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NACA-TR-934
Recommendations for Numerical Solution of Reinforced-Panel And Fuselage-Ring Problems
Year: 1949
Abstract: Procedures 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.
Subject: DISPLACEMENT
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:44:40Z | |
| date available | 2017-09-04T17:44:40Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | EGYHUEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/167772 | |
| description abstract | Procedures 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. | |
| language | English | |
| title | NACA-TR-934 | num |
| title | Recommendations for Numerical Solution of Reinforced-Panel And Fuselage-Ring Problems | en |
| type | standard | |
| page | 34 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext | |
| subject keywords | DISPLACEMENT | |
| subject keywords | FUSELAGES | |
| subject keywords | LOAD DISTRIBUTION (FORCES) | |
| subject keywords | MATRICES (MATHEMATICS) | |
| subject keywords | NUMERICAL ANALYSIS | |
| subject keywords | REINFORCED PLATES | |
| subject keywords | REINFORCEMENT RINGS | |
| subject keywords | RELAXATION METHOD (MATHEMATICS) | |
| subject keywords | STRESS ANALYSIS | |
| subject keywords | STRESS CONCENTRATION | |
| subject keywords | STRESSED-SKIN STRUCTURES |