Accession Number:

AD0902463

Title:

SST Technology Follow-On Program, Phase I. Compression Panel Analysis.

Descriptive Note:

Final rept. on Task 1,

Corporate Author:

BOEING COMMERCIAL AIRPLANE CO SEATTLE WA

Report Date:

1972-07-01

Pagination or Media Count:

298.0

Abstract:

This report presents a structural analysis method development and test program to verify the structural integrity of compression panels for the fuselage of the U.S. SST prototype airplane. Structural analysis procedures, including thermal effects, are established to predict critical loads for 1 flexure crippling, 2 symmetric torsion and flexure, 3 antisymmetric torsion and flexure, and 4 coupled stringer local buckling, symmetric torsion, and flexure. A computerized solution capability is also provided. Test data are presented for 63 five-bay, three-bay, or crippling panels covering 11 basic stringer configurations. In addition, two interrivet buckling tests were performed using titanium shear head countersunk fasteners. Correlation is shown between the analytically predicted critical loads and the actual test loads, including thermal effects to 450 F. Author

Subject Categories:

  • Transport Aircraft
  • Metallurgy and Metallography
  • Computer Programming and Software

Distribution Statement:

APPROVED FOR PUBLIC RELEASE