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Study On Finite Element Analysis For Cockpit Of Hovercraft Simulator

Posted on:2014-09-09Degree:MasterType:Thesis
Country:ChinaCandidate:A W ZhangFull Text:PDF
GTID:2252330425966184Subject:(degree of mechanical engineering)
Abstract/Summary:PDF Full Text Request
Hovercraft simulator can simulate the movement form of the real hovercraft. The cockpitof simulator is under heavy inertia because of its complex working conditions. To ensure thereliability of the cockpit and investigate the response characteristics of the structure, a seriesof detailed finite element analyses were made in this paper.Firstly, the structure was simplified appropriately and the finite element model wasestablished. The working conditions of the cockpit were analyzed and simplified. After thesymmetry of the cockpit under symmetrical loads was verified, the load subcases of finiteelement analysis were determined.Secondly, sandwich plates made of fiber reinforced polymer and aluminium honeycombwere transformed to laminated plates paved by the orthotropic material. And these twomaterials were equivalent. After analyzed the characteristics of stress distribution of thelaminated plates, failure analysis of each ply was made. The results indicated that none of thesandwich plates will fail.Thirdly, distribution feature of stress and displacement of each part was obtained throughstatic strength analyses of the steel parts in the cockpit. And its strength was ensured to meetthe requirements. According to the analysis results the structure was improved. The totalweight of the cockpit decreased significantly and the areas of the stress concentration reduced.Fourthly, dynamic characteristics of the improved cockpit were analyzed. First eighthnatural frequencies and vibration modes of the structure were obtained by modal analysis. Theanalysis results certificated that resonance will not occur. And the dynamic responsecharacteristics of the structure were obtained by frequency response analysis, which indicatedthat the cockpit will not appear severe vibration within working frequency range.In this paper, the analysis results of the cockpit indicated that the properties could meetthe requirements and the structure was improved appropriately. Manufacturing costs weresaved and energy consumption was reduced and response speed of the system was improved.
Keywords/Search Tags:cockpit, failure of composite, static strength analysis, structure improvements, dynamic characteristics analysis
PDF Full Text Request
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