The invention discloses an observation configuration constrained low-thrust collision avoidance prediction guidance method, and belongs to the technical field of satellite constellations. The implementation method comprises the following steps of: considering a group of satellites in an orbit plane of a satellite network, and calculating the maximum distance and the minimum distance between adjacent satellites on the same orbit plane, which can meet the requirement of continuous earth coverage, according to the minimum coverage elevation angle and the orbit height of the satellites; according to the constellation configuration keeping requirement of an orbit plane, the maximum phase deviation of the satellite is given, the boundary condition, the path constraint condition and the control constraint condition of prediction guidance are determined, and a dynamic model of the low-orbit earth satellite is established. A Gaussian pseudo-spectral method is adopted to discretize a continuous trajectory optimization problem into a nonlinear programming problem, a sequential quadratic optimization method is adopted to carry out burnup optimal low-thrust collision avoidance trajectory optimization, a burnup optimal trajectory is used as a waypoint sequence for subsequent prediction guidance, a real-time prediction correction algorithm is adopted to guide waypoints, and the waypoint sequence is optimized. And the accumulative error of orbit prediction is reduced.
本发明公开的观测构型约束的小推力碰撞规避预测制导方法,属于卫星星座技术领域。本发明实现方法为:考虑卫星网络一个轨道平面内的一组卫星,根据卫星最小覆盖仰角和轨道高度,计算出同一轨道平面上相邻卫星之间能够满足对地连续覆盖的最大距离和最小距离。根据轨道平面的星座构型保持要求,给出卫星的最大相位偏差,确定预测制导的边界条件、路径约束条件和控制约束条件,并建立低轨地球卫星的动力学模型。采用高斯伪谱法将连续轨迹优化问题离散为非线性规划问题,采用序列二次优化方法进行燃耗最优小推力碰撞规避轨迹优化,将燃耗最优轨迹作为后续预测制导的航路点序列,并采用实时预测校正算法对航路点进行制导,降低轨道预测的累积误差。
Small-thrust collision avoidance prediction guidance method based on observation configuration constraint
观测构型约束的小推力碰撞规避预测制导方法
2024-02-27
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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