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Characteristics of a plasma wind tunnel for the development of thermal protection materials

Part of: APISAT 2015

Published online by Cambridge University Press:  30 May 2017

B. G. Hong ,
B. R. Kang ,
J. C. Choi  and
P. Y. Oh
B. G. Hong*
Affiliation:
Department of Quantum System Engineering, Chonbuk National University, Jeollabuk-do, Korea
B. R. Kang
Affiliation:
Department of Applied Plasma Engineering, Chonbuk National University, Jeollabuk-do, Korea
J. C. Choi
Affiliation:
High-Enthalpy Plasma Research Center, Chonbuk National University, Jeollabuk-do, Korea
P. Y. Oh
Affiliation:
High-Enthalpy Plasma Research Center, Chonbuk National University, Jeollabuk-do, Korea
*
bghong@jbnu.ac.kr
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Abstract

Thermal plasma wind tunnels with power of 0.4 MW and 2.4 MW have been constructed at Chonbuk National University (CBNU) in Korea. This facility is capable of producing a heat flux greater than 10 MW/m2, a level that is relevant for testing thermal protection materials that are used for re-entry vehicles in space transportation. A segmented arc plasma torch was adopted as a plasma source; this was designed to have high thermal efficiency and long life, and to produce a supersonic plasma flow with enthalpy greater than 10 MJ/kg. We investigated the characteristics of the supersonic plasma flow using intrusive and non-intrusive diagnostic systems. Ablation characteristics of potential thermal protection materials such as carbon/carbon composites and graphite were investigated with the plasma wind tunnel. Cracks and pores in the materials accelerated the erosion. For carbon/carbon composites, the pores grew and the cracks which occurred at the interfaces between the carbon fibres and the matrix propagated, while for the graphite, the erosion started at the pores and peeled off the surface.

Keywords

Segmented arc plasma torchplasma wind tunnelablation testthermal protection materialcarbon/carbon composite
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1240 , June 2017 , pp. 821 - 834
Copyright
Copyright © Royal Aeronautical Society 2017 

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Footnotes

This is an adaptation of a paper first presented at the 2015 Asia-Pacific International Symposium on Aerospace Technology in Cairns, Australia

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