上海航天2012，Vol.29Issue(2)：1-6,17,7.
一种飞行器最优末制导律研究及仿真
Study and Simulation of a Vehicle Based on Optimal Terminal Guidance Law
吕永佳 1张德才 2李挺杉 2牟亚军 2王宝责2
作者信息
- 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
- 折叠
摘要
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.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Key words
Reentry vehicle/Zero-order non-time lag system/Optimal terminal guidance law/Restraint condition/Effectiveness分类
信息技术与安全科学引用本文复制引用
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):1-6,17,7.
