摘要
天文导航方法已经成为深空探测必备的导航方法.为了实现对深空探测器的姿态控制,必须准确知道深空探测器当前时刻的姿态.根据深空探测器机载的两个星敏感器跟踪两颗选定的已知恒星,测量出当前时刻相对初始时刻这两个恒星星光矢量在深空探测器机体坐标系中的角度变化量,通过姿态变换矩阵转换和公式推导,给出了确定深空探测器当前时刻姿态角的解析算法,从而为探测器的姿态控制提供准确的姿态数据.通过仿真结果验证了此方法的正确性和有效性.
The astronomical navigation is an essential navigation method for deep space exploration. In order to control attitude of a deep space explorer, the real time attitude must be measured accurately. Using a pair of on-board star sensors to track prescribed two stars, differences of both certain star vectors at current time relative to initial time in the body frame of a deep space explorer are measured. The analytic solution to determine current attitude angles is given by using attitude matrix transformation and formula derivation, therefore accurate attitude data are provided for attitude control of a deep space explorer. The correctness and effectiveness of this method is validated by a simulation result.
出处
《测试技术学报》
2009年第4期350-353,共4页
Journal of Test and Measurement Technology
关键词
深空探测
天文导航
星光矢量
姿态角
解析算法
deep space exploration
astronomical navigation
star vector
attitude angle
analytic solution
