Rotorcraft Damage Tolerance Evaluated by Computational Simulation

Abstract

An integrally stiffened graphite/epoxy composite rotorcraft structure is evaluated via computational simulation. A computer code that scales up constituent micromechanics level material properties to the structure level and accounts for all possible failure modes is used for the simulation of composite degradation under loading. Damage initiation, growth, accumulation, and propagation to fracture are included in the simulation. Design implications with regard to defect and damage tolerance of integrally stiffened composite structures are examined. A procedure is outlined regarding the use of this type of information for setting quality acceptance criteria, design allowables, damage tolerance, and retirement-for-cause criteria.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 2000
Accession Number
ADP010643

Entities

People

  • Christos C. Chamis
  • Frank Abdi
  • Levon Minnetyan

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms
  • Biomedical
  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Bending Moments
  • Composite Materials
  • Composite Structures
  • Epoxy Composites
  • Fabrication
  • Failure Mode And Effect Analysis
  • Geometry
  • Graphitic Materials
  • Laminates
  • Materials Processing
  • Materials Testing
  • Mechanical Working
  • Mechanics
  • Micromechanics
  • Stiffness
  • Structural Response
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Regression Analysis.
  • Reinforced Composite Materials