Abstract: An aircraft (1) including a fixed wing (7) and a wing tip device (9) moveably mounted thereon. The wing tip device (9) is movable from a load-alleviating configuration to a flight configuration. The wing tip device includes an airflow channel (88) extending between respective apertures (83, 84) on the upper surface and lower surface of the wing tip device. The channel (88) is configurable between an open state in which air can flow through the channel and a closed state in which the airflow through the channel (88), via the apertures (83, 84), is blocked. The channel (88) is configured such that when the wing tip device (9) is in the load-alleviating configuration and the channel (88) is in the open state, the aerodynamic loading on the wing tip device in flight urges the wing tip device towards the flight configuration.

Abstract: An actuator assembly for moving an aircraft wing tip device is disclosed. The wing tip device is rotatable about a hinge axis relative to a fixed wing of the aircraft. The hinge axis is orientated non-parallel to a line-of-flight direction of the aircraft. The actuator assembly includes a primary shaft having an axis of rotation orientated substantially parallel to the line-of-flight direction, a motor to cause rotation of the primary shaft, and a secondary shaft orientated substantially parallel to the hinge axis. The secondary shaft is couplable to the primary shaft and is arranged to rotate the wing tip device in response to the rotation of the primary shaft.

Abstract: A clutch for use in actuating an aircraft wing tip device is disclosed. The clutch includes first and second friction members each having a frusto-conical friction surface, and a third friction member arranged coaxially with, and between, the first and second friction members. The third friction member has first and second frusto-conical friction surfaces. When the clutch is engaged, the first and second friction surfaces of the third friction member are brought into contact with the friction surfaces of the first and second friction members, respectively. The clutch also includes spacer means operable to separate the friction surfaces from one another when the clutch is in a disengaged state.

Abstract: A clutch for use in actuating an aircraft wing tip device is disclosed. The clutch includes first and second friction members each having a frusto-conical friction surface, and a third friction member arranged coaxially with, and between, the first and second friction members. The third friction member has first and second frusto-conical friction surfaces. When the clutch is engaged, the first and second friction surfaces of the third friction member are brought into contact with the friction surfaces of the first and second friction members, respectively. The clutch also includes spacer means operable to separate the friction surfaces from one another when the clutch is in a disengaged state.

Abstract: An actuator assembly for moving an aircraft wing tip device is disclosed. The wing tip device is rotatable about a hinge axis relative to a fixed wing of the aircraft. The hinge axis is orientated non-parallel to a line-of-flight direction of the aircraft. The actuator assembly includes a primary shaft having an axis of rotation orientated substantially parallel to the line-of-flight direction, a motor to cause rotation of the primary shaft, and a secondary shaft orientated substantially parallel to the hinge axis. The secondary shaft is couplable to the primary shaft and is arranged to rotate the wing tip device in response to the rotation of the primary shaft.

Abstract: An aircraft (1) including a fixed wing (7) and a wing tip device (9) moveably mounted thereon. The wing tip device (9) is movable from a load-alleviating configuration to a flight configuration. The wing tip device includes an airflow channel (88) extending between respective apertures (83, 84) on the upper surface and lower surface of the wing tip device. The channel (88) is configurable between an open state in which air can flow through the channel and a closed state in which the airflow through the channel (88), via the apertures (83, 84), is blocked. The channel (88) is configured such that when the wing tip device (9) is in the load-alleviating configuration and the channel (88) is in the open state, the aerodynamic loading on the wing tip device in flight urges the wing tip device towards the flight configuration.