摘要
基于某无人机复合材料机身蒙皮区域结构,以提升其承载能力为研究目的,采用有限元软件对其进行铺层顺序优化,并对碳纤维复合材料蒙皮区域优化前后的形变量、应力应变结果对比分析;通过蔡-希尔强度准则、强度比等计算结果,对优化前后的碳纤维复合材料结构进行破坏失效分析;利用模态结果对比分析铺层顺序优化前后复合材料结构的稳定性。基于力学拉伸试验对优化结果校核。试验结果表明:碳纤维机身蒙皮区域经过铺层顺序优化后,其形变量减小9.9%,应力减小0.6%,应变减小6.2%;通过强度准则判定,优化后的碳纤维复合材料结构承载能力提升16.1%;利用模态计算结果对比分析可得,优化后的结构更加具有稳定性。由此证明,此铺层顺序优化是合理可靠的。
Based on the structure of the skin area of the composite body of a certain type of UAV composite material,with the purpose of improving its bearing capacity,the finite element software is used to optimize the laying sequence,and the shape variables and stress strain results before and after the optimization of the skin area of the carbon fiber composite material are compared and analyzed.Based on the calculation results of Cai-Hill strength criterion and strength ratio,the failure analysis of carbon fiber composite structure before and after optimization is carried out.The stability of the composite structure before and after is optimized by comparing the modal results and analyzing the laying sequence.Based on mechanical tensile tests,the optimization results are verified.The test results show that the carbon fiber fuselage skin area is optimized after the layering sequence,the shape variable of carbon fiber composite material is reduced by 9.9%,the stress is reduced by 0.6%,and the strain is reduced by 6.2%.Determine by strength criterion,the load carrying capacity of the optimized carbon fiber composite structure is increased by 16.1%.The results of the modal calculation can be compared and analyzed,and the optimized structure is more stable.This proves that this plaster sequence optimization is reasonable and reliable.
作者
王伟
王策
金晶
黄盼伟
WANG Wei;WANG Ce;JIN Jing(Beihang Changying UAS Technology Co.,Ltd.,Beijing 100083)
出处
《航空精密制造技术》
2023年第5期20-23,28,共5页
Aviation Precision Manufacturing Technology
关键词
无人机
复合材料
铺层顺序优化
静强度分析
稳定性分析
drone
composites
layup sequence optimization
static intensity analysis
stability analysis
