| タイトル | Legacy of the Space Shuttle from an Aerodynamic and Aerothermodynamic Perspective |
| 本文（外部サイト） | http://hdl.handle.net/2060/20110015743 |
| 著者（英） | Martin, Fred W. |
| 著者所属（英） | NASA Johnson Space Center |
| 発行日 | 2011-08-27 |
| 言語 | eng |
| 内容記述 | The development of the Space Shuttle Orbiter thermal protection system heating environment is described from a design stand point that began in the early 1970s. The desire for a light weight, reusable heat shield required the development of new technology, relative to previous manned spacecraft, and a systems approach to the design of the vehicle, entry guidance, and thermal protection system. Several unanticipated issues had to be resolved in both the entry and ascent phases of flight, which are discussed at a high level. During the life of the Program, significant improvements in computing power and numerical methods have been applied to Space Shuttle aerodynamic and aerothermodynamic issues, with the Shuttle Program often being the motivation, and or sponsor of the analysis development. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | JSC-CN-24648 |
| 権利 | No Copyright |
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