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dcterms.accessRightsThis item may be protected under Title 17 of the U.S. Copyright Law. It is made available by UMBC for non-commercial research and education. For permission to publish or reproduce, please see http://aok.lib.umbc.edu/specoll/repro.php or contact Special Collections at speccoll(at)umbc.edu
dc.contributor.advisorLee, Soobum ;
dc.contributor.departmentMechanical Engineering
dc.contributor.programEngineering, Mechanical
dc.creatorBakhtiarinejad, Mahsan
dc.date.accessioned2021-09-01T13:55:45Z
dc.date.available2021-09-01T13:55:45Z
dc.date.issued2015-01-01
dc.description.abstractThis thesis research proposes a new topology optimization method based on morphing mesh (TOMM) technique in order to determine the optimal layout of components as well as the frame structure. In this method, two types of design variablesmorphing design variables and topology design variablesare defined for simultaneous design optimization of the components relocation and frame structure topology. Component relocation is enabled using FE Morphing approach, implemented by HyperMesh, on the basis of the SIMP method for compliance minimization of frame structure. Three design cases are studied using TOMM method: a simple cantilever beam design and two aircraft wing designs. The prevalent cantilever beam with a nodal force in the middle of the free end is studied to validate the proposed design methodology. Aircraft wing design cases are intended to obtain the best conceptual design by determining optimal placement of various subsystemscontrol system (flight control, engine control), fuel system, hydraulic system, and structural systemand the supporting frame structure. An advanced systematic design approach is needed for effective packaging of multiple subsystems while satisfying load-carrying performance and minimizing weight for energy efficiency. In the first wing design case, additional constraint on maintaining the weight balance is included and the corresponding design sensitivity is formulated. Then this wing design strategy is extensively applied to the commercial Boeing 757 aircraft wing where TOMM method is combined with the genetic algorithm for global search on component locations. The benefit of using the global search algorithm (genetic algorithm) is discussed in terms of high possibility on finding a global optimum and independency of initial design guess. The results of the TOMM method for simultaneous design optimization of components layout and structural topology have been compared to the classical structural topology optimization without component relocation. It has been proved that the inclusion of component relocation can improve structural performance. The proposed TOMM method will provide innovative design insight for complex modern multi-component structure.
dc.formatapplication:pdf
dc.genreM.P.P.
dc.identifierdoi:10.13016/m2uuo3-ukci
dc.identifier.other11224
dc.identifier.urihttp://hdl.handle.net/11603/22889
dc.languageen
dc.relation.isAvailableAtThe University of Maryland, Baltimore County (UMBC)
dc.relation.ispartofUMBC Mechanical Engineering Department Collection
dc.relation.ispartofUMBC Theses and Dissertations Collection
dc.relation.ispartofUMBC Graduate School Collection
dc.relation.ispartofUMBC Student Collection
dc.sourceOriginal File Name: Bakhtiarinejad_umbc_0434M_11224.pdf
dc.subjectframe
dc.subjectmorphing mesh
dc.subjectstructure
dc.subjecttopology
dc.titleTOPOLOGY OPTIMIZATION BASED ON MORPHING MESH FOR SIMULTANEOUS COMPONENT RELOCATION AND FRAME STRUCTURE DESIGN
dc.typeText


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