Vinh Tung LE, Abhendra K SINGH
DOI Number: N/A
Conference number: HiSST-2024-317
In this study, an integrated thermal protection system (TPS) based on alumina-based oxide/oxide ceramic matrix composite is explored. The structure is based on corrugated core sandwich concept and is fabricated using prepregs that constitute NextelTM720 fiber and alumina matrix. Fabricated sandwich panels are tested for survivability, nature and extent of erosion, and overall thermal resilience by being subjected to inductively generated air plasma in near-vacuum environment that simulate high altitude hypersonic flight condition. In addition, one-sided thermal shock and hold tests are performed using a furnace at 1550°C to evaluate pure thermal effects on the structure. Both the high temperature tests are performed for durations up to 30 minutes. The structural integrity of the sandwich structure is evaluated at room temperature using bend test, with strain measurements taken by digital image correlation. The thermal and structural test results combined provide useful information regarding the utility of the adopted design as well as the success of the fabrication method. The study also exposes areas of vulnerability, with potential for improvement, in order to arrive at a robust oxide-based sandwich composite for use as thermal protection system in hypersonic vehicles.