Development Status and Prospect of TPS for RLV
- Paper number
IAC-08.C2.6.9
- Author
Mr. Ting Liu, Beijing Institute of the 7th Academy of China Aerospace Science and Technology Corporation, China
- Year
2008
- Abstract
The thermal protection system (TPS) protects the reusable launch vehicle (RLV) from the severe heating encountered during hypersonic flight through the atmosphere. The instantaneous temperature can even reach to 2100K during the reentry, and the peak heat flux is very high. TPS design is one of the key technologies of RLV. It must be solved as early as possible on the precondition of appropriate configuration and good aerodynamic performance. A lot of research has been doing, especially in America and Europe. The processes of that provide plenty of experience and lessons. The TPS for RLV is introduced include of Space Shuttle, Hermes, HOPPER, HOPE-X, and X-series. Some of them have been changed or redesigned. The technologies under development, such as flexible external insulation (F.E.I), metallic TPS, and C/SiC, are intended for use. The RLV is becoming smaller, and requires sharp leading edges for the wings. So, the Ultra High Temperature Ceramic (UHTC), e.g. Zirconium, Hafnium or Titanium Diborides, are candidate materials for the sharp edges of RLV. The development of these parts is given. Other analysis on the tendency of TPS in recent years and the orientation of TPS research, which a major challenge for China, is also presented based on the facts of technologies.
- Abstract document
- Manuscript document
IAC-08.C2.6.9.pdf (🔒 authorized access only).
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