民机复材机翼主结构优化设计及减重分析

Primary Structure Optimization of Civil Aircraft Composite Wingbox and Weight Saving Analysis

在同一输入条件下,采用两级序列优化方法,基于同一假想飞机的机翼机身有限元模型,在相同的外形输入和载荷工况、以及不同的约束条件下,采用了基于敏度的优化方法,嵌入集成了工程校核方法,以重量最轻为目标进行了金属构型和复材构型两种机翼翼盒主结构的优化设计和分析,优化过程中考虑了长桁蒙皮刚度比例、各剖面EI/GJ刚度、制造限制等约束条件。优化结果分析表明:基于自然网格模型的高精度分析、嵌入式并行校核和多工况、多专业约束优化条件下所给出的设计结果更符合工程实际应用要求;对同一假想飞机翼盒主结构,复材构型比金属构型实现减重约15%。

Based on the wing-fuselage natural GFEM of same target aircraft and same top level input requirement including aerodynamic surface and load cases,design optimization was conducted to achieve the lowest composite and metal configuration wingbox weight considering the multiple constrains by the optimization method of sensitivity.The engineering check procedure was embedded and integrated in the process of optimization and the constrains of stiffness ratio of stringer to skin,profile stiffness requirement EI/GJ and manufacturing limitation was considered in the optimization.The optimization results shown:the multi-constrains optimization method with regularized model and high precision analysis could actually meet with requirements from structure engineering,which confirms the feasibility and efficiency of the current optimization method.And,to the same target wingbox structure,the composite configuration could achieve weight saving up to 15%comparing with the metal one.