Integrated structural design, vibration control, and aeroelastic tailoring by multiobjective optimization
The integrated design of a structure and its control system was treated as a multiobjective optimization problem. Structural mass, a quadratic performance index, and the flutter speed constituted the vector objective function. The closed-loop performance index was taken as the time integral of th...
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| Format: | Others |
| Language: | en |
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Virginia Tech
2014
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| Online Access: | http://hdl.handle.net/10919/38912 http://scholar.lib.vt.edu/theses/available/etd-07282008-134827/ |
| Summary: | The integrated design of a structure and its control system was treated as a
multiobjective optimization problem. Structural mass, a quadratic performance index,
and the flutter speed constituted the vector objective function. The closed-loop
performance index was taken as the time integral of the Hamiltonian. Constraints
on natural frequencies and aeroelastic damping were also considered. Derivatives of
the objective and constraint functions with respect to structural and control design
variables were derived for a finite element beam model of the structure and constant
feedback gains determined by Independent Modal Space Control. Pareto optimal designs generated for a simple beam and a tetrahedral truss demonstrated the benefit
of solving the integrated structural and control optimization problem. The use of
quasi-steady aerodynamic strip theory with a thin-wall box beam model showed that
the integrated design for a high aspect ratio, unswept, straight, isotropic wing can
be separable. Finally, an efficient modal solution of the flutter equation facilitated
the aeroelastic tailoring of a low aspect ratio, forward swept, composite plate wing
model. === Ph. D. |
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