...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Optimal Control Applications and Methods >Adjoints estimation methods for impulsive Moon-to-Earth trajectories in the restricted three-body problem
【24h】

Adjoints estimation methods for impulsive Moon-to-Earth trajectories in the restricted three-body problem

机译：约束三体问题中冲动月地轨迹的伴随估计方法

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A study of optimal impulsive Moon-to-Earth trajectories is presented in a planar circular restricted three-body framework. Two-dimensional return trajectories from circular lunar orbits are considered, and the optimization criterion is the total velocity change. The optimal conditions are provided by the optimal control theory. The boundary value problem that arises from the application of the theory of optimal control is solved using a procedure based on Newton's method. Motivated by the difficulty of obtaining convergence, the search for the initial adjoints is carried out by means of two different techniques: homotopic approach and adjoint control transformation. Numerical results demonstrate that both initial adjoints estimation methods are effective and efficient to find the optimal solution and allow exploring the fundamental tradeoff between the time of flight and required V. Copyright (c) 2014 John Wiley & Sons, Ltd.
机译：在平面圆形受限三体框架中研究了最佳脉冲月地轨迹。考虑圆形月球轨道的二维返回轨迹，最优化的标准是总速度变化。最优条件由最优控制理论提供。应用基于牛顿法的程序解决了最优控制理论的应用所引起的边值问题。由于难以获得收敛性，因此通过两种不同的技术进行初始伴随的搜索：同位方法和伴随控制变换。数值结果表明，两种初始伴随估计方法都是有效且高效的方法，可以找到最优解，并且可以探索飞行时间与所需飞行时间之间的基本权衡。版权所有（c）2014 John Wiley＆Sons，Ltd.。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号