SST Technology Follow-On Program, Phase I. Compression Panel Analysis.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1972
- Accession Number
- AD0902463
Entities
People
- B. A. Harrison
- J. E. Mooney
- J. P. Cotton
- N. E. Connacher
Organizations
- Boeing