21-06-2012, 05:46 PM
Finite element analysis of composites materials for aerospace
applications
Introduction
Composite materials are very flexible and operate in a broad range of applications. It is completed by
integrating two materials which are reinforcement (fiber) and matrix (resin). The integration of both
materials can offer the excellent characteristics compared to the material individually [1-3]. There are
a large application range of composite materials such as for electrical and electronics, buildings and
public work, transportation (road, rail, marine, air and space), sports and recreation, general
mechanical applications and aerospace industry [4].
Nowadays, the application of composite materials in aerospace industry is growing up. Composite
materials provide a completely high strength-to-weight ratio in addition to the capability to produce
large and integrated structure [1].
Simulation
In this study, the simulation was undertaken in framework of ABAQUS commercial finite element
package. Finite element modeling of composites is depending on the purpose of the analysis. In
ABAQUS, there are several techniques for composite modeling such as microscopic modeling,
macroscopic modeling, mixed modeling, discrete reinforcement modeling and submodeling.
However, the most common use in finite element simulations of composite material are layeredshells,
layered-solids, stacked solid elements and stacked or layered continuum shells [11].
Experimental
The experimental work is successfully done which consists of tensile test and thermal-stress test. This
experiment required only simple rectangular-shape test specimen where it is prepared using hand lay
up process. During the experiment, the surface of clean plate flat surface was waxed to facilitate easy
removal of the laminate before apply mix of resin on the waxed surface. Then, cut the first fiber layer
into required dimension and placed on the top of that and apply the resin again. Make even the resin
using serrated roller and brush and removed all trapped air in resin and fiber. Repeat this step for the
next layer until 6 layers. Finally, cover the layers with waxed flat surface and put load on the top of it
to produce a better surface. Specimen was cured at room temperature for 24h in ambient condition.
Then, it was cut into the specimen dimension which is 25 mm x 250 mm.
Results
The simulations were undertaken on two samples of e-glass parameters as detailed in Table 2. The
magnitude of the load for each simulation is 20 kN. For the first simulation, the orientation angle for
composite plate is 45° for ply-1, -45° for ply-2 and 90° for ply-3 and the plies will be symmetric that
made 6 plies. After the first simulation is successfully done, it was repeated by changing the values
orientation angle which is 0° for each ply. Results and data from analysis are able to obtain from the
completed analysis.