Abstract: A process is disclosed for producing a high temperature stable fiber composite ceramic by chemical vapor infiltration (CVI) with a silicon carbide precursor in a suitable carrier gas on carbon fiber preforms or silicon carbide fiber preforms. This process is characterized by the use of a process pressure of ?0.6 bar absolute and a process temperature of ?1100° C. Also disclosed are structural component parts, particularly for aircraft and spacecraft engineering, which are commonly exposed to high thermal and mechanical loading and which have been produced by the above process.

Abstract: Material from a fibre composite ceramic, constructed from a) a dense fabric or cluster of three-dimensional oriented fibres with a high thermal conductivity, b) a crystalline matrix of ?-silicon carbide, that is produced in a CVI process on the fibres, c) a matrix component of ?-silicon carbide that in a polymer infiltration and pyrolysis process is generated in pores of the fabric structure, starting from a suspension of silicon carbide powder in a polymer, and d) a further matrix component of ?-silicon carbide that is created in a CVI process in cracks and pores of the material, caused by the preceding pyrolysis process.

Abstract: A movable structural component for a thermomechanically stressed assembly at least partially from fiber reinforced ceramic is disclosed, wherein the movable structural component comprises at least one structural element made by an polymer infiltration and pyrolysis process and at least one structural element made by an chemical phase infiltration process.

Abstract: A movable structural component for a thermomechanically stressed assembly at least partially from fiber reinforced ceramic is disclosed, wherein the movable structural component comprises at least one structural element made by an polymer infiltration and pyrolysis process and at least one structural element made by a chemical vapor process.

Abstract: A process is disclosed for producing a high temperature stable fiber composite ceramic by chemical vapor infiltration (CVI) with a silicon carbide precursor in a suitable carrier gas on carbon fiber preforms or silicon carbide fiber preforms. This process is characterized by the use of a process pressure of ≧0.6 bar absolute and a process temperature of ≧1100° C. Also disclosed are structural component parts, particularly for aircraft and spacecraft engineering, which are commonly exposed to high thermal and mechanical loading and which have been produced by the above process.

Abstract: A movable structural component for a thermomechanically stressed assembly at least partially from fiber reinforced ceramic is disclosed, wherein the movable structural component comprises at least one structural element made by an polymer infiltration and pyrolysis process and at least one structural element made by an chemical phase infiltration process.