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首页> 外文期刊>Journal of Spacecraft and Rockets >Radiative Heating Uncertainty for Hyperbolic Earth Entry, Part 3: Comparisons with Electric Arc Shock-Tube Measurements
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Radiative Heating Uncertainty for Hyperbolic Earth Entry, Part 3: Comparisons with Electric Arc Shock-Tube Measurements

机译：双曲线地球进入的辐射加热不确定度，第3部分：与电弧冲击管测量的比较

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The computational technique and uncertainty analysis presented in Part 1 (Johnston et al., "Assessment of Radiative Heating Uncertainty for Hyperbolic Earth Entry Part 1: Flight Simulation Modeling and Uncertainty," Journal of Spacecraft and Rockets, Vol. 50, No. 1,2013) for Mars-return radiative heating simulations are applied to Electric Arc Shock-Tube cases. These experimental cases contain wavelength-dependent intensity measurements in a wavelength range that covers 60% of the radiative intensity for the 11 km/s, 5 m radius flight case studied in Part 1. Comparisons between the predictions and Electric Arc Shock-Tube measurements are made for a range of experiments. The uncertainty analysis presented in Part 1 is applied to each prediction, and comparisons are made using the metrics denned in Part 2 (Johnston et al., "Assessment of Radiative Heating Uncertainty for Hyperbolic Earth Entry Part 2: Comparison with 1960s-Era Shock-Tube Measurements," Journal of Spacecraft and Rockets, Vol. 50, No. 1,2013). The agreement between predictions and measurements is excellent for velocities greater than 10.5 km/s. Both the wavelength-dependent and wavelength-integrated intensities agree within 30% for nearly all cases considered. This agreement provides confidence in the computational technique and uncertainty analysis presented in Part 1, and provides further evidence that this approach is adequate for Mars-return simulations. Existing experimental data that include the influence of massive ablation on radiative heating are reviewed. It is concluded that existing data are not sufficient for the present uncertainty analysis. Experiments to capture the influence of massive ablation on radiation are suggested as future work, along with further studies of the radiative precursor and improvements in the radiation properties of ablation products.
机译：第1部分中介绍了计算技术和不确定性分析（Johnston等人，“双曲线地球进入的辐射加热不确定性的评估，第1部分：飞行仿真建模和不确定性”，《航天器和火箭杂志》，第50卷，第1期， 2013）将火星返回辐射加热模拟应用于电弧冲击管壳体。这些实验案例包含在第1部分中研究的11 km / s，5 m半径飞行案例的覆盖60％辐射强度的波长范围内与波长相关的强度测量，这些预测与电弧冲击管测量之间的比较如下：进行了一系列实验。第1部分中介绍的不确定性分析将应用于每个预测，并使用第2部分中定义的度量标准进行比较（Johnston等人，“双曲线地球进入的辐射热不确定度的评估，第2部分：与1960s-时代冲击的比较-管测量”，《航天器和火箭杂志》，第50卷，第1号，2013年）。对于大于10.5 km / s的速度，预测和测量之间的一致性非常好。在几乎所有考虑的情况下，与波长有关的强度和与波长有关的强度都在30％之内。该协议为第1部分中介绍的计算技术和不确定性分析提供了信心，并提供了进一步的证据，表明该方法足以用于火星返回模拟。审查了现有的实验数据，包括大规模烧蚀对辐射加热的影响。结论是现有数据不足以进行当前的不确定性分析。建议捕获大规模烧蚀对辐射的影响的实验作为未来的工作，以及对辐射前体的进一步研究以及对烧蚀产品辐射性能的改进。

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