STRUCTURAL COMPOSITE AIRFOILS WITH DIRECTLY COUPLED FRONT SPARS, AND RELATED METHODS

Structural composite airfoils include a primary structural element, a secondary structural element defining the trailing edge of the structural composite airfoil, and a leading edge skin panel defining the leading edge of the structural composite airfoil. The primary structural element includes an u...

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Bibliographische Detailangaben
Hauptverfasser:	Schupp, Peter, Gruner, Bryan
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIRCRAFT AVIATION COSMONAUTICS DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR HELICOPTERS PERFORMING OPERATIONS TRANSPORTING
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Beschreibung
Zusammenfassung:	Structural composite airfoils include a primary structural element, a secondary structural element defining the trailing edge of the structural composite airfoil, and a leading edge skin panel defining the leading edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a front C-channel spar. A first channel of the front C-channel spar faces the leading edge of the structural composite airfoil, and an upper flange of the front C-channel spar forms an acute angle with an elongated span of the front C-channel spar. The leading edge skin panel is positioned adjacent the leading edge region of the primary structural element, with a first end region of the leading edge skin panel being coupled to the upper flange of the front C-channel spar, and a second end region being coupled to the lower flange of the front C-channel spar.