Abstract
New thermal protection systems (TPSs) with impact resistance, ability of refurbishment and enhanced weather resistance are required for future hypersonic airplanes (HSAs). Compared with reusable launch vehicles, heat flux during flights of HSAs is lower but total heating time of HSAs is much longer. Moreover, TPSs of HSAs will be exposed to elevated temperatures at shorter intervals. The purposes of this study are placed on the designing of multi-layered stand-off TPS (MLS-TPS) using SiC-fiber/SiC matrix composites (SiC/SiCs) and porous Titanium (PoTi) sandwich panels, and on discussing applicability of the TPS to a Mach 5 HSA which is under consideration at JAXA. The MLS-TPS consists of a surface panel made of a SiC/SiC separated from fuselage using SiC/SiC posts (Stand-off structure). PoTi sandwich panels are inserted between the surface panel and fuselage to reduce the heat input to fuselage (Multi-layered insulation structure). Thermal insulation performances at the Mach 5 cruise condition were estimated using three-dimensional finite element analysis (FEA) up to the heat flux of 30kW/m<sup>2</sup>. The FEA results indicated that fuselage temperatures at the heat flux of up to 30kW/m<sup>2</sup> can be lower than allowable upper limit temperature of aluminium alloy without using active cooling. Furthermore, it was shown that the low thermal expansion of SiC/SiC surface panel was highly effective for supressing the thermal deformation of MLS-TPS.
| Original language | English |
|---|---|
| Title of host publication | Proceedings of the International Astronautical Congress, IAC |
| Publisher | International Astronautical Federation, IAF |
| Pages | 5725-5731 |
| Number of pages | 7 |
| Volume | 8 |
| ISBN (Print) | 9781634399869 |
| Publication status | Published - 2014 |
| Event | 65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014 - Toronto, Canada Duration: 2014 Sep 29 → 2014 Oct 3 |
Other
| Other | 65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014 |
|---|---|
| Country | Canada |
| City | Toronto |
| Period | 14/9/29 → 14/10/3 |
Fingerprint
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering
- Astronomy and Astrophysics
Cite this
Design study on multi-layered stand-off thermal protection system using porous titanium panels. / Hayashi, Ryosuke; Aoki, Takuya; Ogasawara, Toshio; Wakita, Yoshinori; Morino, Yoshiki.
Proceedings of the International Astronautical Congress, IAC. Vol. 8 International Astronautical Federation, IAF, 2014. p. 5725-5731.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Design study on multi-layered stand-off thermal protection system using porous titanium panels
AU - Hayashi, Ryosuke
AU - Aoki, Takuya
AU - Ogasawara, Toshio
AU - Wakita, Yoshinori
AU - Morino, Yoshiki
PY - 2014
Y1 - 2014
N2 - New thermal protection systems (TPSs) with impact resistance, ability of refurbishment and enhanced weather resistance are required for future hypersonic airplanes (HSAs). Compared with reusable launch vehicles, heat flux during flights of HSAs is lower but total heating time of HSAs is much longer. Moreover, TPSs of HSAs will be exposed to elevated temperatures at shorter intervals. The purposes of this study are placed on the designing of multi-layered stand-off TPS (MLS-TPS) using SiC-fiber/SiC matrix composites (SiC/SiCs) and porous Titanium (PoTi) sandwich panels, and on discussing applicability of the TPS to a Mach 5 HSA which is under consideration at JAXA. The MLS-TPS consists of a surface panel made of a SiC/SiC separated from fuselage using SiC/SiC posts (Stand-off structure). PoTi sandwich panels are inserted between the surface panel and fuselage to reduce the heat input to fuselage (Multi-layered insulation structure). Thermal insulation performances at the Mach 5 cruise condition were estimated using three-dimensional finite element analysis (FEA) up to the heat flux of 30kW/m2. The FEA results indicated that fuselage temperatures at the heat flux of up to 30kW/m2 can be lower than allowable upper limit temperature of aluminium alloy without using active cooling. Furthermore, it was shown that the low thermal expansion of SiC/SiC surface panel was highly effective for supressing the thermal deformation of MLS-TPS.
AB - New thermal protection systems (TPSs) with impact resistance, ability of refurbishment and enhanced weather resistance are required for future hypersonic airplanes (HSAs). Compared with reusable launch vehicles, heat flux during flights of HSAs is lower but total heating time of HSAs is much longer. Moreover, TPSs of HSAs will be exposed to elevated temperatures at shorter intervals. The purposes of this study are placed on the designing of multi-layered stand-off TPS (MLS-TPS) using SiC-fiber/SiC matrix composites (SiC/SiCs) and porous Titanium (PoTi) sandwich panels, and on discussing applicability of the TPS to a Mach 5 HSA which is under consideration at JAXA. The MLS-TPS consists of a surface panel made of a SiC/SiC separated from fuselage using SiC/SiC posts (Stand-off structure). PoTi sandwich panels are inserted between the surface panel and fuselage to reduce the heat input to fuselage (Multi-layered insulation structure). Thermal insulation performances at the Mach 5 cruise condition were estimated using three-dimensional finite element analysis (FEA) up to the heat flux of 30kW/m2. The FEA results indicated that fuselage temperatures at the heat flux of up to 30kW/m2 can be lower than allowable upper limit temperature of aluminium alloy without using active cooling. Furthermore, it was shown that the low thermal expansion of SiC/SiC surface panel was highly effective for supressing the thermal deformation of MLS-TPS.
UR - http://www.scopus.com/inward/record.url?scp=84937887252&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84937887252&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84937887252
SN - 9781634399869
VL - 8
SP - 5725
EP - 5731
BT - Proceedings of the International Astronautical Congress, IAC
PB - International Astronautical Federation, IAF
ER -