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复合材料波纹板稳定性是飞机机翼结构设计需要考虑的重要方面,是目前飞机结构设计中的一大难点。为了建立波纹板屈曲的数值分析方法,对复合材料波纹板在剪切载荷作用下的屈曲进行试验、工程算法和有限元方法研究。通过试验,探索了3种不同波长的复合材料波纹板的屈曲载荷和破坏载荷;采用工程算法和有限元方法计算了8种不同波长的复合材料波纹板屈曲载荷,并与试验结果进行了比较。在试验和分析研究的基础上,初步提出了对复合材料波纹板屈曲载荷计算值进行修正的修正因子。结果表明,波纹板屈曲载荷的工程计算值大于试验值,而有限元计算值小于试验值,且随着波长的增大,两种方法相对于试验结果的计算误差越来越大。计算结果也表明,所提出的计算载荷修正因子可以有效地对有限元计算值和工程计算值进行修正,使修正后的计算值接近于试验值。
The stability of the composite corrugated board is an important aspect that needs to be considered in the design of the aircraft wing structure and is a major difficulty in the current aircraft structure design. In order to establish the numerical analysis method of the buckling of the corrugated plate, the buckling of the corrugated composite plate under the shear load is tested, the engineering algorithm and the finite element method are studied. The buckling load and failure load of three kinds of composite corrugated plates with different wavelengths were explored by experiments. The buckling loads of corrugated composite plates with eight different wavelengths were calculated by engineering method and finite element method, and compared with the experimental results. Based on the experimental and analytical studies, the correction factor for the calculation of the buckling load of the corrugated composite sheet is preliminarily proposed. The results show that the calculated value of flexural load of corrugated board is larger than the experimental value, while the calculated value of finite element is less than the experimental value. With the increase of wavelength, the calculation errors of the two methods with respect to the test result are more and more large. The calculation results also show that the calculated load correction factor can effectively correct the calculated value of the finite element and the calculated value of the engineering so that the corrected value is close to the experimental value.