Quantifying the thermal response of a heat shield is a key step in the design of a spacecraft to ensure its survivability during atmospheric entry. Recession and swelling of the thermal protection material have a drastic effect on both the heat transfer within the vehicle and aerothermodynamic transients. Postflight analysis of reentry can be achieved after recovery on Earth, but it is more difficult for entries on other bodies of the solar system. A dedicated instrumentation is necessary to understand the evolution of the thermal protection material thickness during flight. This paper investigates the current limitations of the available measurement techniques. A low-mass passive solution is proposed to measure with high accuracy the phenomena of recession and swelling. The QubeSat for Aerothermodynamic Research and Measurements on Ablation (QARMAN) CubeSat mission provides a flight opportunity to develop a dedicated payload to quantify the recession and swelling of an ablative heat shield made of P50 cork from Amorim^TM. In addition, this payload allows us to study the radiation of a reentry plasma in the presence of ablation products through the same optical path. The performance of the measurement technique and the integration of the instrument are discussed for the QARMAN platform, demonstrating its applicability to a space mission.

量化隔热罩的热响应是航天器设计的关键步骤，以确保其在进入大气层期间的生存能力。热保护材料的凹陷和膨胀对车辆内的热传递和空气热力学瞬变都有显着影响。在地球上恢复后可以实现再入的飞行后分析，但进入太阳系其他天体则更加困难。需要专用仪器来了解飞行过程中热保护材料厚度的变化。本文研究了可用测量技术的当前局限性。提出了一种低质量无源解决方案，以高精度测量衰退和膨胀现象。^TM。此外，该有效载荷使我们能够通过相同的光路研究在消融产物存在的情况下再入等离子体的辐射。针对 QARMAN 平台讨论了测量技术的性能和仪器的集成，展示了其在太空任务中的适用性。