Transactions of Nanjing University of Aeronautics & Astronautics
Equivalent Constant Amplitude Spectrum Design Method and Experimental Verification of Structural Crack Growth Flight-by-Flight Spectrum
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Abstract:
In fatigue damage tolerance verification tests of aircraft structures， the simulation and loading of flight-by-flight spectra require considerable time and resources. To improve the efficiency of load spectrum design and testing， an equivalent constant-amplitude spectrum design method for flight-by-flight spectra is proposed based on the equivalence of crack growth behavior. By combining the Paris crack growth model with the Walker stress ratio correction， the equivalent stress amplitude is directly calculated using structural parameters and load spectrum characteristics， enabling a rapid transformation from variable-amplitude spectra to constant-amplitude spectra. The original spectrum is discretized based on the load-exceedance curve， and the equivalence relationship between multi-level block spectra and constant-amplitude spectra is established. Taking a typical lower wing skin structure of a transport aircraft as an example， two equivalent spectra are designed and validated through fatigue crack growth tests on 2024-T351 center-hole plate specimens. The experimental results show that the fatigue life deviation between the equivalent spectra and the original flight-by-flight spectrum is within 10%， demonstrating the effectiveness of the proposed method. Moreover， the equivalent spectrum constructed under the condition of invariant mean flight stress exhibits higher equivalence accuracy. The influence of spectral shape on the equivalent stress amplitude is further analyzed， revealing that the equivalent stress amplitude increases with the spectrum shape coefficient. The proposed method provides a useful reference for load spectrum design in aircraft structural damage tolerance verification tests.
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This work was supported by the National Natural Science Foundation of China （No.52075244）.
Clc Number:
V215
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