Specimen Thickness and Impactor Mass Effects on Drop-Weight Impact Studies of GLARE 5 Fiber-Metal Laminates

2011 ◽  
Author(s):  
A. Seyed Yaghoubi ◽  
B. Liaw
Keyword(s):  
Impact Velocity ◽  
Volume Fraction ◽  
Energy Condition ◽  
Specimen Thickness ◽  
Fiber Metal Laminates ◽  
Drop Weight ◽  
Metal Volume ◽  
Fiber Metal ◽  
The Impact ◽  
Metal Volume Fraction

Impact responses and damage induced by a drop-weight instrument on GLARE 5 fiber-metal laminates (FMLs) with different thicknesses were studied. The effect of impactor mass was also considered. The damage characteristics were evaluated using both nondestructive ultrasonic and mechanical sectioning techniques. The ultrasonic C-scan technique could only assess the contour of entire damage area whereas more details of damage were obtained using the mechanical cross-sectioning technique. As expected, thicker GLARE 5 FMLs offered higher impact resistance. When subjected to the same impact energy, the entire damage contour enlarged as the specimen became thicker. Under the same impact condition, by reducing the impactor mass, the contact force escalated while the contact stiffness increased. Experimental results showed that the threshold cracking energy varied parabolically with respect to the impact velocity, metal volume fraction (MVF) and the specimen thickness. By increasing the metal volume fraction of the panels, the threshold cracking energy decreased parabolically. On the other hand, for the same MVF value, the cracking energy increased as the impactor mass increased. By increasing the panel thickness, the threshold cracking energy condition increased parabolically; whereas under the same impact velocity, the threshold cracking energy increased by increasing the impactor mass.

Investigation on the effect of configuration on tensile and flexural properties of aluminum/self-reinforced polypropylene fiber metal laminates

2018 ◽  
Vol 22 (6) ◽  
pp. 1770-1785
Author(s):  
Lei Pan ◽  
Yifan Wang ◽  
Yubing Hu ◽  
Yunfei Lv ◽  
Aamir Ali ◽  
...  
Keyword(s):  
Volume Fraction ◽  
Polypropylene Fiber ◽  
Tensile Failure ◽  
Flexural Properties ◽  
Metal Composite ◽  
Fiber Metal Laminates ◽  
Metal Volume ◽  
Fiber Metal ◽  
Flexural Tests ◽  
Metal Volume Fraction

Tensile and flexural properties of aluminum/self-reinforced polypropylene fiber metal laminates (Al/SRPP FMLs) based on 2/1 and 3/2 configurations are investigated in this paper. The Al/SRPP FMLs based on 2/1 configuration exhibit better performance than the Al/SRPP FMLs based on 3/2 configuration in terms of tensile and flexural properties. The metal volume fraction plays an important role in the tensile strength and flexural strength in both Al/SRPP-2/1 FMLs and Al/SRPP-3/2 FMLs. The tensile stress–strain curves of Al/SRPP-2/1FMLs and Al/SRPP-3/2FMLs decline while the ductility of both FMLs enhances as the temperature increases. The elevated temperature intensifies the delamination of the Al/SRPP FMLs, especially for Al/SRPP-3/2FMLs because of possible more manufacture defects. The outer metal cracking and inter-laminar delamination are the main tensile failure mechanisms. However, delamination at the metal/composite interface and breakage of the constituent materials does not occur after the flexural tests.

Pilot study of metal volume fraction approach for fiber/metal laminates

1995 ◽  
Vol 32 (3) ◽  
pp. 663-671 ◽  
Author(s):  
H. F. Wu ◽  
L. L. Wu ◽  
W. J. Slagter ◽  
J. L. Verolme
Keyword(s):  
Pilot Study ◽  
Volume Fraction ◽  
Fiber Metal Laminates ◽  
Metal Volume ◽  
Fiber Metal ◽  
Metal Volume Fraction

Experimental-theoretical predictions of stress–strain curves of Glare fiber metal laminates

2017 ◽  
Vol 52 (1) ◽  
pp. 109-121 ◽  
Author(s):  
Hale Ergun ◽  
Benjamin M Liaw ◽  
Feridun Delale
Keyword(s):  
Volume Fraction ◽  
Tensile Tests ◽  
In Situ Stress ◽  
Fiber Metal Laminates ◽  
Stress Strain ◽  
Empirical Parameter ◽  
Metal Volume ◽  
Fiber Metal ◽  
Metal Volume Fraction ◽  
Fraction Method

Monotonic tensile tests are conducted on seven different Glare grades of fiber metal laminates. In-situ stress–strain curves of glass/epoxy laminate interleaved in Glare 2(3/2) are exposed with the application of metal volume fraction method using the stress–strain curves of Glare 2(3/2) and Aluminum 2024-T3 in unidirectional and transverse directions. The strain–stress curves of cross-ply Glares are predicted by the modification of this method with an empirical parameter and a second parameter considering the relative glass/epoxy laminate thickness ratios of Glare grades. Modified metal volume fraction method presented in this study can be used as a preliminary estimation of stress–strain curves of multiple possible fiber metal laminate configurations without testing.

