具有末端落角约束的空地导弹滑模变结构制导律设计  

Design of Sliding Model Variable Structure Guidance Law with Terminal Impact Angle Constraints

作　　者：付主木[1,2] 曹晶[1] 王晓红[1] 

机构地区：[1]河南科技大学信息工程学院,河南洛阳471023 [2]山东大学控制科学与工程学院,山东济南250061

出　　处：《信息与控制》2015年第3期291-297,302,共8页Information and Control

基　　金：国家自然科学基金资助项目(61473115;51277116;51375145);国家航空科学基金资助项目(20110142003);中国博士后科学基金资助项目(2013T60670);河南省科技创新人才杰出青年计划资助项目(144100510004)

摘　　要：为了提高制导精度,达到理想的毁伤效果,提出了一种空地制导武器近垂直俯冲攻击制导律.在建立二维平面内弹—目相对运动模型的基础上,将落角约束转化为末端视线角控制问题.针对落点和落角约束条件,设计了一种含有角度误差项、开关项、趋近律和常值量4个制导参数的滑模变结构制导律.分析了4个参数对制导性能的影响,得到了其选取依据.仿真结果表明,所设计的制导律脱靶量近似为0,落角接近90°,与比例导引律相比,脱靶量减小87.43%,落角增大47.01%.To improve guidance precision and to ensure the ideal damage effect, an approximate vertical diving attacking guidance law of air-to-ground weapons is proposed. Based on the relative motion model for a missile and tarset in a two-dimensional plane, the impact angle constraints are transformed to control the terminal line of sight. According to final the position and the impact angle constraints, a sliding model variable structure guidance law that includes four guidance parameters is designed ： the angle error parameter, the switching pa- rameter, the reaching law parameter, and the constant parameter. The basis for the parameters selection is obtained by analyzing the influence of four guidance law parameters on guidance performance. The simulation is demonstrated for the designed guidance law to obtain a near zero miss distance and a 90° impact angle. The miss distance is decreased by 87.43% and the impact angle is increased by 47.01% in comparison with the proportional guidance law.

关 键 词：空地导弹 落角约束 滑模变结构 制导律 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]