多约束条件下机动飞行器末段最优制导律研究

The Research of Terminal Optimal Guidance Law of Maneuvering Vehicle with Multiple Constrains

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.