基于几何因子的复合材料气动弹性剪裁设计

实现了基于几何因子的复合材料层合板建模，解决了几何因子与Natran的参数输入问题，并根据工艺约束中的最小铺层比例对几何因子可行空间进行了推导补充。在此基础上，提出了一种基于几何因子和Nastran的复合材料气动弹性剪裁优化设计方法。首先以总厚度和几何因子作为设计变量以及以Nastran作为求解器，以强度、刚度、颤振和发散速度以及几何因子相关性约束作为约束条件进行结构寻优，得到最优的铺层总厚度和几何因子。其次，以最优几何因子作为目标，进行铺层结构逆问题求解，约束条件为复合材料铺层工艺约束。因几何因子为铺层厚度和铺层顺序的表达式，与传统的多级优化相比，以几何因子作为设计变量可以避免铺层厚度和铺层顺序的解耦，进而获得更大的设计空间，且得到的铺层结构可以满足工艺约束。最后，对一矩形悬臂复合材料层合板进行剪裁设计，使得铺层结构满足气动弹性约束且质量最小。结果显示，运用该优化方法可以得到质量更小且满足工艺约束的铺层结构。

Composite aeroelastic tailoring design based on lamination parameters

Composite laminate modeling based on lamination parameters was fulfilled and the parameter input problem of lamination parameters with Nastran was solved. Also, the feasible region of lamination parameters was derived and supplemented with rule of minimum amount of fibers. With the two aspects, an optimization method for composite aeroelastic tailoring based on lamination parameters and Nastran was proposed. First, laminate thickness and lamination parameters were as design variables, with constraints of lamination parameters constraints and structure behavior constraints including strength, stiffness, flutter speed and divergence speed constraints. Second, the inverse problem of optimal lamination parameters to real laminate configuration was solved as a discrete numerical optimization problem just with constraints of composite manufacturing constraints. Because the lamination parameters were functions of laminate thickness and stacking sequence, the optimization method with lamination parameters as design variables could obtain larger design freedom compared with the conventional method with layer thicknesses as design variables. Finally, a cantilever plate numerical example with aeroelastic constraints was used to demonstrate the efficiency of the proposed method. Results show that the optimal laminate configuration obtained by the proposed method satisfies the manufacturing constraints with lighter mass.