Thermal Deformation of a Thermal Shield Material Vs. Method of Heat Supply
11 Pages Posted: 20 Jul 2022
Date Written: June 28, 2022
This work aims to analyze the thermal deformation of a thermal shield laminated material under a uniform or one-sided heating of up to 600°C/min. The material is made of a fiberglass composite polymer material based on phenol-formaldehyde matrix. This work describes the method used to study the kinetics of thermal deformation of the composite material at different heating rates and a high temperature of gas flow (2500°C). The state of the stressed-deformed samples made of a reinforced plastic is computed and used to measure the expanded temperature of the materials under one-sided heating. It is shown that under both force and thermal loading, the linear dependence of the coefficient of thermal deformation on temperature, stresses in the sample developed to prevent the bending of free samples. For a bent sample, there is no stress gradient under increased heating rate of the loaded samples, leading to an increase in the stress gradient values. The data are compared with dilatometry results obtained at a uniform temperature field and heating rates of 20 to 1100°C.
Keywords: Thermal shield, spacecraft, re-entry, composite material, high temperature, fiberglass, dilatometer
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