A new geometric guidance approach to spacecraft near-distance rendezvous problem
A new geometric guidance approach to spacecraft near-distance rendezvous problem
复制标题
解决航天器近距交会问题的一种新的几何制导方法
DOI：
10.1016/j.actaastro.2016.09.032
复制
发表时间：
2016
影响因子：
3.5
通讯作者：
Ni Qing
中科院分区：
文献类型：
--
作者：
Meng Yunhe;Chen Qifeng;Ni Qing
对于航天器的近距离交会问题，经典的制导方法如R-bar和V-bar都受到初始相对位置和速度的限制，需要较长的交会时间。本文提出了一种新的基于连续小推力的几何制导方法，该方法避免了对初始状态的限制，大大减少了交会时间，具有较强的鲁棒性。首先，基于经典的微分几何曲线理论，建立了近距离交会的动力学方程，并引入了航天器速度的导数项，利用导数项可以调整航天器的相对速度。在此基础上，通过对视线法向和切向运动的分析，推导出了航天器制导曲率律，并给出了一种导引比和两种速度反馈控制增益。此外，还提出了一种改进的线性二次调节器来改善几何制导的方法，其中交会时间和交会成本可以通过调整“衰减因子”来优化。最后，对制导参数的选取、与滑模法的比较以及考虑测量误差的制导收敛问题进行了数值仿真，证明了几何方法在航天器交会制导问题上的有效性。
For the near-distance rendezvous problem of spacecraft, the classical guidance methods, such as R-bar and V-bar, are restricted by the initial relative positions and velocities and require a long period of time to rendezvous. In this paper, a new geometric guidance approach based on continuous low-thrust, which avoids the restrictions on initial states and decreases rendezvous time dramatically and has the advantages of robustness, is presented. First, based on the classical differential geometric curve theory, the dynamics equation of near-distance rendezvous is presented and a derivative term of spacecraft velocity is introduced, by which the relative velocity can be adjusted. Then, a spacecraft guidance curvature law is derived and one navigation ratio and two velocity feedback control gains are provided based on the analysis of motion in the normal and tangential directions of line-of-sight. Moreover, a method to improve the geometric guidance by using a modified linear-quadratic regulator, in which the time and the cost for rendezvous may be optimized by adjusting a ‘decay factor’, is proposed. Finally, numerical simulations about the selection of guidance parameters, about the comparison with the glideslope method, and about the guidance convergence with measurement errors, which prove the validity of the geometric approach for the rendezvous guidance problem of spacecraft, are presented.