Fatigue and damage tolerance assessment of aircraft structure under uncertaintyReportar como inadecuado


Fatigue and damage tolerance assessment of aircraft structure under uncertainty


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This thesis presents a new modeling framework and application methodology forthe study of aircraft structures. The framework provides a ‘cradle-to-grave’ approach tostructural analysis of a component, where structural integrity encompasses all phases ofits lifespan.The methodology examines the holistic structural design of aircraft componentsby integrating fatigue and damage tolerance methodologies. It accomplishes this bymarrying the load inputs from a fatigue analysis for new design, into a risk analysis for anexisting design. The risk analysis incorporates the variability found from literature,including recorded defects, loadings, and material strength properties.The methodology is verified via formal conceptualization of the structures, whichare demonstrated on an actual hydraulic accumulator and an engine nacelle inlet. Thehydraulic accumulator is examined for structural integrity utilizing different basematerials undergoing variable amplitude loading. Integrity is accomplished through arisk analysis by means of fault tree analysis. The engine nacelle inlet uses the damagetolerance philosophy for a sonic fatigue condition undergoing both constant amplitudeloading and a theoretical flight design case. Residual strength changes are examinedthroughout crack growth, where structural integrity is accomplished through a riskanalysis of component strength versus probability of failure.Both methodologies can be applied to nearly any structural application, notnecessarily limited to aerospace.



Georgia Tech Theses and Dissertations - School of Mechanical Engineering Theses and Dissertations -



Autor: Goksel, Lorens Sarim - -

Fuente: https://smartech.gatech.edu/



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