Encyclopedia of Aluminum and Its Alloys
Encyclopedia of Aluminum and Its Alloys
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DOI：
10.1201/9781351045636
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发表时间：
2018-12
期刊：
影响因子：
--
通讯作者：
G. Totten;M. Tiryakioğlu;O. Kessler
中科院分区：
文献类型：
--
作者：
G. Totten;M. Tiryakioğlu;O. Kessler
飞机部件的选择和制造需要充分抵抗环境、温度、载荷、兼容性等。当飞机需要连接铝合金或纤维增强聚合物复合材料等结构材料时，需要对紧固件、螺栓、铆钉、粘合剂和其他方法的选择进行定量评估，以便确定正确的部件设计和连接方法。有各种各样的紧固件、螺栓和铆钉，使用各种材料制成。铝铆钉经常用来连接飞机中的铝部件。铆钉在拉伸载荷下性能不佳，但在剪切时性能较好，因此限制了专门用于这些目的的应用。螺栓的设计是为了将材料夹在一起，即使螺栓可能足以支撑特定的结构和载荷要求，也必须考虑被夹在一起的组件的弹性系数和刚度。因此，了解每种被夹紧或连接在一起的材料是必要的。例如，钢制螺栓上涂有涂层，以帮助保护它们免受腐蚀。复合材料的使用减少了要使用的铆钉和紧固件的数量。在复合材料中钻孔以插入紧固件会带来许多挑战，因为纤维会受损，可能会形成高应力集中区，而且孔洞是水或水分进入的场所。铝紧固件的插入或铝部件与碳纤维的接触由于电势的巨大差异而造成电偶腐蚀。钛合金(Ti-6Al-4V)是一种典型的紧固件，由于其良好的兼容性(消除了电偶腐蚀)和提高的强度性能，采用了复合连接。在飞机中，用铆钉和紧固件取代焊接也在增加，因为激光焊接(LBW)和搅拌摩擦焊都减少了裂纹、气孔和由于更深的熔透而获得的更好的性能，并减少了热影响区，而这通常是传统弧焊(如金属惰性气体焊和钨极惰性气体焊)所不希望的。由于LBW，剪切和压应力增加，疲劳开裂、重量和成本也降低，包括消除与铆钉相关的应力和腐蚀以及消除粘合剂。不同的金属，如7000系列和2000系列，可以用与这两种金属兼容的填充金属连接，以减轻电偶腐蚀。
Aircraft components need to be selected and manufactured to adequately combat the environment, temperature, loading, compatibility, and so on. When structural materials such as aluminum alloys or fiber-reinforced polymer composites need to be joined in aircraft, the selection of fasteners, bolts, rivets, adhesives, and other methods need to be quantitatively assessed in order that the correct design for the component and joining method is identified. There is a variety of fasteners, bolts, and rivets, made using a variety of materials. Aluminum rivets are often used to join aluminum components in an aircraft. Rivets do not perform well under tension loading, but perform better in shear, thus limiting the application specifically for these purposes. Bolts are designed to clamp material together, and even though the bolt may be adequate to support a particular structure and load requirement, consideration must also be given to the modulus of elasticity and stiffness of the components that are being clamped together. Therefore, an understanding of each of the materials being clamped or joined together is necessary. Bolts manufactured from steel, for instance, have coatings applied in order to help protect them from corrosion. The use of composites translates to a reduced number of rivets and fasteners to be used. Drilling of holes into composites to insert fasteners poses many challenges because the fibers are damaged, a region of high stress concen tration may be formed, and the hole is a site for the ingress of water or moisture. The insertion of aluminum fasteners or the contact of aluminum components with carbon fibers creates galvanic corrosion due to the large difference in electrical potential. Titanium alloy (Ti-6Al-4V) is a typical fastener where there is composite joining due to its better compatibility (elimination of galvanic corrosion) and increased strength properties. Substitution of rivets and fasteners for welding is also on the increase in aircraft because laser beam welding (LBW) and friction stir welding both reduce cracking, porosity, and better properties achieved due to deeper penetration, and reduce the heat-affected zone which would typically be undesirable with conventional arc welding such as metal inert gas and tungsten inert gas welding. The shear and compressive stresses are increased, and fatigue cracking, weight, and cost are also reduced as a result of LBW, including the elimination of stresses and corrosion associated with rivets and the elimination of adhesives. Dissimilar metals such as the 7000 series and the 2000 series can be joined with a filler metal compatible to both metals to mitigate galvanic corrosion.