Project1Presentation

# Project1Presentation - – Calculate stress using formulas...

This preview shows pages 1–4. Sign up to view the full content.

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

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
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 )
Project: Wing-Box Analysis Analysis Bending moment, shear force, and torque

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
This is the end of the preview. Sign up to access the rest of the document.

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...
View Full Document

{[ snackBarMessage ]}

### Page1 / 4

Project1Presentation - – Calculate stress using formulas...

This preview shows document pages 1 - 4. Sign up to view the full document.

View Full Document
Ask a homework question - tutors are online