Design of precision balance and aerodynamic characteristic measurement system for micro aerial vehicles |
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| Institution: | 1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, PR China;2. School of Chemical and Process Engineering, University of Leeds, Leeds LS2 9JT, UK;1. Department of Civil, Environmental and Architectural Engineering, University of Colorado Boulder, ECES 134, UCB 428, Boulder, CO 80309-0428, USA;2. Department of Mechanical Engineering, University of Colorado Boulder, ECME 220, UCB 427, Boulder, CO 80309-0427, USA;1. Laboratory for Turbulence Research in Aerospace and Combustion, Department of Mechanical and Aerospace Engineering, Monash University, VIC 3800, Australia;2. University of Wyoming Aeronautical Laboratories, Department of Mechanical Engineering, University of Wyoming, Laramie, WY 82071, USA;3. Department of Aeronautical Engineering, King Abdulaziz University, Jeddah, Saudi Arabia;1. Department of Biomedical Engineering and Mechanics, Virginia Tech, Blacksburg, VA 24061, USA;2. Department of Mechanical and Aerospace Engineering, University of California Irvine, Irvine, CA 92697-3975, USA |
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| Abstract: | This paper presents the design and validation of a measurement system for the aerodynamic characteristics of micro aerial vehicles. Micro aerial vehicles are very small, have a wingspan of about 100–150 mm, and operate at relatively low Reynolds numbers. A precision aerodynamic balance was designed in order to measure the lift, drag, rolling-moment, and pitching-moment of micro air vehicles, as these parameters are too small to be determined by general-purpose aerodynamic measurement systems. During the design process, the aerodynamic balance was analyzed with the finite-element method in order to produce an optimal design and was calibrated as well. The calibration results and the finite element analysis results were compared and found to be in good agreement and the final design was determined to be acceptable. In addition, a computer-based data acquisition system has been developed to acquire measurement data from the aerodynamic balance. Wind tunnel tests of a 2D airfoil were performed to validate the aerodynamic measurement system. Results of the wind tunnel tests were compared with references and found to be in good agreement. Finally, we measured aerodynamic characteristics of MAV wing model used in Batwing with the developed aerodynamic measurement system. |
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