| タイトル | Thermal design of the IUE hydrazine auxiliary propulsion system |
| 著者（英） | Kelly, W. H.; Skladany, J. T. |
| 著者所属（英） | NASA Goddard Inst. for Space Studies|Fairchild Space and Electronics Co. |
| 発行日 | 1977-07-01 |
| 言語 | eng |
| 内容記述 | The International Ultraviolet Explorer is a large astronomical observatory scheduled to be placed in a three-axis stabilized synchronous orbit in the fourth quarter of 1977. The Hydrazine Auxiliary Propulsion System (HAPS) must perform a number of spacecraft maneuvers to achieve a successful mission. This paper describes the thermal design which accomplishes temperature control between 5 and 65 C for all orbital conditions by utilizing multilayer insulation and commandable component heaters. A primary design criteria was the minimization of spacecraft power by the selective use of the solar environment. The thermal design was carefully assessed and verified in both spacecraft thermal balance and subsystem solar simulation testing. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 77A46886
ASME PAPER 77-ENAS-45 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/436660 |
