Ablation behavior of SiC fiber/carbon matrix composites under simulated atmospheric reentry conditions

Processing, mechanical properties, and ablation behavior of SiC fiber/carbon matrix composites for a thermal protection system material of a re-entry vehicle were examined. Orthogonal 3-D woven fabrics (Vf = 0.21, 0.21 and 0.02 for x, y, z directions) made of SiC fibers (Tyranno ZMI) were applied for reinforcement with a carbon matrix formed by polymer impregnation and pyrolysis (PIP) and/or chemical vapor infiltration (CVI). This SiC/CVI-C composite has high ultimate tensile strength of 415 MPa at 25 °C. Air plasma exposure in a plasma wind tunnel revealed no surface recession. The mass loss rate decreased over time. The SiC/C composites exhibit excellent oxidation resistance in high enthalpy plasma air for short durations.