Optimal thickness distributions of aeroelastic flapping shells |
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| Authors: | Bret Stanford Philip Beran |
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| Institution: | 1. Department of Mechanical Engineering, Urmia University of Technology, Band Road, Urmia, Iran;2. College of Engineering, Swansea University, Swansea SA2 8PP, UK;1. School of Mechanics, Civil Engineering & Architecture, Northwestern Polytechnical University, Xi’an 710072, PR China;2. Centre for Innovative Structures and Materials, School of Civil, Environmental and Chemical Engineering, RMIT University, GPO Box 2476, Melbourne 3001, Australia;1. Department of Mechanical, Materials and Manufacturing Engineering, The University of Nottingham Ningbo China;2. School of Aerospace, Mechanical and Manufacturing Engineering, Royal Melbourne Institute of Technology, Australia;1. School of Kinesiology, The University of Western Ontario, Canada;2. Graduate Program in Neuroscience, The University of Western Ontario, Canada |
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| Abstract: | The severe weight limitations of flapping wing micro air vehicles necessitates the use of thin flexible wings, which in turn requires an aeroelastic modeling tool for proper numerical characterization. Furthermore, due to the unconventional nature of these vehicles, wing design guidelines for thrust and/or power considerations are not generally available; numerical design optimization then becomes a valuable tool. This work couples a nonlinear shell model to an unsteady vortex lattice solver, and then computes analytical design gradients: the derivative of aerodynamic force/power quantities with respect to a large vector of thickness variables. Gradient-based optimization is then used to locate the wing structure that maximizes the thrust, or minimizes the power under a thrust constraint, for a variety of shell boundary conditions. Changes in the topological features of the optimal wing thicknesses highlight important aeroelastic interactions that can be exploited for efficient flapping wings. |
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