An aircraft wing section assembly is disclosed having a structural spine, a movement mechanism including a support rod 1 extending through the structural spine, a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the support rod, a second similar lever for connection to and for moving a second moveable control surface, and a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever causes pivotal movement of the second lever, and an actuation mechanism for actuating pivotal movement of the first lever, such that, in use, when the actuation mechanism actuates pivotal movement of the first lever, the second lever also pivotally moves, thus causing movement of both the first and second moveable control surfaces. Also disclosed is an aircraft wing assembly, an aircraft and a method of operating an aircraft.

An aircraft wing includes a main wing having an outer skin defining an interior space of the main wing, a slat, and a connection assembly for movably connecting the slat to the main wing, such that the slat is movable in a predefined motion between a retracted position and at least one extended position. The assembly includes an elongate guide arranged within the interior space, a bearing at least partly arranged outside the interior space, an elongate slat track with a first end section connected to the slat and a second end section movably and rotatable connected to the guide, such that the second end section is movable along a predefined pathway defined by the guide while being connected to the main wing. An intermediate section of the slat track is movably and rotatably supported on the main wing, such that the guide and the bearing support the predefined motion.

An electric aircraft includes system for operating the aircraft. The electric aircraft includes a wing having a first control surface, a second control surface, a battery and a gearbox mechanically coupled to the first control surface. The first control surface is operated, and a voltage is induced from mechanical energy generated during a deceleration of the first control surface that occurs while operating the first control surface, wherein an airflow across the first control surface causes the deceleration. The induced voltage can be stored at the battery or used to operate the second control surface using the induced voltage.

Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.

Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.

Fluid systems are described. An example fluid system includes a body and a housing. The body has a leading edge, a trailing edge, a first portion, and a second portion attached to the first portion. The second portion is moveable relative to the first portion between a first position and a second position. The housing extends from the first portion to the second portion and is configured to move as the second portion moves relative to the first portion. The housing is moveable between a first configuration and a second configuration. The housing is in the first configuration when the second portion is in the first position and is in the second configuration when the second portion is in the second position. The housing has a first length when in the first configuration and a second length when in the second configuration that is greater than the first length.

A system for controlling a high-lift device of an aircraft may include an interface for placement in a flight deck of an aircraft. The interface may include an edge control device for controlling a position of the high-lift device. The interface may be operable to select any of a plurality of control device positions. Each one of the plurality of control device positions may correspond to a different flight phase of the aircraft. The edge control device may be operable to engage, in response to a selection of a first control device position, a command mode for actuating the high-lift device in an automated manner based on the flight phase associated with the first control device position.

A system for controlling a high-lift device of an aircraft may include an interface for placement in a flight deck of an aircraft. The interface may include an edge control device for controlling a position of the high-lift device. The interface may be operable to select any of a plurality of control device positions. Each one of the plurality of control device positions may correspond to a different flight phase of the aircraft. The edge control device may be operable to engage, in response to a selection of a first control device position, a command mode for actuating the high-lift device in an automated manner based on the flight phase associated with the first control device position.

A high-lift device of a flight vehicle includes: a flap main body provided at a trailing edge portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in a wing span direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of a tip end portion of the flap main body to an upper surface of the tip end portion.

A high-lift device of a flight vehicle includes: a flap main body provided at a trailing edge portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in a wing span direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of a tip end portion of the flap main body to an upper surface of the tip end portion.