Structural composite airfoils include a primary structural element, a secondary structural element defining the trailing edge of the structural composite airfoil, and a discrete leading edge structure defining the leading edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a middle C-channel spar that is coupled to the upper skin panel and the lower skin panel. The discrete leading edge structure is coupled to the upper leading edge end of the upper skin panel and to the lower leading edge end of the lower skin panel. The upper skin panel may include a first panel bend adjacent the discrete leading edge structure, and the lower skin panel may include a second panel bend adjacent the discrete leading edge structure.
STRUCTURAL COMPOSITE AIRFOILS WITH A SINGLE SPAR, AND RELATED METHODS
25.11.2021
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Structural composite airfoils with a single spar, and related methods
Europäisches Patentamt | 2023
|STRUCTURAL COMPOSITE AIRFOILS WITH A SINGLE SPAR, AND RELATED METHODS
Europäisches Patentamt | 2021
|Structural composite airfoils with a single spar, and related methods
Europäisches Patentamt | 2022
|STRUCTURAL COMPOSITE AIRFOILS WITH A SINGLE SPAR, AND RELATED METHODS
Europäisches Patentamt | 2021
|STRUCTURAL COMPOSITE AIRFOILS WITH A MULTI-SPAR PIECE, AND RELATED METHODS
Europäisches Patentamt | 2021
|