摘要
利用非线性规划方法研究了航天器的有限推力最优交会问题。这种方法利用了近年来发展起来的直接优化技术,用分段多项式来表示整个轨道的状态和控制向量,将最优控制问题转化为非线性规划问题。在应用这种方法时,先将整个轨道分为若干推力段和无推力段,然后利用配置方法产生推力段的约束段,利用状态转移矩阵来产生无推力段的约束。最后,对共面轨道情况下的交会进行了数值仿真,验证了方法的有效性和鲁棒性。
Spacecraft optimal rendezvous is studied using nonlinear programming method. A recently developed direct optimization technique is employed, which uses a piecewise polynomial representation for the state and controls, thus converting the optimal control problem into a nonlinear programming one. When using the method, the whole orbit is separated to thrust arcs and nonthrust arcs, then the collocation method is used to produce the constraints of thrust arcs, and state transition matrix is applied to producing the constraints of nonthrust arcs. At last, the simulation of coplanar rendezvous verifies the effectiveness and robustness of the method.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2003年第5期9-13,共5页
Journal of National University of Defense Technology
