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根据机翼气动载荷和机翼弹性变形之间存在的关系,以机翼的总升力不变和结构强度作为约束条件,提出一种新的气动/结构耦合的刚度设计方法。该方法首先通过数值实验设计研究机翼扭转变形和弯曲变形对机翼气动载荷的影响,并用主成分回归方法构建了机翼变形和气动载荷之间的响应面模型。然后以该模型为基础,构建气动/结构一体化设计模型,此模型仅考虑强度约束和总升力不变的要求,放弃了传统优化设计模型中的挠度和扭转约束。通过2种优化模型的对比,说明应用该方法设计出的机翼结构,重量减轻1.23%,机翼总体扭转变形减小33%,刚度设计更为合理。
According to the relationship between the aerodynamic loads on the wing and the elastic deformation of the wing, a new aerodynamic / structural coupling stiffness design method is proposed based on the fact that the total lift of the wing is constant and the structural strength is the constraint condition. In the method, the numerical experimental design is used to study the influence of wing torsion deformation and bending deformation on the aerodynamic loading of the aerofoils. The principal component regression method is used to construct the response surface model between aerofoil deformation and aerodynamic loads. Based on the model, an aerodynamic / structural integrated design model is constructed. The model only considers the requirements of strength constraint and total lift, and abandons the deflection and torsion constraints in the traditional optimization design model. The comparison of the two optimization models shows that the wing structure designed by this method has a weight reduction of 1.23%, a total reduction of wing torsional deformation of 33% and a more reasonable stiffness design.