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通过刚度矩阵转换,将复合材料层合板等效成正交各向异性材料板,并采用beam单元模拟加筋桁条。将机翼盒段的蒙皮厚度和加筋桁条面积作为设计变量,机翼盒段的质量作为目标函数,运用多岛遗传算法和序列二次规划算法相结合的优化方法,对多变量、多约束条件下的大展弦比复合材料机翼进行结构优化设计。通过算例分析,机翼的复合材料结构质量下降了9.55%,优化时间较短。
Through the stiffness matrix conversion, the composite laminates are equivalent to the orthotropic material plate, and the beam element is used to simulate the stiffener. Taking the skin thickness of wing box segment and the area of stiffened stringer as design variables and the quality of wing box segment as the objective function, a multi-variable, multi- Structural Optimization Design of Large Aspect Ratio Composite Wing with Multiple Constraints. Through the analysis of the example, the quality of the wing composite structure decreased 9.55%, the optimization time is shorter.