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Copyright of Journal of Mechanical Strength / Jixie Qiangdu is the property of Zhengzhou Research Institute of Mechanical Engineering and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

The test technology of fuselage panel subjected to combined load is an important technique for aircraft structure strength research. In order to discover the load characters of the fuselage panel subjected to combined internal pressure and shear load, “D” jig was utilized to simulate the boundary conditions of fuselage panel, the internal pressure load was applied by inflating, the shear load was applied by twisting the single box section, the internal pressure load test, shear load test and combined internal pressure and shear load test were completed. The measured stress is in good agreement with the theoretical result, the test shows that the stress level and stress distribution of the fuselage panel skin of the combined internal pressure and shear load test are the superposition of the stress level and stress distribution of the fuselage panel skin of the internal pressure load test and shear load test. Due to the superposition of the outer normal direction deformation of the fuselage panel under the internal pressure load and the normal direction deformation of the fuselage panel under the shear load, the error between the measured stress and the theoretical result in the combined internal pressure and shear load test is larger than that in the single load test, and the precision of the stress distribution becomes worse. [ABSTRACT FROM AUTHOR]