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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。
In order to improve the rapid, maneuver counterattack capability and shooting accuracy of the new generation of ballistic missiles, star / inertial combination guidance is the best choice. This dissertation gives the key technologies of star map matching guidance system based on binary star sensor. In this paper, the design of navigation satellite table based on ballistic trajectory is proposed, which greatly simplifies the missile surface asteroid. A convex polygon algorithm suitable for star guidance is proposed, which can reduce the number of matched star diagonals reasonably. These two technologies ensure the practicability of star matching guidance technology. A method of separating initial position, orientation error and platform drift error is proposed. The convex polygon star recognition algorithm can obtain the instantaneous position of many stars at the same time. Combining the position of the star at the home plane can solve the triaxial attitude of the inertial system at the equatorial inertia and the launch point. Finally, Positioning, orientation error mathematical expression. Simulation results show the effectiveness of the method.