| タイトル | Development of Rene 41 honeycomb structure as an integral cryogenic tankage/fuselage concept for future space transportation systems |
| 著者（英） | Swegle, A. R.; Shideler, J. L.; Fields, R. A. |
| 著者所属（英） | NASA Langley Research Center|Boeing Aerospace Co.|NASA Flight Research Center |
| 発行日 | 1982-01-01 |
| 言語 | eng |
| 内容記述 | The status of the structural development of an integral cryogenic-tankage/hot-fuselage concept for future space transportation systems is reviewed. The concept comprises a honeycomb sandwich structure that serves the combined functions of containing the cryogenic fuel, supporting the vehicle loads, and protecting the spacecraft from entry heating. The inner face sheet is exposed to cryogenic temperature of -423 F during boost; the outer face sheet, which is slotted to reduce thermal stress, is exposed to a maximum temperature of 1400 F during a high-altitude gliding entry. Attention is given to the development of a fabrication process for a Rene 41 honeycomb sandwich panel with a core density of less than 1 percent that is consistent with desirable heat treatment processes for high strength. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 82A30084
AIAA PAPER 82-0653 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/411039 |
