An aircraft airflow modification device, comprising: at least one resiliently deformable base member; and at least one resiliently deformable flap member that extends from the resiliently deformable base member. Deformation of the resiliently deformable base member from a first state to a second state results in corresponding deformation of the resiliently deformable flap member from a first state to a second state.

Disclosed is an aircraft and a method of controlling an aircraft. The aircraft comprises a continuous wing assembly extending from port to starboard sides of the aircraft. The aircraft is controlled partially by flexing portions of the wing, and partially or totally by mechanical systems that alter the position of a fuselage with respect to the wing. The fuselage is attached to the wing by a wing/fuselage joint structure that permits at least two mutually orthogonal axes of rotation of the fuselage relative to the wing. The aircraft includes a sensors, a telemetry system linked to a remote server, and a control system for programming flight information and aircraft control instructions and a plurality of actuators responsive to the control system for rotating the fuselage relative to the wing and flexing the wing for controlling the flight of the aircraft in response to instructions from the control system.

Disclosed is an aircraft and a method of controlling an aircraft. The aircraft comprises a continuous wing assembly extending from port to starboard sides of the aircraft. The aircraft is controlled partially by flexing portions of the wing, and partially or totally by mechanical systems that alter the position of a fuselage with respect to the wing. The fuselage is attached to the wing by a wing/fuselage joint structure that permits at least two mutually orthogonal axes of rotation of the fuselage relative to the wing. The aircraft includes a sensors, a telemetry system linked to a remote server, and a control system for programming flight information and aircraft control instructions and a plurality of actuators responsive to the control system for rotating the fuselage relative to the wing and flexing the wing for controlling the flight of the aircraft in response to instructions from the control system.

A system for changing a shape a structural spar includes, in an exemplary embodiment, a plurality of adjoining structural strips axially aligned to form the structural spar. At least one of the structural strips is formed from a shape memory alloy. The system also includes a temperature control system to control a temperature of the at least one shape memory alloy strip. Heat applied to the at least one shape memory alloy strip causes the structural spar to twist or bend.

A system for changing a shape a structural spar includes, in an exemplary embodiment, a plurality of adjoining structural strips axially aligned to form the structural spar. At least one of the structural strips is formed from a shape memory alloy. The system also includes a temperature control system to control a temperature of the at least one shape memory alloy strip. Heat applied to the at least one shape memory alloy strip causes the structural spar to twist or bend.

An example aircraft wing includes a skin, a composite shear tie, a stringer base charge overlaying the skin, and a stringer overlaying the stringer base charge. The composite shear tie includes a shear-tie web, a first shear-tie flange extending from a first side of the shear-tie web, a second shear-tie flange extending from a second side of the shear-tie web, and a first shear-tie tab extending from an end of the first side of the shear-tie web. The stringer includes a stringer web, a first stringer flange extending from a first side of the stringer web, and a second stringer flange extending from a second side of the stringer web. The first stringer flange is stitched to and integrated with the stringer base charge and the skin. Further, the first shear-tie flange is stitched to and integrated with the first stringer flange.

An example aircraft wing includes a skin, a composite shear tie, a stringer base charge overlaying the skin, and a stringer overlaying the stringer base charge. The composite shear tie includes a shear-tie web, a first shear-tie flange extending from a first side of the shear-tie web, a second shear-tie flange extending from a second side of the shear-tie web, and a first shear-tie tab extending from an end of the first side of the shear-tie web. The stringer includes a stringer web, a first stringer flange extending from a first side of the stringer web, and a second stringer flange extending from a second side of the stringer web. The first stringer flange is stitched to and integrated with the stringer base charge and the skin. Further, the first shear-tie flange is stitched to and integrated with the first stringer flange.

A skin for an aircraft is configured to be disposed on a first rigid member and on a second rigid member. The second rigid member is movable with respect to the first rigid member and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member comprises first segments forming a first portion attached to the first rigid member and second segments forming a second portion attached to the second rigid member. The first and second portions are separated along a substantially linear seam in the absence of change in the distance and an orientation between the first rigid member and the second rigid member.

A skin for an aircraft is configured to be disposed on a first rigid member and on a second rigid member. The second rigid member is movable with respect to the first rigid member and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member comprises first segments forming a first portion attached to the first rigid member and second segments forming a second portion attached to the second rigid member. The first and second portions are separated along a substantially linear seam in the absence of change in the distance and an orientation between the first rigid member and the second rigid member.

A spar assembly for an aircraft wing extends between an upper cover and a lower cover and includes linkages spaced consecutively along the length of the spar assembly, each linkage extending from an upper pivot, to a lower pivot, thereby joining upper and lower attachment structures of the spar assembly together. Each linkage includes a pair of fixed-length links pivotably connected at one end about a center pivot and pivotably connected at respective other ends. The spar assembly includes a drive bar connected to the center pivot of each of the linkages, and an actuator arranged to move the drive bar along the length of the spar assembly. When the actuator moves the drive bar along the length of the spar structure, the links in each pair of links are rotated relative to each other about the center pivot, thereby moving the upper and lower covers and warping the wing.