An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.

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.

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.

A wing tip device for attaching to an aircraft wing comprising a first wing tip device element having a root end and a tip end; a second wing tip device element coupled to the tip end of the first wing tip device element; wherein the second wing tip device element has an inboard portion extending inboard from the tip end of the first wing tip device element and/or an outboard portion extending outboard from the tip end of the first wing tip device element, when viewed in the wing planform direction.

A wing tip device for attaching to an aircraft wing comprising a first wing tip device element having a root end and a tip end; a second wing tip device element coupled to the tip end of the first wing tip device element; wherein the second wing tip device element has an inboard portion extending inboard from the tip end of the first wing tip device element and/or an outboard portion extending outboard from the tip end of the first wing tip device element, when viewed in the wing planform direction.

The invention relates to a hybrid drone for transporting or delivering objects 124, comprising at least one first wing 102 having an airfoil, at least one first and one second longitudinal drive unit 104, wherein the first longitudinal drive unit 104 and the second longitudinal drive unit 104 are arranged on the at least one wing 102, an object-holding device 110 formed on an upper side or on an underside between the first and second longitudinal drive units 104 and for holding an object 124, and a regulating unit formed for regulating the hybrid drone, in particular the drive units, based on control signals. The hybrid drone further comprises at least one first high drive unit 105, wherein the first high drive unit 105 is aligned or is pivotally alignable such that a thrust force that can be generated by means of the high drive unit 105 acts substantially orthogonally to the longitudinal direction 106 and substantially parallel to a vertical axis 116 of the hybrid drone, and the first high drive unit 105 is arranged with a defined lever distance relative to the center of gravity of the hybrid drone, and wherein a pitch angle of the hybrid drone in the flight state is adjustable by means of the first high drive unit 105. In addition, at least one holding element is provided, which is associated with the underside in a front region of the hybrid drone, wherein the holding element is configured for releasably arranging, in particular for hooking, the hybrid drone on a top-ending vertical receiving structure.

The invention relates to a hybrid drone for transporting or delivering objects 124, comprising at least one first wing 102 having an airfoil, at least one first and one second longitudinal drive unit 104, wherein the first longitudinal drive unit 104 and the second longitudinal drive unit 104 are arranged on the at least one wing 102, an object-holding device 110 formed on an upper side or on an underside between the first and second longitudinal drive units 104 and for holding an object 124, and a regulating unit formed for regulating the hybrid drone, in particular the drive units, based on control signals. The hybrid drone further comprises at least one first high drive unit 105, wherein the first high drive unit 105 is aligned or is pivotally alignable such that a thrust force that can be generated by means of the high drive unit 105 acts substantially orthogonally to the longitudinal direction 106 and substantially parallel to a vertical axis 116 of the hybrid drone, and the first high drive unit 105 is arranged with a defined lever distance relative to the center of gravity of the hybrid drone, and wherein a pitch angle of the hybrid drone in the flight state is adjustable by means of the first high drive unit 105. In addition, at least one holding element is provided, which is associated with the underside in a front region of the hybrid drone, wherein the holding element is configured for releasably arranging, in particular for hooking, the hybrid drone on a top-ending vertical receiving structure.

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.