| 總結: | As the main bearing structure of civil aircraft, the fuselage frame is of great significance to the weight of the aircraft.A hoop bending test is carried out on the composite fuselage curved panels with C-type and Z-type integral frames to study the failure mode and load-bearing capacity of the integral frame, as well as the influence of lateral support on the load-bearing capacity of the frame.A pair of force couple is used to apply bending load on the panel.The modified engineering method and finite element (FE) model are used to predict the failure load and compare with the test results.The results show that C-type integral fame has better design redundancy than Z-type integral frame.The arrangement of lateral support is the key to improve the load capability of the integral frame, as it can affect the failure mode.The modified engineering method can predict the frame lateral stability effectively,which can be used for calculation iterations of the integral frame size and lateral support arrangement rapidly.However, the engineering algorithm for inner flange local stability is not conservation, and the FE model should be used for optimization iteration.
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