Field Trials of Aerospace Fasteners in Mechanical and Structural Applications

G. Melhem, P. Munroe, C. Sorrell, Alsten Clyde Livingstone
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Abstract

The present work reports findings for the application of specialized aerospace aluminum rivets, manufactured from Al 7075 (Al-Zn-Mg-Cu) T6 alloy stem/mandrel, with an Al 5056 (Al-Mg) shank or sleeve, which were used for construction rectification of an outdoor louver façade on a high-rise building. These specialized rivets were used to replace failed conventional construction rivets, which consisted of sleeve and mandrel comprised of either all-steel, all-aluminum, or aluminum-steel. The building is in close vicinity to the ocean and exposed to extremely high wind loading, making the rivets susceptible to failure by corrosion and fatigue. The focus of the present work is to report the examination of the specialized replacement rivets following an in-service lifetime of 12 years. The examination revealed that the replacement rivets (mandrel and sleeve) remained intact and uncontaminated, essentially free of corrosion. It is likely that sunlight exposure and the composite nature of the rivets enhanced the performance through age hardening. Analysis of the rivets included visual inspection, optical microscopy, Vickers microhardness testing, and transmission electron microscopy. The aim of the analysis was to correlate microstructures with microhardnesses, using these data to evaluate the ultimate tensile strength (UTS), yield strength (YS), and the potential for further age hardening. The Vickers microhardnesses were observed to have increased by ~8% over the service lifetime of 12 years, which equates to increases in YS (34.8–46.8 MPa) and UTS (23.8–45.6 MPa). Although the results show that there is a large increase in the strength values when comparing the unused rivets to the 12-year-old rivets, this increase in hardness may not necessarily be due purely to natural aging kinetics such as exposure from the sun and outdoor temperature. However, there appears to be some insignificant alteration of the microstructure and mechanical properties as a result of this exposure.
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航空航天紧固件在机械和结构应用中的现场试验
本工作报告了应用专用航空航天铝铆钉的研究结果,该铆钉由Al 7075 (Al- zn - mg - cu) T6合金杆/芯轴制造,带有Al 5056 (Al- mg)柄或套筒,用于高层建筑室外百叶立面的施工纠正。这些专用铆钉用于取代失效的传统结构铆钉,传统结构铆钉由全钢、全铝或铝钢组成的套管和心轴组成。该建筑靠近海洋,暴露在极高的风荷载下,使得铆钉容易因腐蚀和疲劳而失效。本工作的重点是报告使用寿命为12年的专用替换铆钉的检查情况。检查显示,更换的铆钉(心轴和套筒)完好无损,没有受到污染,基本上没有腐蚀。很可能是阳光照射和铆钉的复合性质通过时效硬化增强了性能。铆钉的分析包括目视检查、光学显微镜、维氏显微硬度测试和透射电子显微镜。分析的目的是将显微组织与显微硬度联系起来,利用这些数据来评估极限抗拉强度(UTS)、屈服强度(YS)以及进一步时效硬化的可能性。在12年的使用寿命中,维氏显微硬度增加了8%,相当于YS (34.8-46.8 MPa)和UTS (23.8-45.6 MPa)的增加。尽管结果表明,与使用12年的铆钉相比,未使用的铆钉的强度值有很大的增加,但硬度的增加不一定是纯粹由于自然老化动力学,如阳光和室外温度的暴露。然而,由于这种暴露,微观结构和力学性能似乎有一些微不足道的变化。
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