抗解时间变化的滑动模式控制与任意收时间对刚性航天器的时间
IEEE transactions on cybernetics
|February 18, 2026
概括
这项研究为刚性航天器提供了一种新的姿态机动控制,使得任意的收时间成为可能. 新的控制法确保了稳定性,并避免了放松现象.
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
背景情况:
- 太空飞船的态度控制对于任务的成功至关重要.
- 实现准确和快速的态度机动,保证稳定是一个持续的挑战.
研究的目的:
- 为刚性航天器开发一种新的态度机动控制法.
- 为了实现任意的趋同时间来稳定态度.
- 为了防止航天器态度控制中的不良解现象.
主要方法:
- 设计一个时间变化的滑动模式函数,使用一块指数函数.
- 基于设计的滑动模式功能的态度控制规律的开发.
- 对系统稳定性和收性质的分析.
主要成果:
- 拟议的控制法确保闭环态度系统状态从最初的时间保持在滑动模式表面上.
- 向原点的态度收是在任意预设的时间内实现的.
- 建议的控制策略有效地避免了解现象.
结论:
- 开发的态度控制法提供了对航天器机动的精确和灵活的控制.
- 该方法提供了一个可靠的解决方案,可以实现所需的融合时间,同时确保稳定性.
- 这种方法提高了航天器态度控制系统的可靠性和性能.
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