太阳能无人机机翼肋拓扑优化设计

Topology Optimization of Wing Rib of Solar UAV

与常规无人机相比,太阳能无人机能源有限,且机翼气动载荷非常小,因此对飞机结构重量的要求严苛。而太阳能无人机机翼肋的数量众多,若机翼肋采用传统的腹板肋,则机翼肋的重量将会过大,从而增大飞机结构设计难度,因此需要对机翼肋进行拓扑优化,以减轻机翼肋的重量。在ABAQUS中建立了机翼肋拓扑优化有限元模型,优化变量为机翼肋腹板的材料分布,优化目标为肋的刚度最大,约束条件为优化后的肋腹板的体积不超过原体积的30%。优化后的肋比原肋减重51.07%,Mises应力水平比优化前低77%,证明机翼肋建模及优化方法有较好的可行性,对机翼肋优化设计有一定的参考意义。

Compared with conventional UAV, solar UAV has limited energy and very small aerodynamic load on the wing, which makes the requirements for the weight of aircraft structure very strict. The number of wing ribs of solar UAV is large, if the wing rib adopts the traditional web rib, the weight of the wing rib will be too large, which will increase the difficulty of aircraft structural design. Therefore, it is necessary to optimize the topology of the wing rib to reduce the weight of the wing rib. The finite element model of wing rib topology optimization is established in ABAQUS, the optimization variable is the material distribution of wing rib, the optimization goal is to maximize the stiffness of the rib, and the constraint condition is that the volume of the optimized rib web does not exceed 30% of the original volume. The weight of the optimized rib is51.07% less than that of the original rib, and the Mises stress level is 77% lower than that before optimization. It proves that the wing rib modeling and optimization method is feasible, and has a certain reference significance for the optimization of wing rib.