| タイトル | Heat sink structural design concepts for a hypersonic research airplane |
| 著者（英） | Taylor, A. H.; Jackson, L. R. |
| 著者所属（英） | NASA Langley Research Center|Vought Corp. |
| 発行日 | 1977-01-01 |
| 言語 | eng |
| 内容記述 | Hypersonic research aircraft design requires careful consideration of thermal stresses. This paper relates some of the problems in a heat sink structural design that can be avoided by appropriate selection of design options including material selection, design concepts, and load paths. Data on several thermal loading conditions are presented on various conventional designs including bulkheads, longerons, fittings, and frames. Results indicate that conventional designs are inadequate and that acceptable designs are possible by incorporating innovative design practices. These include nonintegral pressure compartments, ball-jointed links to distribute applied loads without restraining the thermal expansion, and material selections based on thermal compatibility. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 77A25744
AIAA PAPER 77-392 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/438836 |
|
