多约束条件下的最优中制导律设计  

Design of optimal midcourse guidance law with multiple constraints

作　　者：孟克子[1] 周荻[1] 

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150001

出　　处：《系统工程与电子技术》2016年第1期116-122,共7页Systems Engineering and Electronics

基　　金：国家自然科学基金(61174203)资助课题

摘　　要：考虑到三维空间目标-导弹相对运动方程的非线性特性以及中制导段的多约束条件,采用Gauss伪谱法设计了一种多约束条件下的最优中制导律,同时考虑了导弹自动驾驶仪的二阶动态特性。考虑的约束条件包括:交班距离、视线角、视线角速率以及过载指令。性能指标为剩余飞行时间n次方的倒数乘以控制输入的平方的积分。研究结果表明,在性能指标中引入时变权重系数时,虽然消耗的燃料有所增加,但是导弹在满足交班约束条件的同时过载指令能够收敛至零,利于中末制导的顺利交接。In view of nonlinearity of target-missile relative kinematic equations in three-dimensional space and multiple constraints imposed in the midcourse guidance phase,the Gauss pseudospectral method is adopted for the design of the optimal midcourse guidance law with multiple constraints.And the second-order dynamics of the missile autopilot is taken into account.The constraints include handover distance,line-of-sight（LOS）angles,LOS angular rates,and acceleration commands.The performance criterion is the integral of the squared control input multiplied by reciprocal of time-to-go to the power of n.The research results indicate that when time-varying weight coefficient is introduced into the performance criterion,in spite of the increasing fuel usage,the handover conditions are fulfilled while the acceleration commands could converge to zero,which contributes to the smooth transition from midcourse guidance to terminal guidance.

关 键 词：多约束 GAUSS伪谱法 最优中制导律 时变权重系数 

分 类 号：V448.232[航空宇航科学与技术—飞行器设计]