• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>IEEE Congress on Evolutionary Computation >Evolutionary algorithms to optimize low-thrust trajectory design in spacecraft orbital precession mission
【24h】

Evolutionary algorithms to optimize low-thrust trajectory design in spacecraft orbital precession mission

机译：优化航天器轨道进动任务低推力轨迹设计的进化算法

获取原文
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

In space environment, perturbations make the spacecraft lose its predefined orbit in space. One of these undesirable changes is the in-plane rotation of space orbit, denominated as orbital precession. To overcome this problem, one option is to correct the orbit direction by employing low-thrust trajectories. However, in addition to the orbital perturbation acting on the spacecraft, a number of parameters related to the spacecraft and its propulsion system must be optimized. This article lays out the trajectory optimization of orbital precession missions using Evolutionary Algorithms (EAs). In this research, the dynamics of spacecraft in the presence of orbital perturbation is modeled. The optimization approach is employed based on the parametrization of the problem according to the space mission. Numerous space mission cases have been studied in low and middle Earth orbits, where various types of orbital perturbations are acted on spacecraft. Consequently, several EAs are employed to solve the optimization problem. Results demonstrate the practicality of different EAs, along with comparing their convergence rates. With a unique trajectory model, EAs prove to be an efficient, reliable and versatile optimization solution, capable of being implemented in conceptual and preliminary design of spacecraft for orbital precession missions.
机译：在太空环境中，扰动使航天器失去其在太空中的预定轨道。这些不良变化之一是空间轨道的面内旋转，称为轨道进动。为了克服这个问题，一种选择是通过采用低推力轨迹来校正轨道方向。但是，除了作用在航天器上的轨道扰动外，还必须优化与航天器及其推进系统有关的许多参数。本文介绍了使用进化算法（EA）进行的轨道进动任务的轨迹优化。在这项研究中，对存在轨道扰动的航天器动力学进行了建模。根据空间任务根据问题的参数化采用优化方法。在低地球轨道和中地球轨道上已经研究了许多太空任务案例，其中各种类型的轨道扰动作用在航天器上。因此，采用了几种EA来解决优化问题。结果证明了不同EA的实用性，并比较了它们的收敛速度。 EA具有独特的轨迹模型，被证明是一种高效，可靠和通用的优化解决方案，能够在航天器的概念设计和初步设计中用于轨道进动任务。

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