013,34(11):2557-2564.ZHENG A B,MA H D,LUO X Y.Multiobjective multidisciplinary design optimization of missile[J].Acta Aeronautica et Astronautica Sinica,2013,34(11):2557-2564(in Chinese).
[5]王荣,张红军,王贵东,等.吸气式空空导弹外形多学科一体化优化设计[J].航空学报,2016,37(1):207-215.WANG R,ZHANG H J,WANG G D,et al.Multidisciplinary integrated design optimization for an airbreathing air-to-air missile shape[J].Acta Aeronautica et Astronautica Sinica,2016,37(1):207-215(in Chinese).
[6]ZAFAR N,HE L S.Multidisciplinary design optimization of solid launch vehicle using hybrid algorithm:AIAA-2010-3010[R].Reston,VA:AIAA,2010.
[7]王永圣.固体弹道导弹推进/气动/弹道优化设计研究[D].哈尔滨:哈尔滨工业大学,2013:60-64.WANG Y S.Study on the propulsion-aerodynamics-trajectory integrated optimal design for solid ballistic missile[D].Harbin:Harbin Institute of Technology,2013:60-64(in Chinese).
[8]王振国.飞行器多学科设计优化理论与应用研究[M].北京:国防工业出版社,2006:318-337.WANG Z G.Research on the theory and application of multidisciplinary design optimization of flight vehicles[M].Beijing:National Defense Industry Press,2006:318-337(in Chinese).
[9]梁欣欣,李世鹏,陈阳,等.固体运载器大气飞行段内弹道优化设计研究[J].弹道学报,2014,26(4):72-75,81.LIANG X X,LI S P,CHEN Y,et al.Research on interior ballistics optimization design for solid launch vehicle in atmosphere flight phase[J].Journal of Ballistics,2014,26(4):72-75,81(in Chinese).
[10]梁欣欣,陈阳,张艳,等.姿控载荷多约束下的内外弹道联合优化[J].宇航学报,2016,37(6):679-686.LIANG X X,CHEN Y,ZHANG Y,et al.Interior and exterior ballistics coupled optimization with constraints of attitude control and flight load[J].Journal of Astronautics,2016,37(6):679-686(in Chinese).
[11]王铮,胡永强.固体火箭发动机[M].北京:中国宇航出版社,1993:94-106.WANG Z,HU Y Q.Solid rocket motor[M].Beijing:China Aerospace Publishing House,1993:94-106(in Chinese).
[12]刘旸,鲍福廷,蔡强,等.基于GPU计算架构的体素离散化复杂药柱燃面计算方法[J].固体火箭技术,2011,34(1):18-22.LIU Y,BAO F T,CAI Q,et al.GPU computing architecture-based discrete voxelized burning surface calculation method for complex SRM grains[J].Journal of Solid Rocket Technology,2011,34(1):18-22(in Chinese).
[13]贾沛然.远程火箭弹道学[M].长沙:国防科技大学出版社,2009:62-67.JIA P R.Ballistic of long-range-rocket[M].Changsha:National University of Defense Technology Press,2009:62-67(in Chinese).
[14]杨希祥,李晓斌,肖飞,等.智能优化算法及其在飞行器优化设计领域的应用综述[J].宇航学报,2009,30(6):2051-2061.YANG X X,LI X B,XIAO F,et al.Overview of intelligent optimization algorithm and its application in flight vehicles optimization design[J].Journal of Astronautics,2009,30(6):2051-2061(in Chinese).
[2]何允钦,梁国柱.基于蚁群算法的固体火箭发动机总体参数优化[J].推进技术,2010,31(1):5-11.HE Y Q,LIANG G Z.System parameter optimization of solid propellant rocket motors based on ant colony algorithm[J].Journal of Propulsion Technology,2010,31(1):5-11(in Chinese).
[3]刘竹生,张博戎.运载火箭总体设计多学科优化方法发展及展望[J].宇航总体技术,2017,1(2):1-6.LIU Z S,ZHANG B R.An overview of multidisciplinary optimization method in launch vehicle design[J].Astronautical Systems Engineering Technology,2017,1(2):1-6(in Chinese).
[4]郑安波,马汉东,罗小云.战术导弹多目标多学科设计优化[J].航空学报,2013,34(11):2557-2564.ZHENG A B,MA H D,LUO X Y.Multiobjective multidisciplinary design optimization of missile[J].Acta Aeronautica et Astronautica Sinica,2013,34(11):2557-2564(in Chinese).
[5]王荣,张红军,王贵东,等.吸气式空空导弹外形多学科一体化优化设计[J].航空学报,2016,37(1):207-215.WANG R,ZHANG H J,WANG G D,et al.Multidisciplinary integrated design optimization for an airbreathing air-to-air missile shape[J].Acta Aeronautica et Astronautica Sinica,2016,37(1):207-215(in Chinese).
[6]ZAFAR N,HE L S.Multidisciplinary design optimization of solid launch vehicle using hybrid algorithm:AIAA-2010-3010[R].Reston,VA:AIAA,2010.
[7]王永圣.固体弹道导弹推进/气动/弹道优化设计研究[D].哈尔滨:哈尔滨工业大学,2013:60-64.WANG Y S.Study on the propulsion-aerodynamics-trajectory integrated optimal design for solid ballistic missile[D].Harbin:Harbin Institute of Technology,2013:60-64(in Chinese).
[8]王振国.飞行器多学科设计优化理论与应用研究[M].北京:国防工业出版社,2006:318-337.WANG Z G.Research on the theory and application of multidisciplinary design optimization of flight vehicles[M].Beijing:National Defense Industry Press,2006:318-337(in Chinese).
[9]梁欣欣,李世鹏,陈阳,等.固体运载器大气飞行段内弹道优化设计研究[J].弹道学报,2014,26(4):72-75,81.LIANG X X,LI S P,CHEN Y,et al.Research on interior ballistics optimization design for solid launch vehicle in atmosphere flight phase[J].Journal of Ballistics,2014,26(4):72-75,81(in Chinese).
[10]梁欣欣,陈阳,张艳,等.姿控载荷多约束下的内外弹道联合优化[J].宇航学报,2016,37(6):679-686.LIANG X X,CHEN Y,ZHANG Y,et al.Interior and exterior ballistics coupled optimization with constraints of attitude control and flight load[J].Journal of Astronautics,2016,37(6):679-686(in Chinese).
[11]王铮,胡永强.固体火箭发动机[M].北京:中国宇航出版社,1993:94-106.WANG Z,HU Y Q.Solid rocket motor[M].Beijing:China Aerospace Publishing House,1993:94-106(in Chinese).
[12]刘旸,鲍福廷,蔡强,等.基于GPU计算架构的体素离散化复杂药柱燃面计算方法[J].固体火箭技术,2011,34(1):18-22.LIU Y,BAO F T,CAI Q,et al.GPU computing architecture-based discrete voxelized burning surface calculation method for complex SRM grains[J].Journal of Solid Rocket Technology,2011,34(1):18-22(in Chinese).
[13]贾沛然.远程火箭弹道学[M].长沙:国防科技大学出版社,2009:62-67.JIA P R.Ballistic of long-range-rocket[M].Changsha:National University of Defense Technology Press,2009:62-67(in Chinese).
[14]杨希祥,李晓斌,肖飞,等.智能优化算法及其在飞行器优化设计领域的应用综述[J].宇航学报,2009,30(6):2051-2061.YANG X X,LI X B,XIAO F,et al.Overview of intelligent optimization algorithm and its application in flight vehicles optimization design[J].Journal of Astronautics,2009,30(6):2051-2061(in Chinese).