Please use this identifier to cite or link to this item: http://hdl.handle.net/10125/51102

Multi-Objective Optimization of Aerostructures Inspired by Nature

File Description Size Format  
2015-08-phd-kearney_r.pdf Version for non-UH users. Copying/Printing is not permitted 8.28 MB Adobe PDF View/Open
2015-08-phd-kearney_uh.pdf For UH users only 8.27 MB Adobe PDF View/Open

Item Summary

Title:Multi-Objective Optimization of Aerostructures Inspired by Nature
Authors:Kearney, Adam
Keywords:Morphing Wing
Fail Safe
Composite Buckling
L-systems
Genetic Algorithm
show 2 moreLS-Dyna
NASTRAN
show less
Date Issued:Aug 2015
Publisher:[Honolulu] : [University of Hawaii at Manoa], [August 2015]
Abstract:The focus of this doctoral work is on the optimization of aircraft wing structures. The optimization was performed against the shape, size and topology of simple aircraft wing designs. A simple morphing wing actuator optimization is performed as well as a wing panel buckling topology optimization. This is done with biologically-inspired mathematical systems including a map L-system, a multi-objective genetic algorithm, and cellular structures represented by Voronoi diagrams. As with most aircraft optimizations, both studies aim to minimize the total weight of a wing while simultaneously meeting sti ness and strength requirements. Optimization is performed with the scripts developed in MATLAB as well as through the use of finite element codes, NASTRAN and LS-Dyna. The intent of this methodology is to develop unique designs inspired by nature and optimized through natural selection. The optimal designs are those with minimal weight as well as additional requirements specific to the problems. The designs and methodology have the potential to be of use in determining minimum weight designs in aircraft structures.
A literature review of optimization techniques, methodology and method validation, and optimization comparisons is presented. The buckling panel optimization considered here also includes composite buckling failure and manufacturing assumptions for composite panels. The panels are optimized for mass and strength by controlling the laminate stacking sequence, stiffener size, and topology. The morphing wing is optimized for actuator loading and redundancy.
Description:Ph.D. University of Hawaii at Manoa 2015.
Includes bibliographical references.
URI/DOI:http://hdl.handle.net/10125/51102
Appears in Collections: Ph.D. - Mechanical Engineering


Please email libraryada-l@lists.hawaii.edu if you need this content in ADA-compliant format.

Items in ScholarSpace are protected by copyright, with all rights reserved, unless otherwise indicated.