An efficient engineering method to evaluate fatigue buckling life of structure on pure shear is proposed based on detailed fatigue rate value. The typical panel test specimen applies a new design concept of integral inserted plate to avoid the failure of structure on non-critical zone in the process of diagonal tensile loading; Experimental results verify the feasibility of the proposed fatigue buckling model; The failure mechanism of structure on fatigue buckling and the correlated character of crack growth are analyzed to provide a technical support for aircraft anti-buckling design. This research illustrates that fatigue buckling failure is mostly ascribed to the effects of bending stress and shear stress on rivets. Once the structure is cracked, crack propagates along the vertical direction of buckling wave. When it arrives adjacent to the wave center, the growth rate excessively increases; the critical buckling load is decreasing with loading cycles increased. The proposed fatigue life evaluation method provides a convenient engineering algorithm for the fatigue evaluation of structure at post-buckling state.
SU Shaopu
,
CHANG Wenkui
,
CHEN Xianmin
. Fatigue buckling test and analytical approach of aircraft typical panel structures[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022
, 43(5)
: 225219
-225219
.
DOI: 10.7527/S1000-6893.2021.25219
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