Tensile behavior and microstructural evolution of a carbon/silicon carbide composite in simulated re-entry environments

Abstract Carbon fiber reinforced silicon carbide matrix composites with a protective coating were prepared by chemical vapor infiltration. Their tensile strength was about 240–250 MPa at room temperature, and 330–390 MPa in vacuum. Tensile behavior in a simulated re-entry environment was studied and compared with that in vacuum. The microstructural evolution on tensile fracture surfaces were investigated by scanning electron microscopy, and an oxidation damage pattern of fibers on tensile fracture surface was presented and discussed. A significant strength reduction was observed in re-entry environments due to the interaction of load, high temperature, and oxidation. The non-uniform oxidation of fibers weakened the load-carrying ability due to decreasing effective loaded area and hence strength. Finally, a minimum diameter of total fiber cluster embedded in composites is suggested about 220 μm for use under high load in re-entry environments at 1800 °C.

[1]  G. Camus,et al.  Kinetics and Mechanisms of Oxidation of 2D Woven C/SiC Composites: I, Experimental Approach , 1994 .

[2]  Han. Dong,et al.  Tensile creep behavior of notched two-dimensional-C/SiC composite , 2006 .

[3]  J. Lebrun,et al.  THERMAL RESIDUAL STRESSES IN CERAMIC MATRIX COMPOSITES-II. EXPERIMENTAL RESULTS FOR MODEL MATERIALS , 1995 .

[4]  E. Opila,et al.  Effect of Environment on the Stress‐Rupture Behavior of a Carbon‐Fiber‐Reinforced Silicon Carbide Ceramic Matrix Composite , 2004 .

[5]  R. E. Hann,et al.  Paralinear Oxidation of CVD SiC in Simulated Fuel‐Rich Combustion , 2004 .

[6]  Lai-fei Cheng,et al.  Behavior of two-dimensional C/SiC composites subjected to thermal cycling in controlled environments , 2006 .

[7]  L. Guillaumat,et al.  Development of damage in a 2D woven C/SiC composite under mechanical loading: I. Mechanical characterization , 1996 .

[8]  R. Shenoi,et al.  Measurement of braided preform permeability , 2006 .

[9]  A. Calomino,et al.  Temperature Dependence on the Strength and Stress Rupture Behavior of a Carbon‐Fiber Reinforced Silicon Carbide Matrix (C/SiC) Composite , 2008 .

[10]  J. Gotoh,et al.  Development of High Temperature Materials Including CMCs for Space Application , 1998 .

[11]  J. Dentzer,et al.  Reactivity of a C/SiC composite in water vapour , 2001 .

[12]  M. S. Dadkhah,et al.  Effect of Weave Architecture on Tensile Properties and Local Strain Heterogeneity in Thin‐Sheet C–SiC Composites , 2002 .

[13]  A. Mühlratzer,et al.  CMC Body Flaps for the X‐38 Experimental Space Vehicle , 2008 .

[14]  H. Weihs,et al.  Thermo‐Mechanical Qualification Tests of Complex CMC Re‐Entry Structures , 2008 .

[15]  C. Sauder,et al.  The tensile behavior of carbon fibers at high temperatures up to 2400 °C , 2004 .

[16]  H. Eaton,et al.  Accelerated oxidation of SiC CMC's by water vapor and protection via environmental barrier coating approach , 2002 .

[17]  M. Auweter-Kurtz.  Plasma source development for the qualification of thermal protection materials for atmospheric entry vehicles at IRS , 2002 .