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Computational Membrane Model Using Finite Element Method for Flexible-Wing Based Micro Air Vehicles

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dc.contributor.advisor Seshaiyer, Padmanabhan
dc.contributor.author Garrity, Michael J.
dc.creator Garrity, Michael J.
dc.date 2011-07-26
dc.date.accessioned 2011-08-22T18:44:09Z
dc.date.available NO_RESTRICTION en_US
dc.date.available 2011-08-22T18:44:09Z
dc.date.issued 2011-08-22
dc.identifier.uri https://hdl.handle.net/1920/6605
dc.description.abstract Current designs for Micro Air Vehicles (MAVs) consist of a flexible wing with rigid battens for support. This paper analyzes the development and evaluation of strain on the membrane from various constitutive models used for the flexible-wing-based MAVs. A dependable accurate prediction of its aerodynamic performance requires efficient modeling techniques. In this work, a new C++ code has been developed to simulate the computational membrane methodology described in this thesis. Our computational model of the membrane incorporates a finite element analysis that uses Principle of Virtual Work. We develop and implement a computational algorithm to understand the mechanics of a thin “rubber-like” membrane material of the wing. We also study the performance of the method with different constitutive models. The overall objective in our model is to solve for the deflection of the deformed membrane.
dc.language.iso en_US en_US
dc.subject Membrane en_US
dc.subject MAV en_US
dc.subject Flexible en_US
dc.subject Hyperelasticity en_US
dc.subject Model en_US
dc.subject C++ en_US
dc.title Computational Membrane Model Using Finite Element Method for Flexible-Wing Based Micro Air Vehicles en_US
dc.type Thesis en
thesis.degree.name Masters in Mathematics en_US
thesis.degree.level Master's en
thesis.degree.discipline Mathematics en
thesis.degree.grantor George Mason University en


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