A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion, and a flight latch device for latching the foldable wing tip portion in the extended position, wherein the flight latch device includes a housing, a latch bolt linearly movable relative to the housing, and a motor for driving the latch bolt. The flight latch device includes a threaded shaft having an external thread and being mounted to the housing in a torque proof manner, the flight latch device includes a nut having an internal thread engaging the external thread of the shaft, so that the nut can rotate about the shaft along the external thread, the motor is arranged coaxially around the nut, wherein a rotor part is mounted to the nut in a torque proof manner, and wherein a stator part is rotatably connected to the rotor part and is connected to the housing by a first linear guide allowing linear movement and inhibiting rotation of the stator part.

Embodiments are directed to systems and methods for deploying an outboard rotor blade of proprotor pylon to act as an extended lifting surface. Blade control actuators may provide primary rotor flight control as well as providing fold linkage actuation when fold locks are disengaged. During cruise flight, the blade control actuator may provide feathering inputs to the extended rotor blade, wherein the amplitude and frequency of feathering inputs are tuned to mitigate undesirable wing and fuselage dynamic modes thereby enhancing aircraft stability. The deployed rotor blades also improve the total lifting area of the aircraft, which may increase aircraft range and efficiency.

A vehicle comprising a morphing wing and a body is disclosed. The aircraft is configured to transform from a first configuration into a second configuration for ascent or descent of the aircraft. The drag force and lift force on the aircraft in the second configuration are less than in the first configuration. Transforming from the first to the second configuration comprises: contracting the wing within a geometric plane defined by the wing, and rotating the outer edge of the wing downwards, out of the geometric plane.

A vehicle comprising a morphing wing and a body is disclosed. The aircraft is configured to transform from a first configuration into a second configuration for ascent or descent of the aircraft. The drag force and lift force on the aircraft in the second configuration are less than in the first configuration. Transforming from the first to the second configuration comprises: contracting the wing within a geometric plane defined by the wing, and rotating the outer edge of the wing downwards, out of the geometric plane.

An aircraft wing including a fixed wing and a wing tip device rotatable about a hinge at the tip of the fixed wing is disclosed. The wing further includes a hinged panel at the boundary between the wing tip device and the fixed wing. In the flight configuration the panel is closed such that the panel is substantially flush with the upper surface of the wing, and the hinged panel is located in the path of a moveable element (for example part of an actuation mechanism, such as a curved rack). In the ground configuration the panel is hinged open to a position outside the path of the moveable element such that clashing of the moveable element with the stationary structure at the tip of the fixed wing is avoided.

An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a rear portion with a concave surface, such that the fairing acts as a lift-generating surface when the aircraft is in flight.

Disclosed is an aircraft with a super high aspect ratio based on self-unfolding folding wing technology, the aircraft including: an aircraft body; a fixed wing; and a movable wing assembly including a first movable wing and a second movable wing. When the aircraft takes off, the first movable wing and the second movable wing are in a folded position. The first movable wing and the second movable wing are deflected and moved to an unfolded position or a folded position by the aerodynamic force and moment generated by the deflection of aerodynamic control surfaces and the differential thrust and moment generated by a distributed propulsion system.

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.

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.

An aircraft wing having a fixed root part hingedly connected to a moveable tip part is disclosed. The tip part is configured to pivot relative to the root part about a substantially horizontal axis, between a load-alleviating configuration in which the tip part is oriented relative to the root part such that at least one of the upper and lower surface of the tip part is positioned away from the respective surface of the root part and a flight configuration in which the upper and lower surfaces of the tip part are continuations of the upper and lower surfaces of the root part. The shape of the tip part is controllably switchable between a cruise shape in which the tip part has positive camber and a recovery shape in which the tip part has negative camber.