| 发明名称 | Method for forming fuselage stringers | ||
| 摘要 | A composite part, such as a stiffener is formed in place. A composite charge is placed on a tool spanning a mold cavity, with the centerline of the charge offset from the centerline of the mold cavity. Opposite sides of the charge are held against the tool as the charge is formed into the mold cavity. One side of the charge is held against movement on the tool while the other side of the charge is allowed to slip over the tool toward the mold cavity. | ||
| 申请公布号 | US9162396(B2) | 申请公布日期 | 2015.10.20 |
| 申请号 | US201213650502 | 申请日期 | 2012.10.12 |
| 申请人 | THE BOEING COMPANY | 发明人 | Coxon Brad Andrew;Klewiada Mark;Wright Donald Edward;Modin Andrew E. |
| 分类号 | B29C70/44;B29C70/54;B29C70/56;B29D99/00 | 主分类号 | B29C70/44 |
| 代理机构 | Yee & Associates, P.C. | 代理人 | Yee & Associates, P.C. |
| 主权项 | 1. A method of forming a composite part, comprising: placing a composite charge on a tool spanning a mold cavity in the tool; forming the composite charge into the mold cavity; and holding opposite sides of the composite charge against the tool as the composite charge is being formed into the mold cavity, including holding one of the opposite sides of the composite charge against movement on the tool during forming of the composite charge into the mold cavity while allowing the other of the opposite side of the composite charge to slip over the tool. | ||
| 地址 | Chicago IL US | ||