Installation-Induced Stress in a Black Hawk Inner Fuselage Panel,

Abstract

Some S-70A-9 Black Hawk helicopters of the Australian Army fleet are experiencing cracking on the starboard side internal fuselage skin panel. The panel is installed onto curved frames which causes installation-induced stresses in the panel. The PAFEC Finite Element package has been used to model the panel and to indicate the stresses and stress concentrations within it induced by the installation process. The methods used for constructing and verifying the model are presented. The maximum stresses and stress concentration factors produced by the model are discussed.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1996
Accession Number
ADA315874

Entities

People

  • C. G. Knight

Organizations

  • Defence Science and Technology Group

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Aluminum
  • Aluminum Alloys
  • Army Aircraft
  • Elements
  • Engineering
  • Finite Element Analysis
  • Fuselages
  • Helicopters
  • Inspection
  • Modulus Of Elasticity
  • Stress Concentration
  • Stress Relieving
  • Stresses
  • Tail Rotors

Readers

  • Structural Health Monitoring of Composite Structures.