直升机桨叶形态光纤监测与重建方法研究  

Research on 3D Shape Reconstruction Method of Helicopter Blade

作　　者：吴亚星 曾捷[1] 岳应萍 徐云涛[1] 王云嵩 杨宇[2] 孙阳阳 骆梦醒 WU Ya-xing;ZENG Jie;YUE Ying-ping;XU Yun-tao;WANG Yun-song;YANG Yu;SUN Yang-yang;LUO Meng-xing(State Key Laboratory of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China;Aeronautics Science and Technology Key Lab.of Full Scale Aircraft Structure and Fatigue,Aircraft Strength Research Institute of China,Xi’an 710065,China;Army Engineering University of PLA National Defense Engineering College,Nanjing 210007,China)

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016 [2]中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点实验室,西安710065 [3]陆军工程大学国防工程学院,南京210007

出　　处：《强度与环境》2023年第2期54-59,共6页Structure & Environment Engineering

基　　金：国家自然科学基金(52275536);航空科学基金(2020000902317);直升机旋翼动力学国家级重点实验室基金项目(61422202207)。

摘　　要：针对新研制直升机不同任务模式,实现飞行过程中桨叶形态变化的实时监测与精确调控,对于提升飞行品质与保障飞行安全至关重要。为此,提出了一种基于坐标变换理论与光纤应变感知信息的直升机桨叶形态监测与重建方法,并给出了相应光纤Bragg光栅传感器布局形式。建立了NACA2412桨叶构型有限元模型,根据数值仿真结果,验证了坐标变换理论形态重建效果。在此基础上,构建了基于光纤传感器的直升机桨叶动、静态变形监测与形态重建系统。桨叶整体形态重建均方根平均误差为0.370,桨叶桨尖位移静态变形辨识平均相对误差约为5.754%,动态变形辨识平均相对误差约为7.908%。研究表明,本文所提方法能够为未来智能旋翼形态自适应精确调控提供技术支撑。According to the different mission modes of newly developed helicopter,it is very important to realize the real-time monitoring and accurate regulation of blade shape changes in the flight process for improving flight quality and ensuring flight safety.Therefore,a helicopter blade shape monitoring and reconstruction method based on coordinate transformation theory and optical fiber strain sensing information is proposed,and the layout of the corresponding optical fiber Bragg grating sensor is given.The finite element model of NACA2412 blade configuration is established.According to the numerical simulation results,the shape reconstruction effect of coordinate transformation theory is verified.On this basis,a helicopter blade dynamic and static deformation monitoring and shape reconstruction system based on optical fiber sensor is constructed.The average relative error of static deformation identification of blade tip displacement is about 5.754%,and the average root mean square error of blade overall shape reconstruction is 0.370.The average relative error of dynamic deformation identification is about 7.908%.The research shows that the proposed method can provide technical support for the adaptive and accurate control of smart rotor configuration in the future.

关 键 词：坐标变换理论 直升机桨叶 光纤BRAGG光栅传感器 

分 类 号：TP212[自动化与计算机技术—检测技术与自动化装置] V275.1[自动化与计算机技术—控制科学与工程]