A structural composite airfoil includes a primary structural element, and a secondary structural element defining a trailing edge of the structural composite airfoil. The primary structural element includes an upper skin panel extending from an upper leading edge end to an upper trailing edge end, a lower skin panel extending from a lower leading edge end to a lower trailing edge end, and a bracket coupled to the lower skin panel. The leading edge region of the primary structural element has a bullnose shape defined by the lower skin panel. The upper skin panel includes an integrally formed front C-channel spar having a lower flange coupled to the lower skin panel. The lower flange is adjacent the upper leading edge end, and the integrally formed front C-channel spar is coupled to the bracket, thereby further coupling the lower skin panel to the integrally formed front C-channel spar.

Structural composite airfoils include a front C-channel spar having an upper flange coupled to an upper skin panel, and a lower flange coupled to a lower skin panel. The lower skin panel includes a joggle adjacent a lower leading edge end, with the joggle being positioned forward of the front C-channel spar. An upper skin surface of the lower leading edge end faces an internal volume defined between the upper skin panel and the lower skin panel. A lower skin surface of the lower leading edge end faces an internal surface of the upper leading edge end of the upper skin panel, and the lower leading edge end of the lower skin panel is coupled to the upper leading edge end of the upper skin panel forward of the front C-channel spar. The leading edge has a bullnose shape defined by the upper skin panel.

Structural composite airfoils include a primary structural element, and a secondary structural element defining a trailing edge of the structural composite airfoil. The primary structural element extends from a leading edge region to a trailing edge region, with the leading edge region of the primary structural element forming a leading edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a spar. The spar includes a plurality of upper flanges coupled to the upper skin panel and a plurality of lower flanges coupled to the lower skin panel. The spar extends spanwise across the structural composite airfoil. The spar also extends along a chord length of the structural composite airfoil. The spar may be a unitary, monolithic body, with an elongated span extending between each adjacent upper flange and lower flange.

A structural composite airfoil includes a primary structural element, and a secondary structural element defining a trailing edge of the structural composite airfoil. The primary structural element includes an upper skin panel extending from an upper leading edge end to an upper trailing edge end, a lower skin panel extending from a lower leading edge end to a lower trailing edge end, and a bracket coupled to the upper skin panel. The leading edge region of the primary structural element has a bullnose shape defined by the upper skin panel. The lower skin panel includes an integrally formed front C-channel spar having an upper flange coupled to the upper skin panel. The upper flange is adjacent the lower leading edge end, and the integrally formed front C-channel spar is coupled to the bracket, thereby coupling the upper skin panel to the integrally formed front C-channel spar.

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 include a primary structural element and a secondary structural element defining the trailing 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 upper skin panel extends from an upper leading edge end to an upper trailing edge end, and the lower skin panel extends from a lower leading edge end to a lower trailing edge end. The lower leading edge end of the lower skin panel is coupled to the upper leading edge end of the upper skin panel within the leading edge region of the primary structural element.

Structural composite airfoils include a front C-channel spar having an upper flange coupled to an upper skin panel, and a lower flange coupled to a lower skin panel. The upper skin panel includes a joggle adjacent an upper leading edge end, with the joggle being positioned forward of the front C-channel spar. A lower skin surface of the upper leading edge end faces an internal volume defined between the upper skin panel and the lower skin panel. An upper skin surface of the upper leading edge end faces an internal surface of the lower leading edge end of the lower skin panel, and the upper leading edge end of the upper skin panel is coupled to the lower leading edge end of the lower skin panel forward of the front C-channel spar. The leading edge has a bullnose shape defined by the lower skin panel.

An assembly for an aircraft that has a wing and an engine pylon having a primary structure with right-side and left-side panels, an upper and a lower spar and a rear rib, two sets of upper or lower shackles, one set fastening the right-side panel to the wing, and a second set fastening the left-side panel to the wing, a fastening element secured to the rear rib or to the lower spar, a rear rod connecting the fastening element to the wing, a transverse shackle connecting the upper spar to the wing, a line connecting two centers of the transverse shackle being oriented transversely relative to a longitudinal axis of the engine pylon, and a reinforcing panel, at each joint between a right-side or left-side panel and an upper or lower shackle, which is fastened along a height against the panel and to which the shackle is also fastened.

Disclosed is a transformable wing, which comprises: a main wing including multiple ribs extending in the forward and backward direction of the wing wherein the multiple ribs are arranged at intervals in a lengthwise direction of the wing; and a span morphing part including an auxiliary wing extending in the lengthwise direction, a scissors part connected to one end of the auxiliary wing in the lengthwise direction, and a driving part for extending or reducing the scissor part in the lengthwise direction.

A fitting for connecting a first aircraft structure to a second aircraft structure is disclosed including a first substantially planar surface, a second substantially planar surface, a body, and a cavity in the body configured to retain a captive nut. The body connects the first surface to the second surface such that the first surface is at an angle of less than or equal to 90° to the second surface. The cavity is configured such that a captive nut retained therein is adjacent the first surface and the second surface.