Spacecraft formation flying near sun-earth L/sub 2/ Lagrange point: trajectory generation and adaptive output feedback control
Spacecraft formation flying near sun-earth L/sub 2/ Lagrange point: trajectory generation and adaptive output feedback control
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DOI：
10.1109/acc.2005.1470327
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发表时间：
2005-06
期刊：
影响因子：
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通讯作者：
Hong Wong;V. Kapila
中科院分区：
文献类型：
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作者：
Hong Wong;V. Kapila
在本文中，我们提出了轨迹生成和自适应输出反馈控制设计方法，以促进航天器在日地 L/sub 2/拉格朗日点附近编队飞行。具体来说，我们通过将引导航天器放置在所需的 Halo 轨道上并将跟随航天器放置在围绕 Halo 轨道的所需准周期轨道上来创建航天器编队。我们开发了随动航天器的非线性动力学；相对于领航航天器，其中领航航天器被假定处于期望的Halo轨道上。此外，我们设计了编队维持控制器，使跟随航天器跟踪所需的轨迹。具体来说，我们设计了一个自适应输出反馈位置跟踪控制器，它提供滤波速度测量和对跟随器航天器的未知质量的自适应补偿。所提出的控制律针对引导器和跟随器航天器对的情况进行了仿真，并被证明可以产生相对位置跟踪误差的半全局渐近收敛。
In this paper, we present a trajectory generation and an adaptive, output feedback control design methodology to facilitate spacecraft formation flying near the Sun-Earth L/sub 2/ Lagrange point. Specifically, we create a spacecraft formation by placing a leader spacecraft on a desired Halo orbit and a follower spacecraft on a desired quasi-periodic orbit surrounding the Halo orbit. We develop the nonlinear dynamics of the follower spacecraft; relative to the leader spacecraft, wherein the leader spacecraft is assumed to be on a desired Halo orbit trajectory. In addition, we design a formation maintenance controller such that the follower spacecraft tracks a desired trajectory. Specifically, we design an adaptive, output feedback position tracking controller, which provides a filtered velocity measurement and an adaptive compensation for the unknown mass of the follower spacecraft. The proposed control law is simulated for the case of the leader and follower spacecraft pair and is shown to yield semi-global, asymptotic convergence of the relative position tracking errors.