【作者】 李健；

【导师】 张雷；

【作者基本信息】 山东大学 ， 控制工程（专业学位）， 2025， 硕士

【摘要】 大展弦比机翼作为现代飞行器的重要结构部件,不仅能提高飞行器航程,还能有效减少诱导阻力,提升飞行器机动性和稳定性。在服役过程中,大展弦比机翼相较于常规机翼更容易出现变形和载荷分布不均匀,导致局部受力过大,进而造成载荷集中和异常变形,不仅严重影响了挂载设备的对准精度,而且对飞行器的飞行安全产生重大威胁。因此,实时监测机翼结构载荷分布和变形特征显得尤为重要。但是,现有研究主要将机翼结构等效为梁、板等简单结构进行分析,在复杂载荷作用条件下难以准确反映机翼结构真实受力与变形特性。为此,本文以大展弦比非对称机翼结构为对象,围绕载荷识别与变形监测相关原理、关键技术及实验验证等方面展开研究,主要内容包括以下方面:(1)机翼结构力学特性与仿真分析。首先,根据机翼结构的功能特点,分析了结构在服役过程中承受的载荷类型及特点;然后,构建了机翼结构有限元模型,并根据结构特点进行了网格划分和边界约束;最后,结合机翼结构特性及其服役过程中的受力情况,开展了单载荷、双载荷和分布式载荷等典型载荷工况下的力学仿真分析。(2)机翼结构应变监测系统设计与构建。首先,分析了光纤光栅传感器的结构与工作原理;然后,根据机翼结构特点及其监测需求,明确了机翼结构应变监测系统整体设计框架;最后,根据结构的力学仿真分析结果,设计传感器网络布置方案,搭建了机翼结构应变监测系统,实现了对机翼结构应变信号的采集、传输、存储及显示。(3)机翼结构载荷识别方法研究与验证。首先,提出了基于载荷-应变线性叠加的载荷识别方法;然后,根据机翼在实际服役时的典型受力情况,设计了单载荷、双载荷和分布式载荷等典型工况进行仿真验证,结果验证了方法在不同工况下的准确性;最后,搭建载荷识别实验系统开展实验验证,结果验证了方法在实验工况下的可靠性和准确性。(4)机翼结构变形重构方法研究与验证。首先,提出了基于载荷-应变线性叠加的变形重构方法;然后,利用有限元模型,开展典型工况下的仿真验证,并与传统的基于曲率重构的变形重构方法对比,结果表明,该方法能够准确的重构出典型载荷下机翼结构变形;最后,搭建机翼结构变形重构实验系统开展实验验证,结果表明,该方法在实际工况下能够准确重构结构变形,进一步验证了方法在实际工程应用中的有效性。本文针对机翼结构载荷与变形监测需求,提出了基于载荷-应变线性叠加的载荷识别与变形重构方法,依据光纤光栅应变检测原理搭建了实验系统,并开展了单载荷、双载荷和分布式载荷等典型载荷工况下的仿真验证与实验验证,验证了方法准确性及实际工程应用中的可靠性,为飞行器的结构健康监测提供了有力的技术支持。更多还原

【Abstract】 As an important structural component of modern aircraft,the wing with a large aspect ratio can not only increase the range of the aircraft,but also effectively reduce induced drag and enhance the maneuverability and stability of the aircraft.During service,large aspect ratio wings are more prone to deformation and uneven load distribution compared to conventional wings,resulting in excessive local force,which in turn leads to load concentration and abnormal deformation.This not only seriously affects the alignment accuracy of the mounted equipment but also poses a significant threat to the flight safety of the aircraft.Therefore,real-time monitoring of the load distribution and deformation characteristics of the wing structure is particularly important.However,the existing research mainly equivalently analyzes the wing structure as simple structures such as beams and plates,and it is difficult to accurately reflect the true force and deformation characteristics of the wing structure under complex load conditions.Therefore,this paper takes the large aspect ratio asymmetric wing structure as the research object and conducts the principle,technology and experimental research on wing structure load identification and deformation monitoring.The main research contents include:(1)Mechanical Characteristics and Simulation Analysis of Wing Structure.Firstly,based on the functional characteristics of the wing structure,the types and characteristics of the loads borne by the structure during its service were analyzed;Then,a finite element model of the wing structure was constructed,and meshing and boundary constraints were carried out according to the structural characteristics.Finally,combined with the structural characteristics of the wing and the force conditions during its service process,mechanical simulation analyses under typical load conditions such as single load,double load and distributed load were carried out.(2)Design and Construction of Wing Structure Strain Monitoring System.Firstly,the structure and working principle of the fiber Bragg grating sensor were analyzed;Then,based on the characteristics of the wing structure and its monitoring requirements,the overall design framework of the wing structure strain monitoring system was clarified;Finally,based on the mechanical simulation analysis results of the structure,the layout scheme of the sensor network was designed,and the strain monitoring system of the wing structure was built,achieving the collection,transmission,storage and display of the strain signals of the wing structure..(3)Research and Verification of Wing Structure Load Identification Techniques.Firstly,a strain-driven method for identifying structural loads was formulated;Then,based on the typical force conditions of the wing during actual service,typical working conditions such as single load,double load and distributed load were designed for simulation verification.The results verified the accuracy of the method under different working conditions;Finally,a load identification experimental system was built for experimental verification.The results verified the reliability and accuracy of the method under the experimental conditions.(4)Research and Verification of Wing Structure Deformation Reconstruction Methods Firstly,a deformation reconstruction method based on the linear superposition of load-strain was proposed;Then,using the finite element model,simulation verification under typical working conditions was carried out and compared with the traditional deformation reconstruction method based on curvature reconstruction.Results confirm that the deformation of the wing structure under standard loading scenarios can be accurately recovered using this method.An experimental system was constructed to perform validation testing.The results show that this method can accurately reconstruct the structural deformation under actual working conditions,further verifying the effectiveness of the method in practical engineering applications.This paper,aiming at the requirements of load and deformation monitoring of wing structures,proposes a load identification and deformation reconstruction method based on the linear superposition of load and strain.An experimental system is built according to the strain detection principle of fiber Bragg gratings,and simulation verification and experimental verification under typical load conditions such as single load,double load and distributed load are carried out.The accuracy of the method and its reliability in practical engineering applications have been verified,providing strong technical support for the structural health monitoring of aircraft.更多还原