基于外部信息源的临近空间飞行器中制导研究  

Research of Midcourse Guidance Based on External Information Source for Near Space Vehicle

作　　者：呼卫军[1] 杨业[2] 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,西安710072 [2]北京航天自动控制研究所,北京100854

出　　处：《航天控制》2010年第2期23-28,35,共7页Aerospace Control

基　　金：国家自然科学基金重点项目(60736023)

摘　　要：针对用于高超声速巡航飞行器拦截的临近空间飞行器,提出了基于预测校正算法的中制导方法,基于外部预警系统所提供的目标信息,通过对影响末制导段拦截精度的空间交会角分析,给出了中制导虚拟终端目标的生成方法。利用基于单纯形算法的最优化求解算法进行预测校正算法的实现。针对中制导的实现特点,分别建立了适合的目标函数、预测方程和迭代优化算法。最终,通过仿真验证了算法的可行性和有效性,仿真结果标明,对于最大升阻比为2的飞行器,所提出的算法可基于目标的运动实时进行中制导轨迹的调整,到达期望的中制导终端点。最大位置偏差不超过500m,速度偏差小于10m/s,航迹倾角和航迹偏角小于2.5°和3.0°。A predictive guidance algorithm is presented in this paper for near space kill vehicle used for interception ultra speed cruise vehicle.After effect of interception angle on performance of terminal guidance is analyzed,the producing method of virtual midcourse terminal point is given,which is based on the information of target from external information sources.Then a simplex method for resolving optimization problem is adopted to realize the predictive-corrector algorithm.Based on the characteristics of midcourse guidance,corresponding object function,predictive function and iterative optimization algorithms are built.Finally,simulation is used to verify the feasibility and validity of the method presented above.The result shows that the method developed can adjust the trajectory online and meet the required terminal point based on the real time information of target for the vehicle that maximum radio of lift force to drag force is set to two.The errors of location,velocity and flight path angle are respectively less than 500m,10m/s,2.5°and 3.0°.

关 键 词：临近空间飞行器 中制导 预测校正算法 单纯形算法 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]