An experimental apparatus was designed and fabricated to measure the effective thermal conductivities and simulate the temperature and pressure history of reentry of a launch vehicle into a planetary atmosphere with a maximum temperature of $1600°C$. An improved testing method was used to test the thermal conductivities of an alumina fibrous insulation at environmental pressures from $0.03Pato105Pa$ with the average temperature of the sample increased to $864°C$ and its density being $128kg∕m3$. A method based on temperature difference is used to compute the in-plane effective thermal conductivity, and the result shows that the in-plane thermal conductivity along the $y$ axis is 1.47 times that along the $x$ axis. The influences of temperature and pressure on the contribution of three heat transfer mechanisms to the effective thermal conductivities were compared.

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