A folding wing hinge for a wing having a fixed wing portion and a folding wing portion, the folding wing hinge including a hinge pin including a hinge pin spline and having a first longitudinal axis, an input fitting coupled to one of the fixed wing portion and the folding wing portion, the input fitting including an input fitting spline and a second longitudinal axis, and a spline coupling member having a coupling spline configured to couple with the hinge pin spline and the input fitting spline so that the first longitudinal axis moves relative to the second longitudinal axis by a first predetermined amount of movement.

A vehicle includes a fuselage having a longitudinal axis and a propulsion system that is coupled to the fuselage. The vehicle also includes a pair of articulated appendages that is coupled to the fuselage. Each one of the articulated appendages includes a plurality of airfoil segments and is moveable between a ground configuration, in which each one of the pair of articulated appendages supports the vehicle during takeoff or landing of the vehicle, and a flight configuration, in which each one of the pair of articulated appendages produces lift during flight of the vehicle.

A vehicle includes a fuselage having a longitudinal axis and a propulsion system that is coupled to the fuselage. The vehicle also includes a pair of articulated appendages that is coupled to the fuselage. Each one of the articulated appendages includes a plurality of airfoil segments and is moveable between a ground configuration, in which each one of the pair of articulated appendages supports the vehicle during takeoff or landing of the vehicle, and a flight configuration, in which each one of the pair of articulated appendages produces lift during flight of the vehicle.

One embodiment is an apparatus including an airfoil-shaped body; and a chordwise variable vortex generation system associated with the airfoil-shaped body, the chordwise variable vortex generation system controlling a deployment of at least one vortex generator on a surface of the airfoil-shaped body, wherein the deployment of the at least one vortex generator is dependent on a current angle of attack of the airfoil-shaped body. In some embodiments, the chordwise variable vortex generation system includes an actuator for controlling a location of the deployment of the at least one vortex generator responsive to a control signal indicative of the current angle of attack of the airfoil-shaped body. In certain embodiments, the surface of the airfoil-shaped body is a top surface of the airfoil-shaped body. In some embodiments, the airfoil-shaped body is an aircraft wing.

One embodiment is an apparatus including an airfoil-shaped body; and a chordwise variable vortex generation system associated with the airfoil-shaped body, the chordwise variable vortex generation system controlling a deployment of at least one vortex generator on a surface of the airfoil-shaped body, wherein the deployment of the at least one vortex generator is dependent on a current angle of attack of the airfoil-shaped body. In some embodiments, the chordwise variable vortex generation system includes an actuator for controlling a location of the deployment of the at least one vortex generator responsive to a control signal indicative of the current angle of attack of the airfoil-shaped body. In certain embodiments, the surface of the airfoil-shaped body is a top surface of the airfoil-shaped body. In some embodiments, the airfoil-shaped body is an aircraft wing.

An aircraft includes electrical components and a ducted fan with a cooling coil. The aircraft is designed to discharge heat from the electrical components to the cooling coil.

An aircraft wing is disclosed having a main fixed wing portion and a wing tip device at a tip thereof. The wing tip device is configurable between a flight configuration and a ground configuration, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. A hinge arrangement connects the main fixed wing portion and the wing tip device and enables the wing tip device to rotate between the ground configuration and the flight configuration. The hinge arrangement protrudes beyond an outer surface of the main fixed wing portion and wing tip device. A fairing covers at least part of the hinge arrangement on at least a suction side of the wing.

An air vehicle has a body, more than one wing located on the body creating a lifting force, at least one control surface located on the wing and movable along the direction in which the wing extends, an open position in which the control surface moves out of the wing in the direction in which the wing extends and increases the lifting force acting on the body, a closed position in which the control surface is moved from the open position and brought to the wing, a main actuator moving the control surface between the open and closed positions, at least one shaft enabling the control surface to be moved with the triggering of the main actuator and having one end connected to the control surface, and at least one additional actuator enabling the attack angle of the wings to be changed by rotating the wings on the body.

An air vehicle has a body, more than one wing located on the body creating a lifting force, at least one control surface located on the wing and movable along the direction in which the wing extends, an open position in which the control surface moves out of the wing in the direction in which the wing extends and increases the lifting force acting on the body, a closed position in which the control surface is moved from the open position and brought to the wing, a main actuator moving the control surface between the open and closed positions, at least one shaft enabling the control surface to be moved with the triggering of the main actuator and having one end connected to the control surface, and at least one additional actuator enabling the attack angle of the wings to be changed by rotating the wings on the body.

An aircraft includes a fuselage coupled to a wing having a dihedral root section with first and second outboard sections pivotably coupled to respective outboard ends thereof. A thrust array is coupled to the wing. A power system is operably associated with the thrust array to provide power to each of a plurality of propulsion assemblies. A flight control system is operably associated with the thrust array and the wing. The flight control system is operable to control the thrust output from the propulsion assemblies and the configuration of the wing. In a thrust-borne vertical lift mode, the wing has an M-wing configuration with the center of gravity of the aircraft located between the outboard sections of the wing. In a wing-borne forward flight mode, the wing has a gull wing configuration with the center of gravity of the aircraft located below the outboard sections of the wing.