有限推力交会的最省燃料轨迹

给出了航天器有限推力交会的最省燃料轨迹。首先应用三角变换技术将推力约束转化为没有任何约束的虚拟控制,进而利用直接优化方法,应用参数化控制方法以及强化技术将控制向量表示为分段常值函数,将上述最优控制问题转化为非线性规划问题。应用经典的参数优化方法即可求得最优控制律的一个近似解,通过增加参数个数,重复优化得到逼近连续最优解的参数化解。仿真结果表明提出的控制方案是行之有效的。

Fuel-Optimal Trajectories for Finite-Thrust Rendezvous

Spacecraft fuel-optimal trajectories for finite-thrust are developed. Firstly, thrust constraints are transferred into the auxiliary controls without any constraints and then the auxiliary controls are represented as the piece-wise constant value based on the control parametrization method in conjunction with enhancing technique. Optimal control problem is converted into a nonlinear programming one by direct optimization technique. An approximate solution of optimal control law can be obtained by classical parameter optimization method. By means of increasing the number of parameters and the iteration of optimization, the parametric solution which approaches the continuous optimal solution is derived. The simulation results show the effect of the proposed method.