直升机结构响应自适应双陷波多频控制  

Adaptive dual-notch multi frequency control of helicopter structural response

作　　者：沈晓宇 宋来收[1] 夏品奇[1] SHEN Xiaoyu;SONG Laishou;XIA Pinqi(National Key Laboratory of Helicopter Aeromechanics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机动力学全国重点实验室,江苏南京210016

出　　处：《振动工程学报》2025年第4期761-767,共7页Journal of Vibration Engineering

基　　金：国家自然科学基金青年科学基金项目(51505214)。

摘　　要：高效的控制算法是提升直升机减振性能的关键,本文针对直升机振动的多阶频率特征,构建自适应陷波响应分离器和控制器,建立直升机结构响应自适应双陷波控制算法,陷波响应分离器分离控制误差响应中的各阶频率成分,结合陷波控制器实现时域中对各阶频率响应的独立控制。基于某直升机动力学相似模型,对自适应双陷波控制进行了仿真分析和试验研究,结果表明自适应双陷波控制算法在多频率激励条件下具有良好的控制性能和更快的收敛速度,并能提升临界收敛步长,从而增强控制系统鲁棒性。Control algorithm is a key factor to improve the performance for reducing helicopter vibration.In this paper,according to the multi-frequency characteristics of helicopter vibration,both the response separator and controller are constructed utilizing the adaptive notch filter to establish the adaptive dual-notch control of helicopter structural response.The response separator separates each frequency component from the error response to update the control input of each harmonic independently in time domain.Utilizing a dynamic similarity model of helicopter airframe,simulations and experimental studies of the proposed adaptive dual-notch control algorithm are carried out.The results show that the adaptive dual-notch control algorithm has good control performance and faster convergence rate under the multi-frequency excitations,and it can enhance the robustness of active vibration control system by increasing the critical convergence step size.

关 键 词：直升机 结构响应主动控制 自适应双陷波器算法 试验研究 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计] TB535[理学—物理]