| 发明名称 | Process for repairing airplane panels | ||
| 摘要 | A repair process for a composite material panel that forms part of a fuselage, wings, or stabilizers of an aircraft, with the panel having large dimensions and including irregular contours in some areas and edges prone to damages occurring from handling and assembly of the panel. The process a) locates the damage in the element of the composite material panel; b) sands the area that includes the damage in an area larger than the damage, makes a cut in the panel, having the cut of a same form as a piece that will serve to repair panel; c) places the piece in the cut, so that it is perfectly flush with the panel to be repaired; and d) attaches the piece to the composite material panel. | ||
| 申请公布号 | US8800149(B2) | 申请公布日期 | 2014.08.12 |
| 申请号 | US201013266135 | 申请日期 | 2010.05.27 |
| 申请人 | Airbus Operations S.L. | 发明人 | Balsa Gonzalez Alberto;Burgos Gallego Francisco de Paula |
| 分类号 | B21D47/00 | 主分类号 | B21D47/00 |
| 代理机构 | Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P. | 代理人 | Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P. |
| 主权项 | 1. A repair process for a composite material panel that forms part of a fuselage, wings, or stabilizers of an aircraft, with the panel having large dimensions and including irregular contours and edges prone to damages occurring from handling and assembly of the panel, the process comprising: a) locating a damaged area in an element of the composite material panel; b) sanding an area including the damaged area, the area being larger than the damaged area, and making a cut in the panel, the cut being in a same shape as a shape of a predefined piece that will serve to repair the panel; c) placing the predefined piece in the cut such that the predefined piece is perfectly flush with the panel to be repaired; and d) attaching the predefined piece to the composite material panel. | ||
| 地址 | Getafe ES | ||