Chapter 3. Application of TyrannoTm Fiber \ Si-Ti-C-O Matrix Composite to the Thermal Protection System of the Japanese Hope-X Space Vehicle

  1. Mrityunjay Singh and
  2. Todd Jessen
  1. Toshio Ogasawara and
  2. Takashi Ishikawa

Published Online: 26 MAR 2008

DOI: 10.1002/9780470294680.ch3

25th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: A: Ceramic Engineering and Science Proceedings, Volume 22, Issue 3

25th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: A: Ceramic Engineering and Science Proceedings, Volume 22, Issue 3

How to Cite

Ogasawara, T. and Ishikawa, T. (2001) Application of TyrannoTm Fiber \ Si-Ti-C-O Matrix Composite to the Thermal Protection System of the Japanese Hope-X Space Vehicle, in 25th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: A: Ceramic Engineering and Science Proceedings, Volume 22, Issue 3 (eds M. Singh and T. Jessen), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470294680.ch3

Author Information

  1. National Aerospace Laboratory of Japan (NAL), Mitaka, Tokyo, 181–0015, Japan

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 2001

ISBN Information

Print ISBN: 9780470375730

Online ISBN: 9780470294680

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Keywords:

  • amorphous;
  • pyrolysis;
  • atmosphere;
  • aerodynamic;
  • carbon

Summary

National Aerospace Laboratory of Japan (NAL) has conducted a joint program to develop a continuous fiber reinforced ceramic matrix composite (CMC) for aerospace applications with Ube Industries Ltd., Shikibo Ltd., and Kawasaki Heavy Industries Ltd. The composite is referred to as NUSK-CMC from the initials of the collaborators, which exhibits excellent tensile strength and creep strength up to 1200°C in air. NUSK-CMC consists of surface modified TyrannoTM Lox-M (Si-Ti-C-O) fibers, amorphous Si-Ti-C-O ceramic matrix derived from poly-titano-carbosilane (PTCS), and SiO2-Na2O glass sealant. Using the Japanese HOPE-X flight demonstrator, a flight verification test of NUSK-CMC as thermal protection system (TPS) material has been planned. The paper presents experimental results of oxidation behavior under high enthalpy convective environment, and preliminary plan of the flight verification for NUSK-CMC TPS panels.