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为降低飞行器翼面压力检测系统对气动分布的影响,并实现翼面任意位置的压力检测,设计了一种基于CAN总线的翼面压力分布式测量系统。利用微机电系统压力传感器测量翼面压力,并使用柔性材料制作检测节点电路,最后结合CAN总线搭建了分布式测量系统;气罐实验结果显示,各节点测量均方差不超过0.1 kPa,总线连接可靠。风洞试验结果初步验证了该系统可以实现分布式翼面压力测量,同时研究结果表明该测量系统具有较好的应用前景。
In order to reduce the influence of the airfoil pressure detection system on the aerodynamic distribution and to detect the pressure anywhere on the airfoil, a CAN-based airfoil pressure distribution measurement system is designed. The pressure of the airfoil is measured by the MEMS pressure sensor, and the testing node circuit is fabricated by flexible material. Finally, a distributed measuring system is built by CAN bus. The experimental results of the air tank show that the mean square error of each node is less than 0.1 kPa and the bus connection is reliable . Wind tunnel test results preliminarily verify that the system can achieve distributed airfoil pressure measurement, and the results show that the measurement system has a good application prospect.