首页|极限工况下滚珠丝杠副疲劳失效研究分析

极限工况下滚珠丝杠副疲劳失效研究分析

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滚珠丝杠副被广泛应用于航空航天领域,常规工况下的失效机理在航空航天极限工况下不再适用.因此,针对极限载荷下滚珠丝杠副失效机理,提出了基于裂纹萌生和扩展的失效机理研究方法.通过电镜、金相、粗糙度仪和显微硬度等方法进行分析.结果表明,切向表面与次表面裂纹均是垂直于切向力的方向萌生,表面裂纹背离切向力扩展,次表面裂纹沿塑性变形方向扩展;轴向表面产生的疲劳裂纹角度在50°~85°;剥落坑形貌沿切向力方向由深到浅,剥落坑前侧区域比后侧区域更容易受疲劳影响,但后侧区域更容易受磨损影响;国外滚珠丝杠副寿命高于国内,提高滚珠丝杠副接触表面精度和组织均匀度,预计可以提升50%使用寿命.
The Research and Analysis of Fatigue Failure in Ball Screw Under Extreme Operating Conditions
Ball screws are widely used in aerospace applications,and the failure mechanisms under conven-tional operating conditions are no longer applicable under extreme aerospace operating conditions.There-fore,for the failure mechanism of ball screw under extreme load,a failure mechanism research method based on crack sprouting and expansion is proposed.The analysis was carried out by electron microscopy,metallography,roughness meter and microhardness.The results indicated that:tangential surface and sub-surface cracks are sprouted perpendicular to the direction of tangential force,surface cracks expand away from the tangential force,and sub-surface cracks expand along the direction of plastic deformation;fatigue cracks generated on the axial surface are at the angle of 50°~85°;the spalling pit morphology is deeper to shallower along the direction of the tangential force,and the area in front of the spalling pit is more suscep-tible to fatigue than that in back of the spalling pit but the area in back of the spalling pit is more suscepti-ble to wear;Foreign ball screw life is higher than domestic,improve ball screw contact surface accuracy and organisation uniformity,it is expected to enhance the service life by 50% .

ball screw pairfatigue failurecrack initiationcrack propagation

杨飞、周长光、翟光钰、冯虎田、李壮、翁熠扬

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南京理工大学机械工程学院,南京 210094

滚珠丝杠副 疲劳失效 裂纹萌生 裂纹扩展

丽水市经济开发区重点研发计划项目国家自然科学基金项目中央高校基本科研业务专项项目南京理工大学丽水滚动功能部件工业技术联合研究项目

2022KFQZDYF1551905274309230110111214021010507

2024

组合机床与自动化加工技术
大连组合机床研究所 中国机械工程学会生产工程分会

组合机床与自动化加工技术

CSTPCD北大核心
影响因子:0.671
ISSN:1001-2265
年,卷(期):2024.(9)
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