舰载机机身加筋壁板屈曲疲劳试验

doi:10.7527/S1000-6893.2018.22276

Abstract

Abstract: During the catapult launch and the arrested landing processes for carrier-based aircraft, buckling waves of the tension field at fuselage panel will induce additional tension or bending stress, which significantly decreases the structural fatigue strength and changes the fatigue failure position. The fatigue behavior under repeated buckling is studied through three-point bending test of tension-field spar. The critical buckling load measured from the test matches well with that obtained by adopting the engineering tension field theory. Then, the curves of normalized load ratio vs fatigue life and the curves of normalized load ratio vs tensile field factor are derived from the buckling fatigue test under three different load levels. Finally, the lightweight design of stiffened panel can be realized by controlling the severe level of tensile field based on the relationship between tensile field factor and load and curve of load vs life as well as design service goal of the aircraft. This paper accumulates beneficial data for repeated buckling fatigue evaluation of carrier-based aircraft during the catapult launch and arrested landing.

Key words: buckling, fatigue test, tension field, stiffened panel, S-N curve, Digital Image Correlation (DIC)

CLC Number:

V215

ZHANG Yanjun, ZHU Liang, YANG Weiping, LI Xiaopeng, LEI Xiaoxin. Buckling fatigue test of fuselage stiffened panel for carrier-based aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(4): 622276-622276.

References

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Buckling fatigue test of fuselage stiffened panel for carrier-based aircraft

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