A high-fidelity approach to conceptual design

dc.contributor.advisor Richard Wlezien
dc.contributor.author Watson, John
dc.contributor.department Aerospace Engineering
dc.date 2018-08-11T19:16:26.000
dc.date.accessioned 2020-06-30T03:02:03Z
dc.date.available 2020-06-30T03:02:03Z
dc.date.copyright Fri Jan 01 00:00:00 UTC 2016
dc.date.embargo 2001-01-01
dc.date.issued 2016-01-01
dc.description.abstract <p>We created a new methodology to perform conceptual design analysis on aircraft, using off-the-shelf, high-fidelity software tools to explore the project design space, including important preliminary design factors and thereby producing a more robust result which is less subject to compromise at later design stages. We claim that this analysis can be performed in one hour with commonly available computation resources, and therefore is applicable to conceptual design. We used the case study of a supersonic transport jet to develop these methods. For this application, we used Solidworks to create a parameterized three-dimensional CAD solid to define the exterior geometry of the aircraft, and create populations of design candidates. We used STAR-CCM+ to perform an automated fluid flow analysis of these candidates, using three-dimensional, viscous, turbulent finite volume analysis and incorporating internal engine performance characteristics. We then used MATLAB to collect the data produced by these analyses, compute additional results of interest, and quantify the design space represented by a population of candidates. We heavily automated the steps of this process, to allow large studies or optimization frameworks to be implemented. Our results show that the method produces a data set which is much more rich than conventional conceptual design techniques. The method captures many interactions between aircraft systems which are normally not quantified until later phases of design: aerodynamic interactions between external lifting surfaces and between the external body and internal engine performance, and how structural constraints affect wing performance. We also produce detailed information about the aircraft static stability. Further, the method is able to produce these results with commonly available computer hardware within the one-hour timeframe we allow for a conceptual design analysis.</p>
dc.format.mimetype application/pdf
dc.identifier archive/lib.dr.iastate.edu/etd/15183/
dc.identifier.articleid 6190
dc.identifier.contextkey 8943283
dc.identifier.doi https://doi.org/10.31274/etd-180810-4786
dc.identifier.s3bucket isulib-bepress-aws-west
dc.identifier.submissionpath etd/15183
dc.identifier.uri https://dr.lib.iastate.edu/handle/20.500.12876/29367
dc.language.iso en
dc.source.bitstream archive/lib.dr.iastate.edu/etd/15183/Watson_iastate_0097M_15432.pdf|||Fri Jan 14 20:36:54 UTC 2022
dc.subject.disciplines Aerospace Engineering
dc.subject.disciplines Art and Design
dc.subject.keywords Aerospace Engineering
dc.subject.keywords Aircraft
dc.subject.keywords Automation
dc.subject.keywords Conceptual
dc.subject.keywords Design
dc.subject.keywords MDO
dc.subject.keywords Optimization
dc.title A high-fidelity approach to conceptual design
dc.type article
dc.type.genre thesis
dspace.entity.type Publication
relation.isOrgUnitOfPublication 047b23ca-7bd7-4194-b084-c4181d33d95d
thesis.degree.discipline Aerospace Engineering
thesis.degree.level thesis
thesis.degree.name Master of Science
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