有限推力交会的最省燃料轨迹

Fuel-Optimal Trajectories for Finite-Thrust Rendezvous

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。

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 pa- rameter optimization method. By means of increasing the number of parameters and the iteration of optimization, the parametric so- lution which approaches the continuous optimal solution is derived. The simulation results show the effect of the proposed method.