基于改进幂次趋近律的壁板振动主动滑模控制

在传统幂次趋近律滑模控制算法中,幂次系数a值的选取尤为关键;若a值过大会导致在滑模函数较小时,控制出现剧烈的抖动;而a值过小会导致整个控制过程衰减速度过慢。针对该问题,构建了一种自适应的幂次系数,形成了改进的基于幂次趋近律滑模控制算法,选择飞机壁板振动模态为研究对象,仿真验证了该算法的可行性;最后通过NI-CompactRIO平台进行了壁板振动控制实验。实验结果表明,针对壁板的第一阶模态,改进的幂次趋近律滑模算法振动抑制效果达到10.59 d B,而传统幂次趋近律滑模算法效果为7.53 d B,提升了3.06 d B。

Active vibration control for aircraft panel based on improved sliding mode algorithm of power reachinglaw

In the traditional power law sliding mode control algorithm, the selection of power coefficient a is especially critical. if a value is too large, it will cause the controller to shake when the sliding mode function is small. If a value is too small, it will lead to the decay rate of the whole control process too slow. An adaptive power coefficient is constructed, then new improved sliding mode control algorithm based on the power convergence law is formed. The mode of vibration of aircraft siding is chosen as the research object, the feasibility and effect of the algorithm is verified by simulation, and finally through the NI-CompactRIO platform for the panel vibration control experiment. The experimental results show that the effect of the improved first-order modal and the improved power-law-free sliding mode algorithm is 10.59 dB, while the traditional power-law approach is 7.53 dB, which is 3.06 dB.