Determination of Ballistic Limits of GLARE 5 Fiber-Metal Laminates: The Influences of Geometry, Thickness and Stacking Sequence

2011 ◽  
Author(s):  
A. Seyed Yaghoubi ◽  
B. Liaw
Keyword(s):  
Volume Fraction ◽  
Velocity Versus ◽  
Specimen Thickness ◽  
Stacking Sequence ◽  
Ballistic Limit ◽  
Fiber Metal Laminates ◽  
Limit Velocity ◽  
Fiber Metal ◽  
Ballistic Limit Velocity

In this paper, GLARE 5 fiber-metal laminates (FMLs) of two different geometries: 152.4mm×101.6mm (6″×4″) plate and 254mm×25.4mm (10″×1″) beam and with various thicknesses and stacking sequences were impacted by a 0.22 caliber bullet-shaped projectile using a high-speed gas gun. Velocities of the projectile along the ballistic trajectory were measured at different locations. For both geometries, the incident projectile impact velocity versus the residual velocity was plotted and numerically fitted according to the classical Lambert–Jonas equation for the determination of ballistic limit velocity, V50. The results showed that V50 varied in a parabolic trend with respect to the metal volume fraction (MVF) and the specimen thickness for both geometries. It was found that by changing the geometry from a plate to a beam, the ballistic limit velocity increased. On the other hand, changing the stacking sequence had a less pronounced effect on V50 for both geometries. The quasi-isotropic beam and plate specimens offered relatively higher ballistic limit velocities compared to other types of stacking sequences in their own geometrical groups. Furthermore, the cross-ply and unidirectional beam specimens showed relatively higher V50 compared to their plate counterparts. Experimental results showed that the ballistic limit was almost the same for the quasi-isotropic layup FMLs of both plate and beam geometries.

Ballistic performance and damage simulation of fiber metal laminates under high-velocity oblique impact

2020 ◽  
Vol 29 (7) ◽  
pp. 1011-1034 ◽  
Author(s):  
Chao Zhang ◽  
Qian Zhu ◽  
Jose L Curiel-Sosa ◽  
Tinh Quoc Bui
Keyword(s):  
Impact Velocity ◽  
High Velocity ◽  
Damage Mechanics ◽  
Failure Modes ◽  
Element Model ◽  
Oblique Impact ◽  
Ballistic Performance ◽  
Fiber Metal Laminates ◽  
Fiber Metal ◽  
The Impact

Fiber metal laminates have been successfully applied in military aircrafts, armor vehicles and other modern engineering industries as protective structures due to their outstanding impact resistant properties. Prediction of the ballistic performance and investigation on the damage mechanism of the fiber metal laminates under general oblique impact conditions still remain a very challenging issue. In this study, a nonlinear dynamic finite element model in terms of continuum damage mechanics including intra- and inter-layer failure modes is presented. The accuracy of this model is validated with available experimental data. The damage and ballistic performance of two different structural fiber metal laminates subjected to high-velocity oblique impact by rigid hemispherical nose projectile with angles of 0°, 30°, 45° and 60° are studied. The numerical results show that the projectile deflects when the oblique impact occurs and the deflection angle decreases with increasing the impact velocity. The residual velocity of the projectile and the energy absorption of the target are related to the initial impact velocity and impact angle of the projectile. The proposed simulation approach offers a new proper reference for numerical investigations of common oblique impact problems in other fiber metal laminates.

