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Buckling analysis of a strut and design of a fuselage section for a high altitude aerospace vehicle - Airframe Design Coursework



This is a two part paper addressing the AirFrame Design coursework problems. The first part presents the buckling analysis of an aluminium alloy unlipped channel section. Following the linear static and buckling analysis of a strut with spans ranging from 0.2m to 4m with two constraint configurations to maintain a simply supported condition, it was possible to determine its buckling failure modes in Creo Simulate 3.0. These results proved to be consistent with both analytical and empirical (ESDU) solutions. This paper presents the correlation of these means of analysis with the purpose of establishing the limitations and degree of applicability of the model to real cases. The second part presents the design of a ‘double bubble’ fuselage section under loading conditions specific to high altitude aerospace vehicles. The complete design process of the skin-stringers configuration at one fuselage station is presented analytically and an algorithm is developed to automate this process. Furthermore, the report discusses the advantages, limitations and assumptions made in using CFRP as a material when compared to Hiduminium in the design of the fuselage section.
Graphical comparison of numerical and analytical data with ESDU
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