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NASA-TP-1785
Tests of graphite/polyimide sandwich panels in uniaxial edgewise compression
Year: 1980
Abstract: The local and general buckling behavior of graphite/polyimide sandwich panels simply supported along all four edges and loaded in uniaxial edgewise compression were investigated. Material properties of sandwich panel constituents (adhesive and facings) were determined from flatwise tension and sandwich beam flexure tests. Buckling specimens were 30.5 by 33 cm, had quasi-isotropic, symmetric facings, and a glass/polyimide honeycomb core. Core thicknesses were varied and three panels of each thickness were tested at room temperature to investigate failure modes and corresponding buckling loads. Specimens 0.635 cm thick failed by overall buckling at loads close to the analytically predicted buckling load; all other panels failed by face wrinkling. Results of the wrinkling tests indicated that several buckling formulas were unconservative and therefore not suitable for design purposes; a recommended wrinkling equation is presented.
Subject: COMPOSITES
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:28:33Z | |
| date available | 2017-09-04T17:28:33Z | |
| date copyright | 01/01/1980 | |
| date issued | 1980 | |
| identifier other | CPWWAEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/151677 | |
| description abstract | The local and general buckling behavior of graphite/polyimide sandwich panels simply supported along all four edges and loaded in uniaxial edgewise compression were investigated. Material properties of sandwich panel constituents (adhesive and facings) were determined from flatwise tension and sandwich beam flexure tests. Buckling specimens were 30.5 by 33 cm, had quasi-isotropic, symmetric facings, and a glass/polyimide honeycomb core. Core thicknesses were varied and three panels of each thickness were tested at room temperature to investigate failure modes and corresponding buckling loads. Specimens 0.635 cm thick failed by overall buckling at loads close to the analytically predicted buckling load; all other panels failed by face wrinkling. Results of the wrinkling tests indicated that several buckling formulas were unconservative and therefore not suitable for design purposes; a recommended wrinkling equation is presented. | |
| language | English | |
| title | NASA-TP-1785 | num |
| title | Tests of graphite/polyimide sandwich panels in uniaxial edgewise compression | en |
| type | standard | |
| page | 80 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1980 | |
| contenttype | fulltext | |
| subject keywords | COMPOSITES | |
| subject keywords | COMPRESSION | |
| subject keywords | DATA | |
| subject keywords | GRAPHITE | |
| subject keywords | HIGH | |
| subject keywords | HONEYCOMB | |
| subject keywords | LOADS | |
| subject keywords | POLYIMIDE | |
| subject keywords | SANDWICH | |
| subject keywords | STABILITY | |
| subject keywords | STRUCTURAL | |
| subject keywords | STRUCTURES | |
| subject keywords | TABLES | |
| subject keywords | TEMPERATURE | |
| subject keywords | TESTS |