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NACA-TN-951
Tests on thin-walled celluloid cylinders to determine the interaction curves under combined bending, torsion, and compression or tension loads
Year: 1945
Abstract: INTRODUCTION
The modern airplane body is essentially a thin-walled shell. In some body designs, all longitudinal skin stiffeners are removed or only three longitudinal skin stiffeners are used, thus the thin Shell becomes the major structural unit in resisting the applied external loads. In general, the airplane body is subjected to external forces which will produce compressive, bending, and twisting stresses in the body structure.
Very little test information is available at present on the ultimate strength of thin-walled metal cylinders under combined loads, particularly so if compression, bending, and twisting loads are acting simultaneously. One reason for the lack of this information is due, no doubt, to the great cost and amount of time to carry out a complete test program on full-size metal cylinders. The purpose of this research project was to determine whether the tasting of inexpensive small cylinders fabricated from thin celluloid sheet would give valuable reliable data for determining the ultimate strength interaction relationships for circular thin-walled cylinders when subjected to combinations of compressive, bending, and twisting loads.
It is thought that the results obtained in this project have shown definitely that valuable design information can be obtained from tests of celluloid cylinders with comparatively small expenditure of time and money.
The funds for this research project were supplied by the National Advisory Committee for Aeronautics. The project was carried out as a regular research project under the Purdue Research Foundation and. the Purdue University Engineering Experiment Station.
The actual test work was carried on in the department of aeronautics of the School of Mechanical and Aeronautical Engineering under the direct supervision of Professor E.F. Bruhn. The test apparatus was constructed and the majority of the cylinder tests were made by Mr. R. L. Dickinson, former instructor of Aeronautical Engineering at Purdue University. The remainder of the tests were completed by Mr. G. Koerner, senior student at Purdue, and Professor Bruhn. The digest of the data and the writing of the report were carried out by Professor Bruhn.
The writer is indebted to Professor K. D. Wood for valuable suggestions and for reading the final report.
The modern airplane body is essentially a thin-walled shell. In some body designs, all longitudinal skin stiffeners are removed or only three longitudinal skin stiffeners are used, thus the thin Shell becomes the major structural unit in resisting the applied external loads. In general, the airplane body is subjected to external forces which will produce compressive, bending, and twisting stresses in the body structure.
Very little test information is available at present on the ultimate strength of thin-walled metal cylinders under combined loads, particularly so if compression, bending, and twisting loads are acting simultaneously. One reason for the lack of this information is due, no doubt, to the great cost and amount of time to carry out a complete test program on full-size metal cylinders. The purpose of this research project was to determine whether the tasting of inexpensive small cylinders fabricated from thin celluloid sheet would give valuable reliable data for determining the ultimate strength interaction relationships for circular thin-walled cylinders when subjected to combinations of compressive, bending, and twisting loads.
It is thought that the results obtained in this project have shown definitely that valuable design information can be obtained from tests of celluloid cylinders with comparatively small expenditure of time and money.
The funds for this research project were supplied by the National Advisory Committee for Aeronautics. The project was carried out as a regular research project under the Purdue Research Foundation and. the Purdue University Engineering Experiment Station.
The actual test work was carried on in the department of aeronautics of the School of Mechanical and Aeronautical Engineering under the direct supervision of Professor E.F. Bruhn. The test apparatus was constructed and the majority of the cylinder tests were made by Mr. R. L. Dickinson, former instructor of Aeronautical Engineering at Purdue University. The remainder of the tests were completed by Mr. G. Koerner, senior student at Purdue, and Professor Bruhn. The digest of the data and the writing of the report were carried out by Professor Bruhn.
The writer is indebted to Professor K. D. Wood for valuable suggestions and for reading the final report.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:42:38Z | |
| date available | 2017-09-04T15:42:38Z | |
| date copyright | 01/01/1945 | |
| date issued | 1945 | |
| identifier other | PJYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/44895 | |
| description abstract | INTRODUCTION The modern airplane body is essentially a thin-walled shell. In some body designs, all longitudinal skin stiffeners are removed or only three longitudinal skin stiffeners are used, thus the thin Shell becomes the major structural unit in resisting the applied external loads. In general, the airplane body is subjected to external forces which will produce compressive, bending, and twisting stresses in the body structure. Very little test information is available at present on the ultimate strength of thin-walled metal cylinders under combined loads, particularly so if compression, bending, and twisting loads are acting simultaneously. One reason for the lack of this information is due, no doubt, to the great cost and amount of time to carry out a complete test program on full-size metal cylinders. The purpose of this research project was to determine whether the tasting of inexpensive small cylinders fabricated from thin celluloid sheet would give valuable reliable data for determining the ultimate strength interaction relationships for circular thin-walled cylinders when subjected to combinations of compressive, bending, and twisting loads. It is thought that the results obtained in this project have shown definitely that valuable design information can be obtained from tests of celluloid cylinders with comparatively small expenditure of time and money. The funds for this research project were supplied by the National Advisory Committee for Aeronautics. The project was carried out as a regular research project under the Purdue Research Foundation and. the Purdue University Engineering Experiment Station. The actual test work was carried on in the department of aeronautics of the School of Mechanical and Aeronautical Engineering under the direct supervision of Professor E.F. Bruhn. The test apparatus was constructed and the majority of the cylinder tests were made by Mr. R. L. Dickinson, former instructor of Aeronautical Engineering at Purdue University. The remainder of the tests were completed by Mr. G. Koerner, senior student at Purdue, and Professor Bruhn. The digest of the data and the writing of the report were carried out by Professor Bruhn. The writer is indebted to Professor K. D. Wood for valuable suggestions and for reading the final report. | |
| language | English | |
| title | NACA-TN-951 | num |
| title | Tests on thin-walled celluloid cylinders to determine the interaction curves under combined bending, torsion, and compression or tension loads | en |
| type | standard | |
| page | 69 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1945 | |
| contenttype | fulltext |