【摘要】 以某型号的机翼后缘为研究背景,通过采用拓扑优化的方法,设计一种柔性后缘机构来达到减轻质量和实现其自适应变形的目的。以实际位移与目标位移之间的偏差为目标函数,表面所受到的分布载荷为约束,通过SIMP(密度刚度插值)法来建立拓扑机构优化模型,用OC(优化准则)法来求解模型。采用M atlab进行优化计算,然后用Pro/E把优化的结果转化成三维实体模型,并导入到ANSYS中进行验证分析,得到了可实现0~10.8°变形的柔性后缘机构,能够满足无人机从初始状态变化到气动效率最高状态的要求。更多还原

【Abstract】 Taking the airfoil trailing edge of certain concrete typed aircraft as the background of study,a kind of flexible trailing edge mechanism was designed so as to achieve the goal of lightening the masses and realizing its self-adaptive deformation.Taking the deviation between the actual displacement and the target displacement as the objective function,and use the distribution loading received by its surface as the constraint to establish the optimization model of topological mechanism by means of SIMP(density rigidity interpolation) method,and to solve the model by the use of OC(Optimization Criterion) method.Carrying out optimization calculation by adopting the Matlab,and then using the Pro/E to let the optimization result be transformed into a 3D entity model.And this model was leaded into ANSYS for carrying out a verified analysis.The flexible trailing edge mechanism that can achieve the 0~10.8°deformation was obtained,which could satisfy the requirements for the pilot-less aircraft to make changes from the initial state to the highest state of aerodynamic efficiency.更多还原