针对大展弦比机翼总体刚度设计问题,提出了梁架模型气动弹性优化和三维优化模型折算两种设计方法,并以大展弦比机翼为例对两种方法的合理性进行了验证。前者基于机翼梁架式模型,利用气动弹性优化方法对其主梁刚度进行设计,其特点是建模简单、计算效率较高,可以在设计信息较少的概念和初步设计阶段使用,但由于约束条件考虑较少,设计结果相对粗略。后者基于机翼三维模型,利用气动弹性优化方法获得优化模型,再利用工程梁理论对优化模型进行刚度折算,获得机翼总体刚度分布,其特点是综合考虑了强度约束、气动弹性约束甚至是工艺约束,设计刚度最接近实际临界情况,可在有一定结构设计信息的初步详细设计阶段使用,但所需结构信息量较大,对结构建模要求较高,计算耗费相对较大。研究表明,基于两种方法设计的刚度分布具有较好的一致性和工程实用性。此外,与传统的经验公式推算方法相比,基于气动弹性优化手段的两种设计方法设计的刚度更趋合理。 Aiming at the design problem of the overall stiffness of large aspect ratio airfoil, two design methods of aerodynamic elastic optimization and three-dimensional optimization model are proposed. The rationality of the two methods is verified by taking the aspect ratio wing as an example . The former based on the wing beam model, the use of aeroelastic optimization method for the design of the main girder stiffness, which is characterized by simple modeling, high computational efficiency, design information can be less used in the concept and preliminary design stage, but due to Constraints considered less, the design results are relatively rough. The latter based on the wing three-dimensional model, the use of aeroelastic optimization method to obtain the optimal model, and then the use of engineering beam theory to optimize the stiffness of the model and converted to obtain the overall wing stiffness distribution, which is characterized by comprehensive consideration of the strength constraints, aerodynamic constraints and even The process constraints and the design stiffness are the closest to the actual critical conditions and can be used in the preliminary detailed design stage with some structural design information. However, the required structural information is large, the structural modeling is demanding, and the calculation cost is relatively large. The research shows that the stiffness distribution based on the two methods has good consistency and engineering practicability. In addition, compared with the traditional empirical formula estimation method, the stiffness of the two design methods based on the aeroelastic optimization method is more reasonable.