Materials Reports  2019, Vol. 33 Issue (Z2): 215-221 |
| INORGANIC MATERIALS AND CERAMIC MATRIX COMPOSITES |
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| Compression Strength Analysis and Test of CFRP Hat-stringer on Civil Aircraft |
| ZHANG Xu, FENG Rui, ZHANG Ye, GUO Wei, LIU Fu
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| Shanghai Aircraft Design and Research Institute, Shanghai 201210 |
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Abstract In order to verify compression strength analysis method of CFRP hat-stringer on civil aircraft, a set of CFRP hat-stringer test articles layered from unidirectional tapes and fabric prepregs for compression tests were manufactured. As the compression load increased, local buckling appeared at the stringer bottom, wrest and foot skin with the load-strain curves diverging obviously. Then the compression load increased until the stringer crippled. Classical engineering analysis method and finite element modeling (FEM) method were both used to estimate the initial local buckling load and the crippling load. The loads computed via engineering analysis method were less than the test mean value with 37.5% and 27.6% deviation respectively. While the loads via FEM were close to the test mean value only with 1.4% and 2.3% deviation respectively. It was shown that, the engineering method for CFRP hat-stringer initial buckling and crippling loads calculation was more conservative to make sure that the structural design was safe enough.
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Published: 25 November 2019
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| About author:: Xu Zhang received his M.S. degree in June 2009 from Nanjing University of Aeronautics and Astronautics in Engineering Mechanics. Since July 2009, he has worked in structure stress department in Shanghai Aircraft Design and Research Institute. Now his work is mainly on CFRP aircraft structure stress analysis and verification tests. |
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