Abstract:Using different heat insulating materials thickness in the heat insulating composite structure of the
heat protection system as the design variables, the temperature extremes of aircraft main structure (the minmum back
temperature) as the target parameters, the maximum use temperature of the second layer material in the composite
structure as the constraint condition, the heat insulating composite structure model is extablished and verified by the
quartz lamp check test. Using ANSYS software for one-dimensional finite element transient thermal anslysis, the model
calculated results are comprehensive compared with the experimental results, all the data are found in good agreement.
It has a certain theoretical guiding significance to the similar thermal insulation structure design and process optimization.
