陈彦达,周轶,范振民.基于强度约束的复合材料机翼翼盒设计优化[J].民用飞机设计与研 究,2020(1):16-23CHEN Yanda,ZHOU Yi1,FAN Zhenmin.[J].Civil Aircraft Design and Research,2020,(1):16-23.
基于强度约束的复合材料机翼翼盒设计优化
  
DOI:10.19416/j.cnki.1674-9804.2020.01.004
中文关键词:机翼结构  复合材料  轻量化
英文关键词:wing structure  composite material  light weight
基金项目:
作者单位
陈彦达,周轶 东航技术应用研发中心上海 201707 
范振民 上海飞机设计研究院上海 201210 
中文摘要:提出了一个大型飞机复合材料机翼受强度约束条件下的优化问题,基于机翼结构的初步设计进行了设计优化。通过OptiStruct商业软件来完成优化过程,OptiStruct是一个效率高、精确独立的有限元求解器,目前也被广泛应用于航空航天工业中。根据设计目标,优化过程中将机翼上下蒙皮复合材料的层压厚度作为设计变量,优化后的结构重量减少了25.07%。在实际生产限制条件下,为了使设计结果趋于保守,对优化后的层板厚度进行了调整,适当增加了厚度,导致结构重量略有增加,但是最终的重量减少仍然超过20%,证明该方法在实现复合材料机翼结构的轻量化设计中具有实用性,可在机翼设计阶段的静强度评估中进行应用。
英文摘要:This article presents an optimization problem of a large aircraft composite wing subject to structural strength. The investigation demonstrated a design optimization process based on a preliminary design of the wing structure. The optimization process was performed by the commercial software OptiStruct, an efficient, accurate and independent finite element solver, which was widely employed in aerospace industry. According to the design objective, the laminate ply thickness of the wing skins were taken as design variables. The optimized structure weight was reduced by 25.07%. A post-process was performed to trim the optimized skin laminate layup and ply thickness under the manufacturing constraint. For a conservative design, an option of increasing the skin laminate thickness was made and led to a slight increase of the weight. However, the final weight saving was still over 20%. A practical optimum process of the composite wing structure with significant weight saving can be achieved by a practical approach and be applied to static strength evaluation in the wing design stage.
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