比例导引末端区特征与划分  

Critical Guidance Region and Its Characteristics for Proportional Navigation

作　　者：侯明善[1] 

机构地区：[1]西北工业大学自动化学院,西安710072

出　　处：《系统仿真学报》2008年第18期4772-4775,共4页Journal of System Simulation

基　　金：航空基础科学基金(05D53019)

摘　　要：制导末端区是制导系统失稳前一个很短的制导段,制导末端区的正确划分对制导系统设计指标制定和性能分析具有重要意义。基于目标最优机动条件下线性化导弹目标运动学模型,研究了比例导引制导系统在末端区的特性,根据制导系统时间常数和阻尼比变化特征,提出根据制导系统特征参数划分末端区的定义方法,仿真计算表明本文的定义方法是合适的。研究结论对制导系统设计、相关总体指标制定和性能仿真验证具有参考意义。Critical Guidance Region （CGR） is defined as a short guidance phase before the guidance system becomes unstable. In the CGR, the dynamic relationship among missiles and intercepting scenarios will change acutely, and the guidance system characteristics can be validated thoroughly. The main object is to determine CGR in terminal guidance for proportional navigation systems. The system characteristics were first studied based on a speed-type linear kinematics and a first-order missile dynamics. Then, the CGR was defined and its specifications were established. The CGR is depends on effectiveness navigation ratio and the time-constant of missile dynamics. To improve the guidance precision, it is required that the better guidance performance must be ensured in CGR. Examples were also given to demonstrate the results.

关 键 词：比例导引 制导末端区 脱靶量 制导系统 

分 类 号：V448[航空宇航科学与技术—飞行器设计]