基于HAJIF系统的复合材料机翼结构优化

The Optimization of the Composite Wing Based on HAJIF System

复合材料是高度各向异性材料,其结构设计和分析方法等与金属结构存在诸多差异。尤其在复合材料结构优化过程中,强度、稳定性等设计因素众多,导致结构优化设计工作繁琐、优化效率不高。对于需要考虑大量强度约束的复合材料机翼结构初步设计,如何快速获取初始铺层方案成为制约复合材料机翼结构设计的关键之一。针对复合材料机翼结构初始方案快速获取的问题,构建了基于“设计区-关键元”思想的复合材料机翼结构二级优化设计方法,以层合板理论为基础,引入复合材料许用值工程算法,基于工程准则法,构建了复合材料铺层厚度及铺层比例的二级优化策略,基于自主结构分析软件HAJIF系统的有限元求解器,提出了基于全内存数据存取的复合材料结构二级优化方法,完善并开发了复合材料结构铺层优化设计软件。考虑典型复合材料机翼各个设计区强度约束,应用开发的软件完成了机翼结构复合材料壁板铺层厚度及铺层比例快速优化,为机翼精细化设计提供了技术及工具支撑。

Composite material is a highly anisotropic material,and its structure design and analysis method have many differences compared with metal materials.Especially in the optimization process of composite materials,numerous design factors such as strength and stability lead to cumbersome structural optimization and inefficient optimization.Especially for the need to consider a lot of strength of composite wing structure preliminary design,how to obtain the initial lay-up quickly is one of the key constraints to the structure design of composite wing.Aiming at the quick design of composite wing structure initial scheme,this paper proposed the idea of“design domain-key element”.A second-level composite wing structure optimization design method is published based on the laminated plate theory.The allowable value of composite materials is introduced based on engineering algorithm.Based on engineering criterion method,the second-level optimization strategy considering the composite layer thickness and layer ratio is proposed.Based on the finite element solver of HAJIF system,a second-level optimization method of composite structure based on full memory data access is proposed.And the optimization design software of composite structure layup is improved and developed.Considering the strength constraints of each design area of a typical composite wing,the software was developed to optimize the thickness and proportion of the lamination of the composite panels of the wing structure,which provided technical and tool support for the fine design of composite wings.