蜂窝机翼结构计算与优化设计

SIMULATION AND OPTIMIZATION DESIGN OF AIRFOIL HONEYCOMBS STRUCTURE

首先采用三明治夹心板等效理论建立了全高度蜂窝结构的等效模型,通过仿真计算提取出关注区域,将关注区域依据真实模型进行有限元建模,然后采用子模型分析技术进行细节分析,将仿真结果与试验结果进行对比,验证该分析方法的有效性和准确性。利用提出的分析方法对全高度蜂窝机翼结构进行仿真分析,讨论了全高度蜂窝结构各几何参数与单位质量失稳破坏载荷的关系,结果显示单位质量承载失稳载荷随着上、下板厚和壁厚增大呈现递增趋势,而随蜂窝胞单元边长增大呈递减趋势,且在一定范围内变化较小。最后采用多目标参数方法对蜂窝机翼结构进行了优化分析,结果表明蜂窝胞单元三个几何参数分别处于特定范围内时单位质量承受失稳载荷处于较大值。

For honeycomb structure,a analysis method based on equivalent theory combine with sub-model technology was proposed. The equivalent method based on sandwich plate theory is deduced and equivalent model of full height honeycombs structure is obtained. The global equivalent model of full height honeycombs structure is analyzed by finite element simulation,and sub-model analysis technology is applied to extract the region of interest from global equivalent model of full height honeycombs structure for detail analysis,the comparison of simulation and experimentation indicated the analysis method have better accuracy. Appling the analysis method for full height airfoil honeycombs structure,through simulation results investigated the relation between geometry parameters of full height airfoil honeycombs structure and per unit mass of instability failure load through simulations,moreover the result shows that per unit mass buckling load increases along with thickness of wing skin‘s and airfoil honeycombs structure cell＇s wall grow,reduces along with thickness of airfoil honeycombs structure cell＇s grows,besides in a bound which changes on the small side. Appling multi-objective optimization for full height airfoil honeycombs structure,the results show that per unit mass buckling load stay in great bound when the three geometry parameters of honeycombs structure＇cell stay in a specifically bound.