摘要
机翼是飞机的关键部件之一,在飞行过程中对机翼形变进行在线监测,有助于提升飞机的安全性能及任务执行能力。为此,本文提出一种基于光纤布拉格光栅传感技术的机翼动态形变测量系统;理论分析了FBG波长变化量与机翼表面曲率变化的关系,利用FBG温度传感器实现应变补偿,利用三次样条插值实现离散曲率的连续化,采用基于连续曲率的形变重构算法实现机翼形变测量;在CA42飞机的4个翼面上布置了36个FBG应变传感器,4个FBG温度传感器,通过地面静力试验得到了机翼的形变测量误差为2.5%;最后,针对机翼动态形变测量系统开展了飞行试验,试验过程完整地记录下了机翼表面的应变、温度及形变信息。试验结果表明,由机翼形变产生的翼梢位移量正比于机翼法向过载,系数分别为86.33 mm/g(左机翼)及80.04 mm/g(右机翼),翼梢最大位移量250 mm,发生在法向过载为2.25 g的时刻。此外,飞机机动半径越小,机翼形变量越大。机翼动态形变测量系统体现了良好的工程适应性。
Wing is one of the key components of aircraft.On-line monitoring of wing deformation during flight is helpful to improve the safety and mission performance of the aircraft.Therefore,a dynamic wing deformation monitoring system based on the fiber Bragg grating sensor technology is proposed in this article.The relationship between wavelength variation of FBG and wing surface curvature is analyzed theoretically.The strain compensation is realized by the temperature sensor,and the serialization of discrete curvature is realized by cubic spline interpolation.Then,the deformation reconstruction algorithm based on continuous curvature is used to measure the wing deformation.36 FBG strain sensors and 4 FBG temperature sensors are set on the wing surfaces of the CA42 aircraft.The ground static test results indicate that the measuring error of wing-tip deflection is 2.5%.Finally,a flight test is carried out for the wing dynamic deformation measurement system.The strain,temperature and deformation data of the wing surface are recorded completely during the test process.The flight test results show that the wing tip deflection caused by the wing deformation is directly proportional to the vertical acceleration of the wing,and the coefficients are 86.33 mm/g(left wing)and 80.04 mm/g(right wing),respectively.The maximum deflection of the wing tip is 250 mm,which occurs when the normal overload is 2.25 g.In addition,the smaller the radius of the aircraft maneuvering,the more the wing deforms.The dynamic wing deformation monitoring system shows good engineering adaptability.
作者
张俊
陈光辉
倪国新
熊俊
曾捷
Zhang Jun;Chen Guanghui;Ni Guoxin;Xiong Jun;Zeng Jie(School of Information Science and Technology,Hehai University,Shanghai 200433,China;The 23rd Institute of China Electronics Technology Corporation,Shanghai 201900,China;CETC Wuhu General Aviation Industry Technology Research Institute Co.,Ltd.,Wuhu 241199,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《仪器仪表学报》
EI
CAS
CSCD
北大核心
2023年第11期252-260,共9页
Chinese Journal of Scientific Instrument
