摘要
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，
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.
出处
《飞行力学》
CSCD
北大核心
1999年第4期38-42,共5页
Flight Dynamics
关键词
姿态测量
初始轨道
微分校正
卫星
Attitude measurement Initial orbit Differential correction
