太阳能飞机翼肋结构拓扑优化设计

Topology Optimization Design of Rib Structure on Solar Powered Aircraft

太阳能飞机翼肋结构轻薄且数量众多,其结构形式的合理性对于结构减重、机翼刚度设计等具有重要意义。基于现有太阳能飞机翼肋的结构形式,提出一种翼肋拓扑优化设计方法:首先,应用双向渐进结构优化法(BESO),以单元应力为判断指标,对太阳能飞机典型翼肋进行结构拓扑优化;其次,基于拓扑优化结果对翼肋进行结构细节设计;最后,通过有限元计算,验证翼肋的结构强度、刚度和静稳定性。通过本文方法,能够得到太阳能飞机翼肋更为合理的结构布局。

The solar powered aircraft ribs are light, thin structure of large number. Proper rib structural layouts are important to the aircraft lightening and the wing stiffness etc. Based on the rib structures of some typical so- lar powered aircraft, an topology optimization design method of the ribs is introduced： Firstly, a typical solar powered aircraft rib structure is optimized, based on the hi-directional evolutionary structural optimization（BE- SO） ; Secondly, the specific designs of the rib structure are given; Finally, the structural strength, stiffness and stability of the rib are verified through finite element method. Through the method, more suitable structure lay- outs of the solar powered aircraft ribs could be obtained.