FRACTURE MECHANICS ANALYSIS OF CENTERED AND OFFSET FASTENER HOLES IN STIFFENED AND UNSTIFFENED PANELS UNDER UNIFORM TENSION

This report documents a finite-element analysis procedure for computation of Mode I and Mode II stress intensity factors associated with one or two sharp cracks emanating from a fastener hole in a panel under uniform tension. The fastener hole may be offset from the panel centerline, and one or both edges of the panel may be integrally stiffened. The formulation of a special assumed-stress hybrid element for the region near the fastener hole is presented. A detailed description of the programming covers the physical problem, modelling, program flow and options, input/output conventions, execution times, and limitations which must be observed. Results are presented for performance tests of the special element, and for some example analyses of cracked panels.

• Corporate Authors:

  Massachusetts Institute of Technology

  Aeroelastic and Structures Research Laboratory
  Cambridge, MA  United States  02139
• Authors:
  • STALK, G
  • Orringer, O
• Publication Date: 1976-4

Media Info

• Pagination: 185 p.

Subject/Index Terms

• TRT Terms: Aircraft; Calculation; Computer programs; Cracking; Finite element method; Fracture mechanics; Holes; Panels; Stresses; Structural analysis; Tension
• Uncontrolled Terms: Computation; Crack propagation; Stress intensity factors
• Old TRIS Terms: Holes openings; Stiffened cylinders
• Subject Areas: Aviation; Vehicles and Equipment;

Filing Info

• Accession Number: 00146988
• Record Type: Publication
• Source Agency: National Technical Information Service
• Report/Paper Numbers: ASRL-TR-177-2 Intrm Rpt., AFFDL-TR-75-70
• Contract Numbers: F33615-74-C-3063
• Files: TRIS
• Created Date: Feb 16 1977 12:00AM