直升機主旋翼驅(qū)動板組件中螺栓的失效[外文翻譯].rar
直升機主旋翼驅(qū)動板組件中螺栓的失效[外文翻譯],中文字?jǐn)?shù)：4916字英文字符：16881字符a.固體力學(xué)系，材料及系統(tǒng)，特拉維夫大學(xué)，以色列特拉維夫69978 ，以色列b.材料科學(xué)與工程系，麻省理工學(xué)院，劍橋， ma 02139-4307 ，美國c. 車廠22 ，物資部，以色列空軍，郵政信箱02548 ，以色列收到時間2...
該文檔為壓縮文件,包含的文件列表如下:
內(nèi)容介紹
原文檔由會員 快樂每一天6 發(fā)布
直升機主旋翼驅(qū)動板組件中螺栓的失效[外文翻譯]
中文字?jǐn)?shù)：4916字
英文字符：16881字符
a.固體力學(xué)系，材料及系統(tǒng)，特拉維夫大學(xué)，以色列特拉維夫69978 ，以色列
b.材料科學(xué)與工程系，麻省理工學(xué)院，劍橋， MA 02139-4307 ，美國
c. 車廠22 ，物資部，以色列空軍，郵政信箱02548 ，以色列
收到時間2002年12月11日；接受時間 2003年1月15日。 在網(wǎng)上提供時間2003年3月15日。
摘要
直升機的主旋翼驅(qū)動板被定義為飛行安全的一部分。如果未能依照維修指示，可能會導(dǎo)致事故發(fā)生，導(dǎo)致嚴(yán)重乘員受傷或死亡，或嚴(yán)重?fù)p害直升機。在這項工作中，對由于在過猛的扭矩下該驅(qū)動板組件中的5顆受剪螺栓的失效進(jìn)行了分析。通過目視檢查，斷口和金相檢驗，化學(xué)分析和力學(xué)性能測試（靜態(tài)拉伸強度和硬度測試） ，沒有任何偏離航空軍用標(biāo)準(zhǔn)的要求。一個基于應(yīng)變計技術(shù)的螺栓受力傳感器被安裝在螺栓里，用于監(jiān)測當(dāng)扭矩扳手旋入螺母時產(chǎn)生的實際載荷。比較分析了在使用不同的潤滑方式與防卡塞物質(zhì)時螺栓的性能。
關(guān)鍵詞：螺栓失效；預(yù)緊；裝配扭矩；航空器；螺紋潤滑
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?jǐn)?shù)：4916字
英文字符：16881字符
a.固體力學(xué)系，材料及系統(tǒng)，特拉維夫大學(xué)，以色列特拉維夫69978 ，以色列
b.材料科學(xué)與工程系，麻省理工學(xué)院，劍橋， MA 02139-4307 ，美國
c. 車廠22 ，物資部，以色列空軍，郵政信箱02548 ，以色列
收到時間2002年12月11日；接受時間 2003年1月15日。 在網(wǎng)上提供時間2003年3月15日。
摘要
直升機的主旋翼驅(qū)動板被定義為飛行安全的一部分。如果未能依照維修指示，可能會導(dǎo)致事故發(fā)生，導(dǎo)致嚴(yán)重乘員受傷或死亡，或嚴(yán)重?fù)p害直升機。在這項工作中，對由于在過猛的扭矩下該驅(qū)動板組件中的5顆受剪螺栓的失效進(jìn)行了分析。通過目視檢查，斷口和金相檢驗，化學(xué)分析和力學(xué)性能測試（靜態(tài)拉伸強度和硬度測試） ，沒有任何偏離航空軍用標(biāo)準(zhǔn)的要求。一個基于應(yīng)變計技術(shù)的螺栓受力傳感器被安裝在螺栓里，用于監(jiān)測當(dāng)扭矩扳手旋入螺母時產(chǎn)生的實際載荷。比較分析了在使用不同的潤滑方式與防卡塞物質(zhì)時螺栓的性能。
關(guān)鍵詞：螺栓失效；預(yù)緊；裝配扭矩；航空器；螺紋潤滑
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
