基于改进预测制导的深空撞击探测末制导律  

Deep space impact exploration guidance based on advanced predictive guidance

作　　者：周卫文[1] 崔平远[1] 崔祜涛[1] 

机构地区：[1]哈尔滨工业大学深空探测基础研究中心,黑龙江哈尔滨150001

出　　处：《传感器与微系统》2009年第2期116-120,共5页Transducer and Microsystem Technologies

基　　金：国家"863"计划资助项目(2005AA735080)

摘　　要：考虑到机动时机的选取和最终撞击的精度,针对小天体高速撞击任务的特点,设计了一种改进的末段预测制导律。该制导律引入点位误差椭圆来描述导航精度,并基于撞击器与目标的矢量计算出零控脱靶量,以此作为确定机动时机的指标来驱动预测制导律的执行与误差的校正。通过蒙特卡洛仿真分析表明:使用该制导律的GNC系统在节省燃料的同时,可以提高最终的撞击精度。An advanced predictive guidance law of impacting to small asteroids, which takes time of trajectory correction maneuvers and finally precision into account, is proposed. According to the special characteristics of high speed impact mission, the biases of navigation system is presented using error ellipse in the B-plane coordinate. The zero-effort-miss （ZEM） is obtained through the states of probe and target asteroid. The ZEM with navigation bias is compared to determine the time of execute the guidance law to eliminate the predictive error of impact. The results show that this strategy can not only save the fuel consuming, but also obtain a better precision.

关 键 词：预测制导律 动能撞击 误差椭圆 机动时机 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]