| タイトル | Thermal performance of an integrated thermal protection system for long-term storage of cryogenic propellants in space |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770017239 |
| 著者（英） | Boyle, R. J.; Dewitt, R. L. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1977-05-01 |
| 言語 | eng |
| 内容記述 | It was demonstrated that cryogenic propellants can be stored unvented in space long enough to accomplish a Saturn orbiter mission after 1,200-day coast. The thermal design of a hydrogen-fluorine rocket stage was carried out, and the hydrogen tank, its support structure, and thermal protection system were tested in a vacuum chamber. Heat transfer rates of approximately 23 W were measured in tests to simulate the near-Earth portion of the mission. Tests to simulate the majority of the time the vehicle would be in deep space and sun-oriented resulted in a heat transfer rate of 0.11 W. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 77N24183
E-8881
NASA-TN-D-8320 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/182272 |
