Thermal protection systems (TPS) have been used to protect space vehicles from aerodynamic heating during extreme conditions such as hypersonic flights, atmospheric re-entry, and propulsion. Ablation is an erosive high-temperature phenomenon accompanied by physical and chemical changes. Ablation rem...
Thermal protection systems (TPS) have been used to protect space vehicles from aerodynamic heating during extreme conditions such as hypersonic flights, atmospheric re-entry, and propulsion. Ablation is an erosive high-temperature phenomenon accompanied by physical and chemical changes. Ablation removes material by decomposition, melt, vaporization, and sublimation caused by a heat stream, pressure, and velocity. TPS materials have to withstand high temperature, shockwave loading, and ablative degradation, and they have to possess erosion resistance. Carbon-based materials such as carbon/carbon and carbon/phenolic resin composites have been used as TPS materials because of their light weight, high specific strength, low thermal expansion coefficient (CTE). C/C composites are composed of a carbon fiber and a carbon matrix, and various kinds of fibers and matrix precursor materials are used to fabricate them. The fabrication process, including the choice of fibers, precursor materials, and thermal processing, is the main factor that determines the thermophysical properties of the composites. Multidirectional C/C composites can endure high thermal gradient and complex mechanical stresses. We investigate the ablation characteristics of a graphite, a needle-punched C/C composite, and a 3-directional C/C composite currently under development and analyze their relevance for use as TPS materials by using a 0.4 MW supersonic plasma wind tunnel facility.
Thermal protection systems (TPS) have been used to protect space vehicles from aerodynamic heating during extreme conditions such as hypersonic flights, atmospheric re-entry, and propulsion. Ablation is an erosive high-temperature phenomenon accompanied by physical and chemical changes. Ablation removes material by decomposition, melt, vaporization, and sublimation caused by a heat stream, pressure, and velocity. TPS materials have to withstand high temperature, shockwave loading, and ablative degradation, and they have to possess erosion resistance. Carbon-based materials such as carbon/carbon and carbon/phenolic resin composites have been used as TPS materials because of their light weight, high specific strength, low thermal expansion coefficient (CTE). C/C composites are composed of a carbon fiber and a carbon matrix, and various kinds of fibers and matrix precursor materials are used to fabricate them. The fabrication process, including the choice of fibers, precursor materials, and thermal processing, is the main factor that determines the thermophysical properties of the composites. Multidirectional C/C composites can endure high thermal gradient and complex mechanical stresses. We investigate the ablation characteristics of a graphite, a needle-punched C/C composite, and a 3-directional C/C composite currently under development and analyze their relevance for use as TPS materials by using a 0.4 MW supersonic plasma wind tunnel facility.
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