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With the application of new lightweight materials in structures of civil aircraft, evaluation of properties for new materials is required to carry out continually.So it is valuable to develop a few effective engineering methods for properties characterization, which can decrease the research costs and periods.Sonic fatigue problem is one of the important terms of civil aircraft airworthiness examination.In this paper, a kind of engineering analysis method is employed to study the sonic response characteristics of the typical commercial skin-stiffener aircraft structure fabricated from aluminum alloys.In addition, the sonic response experiment for this structure is carried out, and the resonant frequency and root mean square (RMS) stress are measured.According to the comparison of engineering analysis results and experimental results, the analysis error and effectiveness of this method is evaluated.The resonant frequency analysis results for this method are in good agreement with the experimental results, and the prediction results of RMS stress are also acceptable in engineering.