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Methodology for Flight Relevant Arc-Jet Testing of Flexible Thermal Protection Systems

机译：柔性热保护系统与飞行相关的电弧喷射测试方法

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摘要

A methodology to correlate flight aeroheating environments to the arc-jet environment is presented. For a desired hot-wall flight heating rate, the methodology provides the arc-jet bulk enthalpy for the corresponding cold-wall heating rate. A series of analyses were conducted to examine the effects of the test sample model holder geometry to the overall performance of the test sample. The analyses were compared with arc-jet test samples and challenges and issues are presented. The transient flight environment was calculated for the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) Earth Atmospheric Reentry Test (HEART) vehicle, which is a planned demonstration vehicle using a large inflatable, flexible thermal protection system to reenter the Earth's atmosphere from the International Space Station. A series of correlations were developed to define the relevant arc-jet test environment to properly approximate the HEART flight environment. The computed arc-jet environments were compared with the measured arc-jet values to define the uncertainty of the correlated environment. The results show that for a given flight surface heat flux and a fully-catalytic TPS, the flight relevant arc-jet heat flux increases with the arc-jet bulk enthalpy while for a non-catalytic TPS the arc-jet heat flux decreases with the bulk enthalpy.
机译：提出了一种将飞行空气加热环境与电弧喷射环境相关联的方法。对于所需的热壁飞行加热速率，该方法为相应的冷壁加热速率提供了电弧喷射整体焓。进行了一系列分析，以检查测试样品模型支架几何形状对测试样品整体性能的影响。将分析结果与电弧喷射测试样本进行了比较，并提出了挑战和问题。计算了超音速充气气动减速器（HIAD）地球大气折返测试（HEART）车辆的瞬态飞行环境，这是一种计划中的示范车辆，使用大型充气，灵活的热保护系统从国际空间站重新进入地球大气层。开发了一系列相关性，以定义相关的电弧喷射测试环境，以适当地近似HEART飞行环境。将计算的电弧喷射环境与测量的电弧喷射值进行比较，以定义相关环境的不确定性。结果表明，对于给定的飞行表面热通量和完全催化的TPS，与飞行相关的电弧喷射热通量随电弧喷射体的焓增加而增加，而对于非催化的TPS，电弧喷射热通量随电弧体的总焓而减小。整体焓。

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