Abstract
MEMS skin friction sensor, used to measure skin friction and its distribution, possesses smaller volume, higher sensitivity, better stability and other merits, and is very important for air vehicles. As we all know, normal load is much larger than skin friction measured in hypersonic flow field, thus MEMS skin friction sensor applied in hypersonic conditions presents higher requirements. Basing on MEMS technologies in existence and hypersonic flow field traits, a novel skin friction measuring method and meso-scopic sensor-head microstructure, which adopt that floating element even with measured wall and signal output microstructure being isolated from hypersonic flow field, are presented. Sensor-head design, weak capacitance signal detection, MEMS process technology, static calibration and proof experiments in hypersonic wind tunnel for sensor prototypes are implemented. The results of prototype tape-out and proof experiments indicate that: the process technology scheme that meso-scopic sensor-head being divided, fabricated separately and integrated by micro-assembly is feasible, the repeatability precisions of static calibration for prototypes are better than 1.5%; sensor prototypes present stable output, better return-to-zero, higher sensitivity, and repeatability precision better than 2% in proof experiments, and provide a preliminarily feasible experimental research method for skin friction measuring in hypersonic wind tunnel.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.