Evaluation of thermal performance and thickness of carbon phenolic composite structure under aero-thermal loading

Abstract

Aerospace structures contain multilayer structures to sustain severe aerodynamic loading and heating. Hence they will be made with a carbon-epoxy internal layer(as a structural layer) whereas carbon phenolic external layer (as thermal protection layer) as a multi-layered component. Carbon-phenolic composites are meant or heat protection of the aerospace like aircraft skins, nozzles and heat shields during the aerodynamic loading conditions. In this paper, the behavior of the thermal protection system under aero-thermal load during re-entry at hypersonic speed through the earth atmosphere has been studied. Thermal performance of the carbon-phenolic components depends on the shape of the structure, velocity of the object, angle of attack and the heat flux experienced. The heat of reaction and pyrolysis process decides the structural integrity of the thermal layer. For various velocities, shapes and heat Flux conditions, the rate of ablation, surface temperature, residual thickness of the material has been evaluated. The heat of reaction and the volume of chemical species evolved under aerodynamic heating are measured by pyrolysis gas chromatography (Py-GC) and thermo-gravimetry (TG), which will be used as inputs or thermal evaluation of the structure. Modeling of the blunt body using CAD and imported to simulation software USIM to visualize different properties of the atmosphere and blunt body model.