scholarly journals The Maximum Stress Failure Criterion and the Maximum Strain Failure Criterion: Their Unification and Rationalization

2020 ◽  
Vol 4 (4) ◽  
pp. 157
Author(s):  
Shuguang Li
Keyword(s):  
Shear Stress ◽  
Failure Criterion ◽  
Maximum Stress ◽  
Uniaxial Stress ◽  
Longitudinal Shear ◽  
Maximum Strain ◽  
Poisson Effect ◽  
Stress Strain ◽  
Strain Criterion ◽  
Stress Criterion

The maximum strain failure criterion is unified with the maximum stress failure criterion, after exploring the implications of two considerations responsible for this: (1) the failure strains for the direct strain components employed in the maximum strain criterion are all defined under uniaxial stress states, not uniaxial strain states, and (2) the contributions to the strain in a direction as a result of the Poisson effect do not contribute to the failure of the material in that direction. Incorporating these considerations into the maximum strain criterion, the maximum stress criterion is reproduced. For 3D stress/strain state applications primarily, the unified maximum stress/strain criterion is then subjected to further rationalization in the context of transversely isotropic materials by eliminating the treatments that undermine the objectivity of the failure criterion. The criterion is then applied based on the maximum and minimum direct stresses, the maximum transverse shear stress and the maximum longitudinal shear stress as the invariants of the stress state, instead of the conventional stress components directly.

A Note on the Shear Stress Criterion for Fatigue Failure under Combined Stress

1969 ◽  
Vol 20 (1) ◽  
pp. 57-60 ◽  
Author(s):  
R. E. Little
Keyword(s):  
Shear Stress ◽  
Fatigue Limit ◽  
Fatigue Failure ◽  
Failure Criterion ◽  
Basic Problem ◽  
Failure Criteria ◽  
Test Methods ◽  
Combined Stress ◽  
Stress Criterion

SummaryNishihara’s combined bending and torsion out-of-phase fatigue limit data are analysed. The Tresca shear stress failure criterion predicts strengths up to 30 per cent higher than observed. It thus appears that renewed attention should be given to the basic problem of developing reliable combined stress failure criteria. It is suggested that new test methods will be required for this purpose.

A strain-based tensor polynomial failure criterion for anisotropic materials

1988 ◽  
Vol 23 (4) ◽  
pp. 179-186 ◽  
Author(s):  
W Zhang ◽  
K E Evans
Keyword(s):  
Epoxy Resin ◽  
Plane Stress ◽  
Failure Criterion ◽  
Maximum Stress ◽  
Failure Criteria ◽  
Anisotropic Materials ◽  
Maximum Strain ◽  
Stress Space ◽  
Failure Envelope ◽  
Stress Maximum

A strain-based tensor polynomial failure criterion for anisotropic materials is proposed with explicit derivations given in both strain and stress space. The physical distinction between this strain-based criterion and the current stress-based tensorial criterion of Tsai and Wu, is clarified. The viability of the proposed criterion is shown by its application to a graphite—epoxy resin lamina under plane stress. The allowed loadings and failure envelope of this lamina are predicted. Comparison is made with existing failure criteria (both stress-based and strain-based), in particular the maximum stress, maximum strain, and Tsai-Wu criteria.

scholarly journals АНАЛІЗ НАПРУЖЕНО-ДЕФОРМОВАНОГО СТАНУ ФІТИНГОВОГО СТИКУ ПАНЕЛЕЙ ВІД'ЄМНОЇ ЧАСТИНИ КРИЛА ТА ЦЕНТРОПЛАНА ТРАНСПОРТНОГО ЛІТАКА

2021 ◽  
pp. 97-112
Author(s):  
Yifang Sun ◽  
А. А. Вендин
Keyword(s):  
Strain State ◽  
Maximum Stress ◽  
Solid Model ◽  
Force Distribution ◽  
Maximum Strain ◽  
Stress Strain ◽  
Element Analysis ◽  
Wing Section ◽  
Stress Strain State ◽  
Center Section

