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Minimum-Time Trajectory Optimization of Low-Thrust Earth-Orbit Transfers with Eclipsing

机译:带推力的低推力地球轨道转移的最小时间轨迹优化

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摘要

The problem of determining high-accuracy minimum-time Earth-orbit transfers using low-thrust propulsion with eclipsing is considered. The orbit transfer problem is posed as a multiple-phase optimal control problem where the spacecraft can thrust only during phases where it has line of sight to the sun. Event constraints, based on the geometry of a penumbra shadow region, are enforced between the phases and determine the amount of time spent in an eclipse. An initial guess generation method is developed that constructs a useful guess by solving a series of single-phase optimal control problems and analyzing the resulting trajectory to approximate where the spacecraft enters and exits the Earth's shadow. The single-phase and multiple-phase optimal control problems are solved using an hp adaptive Legendre-Gauss-Radau orthogonal collocation method. To demonstrate the effectiveness of the approach developed in this research, optimal transfer trajectories are computed for two Earth-orbit transfers found in the literature. In addition to the two comparison cases studied, a separate Earth-orbit transfer is examined, and solutions are presented for four different departures dates.
机译:考虑了使用带推力的低推力推进来确定高精度的最短时间地球轨道转移的问题。轨道转移问题是一个多阶段最优控制问题,在该问题中,航天器只能在与太阳视线一致的阶段推力。基于半影阴影区域的几何形状的事件约束在两个阶段之间被强制执行,并确定在蚀中花费的时间量。开发了一种初始猜测生成方法,该方法通过解决一系列单相最佳控制问题并分析所得轨迹来近似估算航天器进入和离开地球阴影的位置,从而构建有用的猜测。使用hp自适应Legendre-Gauss-Radau正交配置方法解决了单相和多相最优控制问题。为了证明本研究方法的有效性,针对文献中发现的两次地球轨道转移计算了最佳转移轨迹。除了研究的两个比较案例外,还检查了单独的地球轨道转移,并提出了四个不同出发日期的解决方案。

著录项

  • 来源
    《Journal of Spacecraft and Rockets》 |2016年第2期|289-303|共15页
  • 作者

    Graham Kathryn F.; Rao Anil V.;

  • 作者单位

    Univ Florida, Dept Mech & Aerosp Engn, Gainesville, FL 32611 USA;

    Univ Florida, Dept Mech & Aerosp Engn, Gainesville, FL 32611 USA;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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