| タイトル | Starprobe thermal shield evolution |
| 著者（英） | Royere, C.; Miyake, R. N.; Rolfo, A.; Millard, J. M.; Dirling, R. B. |
| 著者所属（英） | Jet Propulsion Lab., California Inst. of Tech. |
| 発行日 | 1983-12-01 |
| 言語 | eng |
| 内容記述 | The evolution of the Starprobe thermal shield from mission requirements through a preliminary design concept is traced. The diverse environments the spacecraft must survive (ranging from Jovian to near-Sun coronal) established requirements resulting in carbon-carbon material being selected for shield construction for a three axis stabilized spacecraft. Thoriated tungsten is a backup material for spin-stabilized concepts. The preliminary shield design, while being essentially immune to radiation degradation and significant meteoroid threats, provides a thermal environment that insures proper operation of the payload (below 55? C) at perihelion (4 solar radii from the Sun's center) and prevents total mass loss rates from exceeding 2.5 mg/sec, insuring proper operation of fields and particles instruments. It also meets these requirements at perihelion when off-nadir pointing 10 deg, thus insuring desired imaging activity. |
| NASA分類 | COMPOSITE MATERIALS |
| レポートNO | 84N19462 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/401437 |
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