针对变弯度机翼气动优化和轻量化的设计要求，提出了气动外形与结构拓扑分步优化设计。该设计以机翼气动优化的计算结果为基础，通过变密度法建立机翼前后缘拓扑优化设计结构。提出了一种6参数描述机翼外形的参数化方法，通过B样条曲线进行局部修正，采用遗传算法对气动外形进行优化。基于优化后的机翼气动外形采用变密度拓扑优化算法建立RAMP插值模型，设计前后缘拓扑结构与机翼展向模型。通过3D打印技术对前后缘变弯度机翼拓扑结构进行加工并开展变形试验。气动仿真结果表明，6参数变弯度翼型的变形区间最大且外形连续光滑。与基础机翼相比，优化后的机翼在起飞过程中升阻比提高了35.7%，巡航状态下升阻比提高4.4%。通过变形试验结果得出前缘拓扑结构等效偏转角为9.37°、后缘拓扑结构等效偏转角为9.18°，偏转效果良好，验证了气动外形与拓扑分步优化设计的可行性。

A stepwise optimal design of the aerodynamic shape and structural topology is proposed to meet the requirements of aerodynamic optimization and lightweight design for variable camber wings. Based on the results of aerodynamic optimization， we establish the topology optimal structure of the leading and trailing edge of the wing using the variable density method. A six-parameter parameterization method is proposed to describe the wing shape， local correction is performed using the B-spline curve， and the aerodynamic shape is optimized by the genetic algorithm. Based on the optimized aerodynamic shape of the wing， we employ a variable density topology optimization algorithm to establish an RAMP interpolation model， and design the leading and trailing edge topology structures and wing spanwise models. Additionally， using 3D printing technology， we process the topology structure of the variable camber wing with the leading and trailing edge， and conduct deformation tests. The aerodynamic simulation results show that the deformation range of a six parameter variable curvature airfoil is the largest with a continuous and smooth shape. Compared with the basic airfoil， the lift-drag ratio of the optimized wing increases by 35.7% and 4.4% during take-off and cruise， respectively. The deformation test results show that the equivalent deflection angles of the leading edge and trailing edge are 9.37° and 9.18°， respectively， with significant deflection effect， verifying the feasibility of stepwise optimization for the aerodynamic shape and topology.