In this work, a detailed investigation into the development of a high heat flux sensor to improve the Thermal Protection System of spacecraft is presented. The research employs a comprehensive approach that integrates both experimental and numerical methodologies. Experimental trials are conducted in a Kinetic heating simulation facility, exposing the Carbon Silica Carbide (CSiC) material to varying heat flux levels and recording its thermal response. CSiC is a composite material composed of carbon fibers embedded in a silica carbide matrix which gives exceptional thermal conductivity, high-temperature resistance, and lightweight properties, making it an ideal candidate for aerospace applications. Subsequently, numerical simulations analyze temperature gradients within the CSiC specimen over time, yielding a partial differential equation that is solved using the finite difference method of both implicit utilizing the Tridiagonal Matrix Algorithm method (TDMA) and explicit methods. Python programming is utilized to implement the numerical solution, predicting the thermal characteristics for three distinct heat flux values (5W/cm², 10W/cm², 15W/cm²). Furthermore, ANSYS Thermal Workbench is employed to provide a comprehensive understanding of the material's thermal behavior and its interaction with the spacecraft environment. The results of experimental and numerical analyses for different heat flux conditions are meticulously compared, focusing particularly on back wall temperatures. Interestingly, the numerical methods employed for the 5 W/cm² heat flux condition yielded superior accuracy and reliability in predicting the thermal behavior of the CSiC material, showcasing the effectiveness of the numerical approach in this specific scenario.
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