RESEARCH ON TEST METHOD OF FUSELAGE PANEL SUBJECTED TO SHEAR LOAD by ZANG WeiFeng, SU ShaoPu, ZHANG HaiYing, DONG DengKe

Subjects: “…Fuselage panel;Shear load;Boundary condition simulation;"D"jig;Arch angle connector;Shear stress…”
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DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK by CHEN An, WEI YuLong, LIAO JiangHai, DONG DengKe

Subjects: “…Fuselage panel;Longitudinal crack;Damage tolerance experiment;Crack propagation;Residual strength;Stress intensify factor…”
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RESEARCH ON TEST METHOD OF FUSELAGE PANEL SUBJECTED TO INTERNAL PRESSURE LOAD by ZANG WeiFeng, DONG DengKe, ZHANG HaiYing

“…The test method of fuselage panel subjected to internal pressure load is an important technique for aircraft structure strength research.The constraint simulation technique for the curved and straight boundaries of fuselage panel was studied based on boundary requirements.A test method using "D"jig to simulate the straight boundary conditions and airproof end-plate to simulate the curved boundary conditions of fuselage panels were proposed.A test panel and a set of fixtures were designed and manufactured,and validation tests were conducted.Measured stresses in test are reasonably distributed and are consistent with theoretic result.The proposed test method is proven to be proper and valid,and it provides reference for configuration-selection tests of fuselage panel subjected to internal pressure load.…”
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RESEARCH ON SIMPLIFICATION OF LOADING SPECTRUM FOR FATIGUE CRACK GROWTH TEST by ZHANG Kan, DONG DengKe, CHEN Li

“…A new subsection-loading method has been used for solving question that was taken for aircraft structure cracking growth testing（ CGT） in a long time.Based on technology of low load cut-off,the random loading spectrum used in CGT,associated with the stress intensity factor in crack tip of specimens,was investigated.Furthermore,Testing verification of panel specimen has been completed.The testing result showed that pre-simplification agrees with subsection of the random loading spectrum,and application of the method can reduce the time of CGT reliably（ time reducing by 27% in the testing）.Finally,it can be concluded that the method can directly be applied for CGT of fuselage panel and other aircraft structures.…”
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