Accession Number ADA584203
Title Finite Element Analysis of a Highly Flexible Flapping Wing.
Publication Date Mar 2013
Media Count 122p
Personal Author J. K. Mason
Abstract Small unmanned aerial systems are being designed to emulate the flapping kinematics of insects and birds which show superior control in slow speed regimes compared to fixed wing or rotorcraft aircraft. The flight of flapping wing vehicles is characterized by aeroelastic effects. Most research has been dedicated towards understanding the aerodynamic side of the aeroelastic response with minimal effort spent towards validating the structural response. A finite element model of a wing from a commercial flapping wing vehicle was created to validate the structural response. Vacuum testing allowed the isolation of the inertial response for a direct comparison to the finite element model. Wing tip displacement amplitude was matched to within 8%. The membrane kinematics of the finite element model were similar to the vacuum test article but overall membrane deflections predicted by the finite element solver were less than observed deflections seen in the vacuum. This research shows that significant focus must be placed on validating the structural side of a flexible structure in order to correctly model the complete aeroelastic response.
Keywords Aerodynamics
Finite element analysis
Flapping wings
Flexible structures
Mav(Micro air vehicle)

Source Agency Non Paid ADAS
NTIS Subject Category 51C - Aircraft
72B - Algebra, Analysis, Geometry, & Mathematical Logic
44G - Environmental & Occupational Factors
89D - Structural Analyses
Corporate Author Air Force Inst. of Tech., Wright-Patterson AFB, OH. Graduate School of Engineering and Management.
Document Type Thesis
Title Note Master's thesis.
NTIS Issue Number 1402
Contract Number N/A

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