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针对大展弦比机翼飞机自身特点,在结构大变形情况下,将弹性力学几何非线性理论引入到大柔性飞行器的气动弹性力学分析中,建立完整的几何非线性气动弹性分析方法框架。该方法主要包含两方面:结构非线性刚度和曲面气动力的计算。结合优化设计,为了提高优化设计效率,针对迭代过程进行有效简化。基于ISIGHT优化平台,发展一种适用于初步设计阶段大展弦比机翼在大变形情况下的气动弹性优化设计方法,有效地避免了结构大变形情况下线性气动弹性分析造成的设计偏差。为了摆脱对初始设计点的依赖,结合局部算法,采用组合优化策略,开展了大展弦比机翼的几何非线性气动弹性优化设计,首先应用蚁群算法定位目标极值在设计空间中所处的区域,再应用直接搜索算法对该区域精确寻优,获得更加准确的设计结果。
Aiming at the characteristics of large aspect ratio wing aircraft, the geometric nonlinear theory of elasticity is introduced into the aeroelastic analysis of large flexible aircraft under the condition of large structural deformation, and a complete geometric nonlinear aerodynamic analysis framework is established. The method mainly includes two aspects: the calculation of nonlinear stiffness and the aerodynamic force of the surface. Combined with the optimization design, in order to improve the efficiency of the optimization design, the iterative process is effectively simplified. Based on the ISIGHT optimization platform, an aeroelastic optimization design method suitable for the large aspect ratio wing with large deformation at the initial design stage is developed, which effectively avoids the design deviation caused by the linear aeroelastic analysis under large deformation. In order to get rid of the dependence on the initial design point, combined with the local algorithm, using combinatorial optimization strategy, the geometric nonlinear aerodynamic optimization design of large aspect ratio airfoils was carried out. First, the target extreme value was located in the design space by using the ant colony algorithm Of the region, and then use the direct search algorithm for accurate optimization of the region to obtain more accurate design results.