电动飞机蒙皮结构的冲击损伤试验与优化设计  

Impact damage test and optimization design of electric aircraft skin structure

作　　者：张云鹏[1] 王吉 王雪飞[1] 刘冠一 韦迎 杨康 ZHANG Yunpeng;WANG Ji;WANG Xuefei;LIU Guanyi;WEI Ying;YANG Kang(Data Center,Shenyang Aircraft Industry(Group)Co.,Ltd.,Shenyang 110000,China;Design Department,Liaoning General Aviation Academy,Shenyang 110136,China;Liaoning Key Laboratory of General Aviation,Shenyang Aerospace University,Shenyang 110136,China)

机构地区：[1]沈阳飞机工业(集团)有限公司数据中心,沈阳110000 [2]辽宁通用航空研究院设计部,沈阳110136 [3]沈阳航空航天大学辽宁省通用航空重点实验室,沈阳110136

出　　处：《无损检测》2024年第2期1-5,37,共6页Nondestructive Testing

摘　　要：飞机蒙皮结构常受到冰雹、维修碰撞等低能冲击,机身结构易出现损伤,引发飞机性能减退。为了提高蒙皮结构的抗冲击性能,结合Hashin失效准则建立了一种复合材料泡沫夹层结构低速冲击有限元等效模型,并利用超声C扫描对冲击后的复合材料泡沫夹层进行无损检测,试验结果表明,与无损检测结果相比较,模拟结果的误差低于10%,证明了该冲击等效模型的合理性。最后利用该有限元等效模型对某型电动飞机机身复合材料泡沫夹层蒙皮结构进行优化设计,以提高抗冲击能力、减小吸收的破坏能量、降低结构损伤程度为目标,在相同铺层数量下,得到了最优的复合材料泡沫夹层结构铺层设计方案。The aircraft skin structure is often subjected to low energy impacts such as hail and maintenance tools,resulting in damage to the fuselage structure and reduced aircraft performance.In order to improve the impact resistance of the skin structure,this paper established a low⁃speed impact finite element equivalent model of composite foam sandwich structure based on the Hashin failure criterion,and used ultrasonic C⁃scan to conduct nondestructive testing on the impact composite foam sandwich testing.The error between the simulation results and the nondestructive testing results was less than 10%,which proved the rationality of the impact equivalent model.Finally,the finite element equivalent model was used to optimize the design of composite foam sandwich skin structure of an electric aircraft fuselage.With the goal of improving the impact resistance,reducing the absorbed damage energy,and reducing the structural damage degree,the optimal composite foam sandwich structure ply design scheme was obtained under the same number of plies.

关 键 词：泡沫夹层结构 Hashin失效准则 低速冲击 电动飞机 机身蒙皮 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程] TG115.28[金属学及工艺—物理冶金]