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月地返回轨道存在各种摄动误差,终端约束复杂,有必要对其进行中途修正研究。显式制导法通过二体轨道与精确轨道之间的差别进行多次迭代求解给定时刻所需的修正速度。文章利用显式制导法,采用月球段及地球段分段进行中途修正的策略,给出了基于分段落点预报显式制导的月地返回轨道中途修正方案。该方案无需计算雅克比矩阵,算法简单、计算快速、实用性强,能满足再入点参数要求。算例仿真与蒙特卡洛仿真验证了该方案的适用性。
There are various perturbation errors in the orbit returning to the moon, and the terminal constraints are complicated, so it is necessary to carry out the midway revision research. The explicit guidance method performs multiple iterations through the difference between the two body orbit and the exact orbit to find the required correction velocities for a given moment. In this paper, explicit guidance method is used to make mid-course correction using lunar segment and earth segment, and a mid-way correction scheme for lunar return orbit based on explicit guidance of the segment placement forecast is given. The scheme does not need to calculate Jacobian matrix, the algorithm is simple, the calculation is fast, the practicality is strong, and the parameter requirements of the reentry point can be satisfied. The case study and Monte-Carlo simulation show the applicability of the scheme.