二元机翼滑模变结构控制颤振主动抑制

宋晨; 吴志刚; 杨超

二元机翼滑模变结构控制颤振主动抑制

北京航空航天大学航空科学与工程学院, 北京 100191

基金项目: 国家自然科学基金资助项目(90716006, 10902006)

详细信息

中图分类号: V 215.3
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出版历程
- 收稿日期: 2009-10-12
- 网络出版日期: 2010-12-30

Sliding mode variable structure control of flutter suppression for two-dimensional wing

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 颤振主动抑制(AFS,Active Flutter Suppression)是气动弹性综合研究的活跃分支,对飞行器设计具有重要意义.以带后缘控制面的二元机翼为对象,研究滑模控制(SMC,Sliding Mode Control)用于气动弹性AFS的可行性与机理.基于准定常气动力理论建立二元机翼气动弹性系统模型,设计SMC的滑模切换面及状态反馈控制切换函数,以实现受控对象AFS,从相空间状态轨线的角度,阐述SMC使闭环系统稳定的根源.此外,还对SMC的鲁棒性及延时效应做了分析与讨论.研究表明:该控制策略可用于AFS,在气动弹性主动控制方面具有应用前景.
- 气动弹性 /
- 二元机翼 /
- 颤振 /
- 滑模控制 /
- 状态反馈
Abstract: Active flutter suppression (AFS), an attractive branch of aeroelasticity, and playing an important role of aircraft design was conducted on a two-dimensional wing which had a tailing-edge control surface. Sliding mode control (SMC) for AFS and its feasibility were investigated theoretically. The basic equations of motion were established by using quasi-steady aerodynamics forces. A sliding mode surface and a state feedback control for switching were designed in state space to achieve AFS. The principle of system stability provided by the SMC was discussed by state variables trajectory analysis. Further discussions about system robustness and time delay effects were also given. The results indicate that SMC strategy could be used for AFS and has potential usefulness in active aeroelastic control.
- aeroelasticity /
- airfoils /
- flutter /
- sliding mode control /
- state feedback

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参考文献(1)

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