直升机主旋翼驱动板组件中螺栓的失效[外文翻译].rar
直升机主旋翼驱动板组件中螺栓的失效[外文翻译],中文字数：4916字英文字符：16881字符a.固体力学系，材料及系统，特拉维夫大学，以色列特拉维夫69978 ，以色列b.材料科学与工程系，麻省理工学院，剑桥， ma 02139-4307 ，美国c. 车厂22 ，物资部，以色列空军，邮政信箱02548 ，以色列收到时间2...
该文档为压缩文件,包含的文件列表如下:
内容介绍
原文档由会员 快乐每一天6 发布
直升机主旋翼驱动板组件中螺栓的失效[外文翻译]
中文字数：4916字
英文字符：16881字符
a.固体力学系，材料及系统，特拉维夫大学，以色列特拉维夫69978 ，以色列
b.材料科学与工程系，麻省理工学院，剑桥， MA 02139-4307 ，美国
c. 车厂22 ，物资部，以色列空军，邮政信箱02548 ，以色列
收到时间2002年12月11日；接受时间 2003年1月15日。 在网上提供时间2003年3月15日。
摘要
直升机的主旋翼驱动板被定义为飞行安全的一部分。如果未能依照维修指示，可能会导致事故发生，导致严重乘员受伤或死亡，或严重损害直升机。在这项工作中，对由于在过猛的扭矩下该驱动板组件中的5颗受剪螺栓的失效进行了分析。通过目视检查，断口和金相检验，化学分析和力学性能测试（静态拉伸强度和硬度测试） ，没有任何偏离航空军用标准的要求。一个基于应变计技术的螺栓受力传感器被安装在螺栓里，用于监测当扭矩扳手旋入螺母时产生的实际载荷。比较分析了在使用不同的润滑方式与防卡塞物质时螺栓的性能。
关键词：螺栓失效；预紧；装配扭矩；航空器；螺纹润滑
Copyright © 2003 Elsevier Science Ltd. All rights reserved.
Failures of bolts in helicopter main rotor drive plate assembly due to improper application of lubricant
N. Eliaz , G. Gheorghiu , H. Sheinkopf , O. Levi , G. Shemesh , A. Ben-Mordechai and H. Artzi
a Department of Solid Mechanics, Materials and Systems, Tel-Aviv University, Tel-Aviv 69978, Israel
b Department of Materials Science and Engineering, Massachusetts Institute of Technology, Cambridge, MA 02139-4307, USA
c Depot 22, Materials Division, Israel Air Force, PO Box 02548, Israel
Received 11 December 2002; accepted 15 January 2003. ; Available online 15 March 2003.
Abstract
The main rotor drive plate of the helicopter is defined as a flight safety part. Failure to follow maintenance instructions might result in an accident involving serious injury or death of crew members and/or serious damage to the helicopter. In this work, the failure of five of the shear bolts in this assembly during installation torque wrenching was analyzed. Visual inspection, fractographic and metallographic examinations, chemical analysis and mechanical testing (static tensile and hardness tests) did not indicate any deviation from the requirements of the aeronautical military standards. A specially designed bolt force sensor, which is based on strain gauge technology, was used to monitor the actual load that develops in the bolt when it is torque-wrenched into a nut. Based on comparison of the behavior of bolts that had been lubricated in different ways with antiseize material, it was concluded that the bolts failed because of improper application of the antiseize material, which led to development of overloads.
Author Keywords: Bolt failures; Preload; Assembly torque; Aircraft; Thread lubrication
中文字数：4916字
英文字符：16881字符
a.固体力学系，材料及系统，特拉维夫大学，以色列特拉维夫69978 ，以色列
b.材料科学与工程系，麻省理工学院，剑桥， MA 02139-4307 ，美国
c. 车厂22 ，物资部，以色列空军，邮政信箱02548 ，以色列
收到时间2002年12月11日；接受时间 2003年1月15日。 在网上提供时间2003年3月15日。
摘要
直升机的主旋翼驱动板被定义为飞行安全的一部分。如果未能依照维修指示，可能会导致事故发生，导致严重乘员受伤或死亡，或严重损害直升机。在这项工作中，对由于在过猛的扭矩下该驱动板组件中的5颗受剪螺栓的失效进行了分析。通过目视检查，断口和金相检验，化学分析和力学性能测试（静态拉伸强度和硬度测试） ，没有任何偏离航空军用标准的要求。一个基于应变计技术的螺栓受力传感器被安装在螺栓里，用于监测当扭矩扳手旋入螺母时产生的实际载荷。比较分析了在使用不同的润滑方式与防卡塞物质时螺栓的性能。
关键词：螺栓失效；预紧；装配扭矩；航空器；螺纹润滑
Copyright © 2003 Elsevier Science Ltd. All rights reserved.
Failures of bolts in helicopter main rotor drive plate assembly due to improper application of lubricant
N. Eliaz , G. Gheorghiu , H. Sheinkopf , O. Levi , G. Shemesh , A. Ben-Mordechai and H. Artzi
a Department of Solid Mechanics, Materials and Systems, Tel-Aviv University, Tel-Aviv 69978, Israel
b Department of Materials Science and Engineering, Massachusetts Institute of Technology, Cambridge, MA 02139-4307, USA
c Depot 22, Materials Division, Israel Air Force, PO Box 02548, Israel
Received 11 December 2002; accepted 15 January 2003. ; Available online 15 March 2003.
Abstract
The main rotor drive plate of the helicopter is defined as a flight safety part. Failure to follow maintenance instructions might result in an accident involving serious injury or death of crew members and/or serious damage to the helicopter. In this work, the failure of five of the shear bolts in this assembly during installation torque wrenching was analyzed. Visual inspection, fractographic and metallographic examinations, chemical analysis and mechanical testing (static tensile and hardness tests) did not indicate any deviation from the requirements of the aeronautical military standards. A specially designed bolt force sensor, which is based on strain gauge technology, was used to monitor the actual load that develops in the bolt when it is torque-wrenched into a nut. Based on comparison of the behavior of bolts that had been lubricated in different ways with antiseize material, it was concluded that the bolts failed because of improper application of the antiseize material, which led to development of overloads.
Author Keywords: Bolt failures; Preload; Assembly torque; Aircraft; Thread lubrication
