附着小行星的视线制导规律  

LINE-OF-SIGHT GUIDANCE FOR ADHESION ASTEROID

作　　者：崔祜涛[1] 史雪岩[1] 崔平远[1] 李傲霜[1] 

机构地区：[1]哈尔滨工业大学深空探测基础研究中心,哈尔滨150001

出　　处：《空间科学学报》2002年第3期256-260,共5页Chinese Journal of Space Science

基　　金：国防科工委民用航天科研计划资助

摘　　要：提出了一种航天器附着（软着陆）小行星的制导与控制规律.为了保证垂直软着陆,事先规划了满足约束的理想视线与视线角轨迹,通过设计滑模变结构控制器跟踪理想轨迹,实现了在小行星表面垂直软着陆;证明了制导与控制规律的鲁棒性;最后通过数学仿真验证了提出的制导与控制规律的可行性.A guidance and control strategy for attaching a vehicle to a small solar system body is presented. In order to ensure soft-landing, a prescribed line of sight and angle of sight profile satisfying restriction are planned, a sliding mode controller is designed to track the prescribed line of sight and angle of sight profile for safely soft-landing on surface of small asteroid. The robust feature of the close-loop guidance scheme is stressed. Finally, numerical simulations are conducted to verify that the given guidance and control strategy is feasible.

关 键 词：小行星 软着陆 制导与控制 视线角轨迹 航天器 

分 类 号：V476.4[航空宇航科学与技术—飞行器设计]