Modeling elastic and thermal properties of 2.5D carbon fiber and carbon/SiC hybrid matrix composites by homogenization method
doi: 10.5028/jatm.2010.02026510

Luiz Claudio Pardini*
Institute of Aeronautics and Space
São José dos Campos – Brazil
pardini@iae.cta.br

Maria Luisa Gregori
Institute of Aeronautics and Space
São José dos Campos – Brazil
mloug@yahoo.com.br

*author for correspondence

Abstract:

Advanced carbon fiber hybrid carbon-ceramic matrix composites are realizing their potential in many thermostructural components for aerospace vehicles. This work presents ab-initio predictions of elastic constants and thermal properties for 2.5D carbon fiber reinforced carbon-silicon carbide hybrid matrix composites, by using the homogenization technique. The homogenization technique takes properties of individual components of the composites (fiber and matrix) and characteristics of the geometrical architecture of the preform to perform calculations. Ab-initio modeling of mechanical and thermal properties is very attractive, especially during the material development stage, when larger samples may be prohibitively expensive or impossible to fabricate. Modeling is also useful when bigger samples would be prohibitively expensive or impractical. Thermostructural composites made of 2.5D preforms are easy to manufacture in relation to 3D preforms. Besides, 2.5D preforms are also resistant to thermo cycling and have high resistance to crack propagation in relation to ply stacked composites such as unidirectional (1D) and bidirectional (2D) structures. The calculations were performed by setting an overall carbon fiber volume fraction at 40, 45 and 50 for a 2D stacked composite, and volume fraction in Z-direction of 2, 4 and 6.

Keywords:

Mechanical properties, Carbon-SiC composites, Elastic properties, Thermal properties.

J. Aerosp.Technol. Manag., São José dos Campos, Vol.2, No.2, pp. 183-194, May-Aug., 2010
Received: 07/04/10
Accepted: 11/05/10