The invention relates to a method for determining an orbital element reachable set of an electric propulsion spacecraft, and belongs to the field of spacecraft orbital dynamics and control. The method comprises the following steps: firstly, establishing a low-thrust instantaneous orbital element optimal control model under fuel constraint and a low-thrust average orbital element optimal control model considering environmental perturbation, then taking a two-dimensional reachable set of any orbital element binary combination as a to-be-determined reachable set, and in a state space, carrying out optimal control on the two-dimensional reachable set; solving a point on the boundary of the reachable set to be determined as a starting point, taking the terminal state under the track-free maneuvering condition as a reference point, taking the direction of the reference point pointing to the starting point as a reference direction, and constructing a homotopy with a clockwise or anticlockwise direction angle relative to the reference direction as a homotopy parameter; the reachable set boundary under the instantaneous orbital element and the average orbital element is obtained by tracking the homotopy path, and the reachable set of the orbital elements of the electric propulsion spacecraft is determined. The method has the advantages of being wide in applicability, accurate in solution, efficient in calculation, easy and convenient to implement and the like.
本发明涉及一种电推进航天器的轨道根数可达集确定方法,属于航天器轨道动力学与控制领域。本发明首先建立燃料约束下的小推力瞬时轨道根数最优控制模型,以及考虑环境摄动的小推力平均轨道根数最优控制模型,然后将任意轨道根数二元组合的二维可达集作为待确定的可达集,在状态空间中,求解待确定可达集边界上的一点作为起始点,将无轨道机动情况下的终端状态作为参考点,以参考点指向起始点的方向为参考方向,构建以相对参考方向顺时针或逆时针方向角为同伦参数的同伦,通过跟踪同伦路径得到瞬时轨道根数和平均轨道根数下的可达集边界,实现对电推进航天器的轨道根数可达集的确定。本发明具有适用性广、求解精确、计算高效、实现简便等优点。
Method for determining orbital element reachable set of electric propulsion spacecraft
一种电推进航天器的轨道根数可达集确定方法
2024-01-30
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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