| 发明名称 | Methods for manufacturing an i-stringer of an aircraft and devices for use in such methods | ||
| 摘要 | Methods for manufacturing a reinforced composite structure for an aircraft and devices used in such methods are provided. A method includes advancing a composite material layout through a cap-forming device. The advancing results in a preformed cap section, a first length of the layout and a second length of the layout. The layout is removed from the cap-forming device and the preformed cap section of the layout is arranged within a cavity of a flexible mandrel with a foot portion of the first length and a foot portion of the second length remaining outside the cavity of the flexible mandrel. The foot portion of the first length and the foot portion of the second length contact a skin structure. The layout is heated and pressurized using the flexible mandrel to cure the layout and form the reinforced composite structure affixed to the skin structure. | ||
| 申请公布号 | US9475569(B2) | 申请公布日期 | 2016.10.25 |
| 申请号 | US201314066376 | 申请日期 | 2013.10.29 |
| 申请人 | Gulfstream Aerospace Corporation | 发明人 | Aitken Charles;Autry Brenden |
| 分类号 | B29D99/00;B64C1/26;B29C70/54;B64C1/06;B29C70/42;B29C70/44;B64C3/18;B64C1/00 | 主分类号 | B29D99/00 |
| 代理机构 | Lorenz Kopf, LLP (LKGlobal) | 代理人 | Lorenz Kopf, LLP (LKGlobal) |
| 主权项 | 1. A method for manufacturing a reinforced composite structure for an aircraft, the method comprising the steps of: forming a composite material layout by arranging a first composite material ply overlying a second composite material ply and positioning a pre-cured cap insert on the first composite material ply; advancing the composite material layout through a cap-forming device, wherein the advancing results in a preformed cap section, a first length of the composite material layout and a second length of the composite material layout; removing the composite material layout from the cap-forming device; arranging the preformed cap section of the composite material layout within a cavity of a flexible mandrel with a foot portion of the first length and a foot portion of the second length remaining outside the cavity of the flexible mandrel; contacting the foot portion of the first length and the foot portion of the second length with a skin structure: and heating and pressurizing the composite material layout using the flexible mandrel to cure the composite material layout and form the reinforced composite structure affixed to the skin structure. | ||
| 地址 | Savannah GA US | ||