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| Application of surrogate model in qualification test for sloshed fuel tank |
| Received:July 15, 2020 Revised:October 05, 2020 |
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| DOI：10.7511/jslx20200715003 |
| KeyWord:composite fuel tank qualification test low-frequency sloshing Latin hypercube response surface surrogate model |
| Author | Institution |
| 孙滨 |
中国民用航空沈阳航空器适航审定中心, 沈阳 |
| 韩松 |
大连理工大学 工业装备结构分析国家重点实验室, 大连 |
| 王东林 |
中国民用航空沈阳航空器适航审定中心, 沈阳 |
| 李明 |
大连理工大学 工业装备结构分析国家重点实验室, 大连 |
| 缪圣亮 |
中航通飞研究院有限公司, 珠海 |
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| Abstract: |
| An aircraft wing fuel tank has low-frequency sloshing due to disturbances perturbations and excitations during flight, which may cause the deformation failure in the walls of a wing fuel tank.A response surface surrogate model is introduced to the qualification test for the sloshing of the composite fuel tank in an airplane.Taking the sloshing frequency, and the amplitude, and fuel load as design variables, the peak value of the maximum principal strains of the outer wall of the fuel tank as the response, we develop a statistical model for the top and bottom skins of the composite fuel tank and give the explicit response surface function of the peak strain depending on the sloshing frequency and amplitude, and the fuel load.The effectiveness of the surrogate model is verified by results of full-size experiments and solutions of fluid-solid coupling numerical simulations.The results show that there exists a worst fuel load to maximize the peak value of maximum principal strain, and the failure of the fuel tank mostly occurs on the bottom skin. |
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