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- W2077841192 abstract "Flexible flapping wings have garnered a large amount of attention within the micro aerial vehicle community: a critical component of computationalmicro aerial vehicle simulations is the representation of the structural dynamics behavior of the flapping-wing structure. This paper discusses the development of a new nonlinear finite element solver that is based on a corotational approach and suitable for simulating flapping plate/shell-like wing structures undergoing small strains and large displacements/rotations. Partial verification and validation studies are presented on rectangular/elliptic wing structures to test the rigid body kinematics, nonlinear statics, and dynamics capabilities of the solver. Results obtained showed good agreement with available analytical/experimental/commercial solutions. The new structural dynamics formulation along with the numerical test cases contribute to the very limited set of tools and examples existing in the flapping-wing micro aerial vehicle literature." @default.
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- W2077841192 date "2011-01-01" @default.
- W2077841192 modified "2023-10-18" @default.
- W2077841192 title "Flapping-Wing Structural Dynamics Formulation Based on a Corotational Shell Finite Element" @default.
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- W2077841192 doi "https://doi.org/10.2514/1.j050494" @default.
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