摘要：【中文】本发明实施例公开了本发明实施例提供一种多支点翼面结构支点位置优化方法，所述方法包括：沿翼面展向选取至少M个剖面，根据至少M个剖面构建连续梁模型；根据力的等效原理，将预设翼面总载荷f_sum分别输入到所述连续梁模型中的至少M个剖面上，得到翼面载荷分布；根据所述翼面载荷分布和所述连续梁模型，构建支点位置优化模型；根据所述支点位置优化模型获得N组支点位置参数；根据所述N组支点位置参数、相关系数α和预设翼面总载荷f_sum建立适应度函数F，所述相关系数α为支点位置参数中各个参数的权重；用优化算法对适应度函数F进行优化计算，获得支点位置最优解。 【EN】The embodiment of the invention discloses a method for optimizing the position of a fulcrum of a multi-fulcrum airfoil structure, which comprises the following steps: selecting at least M sections along the span direction of the airfoil surface, and constructing a continuous beam model according to the at least M sections; according to the force equivalence principle, presetting the total wing surface load f_sumRespectively inputting the parameters into at least M sections in the continuous beam model to obtain airfoil load distribution, constructing a fulcrum position optimization model according to the airfoil load distribution and the continuous beam model, obtaining N groups of fulcrum position parameters according to the fulcrum position optimization model, and obtaining N groups of fulcrum position parameters, correlation coefficients α and preset airfoil total load f according to the N groups of fulcrum position parameters, the correlation coefficients α and the preset airfoil total load f_sumAnd (3) establishing a fitness function F, wherein the correlation coefficient α is the weight of each parameter in the fulcrum position parameters, and performing optimization calculation on the fitness function F by using an optimization algorithm to obtain an optimal solution of the fulcrum position.