Art

J-GLOBAL ID：201802239608226617   Reference number：18A2046048

Thermal Response Analysis of Porous Carbon-based Non-Ablative Heatshield in an Arcjet Flow Condition

アークジェット流動条件に対する多孔質炭素系非アブレーション熱遮蔽の熱応答解析

Author (8)： Horiuchi Takumi (Department of Aerospace Engineering, Nagoya University) ,  Sakai Takeharu (Department of Mechanical and Aerospace Engineering, Tottori University) ,  Fukui Hiroki (Department of Aerospace Engineering, Nagoya University) ,  Shimamoto Daisuke (Structural Material Research Institute, National Institute of Advanced Industrial Science and Technology) ,  Hotta Yuji (Structural Material Research Institute, National Institute of Advanced Industrial Science and Technology) ,  Ishida Yuichi (Japan Aerospace Exploration Agency) ,  Suzuki Toshiyuki (Japan Aerospace Exploration Agency) ,  Fujita Kazuhisa (Japan Aerospace Exploration Agency)
Material： Transactions of the Japan Society for Aeronautical and Space Sciences (Web)  (Trans Jpn Soc Aeronaut Space Sci (Web))
Volume： 61  Issue： 5  Page： 211-218(J-STAGE)  Publication year： 2018 
JST Material Number： U0630A  ISSN： 2189-4205  Document type： Article
Article type： 原著論文  Country of issue： Japan (JPN)  Language： ENGLISH (EN)

Thesaurus term： X-ray computed tomography ,  tomographic image ,  *arc jet ,  *thermal insulation ,  carbon ,  porous medium ,  *thermal response ,  response analysis ,  radiative heat transfer ,  thermal conductivity ,  model ,  simulation ,  arc heating ,  modeling ,  coefficient ,  optical constant ,  ray tracing ,  surface temperature ,  temperature ,  3D model
Semi thesaurus term： CT image ,  arc heated wind tunnel ,  ray tracing ,  extinction coefficient ,  Deep Temperature ,  Numerical Simulation ,  numerical modeling ,  porous material ,  porous carbon ,  *thermal shield ,  physical modeling

Author keywords (4)： Radiative Transfer in Porous Media ,  Numerical Simulation ,  Arcjet Wind Tunnel ,  Thermal Protection System

JST classification (2)： Convective and radiative heat transfer  (PA02030K) ,  Flying object design and structure  (QK04010H)

Reference (17)：

• 1) Tran, H., Johnson, C., Rasky, D., Hui, F., Chen, Y. K., and Hsu, M.: Phenolic Impregnated Carbon Ablators (PICA) for Discovery Class Missions, NASA TM 110440, 1996.
• 2) Wright, M. J., Beck, R. A. S., Edquist, K. T., Driver, D., Sepka, S. A., Slimko, E. M., Willcockson, W. H., DeCaro, A., and Hwang, H. H.: Sizing and Margins Assessment of the Mars Science Laboratory Aeroshell Thermal Protection System, AIAA Paper 2009-4231, 2009.
• 3) Suzuki, T., Aoki, T., Ogasawara, T., and Fujita, K.: Nonablative Lightweight Thermal Protection System for Mars Aeroflyby Sample Collection Mission, Acta Astronautica, 136 (2017), pp. 407-420.
• 4) Fujita, K., Suzuki, T., Ozawa, T., Sakai, T., Dantsuka, Y., Ishida, Y., and Watanabe, Y.: Ablation Sensor Unit for Flight Demonstration on HTV Small Recovery Capsule, AIAA Paper 2017-0899, 2017.
• 5) Nouri, N., Panerai, F., Tagavi, K. A., Mansour, N. N., and Martin, A.: Evaluation of the Anisotropic Radiative Conductivity of a Low-density Carbon Fiber Material from Realistic Microscale Imaging, Int. J. Heat Mass Transfer, 95 (2016), pp. 535-539.

Terms in the title (7)： アークジェット ,  流動 ,  多孔質炭素 ,  アブレーション ,  熱遮蔽 ,  熱応答 ,  解析