This paper proposes an optimization design method for the modular cellular structure of non-uniform density, which is filled into the morphing wing to generate variable torsion angle. By actively adjusting the distribution of the span-wise torsion angle, the lift distribution on the wing surface can be properly adjusted to avoid the problem of aeroelastic divergence or reduce the bending moment at the wing root. This ability is validated using CFD simulation. In the optimization framework proposed, the adaptive gradient algorithm is used to suppress the divergence of iteration. A finite element model with geometrical nonlinear effects is then proposed to correct the errors of the linear analysis and verify the effectiveness of the optimization method. This design is shown to be able to reduce the overall weight of the structure and achieve control of the macro mechanical performance of the wing. The work provides a general optimization design method for similar modular structures, allowing independent programmable adjustment of the parameters of each single structural cell.

本文提出了一种密度不均匀的模块化蜂窝结构的优化设计方法，将其填充到变形机翼中以产生可变扭转角。通过主动调整展向扭转角的分布，可以适当调整机翼表面的升力分布，避免气动弹性发散问题或减少翼根处的弯矩。使用 CFD 模拟验证了这种能力。在提出的优化框架中，采用自适应梯度算法来抑制迭代发散。然后提出了具有几何非线性效应的有限元模型，以修正线性分析的误差并验证优化方法的有效性。事实证明，这种设计能够减轻结构的整体重量，并实现对机翼宏观机械性能的控制。该工作为类似的模块化结构提供了一种通用的优化设计方法，允许对每个单个结构单元的参数进行独立的可编程调整。