摘要
提出了AD200 双座轻型飞机玻璃纤维纸质蜂窝夹芯结构有限元分析的建模假设,利用试验测得的玻璃纤维(0/90°),(±45°)材料基本性能数据,按复合材料层合板理论得到了实际结构不同组合铺层的材料弹性常数。用通用有限元程序对AD200 飞机实际结构进行了强度分析,并与静力试验结果进行比较,两者吻合很好。结果表明,模型简化合理。
Modeling of glass fiber reinforced plastics (GFRP)/paper sandwich structure of an AD200 light aircraft is presented with finite element (FE) analysis, based on the uniform deformation of the structure. The elastic properties of the laminates with different plies used in the structure are estimated according to the data of unidirectional laminates obtained in the experiment. The stress distribution and the displacement are obtained by FE analysis, and the comparison is made with full scale experimental results. The result proves that the analysis is in good agreement with the experiment. An AD200 light aircraft is designed and manufactured according to CCAR 23 and has got certificates of quality on designing, manufacturing and airworthiness. The whole airframe is manufactured by GFRP and the advanced canard configuration is introduced.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
1999年第6期634-638,共5页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
玻璃钢
有限元
强度
模型
轻型飞机
蜂窝夹芯结
glass fiber reinforced plastics
sandwich laminates
FE analysis
Young′s modulus
model
