A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device (103), a second actuator (104A) for actuating a second aerodynamic device (102), a first drive path (109B) configured to operate between the power drive unit (101) and the first actuator (104C), a second drive path (109A) operably connecting the power drive unit (101) and the second actuator (104A), the first drive path (109B) including a lost motion device (108A), the lost motion device (108A) being configured to selectively operably connect the power drive unit (101) to the first actuator (104C) and selectively operably disconnect the power drive unit (101) from the first actuator (104C).

A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device (103), a second actuator (104A) for actuating a second aerodynamic device (102), a first drive path (109B) configured to operate between the power drive unit (101) and the first actuator (104C), a second drive path (109A) operably connecting the power drive unit (101) and the second actuator (104A), the first drive path (109B) including a lost motion device (108A), the lost motion device (108A) being configured to selectively operably connect the power drive unit (101) to the first actuator (104C) and selectively operably disconnect the power drive unit (101) from the first actuator (104C).

A wing having a main wing section with a forward spar and an aft spar extending through an internal cavity. The forward and aft spars are spaced apart and delimiting a dry segment of the internal cavity. A winglet is rotatably coupled to the main wing section by a cant hinge defining a cant axis about which the winglet rotates relative to the main wing section between an extended position in which the winglet is aligned with the main wing section, and a folded position in which the winglet is rotated about the cant axis. A linkage assembly disposed in the dry segment is pivotably mounted to one of the forward and aft spars and is coupled to the cant hinge. The linkage assembly is displaceable to apply a force to move the winglet between the extended position and the folded position during flight of the aircraft.

A wing having a main wing section with a forward spar and an aft spar extending through an internal cavity. The forward and aft spars are spaced apart and delimiting a dry segment of the internal cavity. A winglet is rotatably coupled to the main wing section by a cant hinge defining a cant axis about which the winglet rotates relative to the main wing section between an extended position in which the winglet is aligned with the main wing section, and a folded position in which the winglet is rotated about the cant axis. A linkage assembly disposed in the dry segment is pivotably mounted to one of the forward and aft spars and is coupled to the cant hinge. The linkage assembly is displaceable to apply a force to move the winglet between the extended position and the folded position during flight of the aircraft.

A wing for an aircraft including a wing tip section with an inboard section, a fairing in which an opening connecting an exterior of the fairing and an interior of the fairing is formed and which is mounted to the inboard section of the wing tip section, a movable device arranged in the exterior of the fairing, a connecting assembly movably connecting the movable device to the wing tip section such that the movable device is movable between a retracted position and at least one extended position, and a drive mechanism. The connecting assembly includes an actuating element, which extends through the opening and includes a first section, which is arranged in the interior of the fairing and is drivingly coupled to the drive mechanism, and a second section, which is arranged in the exterior of the fairing and coupled to the movable device.

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 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.

A tool for fabricating a control surface is disclosed. In various embodiments, the tool includes a first block defining a longitudinal direction running between a leading edge end and a trailing edge end; a first sidewall spaced a first lateral distance from the first block to form a first closeout channel running in the longitudinal direction between the first block and the first sidewall; and a second sidewall configured to form a second closeout channel running in the longitudinal direction, the second closeout channel disposed laterally opposite the tool from the first closeout channel.

A tool for fabricating a control surface is disclosed. In various embodiments, the tool includes a first block defining a longitudinal direction running between a leading edge end and a trailing edge end; a first sidewall spaced a first lateral distance from the first block to form a first closeout channel running in the longitudinal direction between the first block and the first sidewall; and a second sidewall configured to form a second closeout channel running in the longitudinal direction, the second closeout channel disposed laterally opposite the tool from the first closeout channel.

A flying apparatus includes a main structure and a rotative wing surface, the rotation of the wing surface allowing stabilizing the apparatus (100). A fuselage hangs from the wing surface around a hanging point, allowing the wing surface and the fuselage be moveable independently with respect to each other and the wing surface is configured as a disc to manoeuvre the apparatus and including one or more elements acting as security and secondary command and control surfaces, orienting the apparatus in desired directions. The main structure and wing surface can overwrap at least partially the the fuselage in order to improve the aerodynamic performance. The airframe or fuselage and the wing surface are rotatable around any of three rotational axes independently.