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NASA-TN-2601
Compressive Buckling of Simple supported Curved Plates and Cylinders of Sandwich Construction
Year: 1952
Abstract: The use of sandwich construction for compression-carrying components of aircraft will often require the calculation of the compressive buckling strength of curved sandwich plates.
In the present paper, therefore, a theoretical solution is given for the elastic buckling load, in uniform axial compression, of simply supported, cylindrically curved, rectangular plates and circular cylinders of two types of sandwich construction: the corrugated-core type and the isotropic type (e.g. Metalite).
The analysis is based on the small-deflection buckling theory of reference 1 which differs from ordinary curved-plate theory principally by the inclusion of the effects of deflections due to transverse shear. The curvature is assumed constant and the thickness small compared with the radius and axial and circumferential dimensions. The core modulus in the transverse direction is assumed to be infinite; thus, consideration of types of local buckling in which corresponding points on the upper and lower faces do not remain equidistant is eliminated. The corrugated-core sandwich is assumed to be symmetrical, on the average, about the middle surface, so that the force distortion relations are relatively simple (see reference 2), and is assumed to have infinite transverse shear stiffness in planes parallel to the corrugations. The core of the isotropic sandwich (flexural properties identical in axial and circumferential directions) is assumed to carry no face-parallel stresses.
The results of the solution are presented in nondimensional form through equations and graphs. The details of the analysis are given in two appendixes.
The results of the present investigation are compared with previous work on the subject of compressive buckling of curved sandwich plates and cylinders (references 3, 4, and 5). This previous work is confined to sandwich construction of the isotropic type only. The present paper includes results for the isotropic sandwich covering a larger curvature range and gives the same, or more conservative, results.
In the present paper, therefore, a theoretical solution is given for the elastic buckling load, in uniform axial compression, of simply supported, cylindrically curved, rectangular plates and circular cylinders of two types of sandwich construction: the corrugated-core type and the isotropic type (e.g. Metalite).
The analysis is based on the small-deflection buckling theory of reference 1 which differs from ordinary curved-plate theory principally by the inclusion of the effects of deflections due to transverse shear. The curvature is assumed constant and the thickness small compared with the radius and axial and circumferential dimensions. The core modulus in the transverse direction is assumed to be infinite; thus, consideration of types of local buckling in which corresponding points on the upper and lower faces do not remain equidistant is eliminated. The corrugated-core sandwich is assumed to be symmetrical, on the average, about the middle surface, so that the force distortion relations are relatively simple (see reference 2), and is assumed to have infinite transverse shear stiffness in planes parallel to the corrugations. The core of the isotropic sandwich (flexural properties identical in axial and circumferential directions) is assumed to carry no face-parallel stresses.
The results of the solution are presented in nondimensional form through equations and graphs. The details of the analysis are given in two appendixes.
The results of the present investigation are compared with previous work on the subject of compressive buckling of curved sandwich plates and cylinders (references 3, 4, and 5). This previous work is confined to sandwich construction of the isotropic type only. The present paper includes results for the isotropic sandwich covering a larger curvature range and gives the same, or more conservative, results.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:24:22Z | |
| date available | 2017-09-04T17:24:22Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | CEYHUEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/147580 | |
| description abstract | The use of sandwich construction for compression-carrying components of aircraft will often require the calculation of the compressive buckling strength of curved sandwich plates. In the present paper, therefore, a theoretical solution is given for the elastic buckling load, in uniform axial compression, of simply supported, cylindrically curved, rectangular plates and circular cylinders of two types of sandwich construction: the corrugated-core type and the isotropic type (e.g. Metalite). The analysis is based on the small-deflection buckling theory of reference 1 which differs from ordinary curved-plate theory principally by the inclusion of the effects of deflections due to transverse shear. The curvature is assumed constant and the thickness small compared with the radius and axial and circumferential dimensions. The core modulus in the transverse direction is assumed to be infinite; thus, consideration of types of local buckling in which corresponding points on the upper and lower faces do not remain equidistant is eliminated. The corrugated-core sandwich is assumed to be symmetrical, on the average, about the middle surface, so that the force distortion relations are relatively simple (see reference 2), and is assumed to have infinite transverse shear stiffness in planes parallel to the corrugations. The core of the isotropic sandwich (flexural properties identical in axial and circumferential directions) is assumed to carry no face-parallel stresses. The results of the solution are presented in nondimensional form through equations and graphs. The details of the analysis are given in two appendixes. The results of the present investigation are compared with previous work on the subject of compressive buckling of curved sandwich plates and cylinders (references 3, 4, and 5). This previous work is confined to sandwich construction of the isotropic type only. The present paper includes results for the isotropic sandwich covering a larger curvature range and gives the same, or more conservative, results. | |
| language | English | |
| title | NASA-TN-2601 | num |
| title | Compressive Buckling of Simple supported Curved Plates and Cylinders of Sandwich Construction | en |
| type | standard | |
| page | 36 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |