Re-entry Environment Test and Thermal Characteristics Analysis of Needle Punching C/SiC Composites

The application of thermal protection systems(TPS) is essential to ensure the safety and reusability of reusable space vehicles, which re-enter the atmosphere at hypersonic speeds after completing missions. This study focuses on evaluating the thermal resistance of NP-C/SiC(Needle Punching-Carbon/Silicon Carbide) ceramic composites to assess their applicability as TPS for reusable space vehicles. Re-entry environment tests were conducted using a 0.4 MW Arc-heated Wind Tunnel(AWT), where the mass loss, high-temperature resistance, and thermal behavior of the specimens were comprehensively analyzed. The results showed a mass loss of 1-1.5% and a maximum surface temperature of 1894 degrees C. Additionally, a detailed porosity analysis was performed using Micro-CT to evaluate the internal conditions of the specimens before and after testing, as porosity is a critical factor influencing the thermal protection performance and reusability of TPS. The porosity increased by up to 8.67% near the surface of the specimens, indicating the impact of the test conditions. The data obtained from this study provide essential insights into the thermal characteristics of ceramic composite materials, contributing to the development of effective thermal protection systems for reusable space vehicles.