拓扑优化方法在飞机结构件概念设计中的应用  

Application of Aircraft Structural Part Conceptual Design Based on Topology Optimization Method

作　　者：陈华[1] 邓扬晨[2] 

机构地区：[1]西北工业大学机电学院,陕西西安710072 [2]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《航空计算技术》2006年第5期50-54,共5页Aeronautical Computing Technique

基　　金：航空科学基金(03B53003);辽宁省航空科学技术专项(20044007)

摘　　要：为了能够有效地降低飞机结构承力件的重量,针对飞机骨架,以加强框和普通框以及翼梁的概念设计为研究内容,通过对“敏度阈值”概念的分析,指出其不足,提出了“改进的敏度阈值”概念,并与“约束补偿”策略结合而形成新的拓扑优化算法,用于上述结构件的材料布局优化设计。多个算例中的拓扑优化结果均显示其结构型式十分新颖,值得深入地探讨。In the author regards order to decrease the weight of aircraft structural parts effectively, facing to the skeleton of aircrafts, the conceptual design of structural parts （ such as strengthen frame, general frame and canard beam） as research contents. By analyzing the concept of ‘gradient variable - threshold＇and pointing out its weakness, the author proposes the concept of modified gradient threshold＇and combines it with the strategy of constraint compensation＇to form a new kind of topology optimization algorithms for structural layout of structural parts. The topology optimization results of multiple examples show that their layouts are very innovative and are worthy to study in detail. So we can reach three conclusions. One is that using the combination of CAD/CAE and topology optimization for aircraft structural part above mentioned conceptual design is feasible. Second is that the proposed modified gradient threshold＂ topology optimization algorithm is effective. The third is that a new design approach with a good operation that differs from conventional design method is constructed for structural part structure layout.

关 键 词：飞机结构件 概念设计 拓扑优化 敏度阈值 约束补偿 CAD/CAE 集成设计 

分 类 号：V214[航空宇航科学与技术—航空宇航推进理论与工程]