Damage Tolerance Analysis on Repaired Fuselage Skin-Reference-Cited by-同舟云学术

Damage Tolerance Analysis on Repaired Fuselage Skin

Published:2006-03 Issue: Volume:306-308 Page:265-270
ISSN:1662-9795
Container-title:Key Engineering Materials
language:
Short-container-title:KEM

Author:

Legowo Dibyo¹,Susena I Wayan,Tambunan Sharudin¹

Affiliation:

1. Indonesian Aerospace IAe

Abstract

This paper discussed about the method used by operator to perform damage tolerance analysis for repaired fuselage skin. Skin damage may be caused by accidental damage or fatigue crack. Some element needed for damage tolerance analysis and the method to develop load spectrum will be discussed briefly. Therefore, this paper will describe a case study of damage tolerance analysis on repaired fuselage skin of narrow body jet aircraft.

Publisher

Trans Tech Publications, Ltd.

Subject

Mechanical Engineering,Mechanics of Materials,General Materials Science

Link

https://www.scientific.net/KEM.306-308.265.pdf

Reference5 articles.

1. T. Swift, Repairs to Damage Tolerant Aircraft, International Symposium on Structural Integrity of Aging Airplanes, Atlanta, Georgia, (1990).

2. Repair Assessment Procedure and Integrated Design, Analysis Methods Document May 1998, www. tc. faa. gov/its/worldpac/techrpt/rapid. pdf.

3. D.P. Rooke and D.J. Cartwright: Compendium of Stress Intensity Factors (Her Majesty's Stationary Office, London, 1976).

4. [2] [4] [6] [8] [10] [12] [14] [16] [18] [20] 0 20000 40000 60000 80000 100000 120000 140000 Flight number (N, cycle) crack length (inch) a critical = 15. 5 inch Ncritical=127096 a detectable = 13. 5 inch Ndetactable= 126482.

5. 10000 20000 30000 40000 50000 0 5 10 15 20 25 30 35 crack length (inch) residual strength (psi)yield stress = 45000 psi limit stress = 17867 psi.