方案弹道闭环导引方法稳定性分析  

Analysis on the Stability of Project Trajectory Closed-loop Guidance Law

作　　者：顾健[1] 王亚飞[2] 

机构地区：[1]北京航空航天大学电子信息工程学院,北京100191 [2]江苏自动化研究所,连云港222061

出　　处：《战术导弹技术》2016年第6期71-75,共5页Tactical Missile Technology

摘　　要：针对扰动情况下方案弹道闭环导引系统的稳定性问题,通过推导纵向及横向方案弹道导引律的误差传递关系,得到了速度误差随导弹射程的微分方程,并据此分析了系统的稳定性。结果表明,方案弹道导引方法的稳定性与阻力系数、速度、弹道倾角等因素密切相关,在某些情况下,会出现系统导引回路不稳定的情况,此时,扰动引起的速度误差会随着射程的增大而发散,从而导致导弹无法有效跟踪方案弹道。Focusing on the stability of the project trajectory closed-loop guidance disturbed-system, the error transfer relationship equations of the project trajectory guidance law are derived for the vertical and horizontal movements respectively, then the differential equations of the missile＇s velocity error with the flight range are obtained. Based on the error equations, the stability of the guidance system is analyzed. The results show that the stability of the project trajectory guidance law are closely related to the drag force coefficient, velocity, trajectory angle and some other factors. In some cases, it will be an unstable guide loop system. In this case, the disturbance will cause error radiation as the range increases and induce the missile failing in following the project trajectory.

关 键 词：方案弹道 闭环导引 误差方程 稳定性 

分 类 号：TJ761.3[兵器科学与技术—武器系统与运用工程]