Abstract
Pressurized transport aircraft fuselage panels see the combined action of gust loading and internal pressurization that causes a rather complex biaxial pseudo-random cyclic loading action. Stress biaxiality is also known to affect constant amplitude fatigue. Fatigue crack growth was studied using cruciform test coupons under constant amplitude and a modified TWIST load spectrum superposed with biaxial quasi-static load simulating internal cabin pressure. The experiments were performed on a specially designed four-actuator biaxial test system suited for high frequency in-phase and out-of-phase constant amplitude loading as well as biaxial pseudo-random spectrum loading. Observed crack growth rates were correlated with stress intensity values, corrected for biaxiality.
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