高空高速飞行器侧向机动制导律研究  

Research on Lateral Maneuvering Guidance Law for High-altitude High-speed Aircrafts

作　　者：彭双春[1] 卜彦龙[1] 潘亮[1] 沈林成[1] 

机构地区：[1]国防科技大学机电工程与自动化学院,长沙410073

出　　处：《系统仿真学报》2010年第8期1857-1861,共5页Journal of System Simulation

基　　金：湖南省自然科学基金(07JJ3127)

摘　　要：提出了一种面向高空高速飞行器的侧向机动能量较优制导律。首先建立了飞行器侧向机动模型,推导了侧向机动能量最优制导律,并进一步得出侧向机动制导律能量最优条件下的初始航向角限定区间;同时证明了CNG(Circular-Navigation-GuidanceLaw)是初始航向角取该区间内特定值时的能量最优制导律,然后基于CNG基本思想,设计了一种针对大范围初始航向角下的侧向机动能量较优制导律。飞行器作侧向机动时,在限定区间内,能耗最优;在限定区间外,能耗次优。理论分析和仿真实验表明所设计制导律在保证能耗较优的同时还具有位置和角度误差小、稳定性好等优点。An energy efficient guidance law for high-altitude high-speed aircraft lateral maneuvering was proposed.Firstly,a lateral maneuvering model was established,and a corresponding optimized energy guidance law was settled,and furthermore,the initial range of heading angle corresponding to optimal energy was deduced.Secondly,circular navigation guidance law（CNG） was proved to be a typical solution which consume optimal energy when its initial heading angle was defined as a certain value in the range acquired above,then basic principle of CNG was used to design an energy suboptimal guidance law suitable to large space lateral maneuvering.When lateral maneuvering,if the initial heading angle is in the defined range,energy consumption is optimized,otherwise,which is suboptimal.Theoretical analysis and simulation experiments show the guidance law proposed is energy-saving,and meanwhile,owns good stability with smaller position error and angle error.

关 键 词：高速飞行器 高空航迹规划 侧向机动 能量优化制导 CNG 

分 类 号：V448[航空宇航科学与技术—飞行器设计] TJ761.6[兵器科学与技术—武器系统与运用工程]