| タイトル | Drive mechanism for the shuttle orbiter/external tank propellant disconnect |
| 著者（英） | Ulanovsky, J.; Wilders, R.; Thomas, E. |
| 著者所属（英） | Rockwell International Corp. |
| 発行日 | 1981-05-01 |
| 言語 | eng |
| 内容記述 | The space shuttle design required development of a large, 0.43 m nominal diameter separable disconnect for the liquid hydrogen and liquid oxygen propellant lines at the orbiter to external tank interface. The disconnect provides for shutoff of the propellant flow area by simultaneous action of two rotary flapper valves (orbiter and external tank) prior to disconnect separation. In the case of pneumatic system failure, the rotary flapper valves are closed automatically through mechanical interlocking linkage during disconnect separation. The mechanism must meet requirements while accommodating changes in bearing clearances and linkage geometry over a wide temperature range from ambient to 20.37 K. The mechanical design of the separable disconnect, kinematics of the drive mechanism, and the analysis and test methods used to verify proper operation and qualification for the space shuttle dynamic environments are presented. |
| NASA分類 | SPACE TRANSPORTATION |
| レポートNO | 81N22389 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/531047 |
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