采用打靶法设计考虑地球扁率的机动轨道

Maneuver Trajectory Design with J_2 Correction Based on Shooting Procedure

地球扁率对航天器机动轨道的影响不可忽视,因此研究考虑地球扁率的机动轨道设计方法对实现航天器的快速自主轨道机动是很有意义的。打靶法能够很好的解决两点边值问题,因此可以用来设计机动轨道。在仿真过程中发现,虽然一般情况下打靶法都能够很快收敛,但当地心转移角接近π时却出现发散现象,用卫星工具软件包(STK)、拟平均根数等方法验证了这一现象。通过理论分析找到了在两次冲量转移假设下,考虑地球扁率的机动轨道在地心转移角接近π时对末端边界条件比较敏感的原因,并提出了解决办法。

The perturbation of the earth oblateness on the maneuver orbit is unignorable, so it has sense to investigate the design approach of maneuver trajectory when the earth oblateness is taken into account. The achievement is helpful to implement the fast, autonomous maneuver on the spacecraft. The shooting procedure was chosen in the paper to finish the work because of its good performance in resolving the two-boundary value problem. In the process of numerical simulation, it was found that, although in most cases the iterative arithmetic converged, the shooting procedure diverged when the transfer angle is close to π . Other approaches, like Satellite Tools Kit （STK）, Quasi-Mean Elements Theory etc. , also validated the outcome. Finally, theoretical ma- nipulation verified that under the assumption of two transfer impulses, when the transfer angle is close to π , the maneuver orbit is sensitive to the terminal boundary conditions. Some means are suggested to solve the problem accordingly.