THE EFFECT OF VARIATIONS IN THE CREEP EXPONENT ON THE BUCKLING OF CIRCULAR CYLINDRICAL SHELLS

The senior author solved the problem of axially symmetrical creep buckling of thin circular cylindrical shells subjected to uniform axial compression. In that analysis the constitutive equation was a power law, and the exponent was taken to be equal to three. The purpose of the work was to extend the solution to a range of values of the creep exponent, n. To cope with the increasing algebraic complexity, a digital computer was employed in two ways: to generate the set of equations symbolically, and then to solve these equations. The computer programs were used to generate numerical solutions for the cases in which n was equal to 3, 5, 7, and 9. Two simple extrapolation techniques were then employed to obtain approximate solutions to the critical time problem for values of n up to 29.(Author)

• Supplemental Notes:
  • Revision of report dated 3 March 1971. Also available in the International Journal of Solids and Structures, V7 pp 1685-1695, 1971.
• Corporate Authors:

  Stanford University

  Department of Aeronautics and Astronautics
  Stanford, CA  United States  94305
• Authors:
  • Honikman, T C
  • Hoff, N J
• Publication Date: 1971-4-22

Media Info

• Pagination: 12 p.

Subject/Index Terms

• TRT Terms: Buckling; Creep; Cylinders (Geometry); Shells (Structural forms)
• Uncontrolled Terms: Cylindrical shells; Structural stability
• Old TRIS Terms: Shell theory
• Subject Areas: Marine Transportation; Materials;

Filing Info

• Accession Number: 00041464
• Record Type: Publication
• Source Agency: National Technical Information Service
• Report/Paper Numbers: AFOSR-TR-72-1763
• Contract Numbers: F44620-69-C-0009
• Files: TRIS
• Created Date: Mar 2 1973 12:00AM