GLARE® is a composite-metal laminate currently used in the Airbus A380 fuselage due to its excellent impact and fatigue performance. GLARE® undergo extensive drilling for riveting purposes making it prone to thermal effects and increased tool wear. Therefore, using coolants becomes necessary, however, conventional coolants can lead to moisture absorption. An alternative is to use cryogenic coolants due to their positive impact on machining aerospace materials in the past. In this study, through tool cryogenic machining technology is used for machining GLARE® laminates by delivering liquid nitrogen at −196 °C through the spindle allowing the coolant to be in direct and continuous contact with the cutting zone. The aim is to investigate the impact of drilling parameters and cryogenic cooling on surface roughness, hole size, circularity and hardness at hole entry and exit sides. In addition, microstructural evaluation using scanning electron microscopy. The results indicate that the cryogenic cooling improved hole surface finish and gave better hole size at the top, while it had no impact on hole circularity. The hardness was increased at the entry and exit sides of the hole compared to that observed in dry drilling tests while scanning electron microscopy revealed that burr formation was minimised.

GLARE®是一种复合金属层压板，由于其出色的抗冲击和疲劳性能，目前在空客A380机身中使用。GLARE®为了铆接目的而进行了广泛的钻孔，使其易于产生热效应，并增加了工具磨损。因此，有必要使用冷却剂，但是，常规的冷却剂会导致水分吸收。一种替代方法是使用低温冷却剂，因为它们过去对机加工航空航天材料具有积极影响。在这项研究中，通过工具低温加工技术将－ 196°C的液氮通过主轴输送到主轴上，从而使冷却液与切割区直接连续接触，从而对GLARE®层压板进行加工。目的是研究钻孔参数和低温冷却对表面粗糙度，孔尺寸，孔的入口和出口侧的圆度和硬度。另外，使用扫描电子显微镜进行微观结构评估。结果表明，低温冷却改善了孔的表面光洁度，并在顶部提供了更好的孔尺寸，而对孔的圆度没有影响。与在干式钻探测试中观察到的相比，在孔的入口和出口处的硬度增加了，而扫描电子显微镜显示毛刺的形成被最小化了。