基于部分微分方程的轨道上的灵活航天器的积极控制
PloS one
|September 10, 2025
概括
这项研究引入了一种新的控制方法,用于灵活地抑制航天器的振动. 先进的控制器显著减少了沉降时间和超速,提高了航天器的稳定性和在具有挑战性的太空任务中的性能.
科学领域:
- 航空航天工程 航空航天工程
- 控制系统理论 控制系统理论
- 应用数学 应用数学 应用数学
背景情况:
- 灵活的航天器需要精确的振动抑制才能使任务成功,特别是在复杂的机动或在外部干扰的情况下.
- 现有的控制方法经常与输入约束和不可预测的外部力量作斗争,限制了动态空间环境中的性能.
研究的目的:
- 开发和验证一个先进的控制策略,以有效地抑制灵活的航天器系统中的振动.
- 为了应对外部干扰和输入限制在航天器态度控制和深空探索中所带来的挑战.
主要方法:
- 使用汉密尔顿原理推导航天器动力学,从而得到一个局部微分方程 (PDE).
- 设计一个包含纳斯姆功能和干扰观察器的后退控制器,以处理输入约束和外部干扰.
- 利用利亚普诺夫稳定理论来保证系统稳定性,并选择最佳控制参数.
主要成果:
- 数字模拟表明,与传统的比例导数 (PD) 控制相比,结算时间 (通过[公式:参见文本]) 和峰值超标 (通过[公式:参见文本]) 显著减少.
- 拟议的控制器有效地抑制振动,并在具有挑战性的条件下提高系统稳定性.
- 验证控制器在提高灵活航天器动态性能方面的优势.
结论:
- 开发的控制方案为灵活的航天器中抑制振动提供了强大而高效的解决方案.
- 这种方法显著提高了航天器的性能和稳定性,显示了先进太空任务的潜力.
- 控制器处理干扰和约束的能力使其适合用于诸如深空探索和卫星态度控制等苛刻的应用.
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