The determination of the ablation rate for thermal protection systems on atmospheric entry is a difficult task, but can have significant implications in terms of safety and heat shield design. Ablation sensors of various kinds can be used to measure ablation directly, but in the event of a failure of these sensors, the use of thermocouples imbedded in the heat shield for determining the ablation rate is somewhat more difficult. A numerical model was developed as part of this research to determine ablation rate as a function of temperature using measurements from the Mars Science Laboratory Entry, Descent, and Landing Instrumentation Mission, which took place in 2012. The numerical model accounts for ablation as well as temperature-dependent thermal conductivity and volumetric heat capacity. A temperature-dependent ablation rate is calculated simultaneously with the heat flux for each time step of data acquisition. Regularization is provided for the heat flux calculation through the use of cubic splines. A significant reduction in the residual values between the mathematical model and the measured temperatures was obtained when accounting for ablation and refined temperature-dependent thermal properties. In some cases, the standard deviation of the residuals was reduced by 70% or more, indicating a greatly improved conformance of the mathematical model to the measured temperatures when accounting for ablation.

确定进入大气层时的热保护系统的消融率是一项艰巨的任务，但在安全性和隔热屏设计方面可能会产生重大影响。可以使用各种消融传感器直接测量消融，但是在这些传感器出现故障的情况下，使用埋在隔热罩中的热电偶来确定消融率会更加困难。作为该研究的一部分，开发了一个数值模型，以使用2012年进行的火星科学实验室入口，下降和着陆仪器任务的测量值确定作为温度函数的切削速率。温度相关的热导率和体积热容。对于数据采集的每个时间步骤，将同时计算与温度相关的烧蚀速率和热通量。通过使用三次样条为热通量计算提供了正则化。考虑到烧蚀和精确的温度相关的热性能，数学模型和测得的温度之间的残值大大降低。在某些情况下，残余物的标准偏差降低了70％或更多，这表明在考虑消融时，数学模型与测量温度的一致性大大提高。考虑到烧蚀和精确的温度相关的热性能，数学模型和测得的温度之间的残值大大降低。在某些情况下，残余物的标准偏差降低了70％或更多，这表明在考虑消融时，数学模型与测量温度的一致性大大提高。考虑到烧蚀和精确的温度相关的热性能，数学模型和测得的温度之间的残值显着降低。在某些情况下，残余物的标准偏差降低了70％或更多，这表明在考虑消融时，数学模型与测量温度的一致性大大提高。