Development and testing of computational models of a flapping wing and a high altitude long endurance aircraft for high-fidelity nonlinear multidisciplinary simulations
- In the present thesis numerical aeroelastic models are developed for a Flapping Wing System and a High Altitude Long Endurance Aircraft. Fluid and structural models are created separately. Conception and development of highly complex and detailed models for both systems are explained. Common to both models is the characteristic large displacements of their structural dynamic behavior. This raises the need for nonlinear considerations on the structural solver. For the fluid solver the Arbitrary Lagrangian Eulerian formulation revealed to be not appropriate due to the lack of robustness under large deformations of the mesh. Hence, an Eulerian framework is used which showed to be successful in simulating the aeroelastic response of the systems. Numerical tests conducted separately on the fluid and structural models of each system are presented. These are done to study their character and check if their behavior seems physical since no corresponding experimental data is available. After successful tests, an aeroelastic simulation is performed for both systems, demonstrating the readability of the models for fluid-structure interaction analyses. Since the considered models tend to be large-scale, they require massive computational effort to be solved. Finally, a study on Reduced Order Modeling of an aeroelastic problem is performed; this as an attempt to find a way of reducing the resources required to analyze the contemplated systems.
|Type of resource
|electronic; electronic resource; remote
|1 online resource.
|Messingher Lang, Meir
|Stanford University, Department of Aeronautics and Astronautics
|Statement of responsibility
|Meir Messingher Lang.
|Submitted to the Department of Aeronautics and Astronautics.
|Thesis (Engineering)--Stanford University, 2011.
- © 2011 by Meir Messingher Lang
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