Carbon-phenolic ablative materials for re-entry space vehicles: plasma wind tunnel test and finite element modeling
Carbon-phenolic ablative materials for re-entry space vehicles: plasma wind tunnel test and finite element modeling
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DOI：
10.1016/j.matdes.2015.11.066
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发表时间：
2016-01-15
影响因子：
8.4
通讯作者：
Pulci, G.
中科院分区：
文献类型：
--
作者：
Paglia, L.;Tirillo, J.;Pulci, G.
一种密度为0.5 g/cm（3）的轻质碳-酚醛烧蚀材料，设计用作再入空间飞行器的热防护系统，是通过用酚醛树脂渗透碳毡制造的。这种烧蚀材料的样品在等离子体风洞（PWT）设施中进行了测试，模拟与轨道再入一致的侵蚀和热通量条件。PWT试验期间监测供试品的表面温度。对测试样品进行了显微结构和显微断层分析，以通过测量烧蚀量和热解深度来研究高热通量暴露对复合材料的影响。此外，为了重建PWT试验，还建立了有限元模型。在表面绝缘能力和表面凹陷方面取得了非常令人鼓舞的结果。通过建立复杂的有限元模型，对烧蚀材料的热解烧蚀过程进行了数值模拟，模拟结果与实验结果吻合较好。(c)2015爱思唯尔有限公司版权所有。
A lightweight carbon-phenolic ablator, with a density of 0.5 g/cm(3), designed to be used as a thermal protection system for a re-entry space vehicle, was manufactured by infiltration of a carbon felt with a phenolic resin. A sample of this ablative material was tested in a Plasma Wind Tunnel (PWT) facility, simulating erosion and heat flux conditions consistent with an orbital reentry. The surface temperature of the test article was monitored during the PWT test. Microstructural and microtomographic analyses were carried out on the tested sample to investigate the effect of the high heat flux exposure on the composite material, by measuring the amount of ablation and the depth of pyrolyzation. Moreover a finite element model was implemented in order to rebuild the PWT test. Very encouraging results were obtained in terms of surface insulation capacity and surface recession. The pyrolysis and erosion of the ablator was simulated by implementing a complex finite element model, with results in very good agreement with experimental evidences. (c) 2015 Elsevier Ltd. All rights reserved.