A manufacture configured to and process for inhibiting, from wear, a lock in a latching system comprising: a gland surrounding an actuator translating the lock through: a first fixed lock receptor and a moveable lock receptor. The manufacture and process include: inhibiting a skewing, of a lock central axis of the lock with the lock translating through the first opening and the opening in the moveable lock receptor, away from substantially aligning with: a first central axis of a first opening of the first fixed lock receptor, and an actuator central axis of the actuator, via fitting a first translation guide into the first fixed lock receptor. Also included is inhibiting: wear of a gland around an actuator in the lock while translating, and leaking, past the gland, of an actuator fluid within the lock; and skewing of an actuator central axis of the actuator.

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.

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.

A winglet for attachment to a wing portion of an aircraft including a winglet root. The winglet root defines a recess for receiving a connector of the wing portion in use and includes at least one protrusion for receipt into at least one corresponding hole of the wing portion in use. A portion of the winglet root that at least partially defines an upper or a lower side of the recess has at least one hole extending therethrough for receiving a fastener for fastening the winglet to the connector when the connector is located in the recess.

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

A method of flight control including having a vertical takeoff and landing aerial vehicle that has a plurality of lift propellers disposed on two linear support pieces, and there are two vertical stabilizers disposed at the rear of the two linear support pieces. A rotating shaft of each lift propeller from among the multiple lift propellers outwards forms an angle of 5 degrees to 15 degrees relative to a vertical plane of the aerial vehicle perpendicular to a horizontal plane of the aerial vehicle. The aerial vehicle of the present disclosure improves the heading axis control capacity of the aerial vehicle and reduces the restriction to the design size of the aerial vehicle.

A method of flight control including having a vertical takeoff and landing aerial vehicle that has a plurality of lift propellers disposed on two linear support pieces, and there are two vertical stabilizers disposed at the rear of the two linear support pieces. A rotating shaft of each lift propeller from among the multiple lift propellers outwards forms an angle of 5 degrees to 15 degrees relative to a vertical plane of the aerial vehicle perpendicular to a horizontal plane of the aerial vehicle. The aerial vehicle of the present disclosure improves the heading axis control capacity of the aerial vehicle and reduces the restriction to the design size of the aerial vehicle.

An aircraft assembly is disclosed having a wing tip device connected to a wing tip of a wing by a first connector, a second connector, and a third connector. The wing tip device includes a front device spar and a rear device spar. The first connector is associated with the rear device spar. The second connector is spaced apart in a chordwise direction forward of the first connector, and the third connector is spaced apart in a chordwise direction rearward of the first connector. The third connector includes a spigot mounting formation.

An aircraft assembly is disclosed having a wing tip device connected to a wing tip of a wing by a first connector, a second connector, and a third connector. The wing tip device includes a front device spar and a rear device spar. The first connector is associated with the rear device spar. The second connector is spaced apart in a chordwise direction forward of the first connector, and the third connector is spaced apart in a chordwise direction rearward of the first connector. The third connector includes a spigot mounting formation.