/
Multi Site Damage Multi Site Damage

Multi Site Damage - PowerPoint Presentation

calandra-battersby
calandra-battersby . @calandra-battersby
Follow
440 views
Uploaded On 2016-12-13

Multi Site Damage - PPT Presentation

MultiSite Damage is the multiple crack problem in the riveted structure of an aircraft skin The reason behind Aloha Airlines Boeing 737200 April 1988 accident is multiple site damage of a riveted lap joint of skin caused by corrosion fatigue ID: 501070

growth crack site msd crack growth msd site damage multiple fatigue cracks multi engineering formula accident cycle rate aloha

Share:

Link:

Embed:

Download Presentation from below link

Download Presentation The PPT/PDF document "Multi Site Damage" is the property of its rightful owner. Permission is granted to download and print the materials on this web site for personal, non-commercial use only, and to display it on your personal computer provided you do not modify the materials and that you retain all copyright notices contained in the materials. By downloading content from our website, you accept the terms of this agreement.


Presentation Transcript

Slide1

Multi Site Damage

Multi-Site Damage is the multiple crack problem in the riveted structure of an aircraft skin. The reason behind Aloha Airlines Boeing 737-200 ( April 1988) accident is multiple site damage of a riveted lap joint of skin caused by corrosion fatigue. Slide2

Aloha airlines accident Slide3

MSD- Crack initiation and link up from a single row of rivet holes

Slide4

The physics behind MSD

Aircraft cabin pressurization and depressurization cycle due to high altitude operation creates a fatigue loading for the multiple cracks. The crack growth rate can be predicted using the formula.Slide5

Formula to predict the crack growth rate

Where is the crack

growth per cycle, is stress intensity range, C, m, are material constants.

Slide6

Fatigue crack growth of a component

Slide7

Two equal parallel eccentric through cracks under far field tension

Slide8

MSD Software

The software can be used to calculate the criticality of cracks and decide whether any repair is required to be done to avoid any fatality and safe flying hours can also be calculated before next inspection. Slide9

Conference Paper

V. Rangasamy,

X. Wang and R. Bell “On the Analysis of Crack Interactions Using Weight Function Method”,

International conference on Ocean Mechanics and Arctic Engineering, 2002,

Department of Mechanical and Aerospace Engineering, Carleton University, Ottawa, Ontario, Canada.