捷联式制导迫弹末制导弹道优化设计
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摘要
为了提高捷联式制导迫弹的目标捕获概率和命中精度,研究了其末制导段弹道优化设计问题。根据制导迫弹的工作过程,结合捷联导引头的空间模型,以制导迫弹飞行攻角和飞行时间作为设计变量,建立了包含导引头视场角、弹目距离及终端弹道参数等多约束的弹道优化模型,并采用改进的粒子群优化算法进行求解。仿真结果表明:优化后的弹道能够保证捷联导引头在较高高度探测到目标。研究结果可以为捷联式制导迫弹的工程研制提供依据。
In order to improve the target-acquisition-probability and hit-probability of strap-down guided mortars,trajectory optimization of terminal guidance for strap-down guided mortars was researched. According to the the working process of guided mortar and the model of strap-down seeker in space,the attack angle and flight time were taken as design variables,a multi-constraints trajectory optimization model was established and a modified particle swarm optimization algorithm was developed to solve the problem. The simulation results show that the optimal trajectory obtained by modified particle swarm optimization can ensure strap-down seeker to detect targets at higher heights.The results can provide the basis to the engineering development of strap-down guided mortar.
In order to improve the target-acquisition-probability and hit-probability of strap-down guided mortars,trajectory optimization of terminal guidance for strap-down guided mortars was researched. According to the the working process of guided mortar and the model of strap-down seeker in space,the attack angle and flight time were taken as design variables,a multi-constraints trajectory optimization model was established and a modified particle swarm optimization algorithm was developed to solve the problem. The simulation results show that the optimal trajectory obtained by modified particle swarm optimization can ensure strap-down seeker to detect targets at higher heights.The results can provide the basis to the engineering development of strap-down guided mortar.
引文
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[15] RAHIMI A,KUMAR K D,ALIGHANBARI H. Particle swarm optimization applied to spacecraft reentry trajectory[J]. Journal of Guidance,Control,and Dynamics,2013,36(1):307-310.
[2] CONWAY B A. A survey of methods available for the numerical optimization of continuous dynamic systems[J].Journal of Optimization Theory and Applications,2012,152(2):271-306.
[3]白宏阳,李伟明,孙瑞胜,等.航空时敏制导炸弹增程弹道组合优化设计[J].国防科技大学学报,2014,36(6):100-105.
[4]王强,王刚,赵莹.国外末制导迫弹的发展综述[J].四川兵工学报,2014,35(5):20-23.
[5]朱少雄,施冬梅.制导迫击炮弹发展现状及关键技术[J].飞航导弹,2016(4):67-70.
[6]王强,石丽娜,严慎武,等.国外末制导弹药的发展与研究[J].飞航导弹,2013(4):55-60.
[7]靳江锋.某型卫星制导迫弹气动特性分析与弹道仿真[D].南京:南京理工大学,2015.
[8]曹小兵,王中原,史金光.末制导迫弹脉冲控制建模与仿真[J].弹道学报,2006,18(4):76-79.
[9]程振轩,林德福,牟宇,等.简易制导迫弹脉冲力控制建模与仿真[J].系统仿真学报,2009,21(17):5528-5531.
[10]李兴隆,于纪言,姚文进,等.基于末段修正迫弹命中概率的射角优化[J].弹道学报,2014,26(2):90-94.
[11]程振轩,林德福,王辉.激光制导迫弹捕获概率与命中精度分析[J].红外与激光工程,2008,37(s3):296-299.
[12]陈浩,刘秋生,孙希彤,等.制导迫弹修正能力仿真研究[J].战术导弹技术,2015(5):70-74.
[13]钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2000.
[14] EBERHART R,KENNEDY J. A new optimizer using particle swarm theory[C]∥IEEE. Proceedings of the Sixth International Symposium on Micro Machine and Human Science.[S. l.]:IEEE,2002:39-43.
[15] RAHIMI A,KUMAR K D,ALIGHANBARI H. Particle swarm optimization applied to spacecraft reentry trajectory[J]. Journal of Guidance,Control,and Dynamics,2013,36(1):307-310.