摘要
为了应用分布式光纤布拉格光栅(fiber Bragg grating,FBG)传感网络飞行实测直升机旋翼动载荷,综合分析旋翼桨叶的载荷与应变,以及FBG传感器的使用要求,设计了桨叶表面的FBG传感网络布设方案。在此基础上,提出基于FBG应变测量的工程建模方法和校准试验方法。以单项加载试验建立模型,复合加载试验验证模型,验证分析给出最大的载荷相对误差为3.83%,优于5%的飞行实测工程要求。使用FBG传感器和应变计等2种不同传感器,完成直升机旋翼动载荷对比试飞,测量结果在时域和频域都可以相互验证。试飞结果表明:FBG传感网络测量结果正确有效,基于分布式FBG传感测量的旋翼动载荷工程建模方法合理可行。
In order to use distributed fiber Bragg grating sensor network to measure the dynamic loads on rotor blade structure in flight,analyze the blade section loads and strain,combined with operational requirement of FBG sensor,the arrangement scheme of FBG sensor network on blade surface is designed.On this basis,the engineering modeling method and calibration test method of the dynamic loads on rotor blade structure based on FBG strain measurement are given.The model is established by single loading test,and verified by compound loading test.The data analysis shows that the maximum load relative error is 3.83%,which is better than the 5%required by the flight measurement engineering.Use two different sensors such as FBG sensor and strain gauge to measure the dynamic loads on rotor blade structure in flight,Comparative analysis in time domain and frequency domain shows that the measurement results of FBG sensor and strain gauge can be mutually verified.The flight test results show the validity of the FBG sensor measurement results and also verify the feasibility and effectiveness of the dynamic load engineering modeling method for rotor blade structure based on distributed FBG sensor measurement.
作者
张宏林
程卫真
夏品奇
ZHANG Honglin;CHENG Weizhen;XIA Pinqi(Aircraft Flight Test Technology Institute,Chinese Flight Test Establishment,710089 Xi'an,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,210016 Nanjing,China)
出处
《应用力学学报》
北大核心
2025年第3期542-551,共10页
Chinese Journal of Applied Mechanics
基金
直升机旋翼动力学国家级重点实验室基金资助项目(No.61422202104)。
关键词
分布式FBG传感测量
桨叶
动载荷
工程建模
飞行试验
distributed fiber Bragg grating sensing measurement
blade
dynamic load
engineering modeling
flight test
