| 摘要: |
| 针对倾斜转弯高超声速飞行器滚动通道控制中初始误差大，系统参数不确定和干扰严重的问题，基于边界层理论的相关结论，设计了一种自适应的滑模控制方法。该方法采用传统滑模面，避免了积分滑模在大初始误差下导致的大超调。改进的自适应调节律能够逼近系统的参数摄动和干扰上界，保证了整个控制过程的滑模可达性。同时，通过选取合理的参数，能够保证较小的稳态误差。理论分析和仿真结果验证了该方法的有效性。 |
| 关键词: 高超声速飞行器 滚动通道 自适应滑模 切换增益 |
| DOI： |
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| 基金项目: |
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| Adaptive Sliding Mode Control for Roll-channel of Hypersonic Vehicle Based on Boundary Layer Theory |
| JIN Gu-min,XI Yong,CHEN Guang-shan |
| (Shanghai Institute of Spaceflight Control Technology;Shanghai Key Laboratory of Spatial Intelligence Control Technology) |
| Abstract: |
| Due to the large initial errors，uncertainties and disturbances in roll-channel of bank-to-turn hypersonic vehicle，an adaptive sliding mode control rule was introduced based on boundary layer theory.Traditional sliding mode is adopted to avoid the large overshoot when using integral sliding mode.Improved adaptive law can approximate the upper bound of parameter uncertainties and disturbances，which ensures the reachability of the sliding-mode during the whole control process.At the same time，error is controlled to a small extent on the basis of reasonable parameters.Theoretical analysis and simulation results show the effectiveness. |
| Key words: Hypersonic vehicle Roll-channel Adaptive sliding mode Switch-gain |
