多约束条件下机动飞行器末段最优制导律研究
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摘要
针对多约束条件下机动飞行器末段制导问题,提出一种基于最优制导策略的工程化方法。考虑末端位置、倾角约束及过载需求,首先建立末制导线性动力学模型,通过控制法向速度保证末端倾角;然后基于最优控制理论,在性能指标中引入剩余飞行时间幂函数,应用Schwartz不等式定理推导出加速度指令表达式,对其进行化简,得到便于工程应用的形式;通过分析制导阶次对飞行过载及弹道特性的影响得到制导律权系数的特性变化;最后给出末段制导策略设计方法。仿真结果表明,通过合理设计制导阶次,制导律可以降低末端过载,满足飞行器机动需求、命中精度及倾角约束。
To study the terminal guidance problem of maneuvering vehicle under the multiple constraints, an engineering method is proposed based on optimal guidance strategy. Considering of terminal position, impact angle constraint and overload requirement,firstly, the linear dynamic model of terminal guidance is established, and the expression of acceleration command is inferred by the Schwartz inequality theorem, then the form which is convenient for engineering application is get. And then, the features of guidance coefficient are obtained by analyzing the influence of guidance order for overload and trajectory characteristics. At last, the design of terminal guidance law is given. Simulation results indicate that the guidance law can reduce the overload, meet the command of maneuvering, impact angle constraint and hit accuracy.
To study the terminal guidance problem of maneuvering vehicle under the multiple constraints, an engineering method is proposed based on optimal guidance strategy. Considering of terminal position, impact angle constraint and overload requirement,firstly, the linear dynamic model of terminal guidance is established, and the expression of acceleration command is inferred by the Schwartz inequality theorem, then the form which is convenient for engineering application is get. And then, the features of guidance coefficient are obtained by analyzing the influence of guidance order for overload and trajectory characteristics. At last, the design of terminal guidance law is given. Simulation results indicate that the guidance law can reduce the overload, meet the command of maneuvering, impact angle constraint and hit accuracy.
引文
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[2]蔡洪,胡正东,曹渊.具有终端角度约束的导引律综述[J].宇航学报,2010,31(2):315-323.Cai Hong,Hu Zhengdong,Cao Yuan.A Survey of guidance law with trminal impact angle constrains[J].Journal of Astronautics,2010,31(2):315-323.
[3]Kim M,Grider K V.Terminal guidance for impact attitude angle constrained flight trajectories[J].IEEE Transactions on Aerospace and Eletronic System,1973,AES-9(6):852-859.
[4]Taub I,Shima T.Intercept angle missile guidance under timevarying acceleration bounds[J].Journal of Guidance,Control,and Dynamics,2013,36(3):686-699.
[5]Zarchan P.Tactical and strategic missile guidance[M].4th ed.Reston,VA:AIAA,2002.
[6]Lee J I,Jeon I S,Tahk M J.Guidance law to control impact time and angle[J].IEEE Transactions on Aerospace and Electronic Systems,2007,43(1):301-310.
[7]胡正东,郭才发,蔡洪.带落角约束的再入机动弹头的复合导引律[J].国防科技大学学报,2008,30(3):21-26.Hu Zhengdong,Guo Caifa,Cai Hong.Integrated guidance law of reentry maneuvering warhead with terminal angular constraint[J].Journal of National University of Defense Technology,2008,30(3):21-26.
[8]Manchester I R,Savkin A V.Circular navigation guidance law for precision missile/target engagement[C].Nevada:Proceedings of the 41st IEEE Conference on Decision and Control,2002:1287-1292.
[9]Hu Z D,Cai H.An adaptive proportional guidance law against ground stationary target[C].Shenzhen:Proceedings of the 2nd International Symposium on Systems and Control in Aeropsace and Astronautics,2008:1-5.