星图匹配制导中的关键技术  

Star Pattern Matching for Celestial Guidance

作　　者：刘朝山[1] 马瑞萍[2] 肖称贵 刘光斌[1] 

机构地区：[1]第二炮兵工程学院,西安710025 [2]海军潜艇学院,青岛26607 [3]北京航天自动控制研究所,北京100854

出　　处：《宇航学报》2006年第1期31-35,共5页Journal of Astronautics

摘　　要：为了提高新一代弹道导弹的快速、机动反击能力和射击精度,采用星光／惯性组合制导是最佳的选择。本论文给出了基于双星敏感器的、星图匹配制导系统的关键技术。提出了根据弹道设计导航星表,极大地简化了弹载星表；提出了一种适用于星光制导的凸多边形算法,合理地减少了匹配的星对角距数目。这两项技术保证了星图匹配制导技术的实用性。提出了一种分离初始定位、定向误差及平台漂移误差方法。采用凸多边形的星图识别算法可同时获得多颗星的瞬时位置,结合恒星在傢平面的位置可解算导弹在赤道惯性系和发射点惯性系的三轴姿态,最后,给出了导弹初始定位、定向误差的数学表达式。仿真结果表明了该方法的有效性。To improve the precision of hitting the target and to launch quickly and movably, the technique of double star sensors and patterns matching for celestial guidance of ballistic missile was adopted. As the star sensor in ballistic missile worked only for short time, the generation of the different reference catalog of stars was presented according to different trajectories. The star pattern identification algorithm based on convex polygon with star magnitudes - independent was adopted to obtain multi-stars positions, it suitably reduced the matched numbers of star couple. Those stars were used to calculate the missile attitude in the Celestial Reference Frame （CRF）. The missile attitude in the Launch Inertial Coordinate Frame （HCF） is computed in terms of the relationship between the CRF and LICF. The initial localization .and orientation errors models are formulated from the matrix of attitudes. The simulation results show the method is valid.

关 键 词：制导 星敏感器 弹载星表 星图匹配 三轴姿态 初始定位定向误差 

分 类 号：V448[航空宇航科学与技术—飞行器设计]