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dc.contributor.advisorMavris, Dimitri
dc.contributor.authorCampbell, Angela Mari
dc.date.accessioned2015-01-12T20:52:56Z
dc.date.available2015-01-12T20:52:56Z
dc.date.created2014-12
dc.date.issued2014-11-17
dc.date.submittedDecember 2014
dc.identifier.urihttp://hdl.handle.net/1853/53087
dc.description.abstractRecently, the environmental impact of aircraft and rising fuel prices have become an increasing concern in the aviation industry. To address these problems, organizations such as NASA have set demanding goals for reducing aircraft emissions, fuel burn, and noise. In an effort to reach the goals, a movement toward more-electric aircraft and electric propulsion has emerged. With this movement, the number of critical electrical loads on an aircraft is increasing causing power system reliability to be a point of concern. Currently, power system reliability is maintained through the use of back-up power supplies such as batteries and ram-air-turbines (RATs). However, the increasing power requirements for critical loads will quickly outgrow the capacity of the emergency devices. Therefore, reliability needs to be addressed when designing the primary power distribution system. Power system reliability is a function of component reliability and redundancy. Component reliability is often not determined until detailed component design has occurred; however, the amount of redundancy in the system is often set during the system architecting phase. In order to meet the capacity and reliability requirements of future power distribution systems, a method for redundancy allocation during the system architecting phase is needed. This thesis presents an aircraft power system design methodology that is based upon the engineering decision process. The methodology provides a redundancy allocation strategy and quantitative trade-off environment to compare architecture and technology combinations based upon system capacity, weight, and reliability criteria. The methodology is demonstrated by architecting the power distribution system of an aircraft using turboelectric propulsion. The first step in the process is determining the design criteria which includes a 40 MW capacity requirement, a 20 MW capacity requirement for the an engine-out scenario, and a maximum catastrophic failure rate of one failure per billion flight hours. The next step is determining gaps between the performance of current power distribution systems and the requirements of the turboelectric system. A baseline architecture is analyzed by sizing the system using the turboelectric system power requirements and by calculating reliability using a stochastic flow network. To overcome the deficiencies discovered, new technologies and architectures are considered. Global optimization methods are used to find technology and architecture combinations that meet the system objectives and requirements. Lastly, a dynamic modeling environment is constructed to study the performance and stability of the candidate architectures. The combination of the optimization process and dynamic modeling facilitates the selection of a power system architecture that meets the system requirements and objectives.
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.publisherGeorgia Institute of Technology
dc.subjectPower systems
dc.subjectReliability
dc.subjectTurboelectric propulsion
dc.subjectSystem architecting
dc.subjectDynamic modeling
dc.subjectGlobal optimization
dc.subjectStochastic flow network
dc.subjectAdmittance space analysis
dc.subjectNyquist stability
dc.subjectSuperconducting cables
dc.subjectState-space modeling
dc.titleArchitecting aircraft power distribution systems via redundancy allocation
dc.typeDissertation
dc.description.degreePh.D.
dc.contributor.departmentAerospace Engineering
thesis.degree.levelDoctoral
dc.contributor.committeeMemberSchrage, Daniel
dc.contributor.committeeMemberGarcia, Elena
dc.contributor.committeeMemberBrown, Gerald
dc.contributor.committeeMemberDuffy, Kirsten
dc.date.updated2015-01-12T20:52:56Z


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