This report describes the work performed by lockheed palo alto research labora- tory palo alto california 94304. The work was sponsored by air force office of scientific research bolling afb washington d. C. Under grant f49620-77-c-0l22 and by the flight dynamics laboratory air force wright aeronautical laboratories wright-patterson afb ohio under contract f3361s-76-c-31os. The work was completed under task 2307nl basic research in behavior of metallic and composite components of airframe structures . The work was admini- stered by lt. Col. J. D. Morgan afosr and dr. N. S. Khot afwal fibra . The contract work was performed between october 1977 and december 1980. The technical report was released by the author in december 1981. Preface many structures are assembled from parts which are thin. For example a stiffened plate or cylindrical panel is composed of a sheet the thickness of which is small com- pared to its length breadth and stiffener- spacing and stiffeners the thickness of which is small compared to their heights and lengths. These assembled structures loaded in compression can buckle overall that is sheet and stiffeners can collapse together in a general instability mode the sheet can buckle locally between stiffeners the stiffeners can cripple and a variety of complex buckling interactions can occur involving local and overall deformations of both sheet and stiffeners. More complex built-up structures can buckle in more complex and subtle ways.
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