lecture17 - Date: 09.12.2009, Wednesday Prepared by: Özge...

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

View Full Document Right Arrow Icon

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

View Full DocumentRight Arrow Icon

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

View Full DocumentRight Arrow Icon
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: Date: 09.12.2009, Wednesday Prepared by: Özge Ekincioğlu FAILURE CRITERIA Elasticity(3-D) Material(uniaxial exps) 1 2 3 4 NO FLAWS IN THE MATERIAL WITH FLAWS Example: (An edge crack on aircraft panel) w= 100mm t= 16mm Al 7075-1735 I = 31MPa = 392MPa Estimate the maximum load P that can be applied without causing sudden fracture when on edge crack grows to length of a=20mm. β ( = 0.2)= 1.37 = 31 MPa   QUIZ Ti-6Al-6V w= 60mm P= 160kN crack length= 18mm N= 2.5 Central transverse crack. Calculate the thickness t required to prevent sudden fracture. β ( = 0.15)= 1.02    is satisfied.   Calculating stress intensity factors using finite element analysis For solids with a complicated geometry, finite element methods (or boundary element methods) are the only way to calculate stress intensity factors. It is conceptually very straightforward to calculate stress intensities using finite elements – you just need to solve a routine linear elastic boundary value problem to determine the stress field in the solid, and then deduce the stress intensity factors by taking...
View Full Document

This note was uploaded on 02/28/2011 for the course AEE 361 taught by Professor Daglas during the Spring '11 term at College of E&ME, NUST.

Page1 / 4

lecture17 - Date: 09.12.2009, Wednesday Prepared by: Özge...

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

View Full Document Right Arrow Icon
Ask a homework question - tutors are online