CAJ | 학술논문

为研究玻璃纤维增强铝合金层板（FMLs）抗低速冲击力学特性以及受低温处理的影响，采用2A12铝合金板和单向 S2-glass/epoxy 预浸料制成 FMLs，通过落锤低速冲击试验设备对其抗低速冲击力学特性进行研究。并采用较高冲击能量对经过-25℃和0℃低温处理1 h 后的 FMLs 进行冲击试验，与未低温处理结果对比研究低温处理对 FMLs冲击力学特性的影响。结果表明：未低温处理的 FMLs 在低速冲击条件下，正面铝合金铺层主要发生成坑、环向裂纹以及穿孔等损伤，背面铝合金层则发生鼓包、单向裂纹和花瓣开裂等损伤。峰值冲击载荷随着冲击能量的提高而增大，但当冲击能量达到 FMLs 临界穿透能后峰值冲击载荷基本保持稳定。随着冲击能量的提高，峰值位移逐渐增大，能量回弹系数逐渐减小。另一方面，低温处理可提高 FMLs 抗冲击性能，但会降低 FMLs 中铝合金/复合材料铺层界面黏结效果。处理温度越低，FMLs 峰值冲击载荷越高，峰值位移越小，FMLs 中复合材料和铝合金铺层发生脱胶损伤的面积越大。
위연구파리섬유증강려합금층판（FMLs）항저속충격역학특성이급수저온처리적영향，채용2A12려합금판화단향 S2-glass/epoxy 예침료제성 FMLs，통과락추저속충격시험설비대기항저속충격역학특성진행연구。병채용교고충격능량대경과-25℃화0℃저온처리1 h 후적 FMLs 진행충격시험，여미저온처리결과대비연구저온처리대 FMLs충격역학특성적영향。결과표명：미저온처리적 FMLs 재저속충격조건하，정면려합금포층주요발생성갱、배향렬문이급천공등손상，배면려합금층칙발생고포、단향렬문화화판개렬등손상。봉치충격재하수착충격능량적제고이증대，단당충격능량체도 FMLs 림계천투능후봉치충격재하기본보지은정。수착충격능량적제고，봉치위이축점증대，능량회탄계수축점감소。령일방면，저온처리가제고 FMLs 항충격성능，단회강저 FMLs 중려합금/복합재료포층계면점결효과。처리온도월저，FMLs 봉치충격재하월고，봉치위이월소，FMLs 중복합재료화려합금포층발생탈효손상적면적월대。
In order to investigate the low velocity impact performance of fiber metal laminates (FMLs)and the effect of exposure temperature on their impact performance,a series of low velocity impact tests on FMLs made of 2A12 aluminum alloy and S2-glass/epoxy composite prepregs were conducted with drop weights.Some FMLs were then cooled at-25℃ and 0℃ for one hour and impacted with higher impact energy.The experimental results showed that when FMLs without cooling are impacted at low impact velocity,denting,circumferential cracking even perforation occur in the front aluminum layer of FMLs,and bulging,linear cracking even petaling occur in the rear aluminum layer;the peak impost force increases with increase in impact energy until the impact energy reaches the perforation energy of FMLs,then the peak impact force is almost constant after perforation;the peak displacement increases with increase in impact energy but the energy restitution coefficient decreases with increase in impact energy;the low velocity impact performance of FMLs after cooled at -25℃ and 0℃ for 1 hour is improved in contrast to that without cooling but the bonding performance at the aluminum-composite interface is reduced;the peak impact force and the damage area of debonding at the aluminum-composite interface increased with decrease in exposure temperature but the peak displacement decreases with decrease in exposure temperature.