A new material model for 2D numerical simulation of serrated chip formation when machining titanium alloy Ti–6Al–4V

Calamaz, Madalina; Coupard, D.; Girot, F.

doi:10.1016/j.ijmachtools.2007.10.014

Cited by 525 publications

(340 citation statements)

References 30 publications

Supporting

Mentioning

314

Contrasting

Unclassified

Order By: Relevance

“…the ultimate bearing strength of the E-layup joints is controlled by the fastener not the laminate. The logarithmic increase of titanium strength with strain rate [36], would account for improved fastener performance and hence increased strength in joints where ultimate strength is governed by fastener damage.…”

Section: Single-bolt Joint Bearing Response Curvesmentioning

confidence: 99%

Static and high-rate loading of single and multi-bolt carbon–epoxy aircraft fuselage joints

Egan

McCarthy

et al. 2013

Composites Part A: Applied Science and Manufacturing

View full text Add to dashboard Cite

Single-lap shear behaviour of carbon-epoxy composite bolted aircraft fuselage joints at quasi-static and dynamic (5 m/s and 10 m/s) loading speeds is studied experimentally. Single and multi-bolt joints with countersunk fasteners were tested. The initial joint failure mode was bearing, while final failure was either due to fastener pull-through or fastener fracture at a thread. Much less hole bearing damage, and hence energy absorption, occurred when the fastener(s) fractured at a thread, which occurred most frequently in thick joints and in quasistatic tests. Fastener failure thus requires special consideration in designing crashworthy fastened composite structures; if it can be delayed, energy absorption is greater. A correlation between energy absorption in multibolt and single-bolt joint tests indicates potential to downsize future test programmes. Tapering a thin fuselage panel layup to a thicker layup at the countersunk hole proved highly effective in achieving satisfactory joint strength and energy absorption.

show abstract

Section: Single-bolt Joint Bearing Response Curvesmentioning

confidence: 99%

Static and high-rate loading of single and multi-bolt carbon–epoxy aircraft fuselage joints

Egan

McCarthy

et al. 2013

Composites Part A: Applied Science and Manufacturing

View full text Add to dashboard Cite

show abstract

“…In segmented chips, a narrow zone of high deformation appeared between the segments, the so-called adiabatic shear-band. During the cutting process, deformation localizes in the primary shear zone and temperature increase significantly (Siemers et al, 2012 In the past, the chip-formation process of titanium alloys was intensively studied by means of cutting experiments (Sutter and List, 2013) and simulations (Calamaz et al, 2008).…”

mentioning

confidence: 99%

Analysis of a free machining α+β titanium alloy using conventional and ultrasonically assisted turning

Muhammad

Hussain

Maurotto

et al. 2014

Journal of Materials Processing Technology

View full text Add to dashboard Cite

• This is the author's version of a work that was accepted for publication in the Journal of Materials Processing Technology. Changes resulting from the publishing process, such as peer review, editing, corrections, structural formatting, and other quality control mechanisms may not be reflected in this document. Changes may have been made to this work since it was submitted for publication.A definitive version was subsequently pub- enhanced machinability generating short chips during metal cutting, which prevents entanglement with cutting tools improving productivity. To further enhance the machinability of this material, a novel hybrid machining technique called ultrasonically assisted turning (UAT) was used. Experimental investigations were carried out to study the machinability, chip shapes, cutting forces, temperature in the process zone and surface roughness for conventional and ultrasonically assisted turning of both alloys. UAT shows improved machinability with reduced nominal cutting forces, improved surface roughness of the machined workpiece and generation of shorter chips when compared to conventional machining conditions.

show abstract

“…Semi-empirical model models have been developed to include those effects. Calamaz et al (Calamaz, Coupard et al 2008) investigated the chip formation in the machining of Ti-6Al-4V and pointed out that the segmented chip formation was influenced by the strain softening and thermal softening. A modified chip formation model was developed by introducing the softening term in to the traditional JC model.…”

Section: Mts Model Based Force Prediction For Machining Of Ti-6al-4vmentioning

confidence: 99%

MTS model based force prediction for machining of Ti-6Al-4V

Pan

Shih

Garmestani

et al. 2017

JAMDSM

View full text Add to dashboard Cite

The high temperature and severe plastic deformation could promote workpiece material microstructure evolution in the machining process. The material mechanical properties are functions of the material microstructure attributes. Traditional material flow stress model approximates the material mechanical behavior at a continuum level by ignoring the microstructure effects. In the current study, a microstructure based mechanical threshold stress (MTS) model is proposed for the machining process application. The MTS model takes the material grain boundary and dislocation resistance into account. Within both the analytical and FEA machining process modeling framework, the MTS model is implemented for the machining forces prediction. The validation of the MTS application into machining forces prediction are conducted by comparison with experimental results. Good agreement is found between the experiment and prediction. Additionally, slight force prediction improvement is observed by comparing with the traditional Johnson-cook flow stress model.

show abstract

A new material model for 2D numerical simulation of serrated chip formation when machining titanium alloy Ti–6Al–4V

Cited by 525 publications

References 30 publications

Static and high-rate loading of single and multi-bolt carbon–epoxy aircraft fuselage joints

Static and high-rate loading of single and multi-bolt carbon–epoxy aircraft fuselage joints

Analysis of a free machining α+β titanium alloy using conventional and ultrasonically assisted turning

MTS model based force prediction for machining of Ti-6Al-4V

Contact Info

Product

Resources

About