Fitting joints are widely used in aircraft structures, and they are responsible for the interconnection of important components. The stress-strain state analysis of the fitting joint must be carried out before the performance analysis of the fitting joint. With the help of 3D modeling software (CATIA) and finite element analysis software (ANSYS), the stress-strain state of each component in the fitting joint of outer wing section was calculated in this paper. In the CATIA, the solid model is simplified and segmented according to the size of the cross section and the height of the center of gravity of the model. In the ANSYS, the beam elements are used to replace the simplified segmented model to obtain the internal force distribution of the solid model and to determine the magnitude and change law of the stress applied to the end of the solid model. When calculating the force transmitted by the fastener, the pre-tightening force of the bolt and the interaction between the surfaces of the component are taken into account, so as to simulate the real force situation well. Therefore, it is a very feasible method to use the CATIA and ANSYS to obtain the stress-strain state of components in the fitting joint of center wing section and outer wing section.The results show that under the working conditions of the fitting joint (130Mpa), the fitting of outer wing section with center section has a maximum stress of 245.79Mpa and a maximum strain of 0.0035, the stringer of outer wing section has a maximum stress of 293.17Mpa and a maximum strain of 0.0047, the lower panel of outer wing section has a maximum stress of 289.53Mpa and a maximum strain of 0.0042. The connecting bolts (M8 and M6) have a maximum stress of 686.81Mpa and a maximum strain of 0.0063, which meets the design requirements. In addition, according to the analysis results of the stress-strain state of the fitting joint of outer wing section, the force distribution of the bolts in the fitting joint of outer wing section with center section was obtained in this paper. It has been confirmed that due to the different positions and force areas of the bolts, the force distribution between rows of bolts is uneven, and the first row of bolts has a more force.

scholarly journals Respon struktur akibat perubahan jarak stiffener pada car deck Kapal Ferry Ro-Ro

2021 ◽  
Vol 10 (2) ◽  
Author(s):  
Alamsyah Alamsyah ◽  
Septiany Tri Pangestu ◽  
Amalia Ika Wulandari
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Structural Damage ◽  
Maximum Stress ◽  
Maximum Strain ◽  
The Finite Element Method ◽  
Stress Strain ◽  
Element Method

Ro-Ro type trans ships have a Car Deck which is useful for accommodating cargo in the form of vehicles. The construction of the deck must be strong enough so that it does not suffer structural damage when working with a certain load. In this case the stress strain becomes very important as an element of deck strength. As for what affects the strength of the deck construction, one of which is the stiffener distance. This purpose of research to determine the response of the car deck structure with variations in stiffener distance to the stress-strain value. The method used is the Finite Element Method. The results of detected the maximum stress value at a stiffener distance of 550 mm 325.471 N/mm2 with a maximum strain of 3.33 x 10-2 mm, for a stiffener distance of 650 mm the maximum stress was 407.521 N/mm2 and a maximum strain of 3.35 x 10-2 mm, a stiffener distance of 750 mm the maximum stress generated is 444.129 N/mm2 with a maximum strain of 3.36 x 10-3 mm, a stiffener distance of 850 mm, the maximum stress generated is 448.469 N/mm2 with a maximum strain of 3.43 x 10-3 mm. For a stiffener distance of 950 mm, the maximum stress is 452.567 N/mm2 with a maximum strain of 3.53 x 10-3 mm.

Delamination in the scoring and folding of paperboard

TAPPI Journal ◽  
2012 ◽  
Vol 11 (1) ◽  
pp. 61-66 ◽  
Author(s):  
DOEUNG D. CHOI ◽  
SERGIY A. LAVRYKOV ◽  
BANDARU V. RAMARAO
Keyword(s):  
Finite Element ◽  
Plane Deformation ◽  
Strain Analysis ◽  
Local Strain ◽  
Uniaxial Stress ◽  
Material Model ◽  
Element Model ◽  
Plastic Behavior ◽  
Stress Strain ◽  
Strain Fields

Delamination between layers occurs during the creasing and subsequent folding of paperboard. Delamination is necessary to provide some stiffness properties, but excessive or uncontrolled delamination can weaken the fold, and therefore needs to be controlled. An understanding of the mechanics of delamination is predicated upon the availability of reliable and properly calibrated simulation tools to predict experimental observations. This paper describes a finite element simulation of paper mechanics applied to the scoring and folding of multi-ply carton board. Our goal was to provide an understanding of the mechanics of these operations and the proper models of elastic and plastic behavior of the material that enable us to simulate the deformation and delamination behavior. Our material model accounted for plasticity and sheet anisotropy in the in-plane and z-direction (ZD) dimensions. We used different ZD stress-strain curves during loading and unloading. Material parameters for in-plane deformation were obtained by fitting uniaxial stress-strain data to Ramberg-Osgood plasticity models and the ZD deformation was modeled using a modified power law. Two-dimensional strain fields resulting from loading board typical of a scoring operation were calculated. The strain field was symmetric in the initial stages, but increasing deformation led to asymmetry and heterogeneity. These regions were precursors to delamination and failure. Delamination of the layers occurred in regions of significant shear strain and resulted primarily from the development of large plastic strains. The model predictions were confirmed by experimental observation of the local strain fields using visual microscopy and linear image strain analysis. The finite element model predicted sheet delamination matching the patterns and effects that were observed in experiments.

Sign in / Sign up

Export Citation Format

Share Document