| 一种飞行器最优末制导律研究及仿真 |
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| 引用本文： | 吕永佳,张德才,李挺杉,牟亚军,王宝责. 一种飞行器最优末制导律研究及仿真[J]. 上海航天, 2012, 29(2): 1-6,17 |
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| 作者姓名： | 吕永佳 张德才 李挺杉 牟亚军 王宝责 |
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| 作者单位： | 1. 第二炮兵工程学院,陕西西安710025／中国人民解放军96612部队,河北宣化075100
2. 中国人民解放军96612部队,河北宣化,075100 |
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| 摘 要： | 为使再入飞行器攻击目标时获得最大毁伤效果,基于弹目相对运动方程,并考虑落角等多约束条件,用线性二次型(LQR)最优控制的黎卡提方程,设计了一种新的最优末制导律,并给出了零阶无时延系统的近似表达式。典型弹道和不同约束条件下的仿真结果表明:该末制导律有较优的精确性、有效性和弹道性能。
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| 关 键 词： | 再入飞行器 零阶无时延 最优末制导律 约束条件 有效性 |
Study and Simulation of a Vehicle Based on Optimal Terminal Guidance Law |
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| LU Yong-jia,ZHANG De-cai,LI Ting-shan,MOU Ya-jun,WANG Bao-gui. Study and Simulation of a Vehicle Based on Optimal Terminal Guidance Law[J]. Aerospace Shanghai, 2012, 29(2): 1-6,17 |
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| Authors: | LU Yong-jia ZHANG De-cai LI Ting-shan MOU Ya-jun WANG Bao-gui |
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| Affiliation: | 1.The Second Artillery Engineering College,Xi’an,710025,Shaanxi,China; 2.The Unit 96612 of CPLA,Xuanhua 075100,Hebei,China) |
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| Abstract: | To achieve the maximum damage effect when a reentry vehicle attacked the target,a new optimal terminal guidance law according to the missile-target relative equation was designed in this paper,in which the falling angle and other multi-restraint conditions were considered,and the LQR optimal control Riccati equation was utilized.The approximate expression of the zero-order non-time lag system was given out.The simulation results of the typical trajectory with the different constraint conditions showed that the law proposed had the advantages of accuracy,effectiveness and better trajectory performance. |
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| Keywords: | Reentry vehicle Zero-order non-time lag system Optimal terminal guidance law Restraint condition Effectiveness |
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