Abstract
ABSTRACTThe work carried out under the XMat research programme (Materials Systems for Extreme Environments, EPSRC Programme Grant number EP/K008749/1-2) in the field of ultra-high temperature ceramic matrix composites has been focused on the design, development and manufacture of complex shapes and large panels for use under extreme conditions. The composites are made from 2.5D woven carbon fibre preforms impregnated with HfB2 powders and with a pyrolytic carbon, PyC, matrix created using chemical vapour infiltration, CVI. More recently, the knowledge acquired during the development of these Cf-HfB2-C composites has been focused on shortening the densification time by moving from conventional CVI to Radio Frequency-heated CVI; the work has also switched to Cf-ZrB2-C composites. In addition, the use of 3D carbon fibre preforms has begun to be explored to improve the mechanical properties and also the replacement of PyC matrix with ZrB2 to reducing the oxidation of the composites at ultra-high temperature.
Highlights
Interest in advanced materials with a temperature capability over 2500°C for a range of aerospace applications involving launch and/or re-entry into Earth’s atmosphere has increased over the last few decades [1,2,3,4]
The knowledge acquired during the development of these Cf-HfB2-C composites has been focused on shortening the densification time by moving from conventional chemical vapour infiltration (CVI) to Radio Frequency-heated CVI; the work has switched to Cf-ZrB2-C composites
The impregnation of 2.5D woven carbon fibre preform with UHTC powder before infiltration with carbon has allowed the temperature capabilities of the carbon–carbon composites to be extended beyond 2500°C
Summary
Interest in advanced materials with a temperature capability over 2500°C for a range of aerospace applications involving launch and/or re-entry into Earth’s atmosphere has increased over the last few decades [1,2,3,4]. The most promising lightweight materials are carbon/carbon (C/C) composites; there is a critical need to improve their oxidation [5,6,7] and ablation [8,9,10] resistance. Addition of UHTCs, which inherently have a higher thermal conductivity and form in situ oxidation scales, have been reported to improve the oxidation and ablation resistance of C/C, C/SiC and SiC/SiC composites [17,18]. The ceramic matrix used in the design of the composite is going to depend on the working temperature, exposure time and mechanical stresses that the material needs to bear for the application.
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