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Heriberto David Solano
(Advisor: Prof. Dimitri Mavris)
will propose a doctoral thesis entitled,
A Robust Methodology For Analysis And Optimization Of Wing Structural Geometries Using A Preconditioned Aeroelastic Model
On
Wednesday, January 19 at 2:00 p.m
CoVE Weber SST II
and
https://bluejeans.com/212199472/8904
Abstract
Aerospace research and industry have been focused on pushing boundaries and designing next-generation aircraft to meet the aviation sector needs and reducing its impact on climate change. During early stages of design, it is important to design the structure to sustain loads specified by 14-CFR regulatory authorities while keeping the weight, sizes and costs low. Unconventional designs, such as the truss-braced wing design, promise great structural and aerodynamic efficiency, but require additional dynamic load considerations, and more accurate physical structural models. This work centers around design and optimization of unconventional wing structures. A methodology is developed to best decide which model fidelity and tools to use during design space exploration to maximize exploration performance, with respect to number of configurations considered, solution uncertainty, and confidence of optimum.
Additionally, a computationally efficient model is developed that allows for the simulation of the truss-braced concept that has multiple components joined to one another as the primary structure. The model will be shown to have well-conditioned low-order physics, improve fidelity by including strength and buckling considerations and accounting for stress concentrations.
To test the framework, three experiments will be carried out: 1) demonstrate the methodology of choosing appropriate model fidelity by tracking the number of feasible alternatives explored and fitness of solution tracked, 2) demonstrate accuracy of the developed lower-fidelity model to by comparing to a higher-fidelity model, and 3) demonstrate that the developed sequence of pre-conditioners lowers the condition number of the differential algebraic equation system.
Finally, the capabilities developed will be demonstrated to perform multi-fidelity design space exploration of a truss-braced wing model.
Committee
