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针对某大展弦比复合材料无人机机翼结构,利用有限元素法进行机翼结构的屈曲及后屈曲分析。首先采用MSC.Patran/Nastran软件进行结构屈曲分析,目的是确定机翼结构易发生屈曲的区域;然后对不同区域进行分析,确定需要进行后屈曲分析的细节模型。对细节模型进行后屈曲分析时采用MSC.Patran/Marc软件,分析方法采用弧长法。通过机翼结构的后屈曲分析,可以分析出结构的失稳路径。结果表明,该机翼存在屈曲失稳问题。该机翼的地面静力试验结果验证分析结果的可信性。
Aiming at the wing structure of a large aspect ratio composite UAV, the finite element method is used to analyze the buckling and post-buckling of the wing structure. The structural buckling analysis is first performed using MSC.Patran / Nastran software to determine the areas prone to buckling of the wing structure. The different areas are then analyzed to determine the detail model that requires post-buckling analysis. The post-buckling analysis of the detail model was performed using the MSC.Patran / Marc software and the analysis method using the arc-length method. By the post-buckling analysis of the wing structure, the instability path of the structure can be analyzed. The results show that the wing has buckling instability problem. The wing static test results verify the credibility of the results.