Wei Wang, Zhitao Zhang, Changchuan Xie, Chao Yang, Kunhui Huang

DOI Number: N/A

Conference number: IFASD-2024-156

An integrated measurement and control system suitable for ground and wind tunnel testing of a distributed propeller-wing system was designed. The real-time measurement, recording and display of several indicators including the propeller aerodynamic load, wing root load, propeller rotation speed, wing structural deformation and wing surface pressure during the experiment were obtained by using a six-component balance, an optical sensor, a data acquisition device and graphic display. Computer software was also utilized to process the collected test data, which were then compared with the numerical simulation results to verify the effectiveness and reliability of the measurement and control system. Results of high-precision computational fluid dynamics (CFD)/computational structural dynamics (CSD) aeroelastic simulations and Nastran SOL144 calculations used in this study are collected. In terms of vertical displacement of the wing tip and wing deformation distribution tested during the experiment. It is observed that the simulation results obtained in this study are in consistency with the results of wind tunnel tests using commercial software, proving the effectiveness of the experiment design.

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In Categories: 1. IFASD 2024, 1.Events, Experimental Methods Structural Dynamics and Aeroelasticity
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