Distributed airfoil surface pressure measurement system based on CAN bus

XV Yuan-yuan， MA Bing-he
（Micro and Nano Electromechanical Systems Laboratory， Northwestern Polytechnical University，
Xi'an 710072， China）

Abstract： 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.
Key words： aircraft；airfoil pressure；pressure sensor；micro-electro-mechanic system（MEMS）；CAN bus