利用姿态测量数据确定卫星初始轨道

提出了一种利用姿态测量数据确定卫星初始轨道的新方法。姿态确定后，根据卫星姿态与位置函数的关系，可确定位置矢量的方向数。采用三个不同时刻的测量值，根据飞行时间定理和几何约束条件，得到卫星轨道的解析方程。利用微分校正法解方程即可得卫星轨道参数，最后对卫星多种姿态及飞行轨道进行了仿真计算，结果显示迭代算法收敛，证明此方法是可行的。

Determining Satellite Initial Orbit with Attitude Data

A new method of determining the satellite initial orbit with attitude data is presented. First, if attitude is known, the direction number of the position vector of satellite can be determined; then equations which satisfy flight time theorem and geometrical constraint condition are derived by use of three different time measurement value; finally the analytical equation used by differential correction is given. For many attitude and orbits, simulation results show that iteration is convergent and this way is feasible.