论文部分内容阅读
针对中低轨近圆轨道卫星无源探测的空间飞行器主动段轨道进行定位估计和研究.根据观测卫星的简化运动方程,通过变步长欧拉折线法计算出09号观测卫星在各观测时刻的三维位置.进而通过建立几何定位模型和双星同步定位模型计算出观测点的位置参数,根据12态线性多项式拟合模型,建立状态转移矩阵,利用待定系数法建立优化模型,给出主动段目标初值估计,综合运用目标跟踪算法,演化出主动段任意时刻的状态参数,由几何定位算法与双星同步定位的结果比较可知,总体最大误差保持在1.24%以内.在仅考虑双星同步定位的情况下,根据双星同步定位算法,利用双星与空间飞行器应处同一平面的约束条件,建立优化模型,计算出两颗观测卫星的系统误差估计结果d_θ,d_α,d_β.
Aiming at the positioning estimation and research of the active orbit of a spacecraft with orbital orbital satellite passive detection, according to the simplified equation of motion of the observing satellite, the numbering observation satellite No. 09 Then the position parameters of the observation points are calculated by establishing the geometric positioning model and the binocular synchronization positioning model. Based on the 12-state linear polynomial fitting model, the state transition matrix is established, and the optimal model is established by using the undetermined coefficient method. Value estimation, the target tracking algorithm is used synthetically to evolve the state parameters of the active segment at any moment. Comparing the results of the geo-location algorithm and the binary satellite synchronization, the maximum overall error remains within 1.24% .By considering the simultaneous positioning of binary stars According to the binocular synchronization algorithm, the optimization model is established by using the constraints that the binary spacecraft and the spacecraft should be in the same plane. The system error estimation results d_θ, d_α and d_β of two observation satellites are calculated.