EXPERIMENT AND SIMULATION RESEARCH OF THE OPTIMUM INTERFERENCE OF HI-LOCK ASSEMBLY

XIE JieDong; CHEN Guo; ZENG XinLiang; SHU MaoSheng; LUO Yun; GAO Hong; ZHENG QiHui

doi:10.16579/j.issn.1001.9669.2018.06.009

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EXPERIMENT AND SIMULATION RESEARCH OF THE OPTIMUM INTERFERENCE OF HI-LOCK ASSEMBLY

更新时间：2022-09-22

- EXPERIMENT AND SIMULATION RESEARCH OF THE OPTIMUM INTERFERENCE OF HI-LOCK ASSEMBLY
- Journal of Mechanical Strength Vol. 40, Issue 6, Pages: 1321-1329(2018)
- 作者机构：
  
  1. 南京航空航天大学民航学院
  2. 成都飞机工业(集团)有限责任公司
  3. 成都飞机设计研究所
- 作者简介：
- 基金信息：
- DOI：10.16579/j.issn.1001.9669.2018.06.009
  CLC：
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XIE JieDong, CHEN Guo, ZENG XinLiang, et al. EXPERIMENT AND SIMULATION RESEARCH OF THE OPTIMUM INTERFERENCE OF HI-LOCK ASSEMBLY. [J]. 40(6):1321-1329(2018)
DOI：

XIE JieDong, CHEN Guo, ZENG XinLiang, et al. EXPERIMENT AND SIMULATION RESEARCH OF THE OPTIMUM INTERFERENCE OF HI-LOCK ASSEMBLY. [J]. 40(6):1321-1329(2018) DOI： 10.16579/j.issn.1001.9669.2018.06.009.

摘要

目前我国飞机高锁螺栓装配标准均是沿用国外标准,缺乏相关理论和试验研究。针对某型飞机铝合金结构,通过疲劳试验和有限元仿真相结合的方法,研究了高锁螺栓干涉量在不同夹层厚度的基体上对结构件的疲劳增益机理。首先,设计并进行疲劳试验,对疲劳试验结果进行S-N曲线分析、细节疲劳额定值(DFR)分析及断裂位置分析。然后,利用有限元法对试验件建模仿真,对试验现象进行解释,对干涉配合疲劳增益机理进行研究。最后,综合细节疲劳额定值结果与有限元仿真结果得到高锁螺栓装配的标准建议值,对现有安装规范进行验证,从而保障某型飞机的装配质量。

Abstract

At present, the high lock bolt assembly standard of our country are come from abroad, lack of relevant theoretical and experimental research. Fatigue gain mechanism of high lock bolt interference on the base of different layer thickness is researched,through the method of combining the fatigue test and finite element simulation in a certain type of aircraft aluminum alloy structure. First, the fatigue test was designed and tested, and the results were analyzed by S-N curve, detail fatigue rating（DFR） and fracture location. Then, the finite element modeling and simulation are used to explain the experimental phenomena, and the mechanism of the interference fit to the fatigue gain is studied. Finally, the comprehensive detail fatigue rating results and the finite element simulation results are obtained, which are the standard recommended values of the high lock bolt assembly,and verified existing installation specifications, ensure the assembly quality of a certain type of aircraft.

关键词

干涉配合高锁螺栓疲劳强度有限元法细节疲劳额定值

Keywords

Interference fitHi-lock boltFatigue strengthFinite element methodDetail fatigue rating

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