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In the frame of the ESA “Manned Space Transportation Programme” (MSTP) the applicability of flexible insulation blankets as thermal protection system of the conical surface of capsules is investigated. The blankets have to withstand the severe ascent and re-entry aerothermal and aerodynamical environment at temperatures of up to 1200 °C. For this temperature regime ceramic components are to be applied due to their excellent temperature stability and strength properties. In the frame of a comprehensive thermal and structural characterization of these materials thermal conductance measurements are performed on a ceramic fibrous core material and a blanket in this operational temperature range at gas pressures ranging from near vacuum up to ambient conditions.