Failure analysis of damaged panel of an aircraft

Madan, M and Bhuvana, R and Sujata, M and Venkataswamy, MA and Bhaumik, SK (2008) Failure analysis of damaged panel of an aircraft. Project Report. National Aerospace Laboratories, Bangalore, India.

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Abstract

The sheared part of starboard wing leading edge skin, located close to the slat groove, of an aircraft was sent to the laboratory for investigation. Examination revealed that the skin sheared off by overload fracture. The fracture was associated with gross deformation suggesting possible interference with other movable parts of the wing. There were no evidences of progressive failure such as fatigue or stress corrosion cracking.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: Aircraft;Wing leading edge skin;Overload failure
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Division/Department: Materials Science Division, Materials Science Division, Materials Science Division, Materials Science Division, Materials Science Division
Depositing User: Ms. Alphones Mary
Date Deposited: 18 Jul 2011 11:05
Last Modified: 18 Jul 2011 11:05
URI: http://nal-ir.nal.res.in/id/eprint/9419

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