基于零效脱靶量的高精度末制导律设计  

Design of High-precision Terminal Guidance Law Based on the Zero Effort Miss

作　　者：谭丽伟[1] 殷兴良[1] 郭大勇[1] 

机构地区：[1]中国航天科工集团公司二院二部,北京100854

出　　处：《航天控制》2011年第3期3-7,共5页Aerospace Control

摘　　要：提出在大气层外动能拦截器上引入激光测距仪提供距离信息,与导引头信息融合获得速度信息进而估计零效脱靶量(Zero Effort Miss,ZEM),并将其用于末制导。设计的零效脱靶量制导律仅使用一次常规常值力修正,而后以带记忆功能的时变阶梯式参量为门限进行脉冲修正,对拦截器进行制导。该导引律既发挥了常规零效脱靶量制导节省燃料的优点,又具备比例导引高精度的优势,同时开机门限的设定充分考虑了发动机的实际特性,避免了交替对开与重复开启,具有工程实用价值。仿真结果验证了其在精度和燃料消耗方面的性能。The laser rangefinder is proposed to involve as an instrument for exo-atmospheric interceptor to get distance.The velocity can be obtained through information fusion with infrared seeker and then the zero effort miss（ZEM） can be calculated and used to terminal guidance.The terminal guidance law based on ZEM realizes the orbit control by using constant force only one time,and then realizes the pulse control by using memorial time variant stepped parameter as control threshold.The guidance law takes the advantages of both fuel economization in the normal ZEM guidance and high precision in the proportional guidance.According to the realistic characteristics of the orbit control thrustors,the design of the on-off control laws can avoid the repeated turn-on of the thrustors.The simulation results show the validation of the performance of the guidance law on fuel and precision.

关 键 词：零效脱靶量 末制导 记忆时变阶梯门限 节省燃料 高精度 

分 类 号：V448.23[航空宇航科学与技术—飞行器设计]