摘要
以期望的落角方向为坐标轴定义了落角坐标系,在落角坐标系中建立了线性化的运动关系方程。应用Schwarz不等式,分别研究了控制系统为一阶惯性环节和无惯性环节情况下带落角约束的任意加权最优制导律,得到了制导律的一般表达式。对于无惯性环节控制系统以及加权函数为一般初等函数类型的一阶惯性环节控制系统,当加权函数的逆的一次到三次积分都能求出解析表达式时,均可以得到解析形式的最优制导律。对于不同的制导目的,应用本文结果可以方便地设计相应的制导律。对于某些特定的加权函数,所得制导律推广了现有文献的结论,并给出了指数权函数下满足落角约束的最优制导律的仿真结果。
The impact angle frame is defined which axis is in the direction of the desired impact angle, and the engagement kinematics is established in the impact angle frame. Generalized weighted optimal guidance laws with impact angle con- straints are studied for first-order lag control systems and lag-free control systems respectively using Schwarz＇s inequality approach. For lag-free control systems and first-order lag control systems with elementary function weighting, the analytical forms of weighted optimal guidance laws can be obtained if the integrations of the inverse of the weighting functions up to tri- ple can be analytically given. The results can be applied to guidance law designs for accomplishing different guidance objec- tives. For some specific weighted functions, the proposed guidance law has extended the results in references. Simulation results are given for the exponential weighting optimal guidance law with impact angle constraints.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2014年第3期848-856,共9页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(61273058)~~
关键词
导弹
落角约束
加权函数
最优制导
SCHWARZ不等式
指数加权
missiles； impact angle constraint； weighted function； optimal guidance； Schwarz＇s inequality； exponentiaweighting
