| タイトル | Electron penetration of spacecraft thermal insulation |
| 著者（英） | Adams, B. F.; Inouye, G. T.; Powers, W. L. |
| 著者所属（英） | TRW Defense and Space Systems Group |
| 発行日 | 1981-10-01 |
| 言語 | eng |
| 内容記述 | The external thermal blanket with 13 mils of polyethylene which has the known range and stopping power as a function of electron energy is investiated. The most recent omnidirectional peak Jovian electron flux at 5 Jupiter radii is applied, the electron current penetrating the thermal blanket is calculated and allowed to impinge on a typical 20 mil polyethylene insulator surrounding a wire. The radiation dose rate to the insulator is then calculated and the electrical conductivity found. The results demonstrate that the increased electronic mobility is sufficient to keep the maximum induced electric field two orders of magnitude below the critical breakdown strength. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 82N14220 |
| 権利 | No Copyright |
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