首页> 外文期刊>Journal of the Franklin Institute >Robust orbital transfer for low earth orbit spacecraft with small-thrust
【24h】

Robust orbital transfer for low earth orbit spacecraft with small-thrust

机译:小推力低地球轨道航天器的稳健轨道转移

获取原文
获取原文并翻译 | 示例
       

摘要

This paper studies the problem of robust orbital control for low earth orbit (LEO) spacecraft rendezvous subjects to the parameter uncertainties, the constraints of small-thrust and guaranteed cost during the orbital transfer process. In particular, the rendezvous process is divided into in-plane motion and out-plane motion based on C-W equations, and the relative motion models with parameter uncertainties are established. By considering the property of null controllable with vanishing energy (NCVE), the problem of orbital transfer control with small thrust and bounded control cost is proposed. A new Lyapunov approach is introduced, and the controller design problem is cast into a convex optimization problem subjects to linear matrix inequality (LMI) constraints. With the obtained controller, the orbit transfer process can be accomplished with small thrust and the control cost has an upper bound simultaneously. Different possible initial states of the transfer orbit are also analyzed for the controller design. An illustrative example is provided to show the effectiveness of the proposed control design method, and the different performances caused by different initial states of the transfer orbit are illustrated.
机译:本文针对低地球轨道(LEO)航天器交会对象在轨道转移过程中参数不确定性,小推力约束和保证成本等问题,研究了鲁棒轨道控制问题。特别地,基于C-W方程将交会过程分为平面内运动和平面外运动,并建立了具有参数不确定性的相对运动模型。考虑到零能量可控的性质,提出了推力小,控制成本有限的轨道转移控制问题。引入了一种新的Lyapunov方法,并将控制器设计问题转化为受线性矩阵不等式(LMI)约束的凸优化问题。利用所获得的控制器,可以以较小的推力完成轨道转移过程,并且控制成本同时具有上限。还针对控制器设计分析了传输轨道的不同可能的初始状态。提供了一个说明性示例,以显示所提出的控制设计方法的有效性,并说明了由转移轨道的不同初始状态引起的不同性能。

著录项

  • 来源
    《Journal of the Franklin Institute》 |2010年第10期|p.1863-1887|共25页
  • 作者

    Xuebo Yang; Huijun Gao; Peng Shi;

  • 作者单位

    Space Control and Inertial Technology Research Center, Harbin Institute of Technology, Harbin 150001, China;

    Space Control and Inertial Technology Research Center, Harbin Institute of Technology, Harbin 150001, China;

    Department of Computing and Mathematical Sciences, University of Glamorgan, Pontypridd CF37 1DL, United Kingdom;

  • 收录信息
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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