Station-keeping for a solar sail during lander/probe deployment using feedback control
Station-keeping for a solar sail during lander/probe deployment using feedback control
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DOI：
10.1016/j.actaastro.2022.09.005
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发表时间：
2022-09
影响因子：
3.5
通讯作者：
Iain Moore;M. Ceriotti;C. McInnes
中科院分区：
文献类型：
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作者：
Iain Moore;M. Ceriotti;C. McInnes
由于其无推进剂的性质，太阳帆可以为高能量使命提供主要的推进系统，例如多个小行星会合。到达小行星后，通常需要与物体表面进行互动，例如进行样本提取。从太阳帆上展开着陆器的困难在于，在分离点上，系统动力学会发生瞬时的、有时是相当大的变化。本文研究了在释放多个“ChipSat”探测器以及一个大型MASCOT型着陆器和控制帆进入平衡点或周期轨道的位置保持期间改变帆性能的影响。在一种情况下，释放20个ChipSat探测器，每次释放之间间隔一小时。然后控制帆以保持帆船接近初始部署点。线性二次型调节器（LQR）的性能进行比较，保持一个固定的帆姿态后部署。在第二种情况下，在较大的MASCOT型着陆器的分离点，帆特征加速度将有相当大的瞬时变化，而不是小的ChipSat探测器交错部署的逐渐小的变化。仿真结果表明，采用时滞反馈控制方法可以有效地控制展开后的轨道。当从较低和较高倾角轨道进行部署时，帆收敛到相空间的相同区域中的轨道。
Due to its propellantless nature, a solar sail can provide the primary propulsion system for a high energy mission, such as that of a multiple asteroid rendezvous. Upon arrival at an asteroid, it is often desirable to interact with the surface of the body, such as for sample extraction. The deployment of a lander from a solar sail carries the difficulty of an instantaneous, and sometimes considerable, change to the system dynamics at the point of separation. This paper investigates the effects of changing sail performance during the release of multiple “ChipSat” probes as well as a large MASCOT-type lander and the control of the sail into a positional hold at an equilibrium point or periodic orbit. In one scenario, 20 ChipSat probes are released, with one-hour spacing between each release. The sail is then controlled to maintain the sailcraft close to the initial deployment point. The performance of a Linear Quadratic Regulator (LQR) is compared with maintaining a fixed sail attitude after deployment. In a second scenario, at the point of separation of the larger MASCOT-type lander, there will be a considerable instantaneous change in the sail characteristic acceleration, as opposed to the gradual small change for the staggered deployment of the small ChipSat probes. It is shown that the Time-Delayed Feedback Control (TDFC) method is effective in controlling the orbit of the sail after this deployment. The sail converges to an orbit in the same region of phase space when deployment is made from both a lower and higher inclination orbit.