摘要
根据弹道导弹飞行时间短,飞行姿态相对稳定的特性,提出了一种弹载导航星表的设计方法。分析了导弹飞行轨迹投影的特点,其在天球上投影为大圆,在地心惯性坐标系XOY平面上的投影为椭圆,并对飞行轨迹进行分类。根据限制条件,确定出星敏感器扫描的视场区域,挑选出视场中的恒星,构建出弹载导航星表,并与传统的三角形星表进行比较。仿真结果表明,该方法简单、易行,存储容量较小,同时避免了在两极的情况下,赤经难以表示的问题。减少了星图识别时间,提高了星光制导的数据输出率,满足了星光制导在弹道导弹上应用的要求。
Based on the flight character of ballistic missile with short flight time and relatively steady flight attitude,a design method for the guide catalog of missile is proposed.The feature of projection of missile flight path is analyzed,which is a great circle in celestial sphere and an ellipse in XOY coordinate planes of the earth-centered inertial coordinate,and also the flight path is classified.Based on constraint conditions,the field of view（FOV） of star sensor is determined,the stars in FOV are selected,and the guide catalog of missile is constructed and compared with traditional triangle catalog.The simulation shows that the method is simple,easy and small in storage capability.The problem which the right ascension is difficulty to express under tow-pole conditions is also is resolved by the method.In addition,the time for star map identification is reduced,the data output rate is enhanced,and the demand for application of stellar guidance placation to ballistic missile is satisfied.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2011年第9期1895-1901,共7页
Journal of Astronautics
基金
"十一五"预研项目(51309060302)
关键词
弹载导航星表
星光制导
投影
设计与实现
Guide star catalog of missile
Stellar guidance
Projection
Design and implementation
