Abstract
In order to develop efficient space transportation systems, composite materials application to cryogenic propellant tanks would be one of the most important technological challenges particularly when aiming to establish Single Stage to Orbit (SSTO) space transportation vehicles which have been dreamed of for long years. However, as recognized through the development efforts and failures such as the X-33 experimental vehicle by the United States, many technological barriers still remain mainly due to the cryogenic brittleness of resin systems and severe thermal environments on the way to establish high reliability space structures. In this study, previous and current research results in this field are reviewed particularly focused on material and structural characteristics at cryogenic temperature. Then several kinds of possible structural options are proposed. Options discussed include stringer-frame stiffened CFRP panel with internal or external foam insulation and three kinds of sandwich structures. Preferable structural configurations are searched based on structural design trade-offs. Finally necessary technological tasks to be conducted in the future are identified.
| Original language | English |
|---|---|
| Title of host publication | Proceedings of 2010 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2010 |
| Publisher | Northwestern Polytechnical University |
| Pages | 844-847 |
| Number of pages | 4 |
| ISBN (Print) | 9787561228999 |
| Publication status | Published - 2010 |
| Event | 2010 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2010 - Xi'an Duration: 2010 Sep 13 → 2010 Sep 15 |
Other
| Other | 2010 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2010 |
|---|---|
| City | Xi'an |
| Period | 10/9/13 → 10/9/15 |
Fingerprint
Keywords
- Composite materials
- Cryogenic tank
- Space transportation
ASJC Scopus subject areas
- Aerospace Engineering
Cite this
Trade-off study on structural configuration of cryogenic composite tank for reusable launch vehicles. / Morino, Yoshiki.
Proceedings of 2010 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2010. Northwestern Polytechnical University, 2010. p. 844-847.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Trade-off study on structural configuration of cryogenic composite tank for reusable launch vehicles
AU - Morino, Yoshiki
PY - 2010
Y1 - 2010
N2 - In order to develop efficient space transportation systems, composite materials application to cryogenic propellant tanks would be one of the most important technological challenges particularly when aiming to establish Single Stage to Orbit (SSTO) space transportation vehicles which have been dreamed of for long years. However, as recognized through the development efforts and failures such as the X-33 experimental vehicle by the United States, many technological barriers still remain mainly due to the cryogenic brittleness of resin systems and severe thermal environments on the way to establish high reliability space structures. In this study, previous and current research results in this field are reviewed particularly focused on material and structural characteristics at cryogenic temperature. Then several kinds of possible structural options are proposed. Options discussed include stringer-frame stiffened CFRP panel with internal or external foam insulation and three kinds of sandwich structures. Preferable structural configurations are searched based on structural design trade-offs. Finally necessary technological tasks to be conducted in the future are identified.
AB - In order to develop efficient space transportation systems, composite materials application to cryogenic propellant tanks would be one of the most important technological challenges particularly when aiming to establish Single Stage to Orbit (SSTO) space transportation vehicles which have been dreamed of for long years. However, as recognized through the development efforts and failures such as the X-33 experimental vehicle by the United States, many technological barriers still remain mainly due to the cryogenic brittleness of resin systems and severe thermal environments on the way to establish high reliability space structures. In this study, previous and current research results in this field are reviewed particularly focused on material and structural characteristics at cryogenic temperature. Then several kinds of possible structural options are proposed. Options discussed include stringer-frame stiffened CFRP panel with internal or external foam insulation and three kinds of sandwich structures. Preferable structural configurations are searched based on structural design trade-offs. Finally necessary technological tasks to be conducted in the future are identified.
KW - Composite materials
KW - Cryogenic tank
KW - Space transportation
UR - http://www.scopus.com/inward/record.url?scp=84914124660&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84914124660&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84914124660
SN - 9787561228999
SP - 844
EP - 847
BT - Proceedings of 2010 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2010
PB - Northwestern Polytechnical University
ER -