摘要
针对某典型前缘结构,研究了使用纤维金属层板(Fibre Metal Laminates,FMLs)蒙皮进行抗鸟撞设计的可行性。以显式动态冲击分析程序PAM-CRASH为平台,结合由鸟撞平板试验结果验证的鸟体本构模型参数,建立了鸟撞前缘结构数值模型。通过计算研究了使用不同蒙皮(铝合金、FMLs)的前缘结构在鸟撞作用下的变形破坏模式及吸能效果。结果表明:采用适当铺层的FMLs蒙皮可以有效地提高前缘结构的抗鸟撞性能。研究结论对飞机结构的抗鸟撞研究具有一定的参考价值。
The feasibility of anti-bird strike design of using fibre metal laminates （FMLs） skin is studied for a typical leading edge structure. The model of bird strike on the leading edge structure is established by explicit finite element code PAM-CRASH using the constitutive model parameters of bird materials which are verified by the experimental results of bird strike on plate. Then, the processes of bird strike on the leading edges with aluminum and FMLs skins are respectively studied by numerical simulation, in which deformation modes, failure modes and energy absorption of the leading edge structures are investigated. The results show that FMLs with appropriate laminate layers can effectively improve the anti-bird strike performance of the leading edge. The conclusion could have some reference values on anti-bird strike study of the aircraft structure.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2010年第9期1781-1787,共7页
Acta Aeronautica et Astronautica Sinica
基金
国防科技工业民用专项科研技术研究项目
