12 results about "Wingtip device" patented technology

An aircraft including an aircraft wing wherein the aircraft wing includes a fixed wing, a wing tip device at an end of the fixed wing, and a wing tip device actuator configured to move the wing tip device between a flight configuration and a ground configuration. The wing tip device actuator includes a shaft which is rotatable about a shaft axis to selectively displace respective first and second elbows of the wing tip device actuator towards or away from the shaft. The first elbow is connected to the wing tip device and the second elbow is connected to the fixed wing such that movement of the respective elbows away from the shaft causes the wing tip device to move away from the flight configuration and such that movement of the respective elbows towards the shaft causes the wing tip device to move towards the flight configuration.

A wing assembly for an aircraft, the wing assembly having a fixed wing and a wing tip device moveably mounted at the end of the fixed wing. A wiring harness extends between the fixed wing and the wing tip device, a length of the wiring harness being encased in a length of protective sleeve. The protective sleeve is pre-shaped, for example pre-molded, to follow a path along a helical curve.

An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The clutch is coupled to the geared rotary actuator by a shaft and the shaft is fixed in rotation to a mass disposed radially outwardly from the shaft.

A wing assembly for an aircraft including a fixed wing and a wing tip device rotatable about a joint assembly. The wing assembly is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. The wing assembly includes joint-bordering structure located adjacent the joint assembly, the joint-bordering structure having a rib, an upper cover and a lower cover. The joint assembly includes a moveable panel. The panel includes a first hard stop element, and the joint-bordering structure includes a second hard stop element. The first hard stop element is integrally formed in the panel, and the second hard stop element is integrally formed in one of the rib, the upper cover or the lower cover of the joint-bordering structure. The hard stop elements may be configured to self-align.

An aircraft wing having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing. The wing tip device is rotatable about the hinge. An actuation system rotates the wing tip device about the hinge. The actuation system has a motor, a plurality of geared mechanical actuators, and an angle gearbox coupled between the plurality of geared mechanical actuators and the motor. Each geared mechanical actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion. Each geared mechanical actuator is arranged along a hinge line of the hinge. The angle gearbox is arranged along the hinge line and between two of the plurality of geared mechanical actuators.

To provide an improved wing assembly comprising a fixed wing and a wingtip device that can rotate around a joint assembly at the tip of the fixed wing. [Solution] The main wing assembly 10 for an aircraft can be configured between a flight configuration for use in flight and a ground configuration for use during ground-based operations. The main wing assembly 10 includes a joint boundary structure positioned adjacent to a joint assembly 16, the joint boundary structure comprising ribs, an upper cover, and a lower cover. The joint assembly 16 includes a movable panel 32. The movable panel 32 includes a first hard stop element, and the joint boundary structure includes a second hard stop element. The first hard stop element is integrally formed with the panel 32, and the second hard stop element is integrally formed with one of the ribs, the upper cover, or the lower cover of the joint boundary structure. The hard stop elements may be configured to self-align.

A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to alleviate a load on the wingtip device. The flow disrupter may comprise an edge that extends into a boundary layer at a threshold angle of attack that may disrupt the boundary layer and cause a flow to separate from the wingtip device. This separated flow may reduce stresses experienced by the wingtip device and wing during various flight conditions where a transverse flow is encountered.

The present invention relates to a wing assembly, a folding wingtip arrangement in an aircraft wing, and an aircraft. In one aspect, a wing assembly for an aircraft is provided, the wing assembly comprising a fixed wing and a wingtip device rotatable about a joint assembly. The wing assembly is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. The wing assembly comprises a joint boundary structure positioned adjacent to the joint assembly, the joint boundary structure comprising a rib, an upper cover, and a lower cover. The joint assembly comprises a movable panel. The panel comprises a first hard stop element, and the joint boundary structure comprises a second hard stop element. The first hard stop element is integrally formed in the panel, and the second hard stop element is integrally formed in one of the rib, the upper cover, or the lower cover of the joint boundary structure. The hard stop elements can be configured to self-align.

An aircraft wing assembly with a fixed wing and a wing tip device are disclosed. The wing tip device is moveable between a flight configuration and a ground configuration. In the ground configuration the span of the aircraft wing assembly is reduced. The fixed wing includes a fixed wing lug and the wing tip device comprises a wing tip lug. A locking pin is provided. In the flight configuration the fixed wing lug and wing tip device lug are aligned such that the locking pin may be inserted through the fixed wing lug and wing tip device lug into a locking position to lock the wing tip device in the flight configuration. The locking pin is hollow and includes a heating element.

A wing assembly for an aircraft 1, the wing assembly comprising: a fixed wing 5 and a wingtip device 11 moveably mounted at the end of the fixed wing. A wiring harness 15 extends between the fixed win

An aircraft wing 3 comprising a fixed wing 5 and a moveably mounted wing tip device 11 having a flight and ground configuration, a first cable harness 15a and a second cable harness 15b which are rece

An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The reduction gearbox is positioned between the clutch and the geared rotary actuator along a drive train between the motor and the geared rotary actuator.