中文摘要：

为了克服现有机翼结构重量计算方法的局限性，提出一种基于多学科分析优化的机翼结构重量计算方法。以客机机翼为例，阐述整个计算流程。计算流程的关键步骤包括机翼外形和结构参数化建模、气动分析模型自动生成与外形优化、结构有限元模型的自动生成和结构优化。应用CAD软件CATIA的二次开发方法，实现机翼外形几何模型、结构布置几何模型和气动分析模型的自动生成；应用MSC．Patran的PCL编程技术，实现结构有限元模型的自动生成；应用等效刚度和等效强度方法，提高结构有限元模型自动生成的稳健性，缩短结构分析和优化的计算时间；应用多学科集成和优化技术，建立机翼结构重量预测的计算平台，实现整个计算过程的自动化。算例表明这种方法稳健、有效，可快速地分析机翼外形参数与结构重量之间的关系，分析不同展向载荷分布和不同选材方案对机翼结构重量的影响。

英文摘要：

A wing-structure weight prediction method using multidisciplinary analysis and optimization is proposed to over- come the limitations of the current predictions of wing-structure weight. The wing of a short/medium haul transport was used as an example to illustrate the procedure of the method. The key steps of the method include parametric modeling for wing configuration and structural layout, automatic generation of wing aerodynamic model, aerodynamic optimization, automatic generation of the wing structural finite element model and wing structural optimization. The parametric modeling for the wing configuration and structural layout, and automatic generation of aerodynamic model was implemented by running VB codes in CATIA. The automatic generation of wing structural finite element model was implemented by running MSC. Patran Command Language （PCL~） codes. The equivalent stiffness and strength method was used to enhance the robustness of the finite ele- ment model generation of the wing structure and reduce the computational burden of the structural analysis and optimization. A computational framework for the wing-structure weight prediction was established using multidisciplinary integration and optimization, and the overall process for the wing-structure weight computation was carried out automatically. The example indicates that the method is robust and efficient, and is able to rapidly obtain the impacts of wing configurations, spanwise load distributions and structural materials on the wing-structure weights.