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dc.contributor.authorRajaram, Dushhyanth
dc.contributor.authorYu, Cai
dc.contributor.authorChakraborty, Imon
dc.contributor.authorMavris, Dimitri N.
dc.date.accessioned2020-03-23T19:22:50Z
dc.date.available2020-03-23T19:22:50Z
dc.date.issued2018-06
dc.identifier.citationRajaram, D., Cai, Y., Chakraborty, I., & Mavris, D. N. (2018). Integrated Sizing and Optimization of Aircraft and Subsystem Architectures in Early Design. Journal of Aircraft, 55(5), 1942–1954. DOI: https://doi.org/10.2514/1.c034661en_US
dc.identifier.urihttp://hdl.handle.net/1853/62531
dc.description© 2018 American Institute of Aeronautics and Astronauticsen_US
dc.description.abstractThe aerospace industry’s current trend towards novel or More Electric architectures results in some unique challenges for designers due to both the scarcity or absence of historical data and a potentially large combinatorial space of possible architectures. These add to the already existing challenges of attempting to optimize an aircraft design in the presence of multiple possible objective functions while avoiding an overly compartmentalized approach. This paper uses the Integrated Subsystem Sizing and Architecture Assessment Capability to pursue a multi-objective optimization for a large twin-aisle aircraft and a small single-aisle aircraft using the Non-Dominated Sorting Genetic Algorithm II (NSGA-II) algorithm with parallel function evaluations. One novelty of the optimization setup is that it explicitly considers the impacts of subsystem architectures in addition to those of traditional aircraft-level design variables. The optimization yields generations of nondominated designs in which substantially electrified subsystem architectures are found to predominate. As a first assessment of the impact of epistemic uncertainty on the results obtained, the optimization is rerun with altered sensitivities for the thrust-specific fuel consumption penalties due to shaft-power and bleed air extraction. This analysis demonstrated that the composition of architectures on the Pareto frontier is sensitive to the secondary power extraction penalties, but more so for the small single-aisle aircraft than the large twin-aisle aircraft.en_US
dc.language.isoen_USen_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesASDL;en_US
dc.subjectAircraft optimizationen_US
dc.titleIntegrated Sizing and Optimization of Aircraft and Subsystem Architectures in Early Designen_US
dc.typePost-printen_US
dc.contributor.corporatenameGeorgia Institute of Technology. Aerospace Systems Design Laboratoryen_US
dc.identifier.doi10.2514/1.c034661en_US


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