Ref.: MceMac04-001

STUDY OF THE BEHAVIOR OF ULTRA-HIGH TEMPERATURE CERAMIC COMPOSITES SUBJECTED TO A HYPERSONIC PLASMA TORCH

Apresentador: Cristian Cley Parteniani Rita

Autores (Instituição): Rita, C.C.(Faculdade de Tecnologia de Pindamonhangaba); Miranda, F.S.(Instituto Tecnológico de Aeronáutica); Essiptchouk, A.M.(Universidade Estadual Paulista); Petraconi, G.(INSTITUTO TECNOLÓGICO DE AERONÁUTICA);

Resumo:
Thermal protection systems, crucial for spacecraft enduring intense thermal conditions during atmospheric reentry, rely on specialized coatings. This study aims to simulate and analyze the ablative characteristics of Ultra High Temperature Ceramic composite (UHTC) within the LPP-ITA plasma tunnel, employing a hypersonic plasma torch as an ablative tool. UHTC variants, incorporating Zirconium Diboride (ZrB2) with different Silicon Carbide (SiC) concentrations (10%, 20%, and 30% by volume), exhibited diverse behaviors under hypersonic thermal exposure. Notably, the 20% SiC composition displayed superior resistance to thermal erosion in simulated conditions. Ablation trials were conducted in the Plasma Tunnel at LPP-ITA, utilizing a non-transferred arc DC plasma torch in a low-pressure air reactive setting (P = 75 Pa), with the plasma operating at 35 kW power and coupled with a hypersonic Mach 5 nozzle, generating a thermal flux of 2.2 MW/m2 and an average enthalpy of 18.61 MJ/kg. Microstructural and chemical analyses of SiC-doped UHTC composites were conducted pre- and post-SEM/EDS ablation to assess microstructural behavior and chemical composition. This investigation confirmed the feasibility of replicating steady-state conditions essential for spacecraft thermal protection materials development. Oxidation assessments revealed distinct oxidation pathways and the formation of protective oxide layers based on SiC ratios, underscoring the significance of optimizing ZrB2-SiC proportions for effective thermal protection.