Bolt Bearing Strength of Commingled Boron/Glass Fiber Reinforced Aluminum Laminates

2012 ◽  
Author(s):  
P. C. Yeh ◽  
P. Y. Chang ◽  
J. M. Yang ◽  
P. H. Wu ◽  
M. C. Liu
Keyword(s):  
Fiber Orientation ◽  
Fiber Volume Fraction ◽  
Volume Fraction ◽  
Fiber Volume ◽  
Fiber Metal Laminates ◽  
Boron Fiber ◽  
Bearing Strength ◽  
Glass Fiber Reinforced ◽  
Metal Volume ◽  
Fiber Metal

The bearing properties of recently developed hybrid fiber/metal laminates, or COmmingled Boron/glass fiber Reinforced Aluminum laminates (COBRA), are investigated in this study. The bolt-type bearing tests on GLass REinforced aluminum laminates (GLARE), non-commingled hybrid boron/glass/aluminum fiber/metal laminates (HFML) and COBRA were carried out as a function of e/D ratio, metal volume fraction, fiber volume fraction, and fiber orientation. Experimental results show that with the same joint geometry and metal volume fraction, the commingling of boron fibers improves the bearing strength of fiber/metal laminates. The bearing strength of COBRA with longitudinal fibers is lower than that with transverse fibers due to the fact that shearout failure takes place before maximum bearing strength is reached. The experimental results show that, with only either transverse fiber orientation or longitudinal fiber orientation, COBRA with 18% boron fiber volume fraction possesses a higher bearing strength when compared to HFML with 6% boron fiber volume fraction. In addition to the properties in COBRA with parallel-plies commingled prepreg, the bearing properties of various COBRA with [0°/90°] and [0°/90°/90°/0°] cross-ply commingled prepregs are also discussed.

scholarly journals The Plastic Behavior in the Large Deflection Response of Fiber Metal Laminate Sandwich Beams under Transverse Loading

Materials ◽  
2022 ◽  
Vol 15 (2) ◽  
pp. 439
Author(s):  
Mingshi Wang ◽  
Jianxun Zhang ◽  
Hui Yuan ◽  
Haoyuan Guo ◽  
Wenbo Zhuang
Keyword(s):  
Large Deflection ◽  
Volume Fraction ◽  
Composite Layer ◽  
Plastic Behavior ◽  
Sandwich Beams ◽  
Transverse Loading ◽  
Fiber Metal Laminate ◽  
Metal Volume ◽  
Fiber Metal ◽  
Metal Volume Fraction

The plastic behavior in the large deflection response of slender sandwich beams with fiber metal laminate (FML) face sheets and a metal foam core under transverse loading is studied. According to a modified rigid–perfectly plastic material approximation, an analytical model is developed, and simple formulae are obtained for the large deflection response of fully clamped FML sandwich beams, considering the interaction of bending and stretching. Finite element (FE) calculations are conducted, and analytical predictions capture numerical results reasonably in the plastic stage of large deflection. The influences of metal volume fraction, strength ratio of metal to composite layer, core strength, and punch size on the plastic behavior in the large deflection response of FML sandwich beams are discussed. It is suggested that, if the structural behavior of fiber-metal laminate sandwich beams is plasticity dominated, it is similar to that of metal sandwich beams. Moreover, both metal volume fraction and the strength ratio of metal to composite layer are found to be important for the plastic behavior in the large deflection response of fiber metal laminate sandwich beams, while core strength and punch size might have little influence on it.

Residual Stresses in Intrinsic UD-CFRP-Steel-Laminates - Experimental Determination, Identification of Sources, Effects and Modification Approaches

2015 ◽  
Vol 825-826 ◽  
pp. 369-376 ◽  
Author(s):  
Robert Prussak ◽  
Daniel Stefaniak ◽  
Christian Hühne ◽  
Michael Sinapius
Keyword(s):  
Mechanical Properties ◽  
Residual Stress ◽  
Tensile Strength ◽  
Epoxy Composite ◽  
Thermal Residual Stress ◽  
Fiber Metal Laminates ◽  
Fiber Metal ◽  
Impact Energies ◽  
The Impact ◽  
Specific Impact

This paper focuses on the reduction of process-related thermal residual stress in fiber metal laminates and its impact on the mechanical properties. Different modifications during fabrication of co-cure bonded steel/carbon epoxy composite hybrid structures were investigated. Specific examinations are conducted on UD-CFRP-Steel specimens, modifying temperature, pressure or using a thermal expansion clamp during manufacturing. The impact of these parameters is then measured on the deflection of asymmetrical specimens or due yield-strength measurements of symmetrical specimens. The tensile strength is recorded to investigate the effect of thermal residual stress on the mechanical properties. Impact tests are performed to determine the influence on resulting damage areas at specific impact energies. The experiments revealed that the investigated modifications during processing of UD-CFRP-Steel specimens can significantly lower the thermal residual stress and thereby improve the tensile strength.

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