| タイトル | Z-2 Threaded Insert Design and Testing |
| 本文（外部サイト） | http://hdl.handle.net/2060/20160003485 |
| 著者（英） | Jones, Robert J.; Ferl, Jinny; Sweeny, Mitch; Rhodes, Richard; Ross, Amy; Graziosi, David; Scarborough, Stephen |
| 発行日 | 2016-07-10 |
| 言語 | eng |
| 内容記述 | NASA's Z-2 prototype space suit contains several components fabricated from an advanced hybrid composite laminate consisting of IM10 carbon fiber and fiber glass. One requirement was to have removable, replaceable helicoil inserts to which other suit components would be fastened. An approach utilizing bonded in inserts with helicoils inside of them was implemented. During initial assembly, cracking sounds were heard followed by the lifting of one of the blind inserts out of its hole when the screws were torqued. A failure investigation was initiated to understand the mechanism of the failure. Ultimately, it was determined that the pre-tension caused by torqueing the fasteners is a much larger force than induced from the pressure loads of the suit which was not considered in the insert design. Bolt tension is determined by dividing the torque on the screw by a k value multiplied by the thread diameter of the bolt. The k value is a factor that accounts for friction in the system. A common value used for k for a non-lubricated screw is 0.2. The k value can go down by as much as 0.1 if the screw is lubricated which means for the same torque, a much larger tension could be placed on the bolt and insert. This paper summarizes the failure investigation that was performed to identify the root cause of the suit failure and details how the insert design was modified to resist a higher pull out tension. |
| NASA分類 | Engineering (General); Metals and Metallic Materials |
| レポートNO | ICES-2016-217
JSC-CN-35679 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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