Project1Presentation

Project1Presentation - – Calculate stress using formulas...

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Project: Wing-Box Analysis Objective: to estimate stresses at the root of a wing and determine the safety of the wing using failure criteria Sweep angle c/4 chord line x y L /2 b c tip c root h root
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Project: Wing-Box Analysis Load estimation The lift, w, over the surface of the entire wing is replaced by a line load (lift per unit length) elliptically distributed along c/4 line Total lift = airplane weight * load factor Modeling Cantilevered beam with thin-walled rectangular cross section ( c root X h root )
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Project: Wing-Box Analysis Analysis Bending moment, shear force, and torque
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Unformatted text preview: – Calculate stress using formulas in Chapter 3, 4, 5 • Failure prediction – Find material properties and failure strength of Aluminum 7075-T3 – Calculate maximum von Mises stress at the root – Calculate safety factor (failure strength/von Mises stress) Project: Wing-Box Analysis • Individual project • Online submission (Project1_SortNo.doc(pdf)) • Report must explain step-by-step procedure with equations, figures, and/or tables • Will check plagiarism • Due date: Starting class of Nov. 11 th...
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Project1Presentation - – Calculate stress using formulas...

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