Fast solar sail rendezvous mission to near Earth asteroids

Fast solar sail rendezvous mission to near Earth asteroids
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前往近地小行星的快速太阳帆交会任务

DOI:
10.1016/j.actaastro.2014.08.023
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发表时间:
2014-12
期刊:
影响因子:
3.5
通讯作者:
Li, Junfeng
Li, Junfeng
中科院分区:
工程技术3区
文献类型:
--
作者:
Zeng, Xiangyuan;Gong, Shengping;Li, Junfeng

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以双曲线发射超速为设计参数,提出了近地小行星快速太阳帆交会任务的概念。在引入双曲线超速的初始约束后,导出了时间最优控制框架并使用间接方法求解。首先研究共面圆形轨道交会场景,以评估传输时间相对于不同双曲超速度和太阳帆特征加速度的变化趋势。采用参数化方法研究了小行星轨道倾角和偏心率对转移时间的影响。通过数值模拟确定双曲线超速度的最佳方向和大小。共面圆形场景的发现结果在燃料消耗方面与相同飞行时间但不使用太阳帆的相应双脉冲转移进行了比较。讨论了所需的双曲线超速度和可实现的飞行时间之间的燃料消耗权衡。特定太阳帆所需的总发射质量以分析形式得出。提出了一个实际的任务应用,通过使用太阳帆与所提供的双曲线超速来与小行星 99942 阿波菲斯会合。
The concept of fast solar sail rendezvous missions to near Earth asteroids is presented by considering the hyperbolic launch excess velocity as a design parameter. After introducing an initial constraint on the hyperbolic excess velocity, a time optimal control framework is derived and solved by using an indirect method. The coplanar circular orbit rendezvous scenario is investigated first to evaluate the variational trend of the transfer time with respect to different hyperbolic excess velocities and solar sail characteristic accelerations. The influence of the asteroid orbital inclination and eccentricity on the transfer time is studied in a parametric way. The optimal direction and magnitude of the hyperbolic excess velocity are identified via numerical simulations. The found results for coplanar circular scenarios are compared in terms of fuel consumption to the corresponding bi-impulsive transfer of the same flight time, but without using a solar sail. The fuel consumption tradeoff between the required hyperbolic excess velocity and the achievable flight time is discussed. The required total launch mass for a particular solar sail is derived in analytical form. A practical mission application is proposed to rendezvous with the asteroid 99942 Apophis by using a solar sail in combination with the provided hyperbolic excess velocity.
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