C-5 A Fuselage Stress Analysis.

Abstract

This report describes the work performed to provide analytical predictions that can be used to address cracking problems that have arisen in particular areas of the C-5A forward fuselage section. The specific objective of the present study was to investigate various factors in as much detail as possible that are likely to contribute to cracking of the fuselage skin. Three distinct activities were undertaken to establish the cause of skin cracking: review and evaluation of available data, creation and execution of test plans, and performance of static and dynamic stress analysis; results from tests were used to validate analytical models. Recommendations for a follow-on study and possible fixes based on results obtained to date are presented.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1992
Accession Number
ADA361350

Entities

People

  • Jatin C. Parekh
  • Warren C. Gibson

Tags

Communities of Interest

  • Air Platforms
  • Human Systems
  • Space

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Bending Moments
  • Bending Stress
  • Computer Programs
  • Corrosion
  • Fasteners
  • Finite Element Analysis
  • Frequency
  • Fuselages
  • Internal Pressure
  • Resonant Frequency
  • Stress Analysis
  • Stress Corrosion
  • Stresses
  • Structural Analysis
  • Test And Evaluation

Readers

  • Computational Modeling and Simulation
  • Structural Health Monitoring of Composite Structures.
  • Systems Analysis and Design