航空学报 > 2014, Vol. 35 Issue (3): 848-856   doi: 10.7527/S1000-6893.2013.0364

带有落角约束的一般加权最优制导律

张友安1, 黄诘1,2, 孙阳平1   

  1. 1. 海军航空工程学院 控制工程系, 山东 烟台 264001;
    2. 海军航空工程学院 青岛校区, 山东 青岛 266041
  • 收稿日期:2013-06-24 修回日期:2013-08-15 出版日期:2014-03-25 发布日期:2013-08-22
  • 通讯作者: 张友安,Tel.:0535-6635071 E-mail:zhangya63@sina.com E-mail:zhangya63@sina.com
  • 作者简介:张友安 男,博士,教授。主要研究方向:先进控制技术及其在飞行器导航、制导与控制中的应用。Tel:0535-6635071 E-mail:zhangya63@sina.com
  • 基金资助:

    国家自然科学基金(61273058)

Generalized Weighted Optimal Guidance Laws with Impact Angle Constraints

ZHANG Youan1, HUANG Jie1,2, SUN Yangping1   

  1. 1. Department of Control Engineering, Naval Aeronautical and Astronautical University, Yantai 264001, China;
    2. Qingdao Branch, Naval Aeronautical and Astronautical University, Qingdao 266041, China
  • Received:2013-06-24 Revised:2013-08-15 Online:2014-03-25 Published:2013-08-22
  • Supported by:

    National Natural Science Foundation of China (61273058)

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。

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

Abstract:

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 constraints 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 triple can be analytically given. The results can be applied to guidance law designs for accomplishing different guidance objectives. 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.

Key words: missiles, impact angle constraint, weighted function, optimal guidance, Schwarz's inequality, exponential weighting

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