| 发明名称 |
AIRCRAFT FUSELAGE FRAME |
| 摘要 |
An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece. |
| 申请公布号 |
US2016152315(A1) |
申请公布日期 |
2016.06.02 |
| 申请号 |
US201514952376 |
申请日期 |
2015.11.25 |
| 申请人 |
Airbus Operations S.L. ;Airbus Operations SAS |
发明人 |
MARTINO GONZALEZ Esteban;FOLCH CORTES Diego;GOYA ABAURREA Pablo;PASCUAL FUERTES Angel;LINARES MENDOZA Sandra;GUILLEMAUT Julien;BOUCHET Eric;COLMAGRO Jerome;BLANC Jonathan |
| 分类号 |
B64C1/06;B64C3/32;B64C1/12 |
主分类号 |
B64C1/06 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An aircraft fuselage frame comprising:
a central element configured to be located within a perimeter of the fuselage, and two lateral extensions projecting out from the fuselage from both sides of the central element, wherein the lateral extensions are each a portion of a longitudinal structure of a lifting surface, and the central element and the two lateral extensions are an integrated piece. |
| 地址 |
Madrid ES |
