Tensile and Compressive Failure Modes of Laminated Composites Loaded by Fatigue with Different Mean Stress

1990 ◽  
Vol 12 (4) ◽  
pp. 201 ◽  
Author(s):  
W Steven Johnson ◽  
PA Lagace ◽  
JE Masters ◽  
A Rotem
Keyword(s):  
Failure Modes ◽  
Laminated Composites ◽  
Mean Stress ◽  
Compressive Failure

Longitudinal Compressive Failure Modes in Fiber Composites: End Attachment Effects on IITRI Type Test Specimens

1985 ◽  
Vol 7 (4) ◽  
pp. 129 ◽  
Author(s):  
KL Reifsnider ◽  
GP Sendeckyj ◽  
SS Wang ◽  
TT Chaio ◽  
W Feng ◽  
...  
Keyword(s):  
Failure Modes ◽  
Fiber Composites ◽  
Compressive Failure ◽  
Type Test

Compression after impact behavior of titanium honeycomb sandwich structures

2017 ◽  
Vol 20 (5) ◽  
pp. 639-657 ◽  
Author(s):  
Wei Zhao ◽  
Zonghong Xie ◽  
Xiang Li ◽  
Xishan Yue ◽  
Junfeng Sun
Keyword(s):  
Failure Modes ◽  
Sandwich Structures ◽  
Impact Damage ◽  
Sandwich Panels ◽  
Low Velocity Impact ◽  
Impact Behavior ◽  
Failure Strength ◽  
Compressive Failure ◽  
Low Velocity ◽  
Honeycomb Sandwich

Titanium honeycomb sandwich structures are gradually used in several newly developed aircrafts in China. During the manufacturing process and aircraft service life, low-velocity impacts from foreign objects (typically stones, tools and hails, etc.), would quite likely happen and could not be completely avoided. In order to evaluate the influence of low-velocity impact damage on titanium honeycomb sandwich structures, unidirectional in-plane compression tests on both intact and impact damaged sandwich panels were conducted to obtain their failure modes and compressive failure strength. Test results showed that the low-velocity impact damage could cause the change in failure modes and a 9% to 15% decrease in the compressive failure strength. Different impact energy levels showed a limited influence on the compressive failure strength. Numerical analysis was conducted to study the compression after impact behavior of titanium sandwich panels. Parametric finite element models that contained all the geometric and the structural details of honeycomb core cells, as well as the indentation and the crushed core region, were developed in the analysis. The numerical results successfully exhibited the failure process of the intact and impact damaged titanium sandwich panels subjected to unidirectional in-plane compression, similar to what observed in the tests. The predicted compressive failure strength also agreed very well with the test data.

Load and Geometry Effect on Failure Mode Initiation of Composite Sandwich Beams

2006 ◽  
Vol 3-4 ◽  
pp. 173-178
Author(s):  
E.E. Gdoutos ◽  
M.S. Konsta-Gdoutos
Keyword(s):  
Failure Mode ◽  
Failure Modes ◽  
Shear Failure ◽  
Sandwich Beams ◽  
Compressive Failure ◽  
Honeycomb Core ◽  
Composite Sandwich ◽  
Failure Mode Transition ◽  
Aluminum Honeycomb ◽  
Geometrical Dimensions

Facing compressive failure, facing wrinkling and core shear failure are the most commonly encountered failure modes in sandwich beams with facings made of composite materials. The occurrence and sequence of these failure modes depends on the geometrical dimensions, the form of loading and type of support of the beam. In this paper the above three failure modes in sandwich beams with facings made of carbon/epoxy composites and cores made of aluminum honeycomb and two types of foam have been investigated. Two types of beams, the simply supported and the cantilever have been considered. Loading included concentrated and uniform. It was found that in beams with foam core facing wrinkling and core shear failure occur, whereas in beams with honeycomb core facing compressive failure and core shear crimping take place. Results were obtained for the dependence of failure mode on the geometry of the beam and the type of loading. The critical beam spans for failure mode transition from core shear to wrinkling failure were established. It was found that initiation of a particular failure mode depends on the properties of the facing and core materials, the geometrical configuration and loading of composite sandwich beams.

Bending Fatigue Design Method for Double Sides Loaded Gears

2009 ◽  
Vol 419-420 ◽  
pp. 865-868
Author(s):  
Guo Jun Wang ◽  
Mei Hua Jiang ◽  
Shi Shun Zhu ◽  
An Tao Xu
Keyword(s):  
Failure Modes ◽  
Design Method ◽  
Mean Stress ◽  
Bending Fatigue ◽  
Gear Design ◽  
Fatigue Design ◽  
Single Side ◽  
The Mean ◽  
New Formula

Bending fatigue is one of the main failure modes of gears. The method of gear fatigue design was discussed in many papers. Most of them are based on GB/T3480-83.But study shows that the method current widely used only fits for the single side loaded gear. For double sides loaded gear, only a mean stress modification coefficient is concerned compared to single side loaded gear. A new formula based on fatigue theory is given to modify the mean stress in consideration of the load character of doubled sides loaded gear. The method given in the paper is an addition to the traditional gear design method.

Low Velocity Impact Analysis on GFRP Laminates under Different Temperatures

2011 ◽  
Vol 110-116 ◽  
pp. 632-636
Author(s):  
K. Pazhanivel ◽  
G.B. Bhaskar ◽  
S. Arunachalam ◽  
V. Hariharan ◽  
A. Elayaperumal
Keyword(s):  
Composite Materials ◽  
Impact Analysis ◽  
Failure Modes ◽  
Laminated Composites ◽  
Low Velocity Impact ◽  
Impact Behavior ◽  
Low Velocity ◽  
Aerospace Applications ◽  
Different Temperatures ◽  
The Impact

Composite materials have a number of properties that make them attractive for use in aerospace applications. The impact behavior of fiber reinforced composite materials is much more complex than conventional metallic structures due to a number of different failure modes on the inter laminar and intra laminar level. The aim of this study is to investigate the effects of temperature and thermal residual stresses on the impact behavior and damage of glass/epoxy laminated composites. To this end, thermal stress analyses of the laminates with lay-ups [90/0/0/90] s, [90/0/45/45] s, [0/90/45/-45] s, [45/0/-45/90] s are carried out under different temperatures by using ANSYS software. Also, the impact analysis on the laminated composites was performed at the different range of impact energies under different temperatures. The specific energy values and impact parameters were obtained and compared for each type of specimens and temperatures.

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