基于MPSC和CPN制导方法的协同制导律  

Cooperative guidance law based on MPSC and CPN guidance method

作　　者：李新三 汪立新 王明建 闫循良 刘国辉 丁邦平 LI Xinsan WANG Lixin WANG Mingjian YAN Xunliang LIU Guohui DING Bangping(Department of Control Engineering, Rocket Military Engineering University, Xi＇ an 710025, China Petty Officer Academy, Rocket Military Engineering University, Qingzhou 262500, China)

机构地区：[1]火箭军工程大学控制工程系,西安710025 [2]火箭军工程大学士官学院,青州262500

出　　处：《北京航空航天大学学报》2016年第9期1857-1863,共7页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(61203354)~~

摘　　要：针对带有末端攻击角度约束的多导弹协同制导问题,运用模型预测扩展控制(MPSC)和协同比例制导(CPN),设计了一种满足末端攻击角度约束的多导弹协同次优制导律。阐述了MPSC制导方法的基本理论,详细给出了控制量表达式以二次形式近似时MPSC制导律的设计过程。采用CPN对MPSC制导方法的初始控制量进行猜测,并确定协同攻击时间。仿真时考虑两枚导弹对地面静止目标进行协同攻击。仿真结果表明,两枚导弹攻击时间偏差和末端攻击角度偏差均可控制在给定范围内,即本文所设计的制导律在实现多导弹协同攻击时,还可以很好地满足末端攻击角度约束。Cooperative guidance of multiple missiles satisfying terminal impact angle constraints is consid- ered. A suboptimal guidance law is presented using the recently proposed model predictive spread control （MPSC） method and cooperative proportional navigation （CPN） guidance law. The basic principle of the MPSC method is given and the MPSC guidance law is designed on the assumption that the control is considered to be a function of quadratic formulation. The MPSC method requires a control history to begin the algorithmic sequence. Guess control history is computed using the CPN technique, subject to constraint on impact time. A stationary target is attacked by two missiles in the simulation. It is observed from the simulation that the impact time error and terminal impact angle error are within the specified convergence tolerance. The terminal impact angle constraint is well satisfied in salvo attack scenario.

关 键 词：制导 协同制导 模型预测扩展控制(MPSC) 攻击角度约束 攻击时间约束 

分 类 号：V444[航空宇航科学与技术—飞行器设计]