飞机结构振动监测用微型测试系统研制

Development of a Micro Test System for Monitoring Structural Vibration of Aircraft

飞行过程中各种扰动气流容易导致飞机薄壁结构发生振动疲劳破坏,严重影响飞机的安全性和出勤率。针对受扰动气流作用下飞机结构的振动安全监测对仪器提出的微型化要求,基于STM32F103芯片设计了微型振动测试系统及配套软件。测试系统样机体积小,重量约160g,由内置加速度传感器触发采集,3个应变通道的采样率可达10K/s,以高速SD卡为存储器实现数据的便携取用,不依赖飞机电源系统而用安全性高的锂聚合物电池供电。采用LabVIEW编写的数据分析处理软件包含时域分析、频域分析及时频联合分析等功能。通过悬臂梁固有频率及自由衰减振动实验对测试系统进行功能验证测试,结果表明系统可满足对结构振动信号的采集和分析。

Vibration fatigue failure of aircraft thin-wall structure due to various disturbance airflow during flight influences seriously security and attendance rate of airplane. In order to monitor the vibration safety of aircraft structures using miniature instrument, a micro test system and supporting software are proposed, based on STM32F103 chip. The volume of test system prototype is very small, its weight is less than 160g. Data acquisition is triggered by a built-in acceleration sensor, the sampling rate of 3 strain channels is up to 10K/s. Convenient data storage and access are achieved by a high-speed SD card. Its power supply does not rely on aircraft power system but is implemented by safer lithium polymer battery. The data analysis software （including time-domain analysis, frequency domain analysis and time-frequency joint analysis） is developed by LabVIEW. Test system functional verification test was carried out through cantilever natural frequency and vibration free attenuation experiment. Results show that this system can meet the requirements for structural vibration signal acquiring and processing.