An uplock is disclosed including a hook configured to engage a capture pin mounted on an aircraft component. The hook is mounted for movement between a closed position and an open position. The uplock further includes an indicator system configured to detect whether a pin is engaged with the hook when the hook is in the closed position.

A pylon assembly for a tiltrotor aircraft includes a rotor assembly rotatably coupled to a fixed pylon and operable to rotate between a vertical takeoff and landing orientation and a forward flight orientation. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension is rotatably disposed to the outboard end of the fixed pylon such that the rotor assembly and the wing extension are separated by at least a portion of the fixed pylon. The wing extension has a forward edge and an outboard end. A winglet is coupled to the outboard end of the wing extension and has a forward edge. The wing extension and the winglet are configured to rotate in synchrony with the rotor assembly such that the forward edges of the wing extension and the winglet remain in the slipstream of the proprotor.

An aircraft wing assembly including a wing having a main body 5 and a movable portion 6, so that the wing may be folded when taxiing. A lighting system is provided with a light source 9; a light emitter 11 arranged on one of the main body and the movable portion, and a light guide 10 arranged to transmit light from the light source along a path between the main body and the movable portion to the light emitter. The provision of a light guide between the light source and the emitter allows for light to be transmitted to the emitter across the joint 8 between the wing main body and the movable portion. Thus, lighting on the wing may be provided without the need to provide electrical wiring across the joint. A single light source 9 may be employed to illuminate multiple light emitters 11, 13 on the wing.

An actuation unit (15) for actuating a foldable wing tip portion (9) includes a first housing part (19) including a first attachment device (23) configured for attachment to a fixed wing (5), and a second housing part (21) including a second attachment device (25) configured for attachment to a foldable wing tip portion (9). The second housing part (21) is rotatable about a main axis of rotation (35). The second housing part (21) includes a toothed rack (37) having a concave shape and facing the main axis of rotation (35). A drive pinion (39) is supported at the first housing part (19) and engaging the toothed rack (37) for driving the second housing part (21) rotatingly relative to the first housing part (19). The drive pinion (39) is driven by a coupling arrangement (43) that is configured to be coupled to an output (45) of a motor unit (47).

An exterior aircraft light for indicating a movement of a foldable wing tip between a folded up position and a laterally extended position includes a light source; and a control unit; wherein the control unit is configured to operate the light source to emit a warning light output in response to a warning light control signal indicative of the movement of the foldable wing tip.

Aircrafts having foldable wings are disclosed. An example aircraft includes a fixed wing portion, a foldable wing tip, and a hinge interface to pivotally couple the foldable wing tip and the fixed wing portion. The hinge interface has a first hinge defining a hinge axis that is substantially parallel to a fuselage centerline. The first hinge has a first dimension in a spanwise direction and a second dimension in a chordwise direction. The first dimension is greater than the second dimension.

Foldable raked wing tips having aerodynamic devices are disclosed. A disclosed example wing for use with an aircraft includes a fixed portion, and a folding portion proximate a distal end of the wing. The folding portion includes a raked surface. The wing also includes at least one of a feather or a winglet, and a hinge operatively coupled between the fixed and folding portions to enable the folding portion to fold relative to the fixed portion.

An adjustable lift modification wingtip may be attached to a baseline wing of an aircraft. The adjustable lift modification wingtip may comprise a horizontal portion including a control surface and a vertical portion coupled to the horizontal portion. The vertical portion may move about an axis that may be substantially perpendicular to the horizontal portion. The control surface and the vertical portion may be adjusted in conjunction to increase wing efficiency at a flight condition.

A structure adapted to traverse a fluid environment includes an elongate body having a root, a wingtip, a leading edge and a trailing edge; and a rigid winglet associated with the wingtip and having a winglet body extending substantially normal to one of a suction side and a pressure side of the elongate body to a termination point that is rearward of the trailing edge. In an embodiment, the structure is a rotor blade that may be incorporated into a wind turbine.

A joint for coupling a wing tip to a wing base includes a linking member that extends from a first end to a second end. The linking member first end is coupleable to the wing base, and the linking member second end is coupleable to the wing tip. The linking member defines first second hinge lines that are substantially parallel. The joint also includes at least one actuator. A first end of each at least one actuator is coupled to the linking member, and a second end of each at least one actuator is coupleable to one of the wing base and the wing tip. The at least one actuator is operable to rotate the wing tip about the first and second hinge lines between a first orientation and a second orientation relative to the wing base.