Review of research on loosening of threaded fasteners

Gong, Honghan; Ding, Xiaoyu; Liu, Jianhua; Feng, Huihua

doi:10.1007/s40544-021-0497-1

Cited by 48 publications

(17 citation statements)

References 99 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Sakai 3 analyzed the effect of external axial cyclic loading and concluded that bolt rotation loosening was caused by bolt radial contraction and nut expansion. Gong et al 4 summarized the causes and mechanisms of non-rotational and rotational loosening. He deemed that transverse vibration was the main cause of bolt rotation loosening and believed that the bolt rotation loosening would occur when the static friction between threads was overcome, and if the inertial force of transverse vibration load was greater than the static friction, then rotational loosening of the threads occurred.…”

Section: Introductionmentioning

confidence: 99%

Preload loss of CFRP bolted joint without rotation under transverse and axial loading

Yang

Chen

et al. 2023

Advances in Mechanical Engineering

View full text Add to dashboard Cite

There are a large number of CFRP-steel bolted joints with jet nuts subjected to transverse and axial load in aircraft structures, which have passed standard testing of locking characteristics of fasteners under transverse loading conditions. This fastener has a great preload loss and no rotation loosening occurs. Based on the observation, we designed a biaxial loading experiment for CFRP bolted joint, and measured the preload and loosening angle under different initial preload. The biaxial research suggests that compared with the uniaxial loading condition, the preload loss is larger, the rotation is minimal and only appears in the early stage of test, and there are obvious indentations on the surface of CFRP panel. Embedment as an important factor leads to the preload loss due to the weak ability of CFRP panel suffering out of plane load. In order to study the effect of embedment, the relationship between stress S22 and indentation depth under different preload, the relationship between biaxial load amplitude and embedding depth, and the ratio of the preload loss caused by embedding to the total preload loss are revealed by finite element analysis.

show abstract

Section: Introductionmentioning

confidence: 99%

Preload loss of CFRP bolted joint without rotation under transverse and axial loading

Yang

Chen

et al. 2023

Advances in Mechanical Engineering

View full text Add to dashboard Cite

show abstract

“…The mechanisms of bolt loosening have been summarized as the slippage, fretting wear and repeated plastic deformation [1]. Many studies have focused on different methods to avoid bolt loosening initiated by the slippage behavior on the thread surface, which called rotational loosening.…”

Section: Introductionmentioning

confidence: 99%

An investigation on the effect of thread pitch on the self-loosening of bolted joint caused by fretting wear

Zhang

Huang

Liu

et al. 2023

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

To study the effect of thread pitch on the bolt loosening behavior with consideration of fretting wear, the loosening experiments and finite element analysis were carried out to the bolts with different thread pitches. The experimental results demonstrate that fretting wear existed on the thread surface. It caused a slow bolt loosening without the nut rotation. With the thread pitch increases, the clamping force will become smaller, so that the fretting wear on the thread surface will also decrease, indicating that lager thread pitch could increase the anti-loosening ability through alleviating the fretting wear. The FE (Finite Element) results show that the decrease of sliding distance on thread surface had more beneficial effects than the increase of contact stress on the reduction in the fretting wear for the bolt with larger thread pitch.

show abstract

“…High-strength titanium alloys are widely used for aircraft fasteners due to their strong ability to lose weight, excellent corrosion resistance, cold formability, and good compatibility with composite materials. − For high-strength titanium alloy fasteners, fretting damage, as one of the common damage failure modes of aircraft fasteners, is the key factor restricting their reliability and service life . According to the statistics from the United States Air Force, fretting damage accounts for over one-sixth of damage in aero-engines, especially reducing the fatigue limit to only one-third of the ordinary fatigue limit. − Hence, a number of researchers have paid extensive attention to fretting damage in titanium alloys. − …”

Section: Introductionmentioning

confidence: 99%

Wear- and Surface-Fatigue-Mediated Damage during Fretting in a High-Strength Titanium Alloy

Tong

Hua

Zhang

et al. 2022

ACS Appl. Eng. Mater.

View full text Add to dashboard Cite

Fretting damage is a key factor restricting the reliability and long life of high-strength titanium alloy fasteners. The fretting damage mechanisms correlated by the interplay relationship between wear damage and surface fatigue damage still need to be addressed. In the present work, fretting damage mechanisms of a high-strength titanium alloy (Ti-15Mo-2.7Nb-3Al-0.25Si, in wt %) were studied in depth. To represent the different matches of strength and toughness, three microstructures with different volume fractions of the primary α phase (A-20%, B-10%, C-1%) were applied to fretting wear tests. The evolution process of fretting wear effected by different microstructures is simulated and quantitatively combined with the sectional inclined angle of scars and the antiwear velocity of wear debris. The results demonstrate that the final worn volume of B-10% is the greatest and the best fretting wear resistance is achieved in A-20%. For wear damage, due to both the poor protective effect of the tribolayer and the fact that the tribolayer is hard to compact, B-10% has the highest wear velocity. For surface fatigue damage, the slip ratio was calculated and used as a bridge to correlate and predict wear damage and fatigue damage. The microcrack damage is most severe in C-1% but slight in A-20%. This study provides valuable experimental data for the prediction of fatigue life for fretting of titanium fasteners, and the quantitative analysis method could be generalized to other alloys.

show abstract

Review of research on loosening of threaded fasteners

Cited by 48 publications

References 99 publications

Preload loss of CFRP bolted joint without rotation under transverse and axial loading

Preload loss of CFRP bolted joint without rotation under transverse and axial loading

An investigation on the effect of thread pitch on the self-loosening of bolted joint caused by fretting wear

Wear- and Surface-Fatigue-Mediated Damage during Fretting in a High-Strength Titanium Alloy

Contact Info

Product

Resources

About