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Buckling and collapse of an axially compressed, thin cylindrical shell with a rectangular cut-out under uniform end shortening.
A general-purpose nonlinear finite element computer program such as STAGS can be used for the prediction of the nonlinear behavior of this non-symmetric shell, which was tested by Almroth and his colleagues at the Lockheed Missiles & Space Company in the early 1970s.
STAGS REFERENCES:
Almroth, B. O. and Brogan, F. A., "The STAGS computer code", NASA CR-2950, NASA Langley Research Center, Hampton, VA, 1978.
STAGS Brochure (2002) available online by request: crankin@rhombuscgi.com (pdf format).
(A) Rankin, C.C., Stehlin, P., and Brogan, F.A., "Enhancements to the STAGS computer code", NASA CR-4000, NASA Langley Research center, Hampton, VA, 1986. See also: (B) Rankin, C.C, “Application of Linear Finite Elements to Finite Strain Using Corotation.” AIAA Paper AIAA-2006-1751, 47th AIAA Structures, Structural Dynamics and Materials Conference, May 2006; (C) Rankin, C.C., Brogan, F.A., Loden, W.A., Cabiness, H.D., “STAGS User Manual – Version 5.0,” Rhombus Consultants Group, Inc., Palo Alto, CA, Revised January 2005 (on-line). Previously Report No. LMSC P032594, Lockheed Martin Missiles and Space Company, Palo Alto, CA, June 1998; (D) Rankin, C.C., “The use of shell elements for the analysis of large strain response, AIAA Paper 2007-2384, 48th AIAA Structures, Structural Dynamics and Materials Conference, Hawaii, April 2007.
Riks, E., Rankin C. C., Brogan F. A., "On the solution of mode jumping phenomena in thin walled shell structures", First ASCE/ASM/SES Mechanics Conference, Charlottesville, VA, June 6-9, 1993, in: Computer Methods in Applied Mechanics and Engineering, Vol. 136, 1996.
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