Fusion of correlated information in multifidelity aircraft design optimization
Name
921147270-MIT.pdf
Description
Full printable version
Size
18.42 MB
Format
Adobe PDF
Checksum (MD5)
99910a9436261fd6e59abb18b2cb1997
Author(s)
Zhao, Zipeng, S.M. Massachusetts Institute of Technology
Advisor(s)
Karen Willcox.
Alternative Title
Fusion of correlated information in multifidelity aircraft design and optimization
Date Issued
2015
Publisher
Massachusetts Institute of Technology
Abstract
Models used in engineering design often face trade-offs between computational cost and prediction uncertainty. To ameliorate this problem, correlated models of varying fidelities are used together under different fidelity management strategies to produce accurate predictions while avoiding typically expensive costs. However, existing strategies either account for model correlation and operate under the assumption of a strict fidelity hierarchy, or do not consider model correlation but allow model fidelities to vary across the design space. In this thesis, we present a surrogate-based multifidelity framework that simultaneously accounts for model correlation and accommodates non-hierarchical fidelity specifications. The development of our multifidelity framework can be classified into three stages. The first stage involves the construction of three separate wing weight estimation models that simplify different aspects of the wing sizing problem, thereby creating a scenario where model fidelities are not confined to a rigid hierarchy. The second stage involves the establishment of a formal definition of model correlation, and an extension that allows model correlations to vary across the design space. The third stage involves the incorporation of model correlation in surrogate-based information fusion. To illustrate the application of our framework, we set up a wing weight estimation problem using wing span as design variable. In a later chapter, the problem is extended to two dimensions for increased complexity using body weight and aspect ratio as design variables. Results from both wing weight estimation problems indicate a combination of variance reduction and inflation at different positions in the design space when model correlation is considered, in comparison to the case where model correlation is ignored.
Description
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 117-119).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.
Persistent DSpace Link
