Carbon-phenolic ablative materials for re-entry space vehicles: plasma wind tunnel test and finite element modeling

被引：52

作者：

Paglia, L. ^{[1
]}

Tirillo, J. ^{[1
]}

Marra, F. ^{[1
]}

Bartuli, C. ^{[1
]}

Simone, A. ^{[2
]}

Valente, T. ^{[1
]}

Pulci, G. ^{[1
]}

机构：

[1] Univ Roma La Sapienza, INSTM Reference Lab Engn Surface Treatments, Dept Chem Engn Mat Environm, I-00184 Rome, Italy

[2] Thales Alenia Space Italia, I-10146 Turin, Italy

来源：

MATERIALS & DESIGN | 2016年 / 90卷

关键词：

Lightweight ablative materials; Plasma Wind Tunnel (PWT) test; Ablation; Pyrolysis; FE modeling; SIMULATIONS; COMPOSITES; ENTRY;

D O I：

10.1016/j.matdes.2015.11.066

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

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.

引用

页码：1170 / 1180

页数：11

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