Optimal switching strategy for radially accelerated trajectories
Optimal switching strategy for radially accelerated trajectories
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DOI：
10.1007/s10569-009-9233-2
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发表时间：
2009-11
影响因子：
1.6
通讯作者：
A. Quarta;G. Mengali
中科院分区：
文献类型：
--
作者：
A. Quarta;G. Mengali
本文研究了航天器在径向外推力作用下的动力学问题，该推力具有常系数，且可以在适当的时间间隔内打开或关闭。问题是要找到最佳的策略，以保证转移的航天器从初始位置到最终位置在给定的时间间隔内使用最少量的推力水平的可能性。该问题是在一个最佳的框架，使用间接的方法来解决。详细研究了一些不同的使命方案：逃逸任务，飞越任务和会合任务。在后一种情况下，航天器使用混合系统，包括用于最终脉冲机动的高推力推进系统。与连续情况（没有推力调制）相比，最佳切换策略允许大幅降低推力水平。
This paper studies the problem of a spacecraft subject to an outward radial thrust, with constant modulus, that may be switched on or off at suitable time intervals. The problem is to find the optimal strategy to guarantee the possibility of transferring the spacecraft from an initial to a final position in a given time interval using the least amount of thrust level. The problem is solved in an optimal framework, using an indirect approach. A number of different mission scenarios are studied in detail: escape missions, flyby missions and rendezvous missions. In the latter case the spacecraft uses a hybrid system comprising an high thrust propulsion system for the final impulsive maneuver. The optimal switching strategy allows one to substantially decrease the thrust level when compared to the continuous case (without thrust modulation).