| タイトル | The drag coefficient of cylindrical spacecraft in orbit at altitudes greater than 150 km |
| 本文（外部サイト） | http://hdl.handle.net/2060/19830021023 |
| 著者（英） | Herrero, F. A. |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 1983-05-01 |
| 言語 | eng |
| 内容記述 | The spacecraft of the Geopotential Research Mission (GRM) are cylindrical in form and designed to fly with their longitudinal axes parallel to their direction of flight. The ratio of length to diameter of these spacecraft is roughly equal to 5.0. Other spacecraft previously flown had corresponding ratios roughly equal to 1.0, and therefore the drag produced by impacts on the lateral surfaces of those spacecraft was not as large as it will be on the GRM spacecraft. Since the drag coefficient is essentially the drag force divided by the frontal area in flight, lateral impacts, when taken into account make the GRM drag coefficient significantly larger than the coefficients used before for shorter spacecraft. A simple formula is derived for the drag coefficient of a cylindrical body flying with its long axis along the direction of flight, and it is used to estimate the drag for the GRM. The formula shows that the drag due to lateral surface impacts depends on the ratio of length-to-diameter and on a coefficient C sub LS (lateral surface impact coefficient) which can be determined from previous cylindrical spacecraft flown with the same attitude, or can be obtained from laboratory measurements of momentum accommodation coefficients. |
| NASA分類 | LAUNCH VEHICLES AND SPACE VEHICLES |
| レポートNO | 83N29294
NAS 1.15:85043
NASA-TM-85043 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/162126 |
