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Recommendations for Numerical Solution of Reinforced-Panel And Fuselage-Ring Problems

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:44:40Z
date available2017-09-04T17:44:40Z
date copyright01/01/1949
date issued1949
identifier otherEGYHUEAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std/handle/yse/167772
description abstractProcedures are recommended for solving the equations of equilibrium of reinforced panels and isolated fuselage rings as represented by the external loads and the operations table established according to Southwell's method. From the solution of these equations the stress distribution can be easily determined. The method of systematic relaxations, the matrix-calculus method, and several other methods applicable in special cases are discussed. Definite recommendations are made for obtaining the solution of reinforced-panel problems which are generally designated as shear lag problems. The procedures recommended are demonstrated in the analysis of a number of panels. In the case of fuselage rings it is not possible to make definite recommendations for the solution of the equilibrium equations for all rings and loadings. However, suggestions based on the latest experience are made and demonstrated on several rings.
languageEnglish
titleNACA-TR-934num
titleRecommendations for Numerical Solution of Reinforced-Panel And Fuselage-Ring Problemsen
typestandard
page34
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1949
contenttypefulltext
subject keywordsDISPLACEMENT
subject keywordsFUSELAGES
subject keywordsLOAD DISTRIBUTION (FORCES)
subject keywordsMATRICES (MATHEMATICS)
subject keywordsNUMERICAL ANALYSIS
subject keywordsREINFORCED PLATES
subject keywordsREINFORCEMENT RINGS
subject keywordsRELAXATION METHOD (MATHEMATICS)
subject keywordsSTRESS ANALYSIS
subject keywordsSTRESS CONCENTRATION
subject keywordsSTRESSED-SKIN STRUCTURES


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