基于CAN总线的分布式翼面压力测量系统  

Distributed airfoil surface pressure measurement system based on CAN bus

作　　者：徐媛媛[1] 马炳和[1] 

机构地区：[1]西北工业大学微纳米系统重点实验室,陕西西安710072

出　　处：《机电工程》2012年第8期902-906,共5页Journal of Mechanical & Electrical Engineering

摘　　要：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 achieve the random extend function of the testing nodes on the measurement system, a distributed airfoil surface pressure measurement system based on CAN bus was designed and realized. Micro-electro-mechanic system（MEMS） pressure sensors were adopted as the core of testing nodes, and CAN bus which is high expansibility was used to build the distributed measurement system, use flexible PCB to realize the final circuit with the purpose of minimizing negative influence to aerodynamic characteristics of airfoil surface. Measuring effects of testing nodes and the reliability of bus connection were tested. The wind tunnel test verifies that this system could achieve distributed wing surface pressure measurements preliminary, and it has well application prospect.

关 键 词：飞行器 翼面压力 微型压力传感器 微机电系统 CAN总线 

分 类 号：V224[航空宇航科学与技术—飞行器设计] TP212.9[自动化与计算机技术—检测技术与自动化装置]