Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.

Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.

A morphing aerofoil comprising: a leading edge; a trailing edge; and upper and lower surfaces extending between the leading and trailing edges. An upper thermal actuation member is provided proximate the upper surface; and a lower thermal actuation member is provided proximate the lower surface opposite the upper thermal actuator. The upper and lower thermal actuation members have different thermal expansion coefficients and are positioned such that they cause the trailing edge to deflect when they expand or contract by different amounts in response to a change in ambient temperature, thereby changing a camber of the aerofoil.

A morphing aerofoil comprising: a leading edge; a trailing edge; and upper and lower surfaces extending between the leading and trailing edges. An upper thermal actuation member is provided proximate the upper surface; and a lower thermal actuation member is provided proximate the lower surface opposite the upper thermal actuator. The upper and lower thermal actuation members have different thermal expansion coefficients and are positioned such that they cause the trailing edge to deflect when they expand or contract by different amounts in response to a change in ambient temperature, thereby changing a camber of the aerofoil.

Processes for real-time drag optimization control for aeroelastic wing structures are disclosed. Adaptive reconfiguration of aircraft control surfaces by an online real-time drag optimization control approach to reduce or minimize drag may reduce the amount of fuel that is consumed by the aircraft during flight. The input data may be obtained from sensor information pertaining to the wing deflection and aircraft state information. The optimization approach may compute an optimal solution of the distributed flight control surface deflections that are integrated in a flight path angle flight control system.

A deformable aerospace structure includes a first layer and a second layer spaced from the first layer and defining a space therebetween. The space includes one or more reinforcement elements extending between the first layer and the second layer. The ends or portions of the reinforcement element(s) proximate to the first layer are connected thereto and ends or portions of the reinforcement element(s) proximate to the second layer are moveable with respect to ends or portions of adjacent reinforcement element(s) proximate to the second layer.

A deformable aerospace structure includes a first layer and a second layer spaced from the first layer and defining a space therebetween. The space includes one or more reinforcement elements extending between the first layer and the second layer. The ends or portions of the reinforcement element(s) proximate to the first layer are connected thereto and ends or portions of the reinforcement element(s) proximate to the second layer are moveable with respect to ends or portions of adjacent reinforcement element(s) proximate to the second layer.

An aircraft wing trailing edge section assembly is disclosed having an upper skin structure providing an upper external aerodynamic trailing edge surface, a lower skin structure providing a lower external aerodynamic trailing edge surface, and a movement mechanism including a first portion attached to an internal surface of the upper skin structure, a second portion attached to an internal surface of the lower skin structure, and a rotationally mounted connector member connected between the first and second portions, such that rotational movement of the connector member causes simultaneous movement of both first and second portions and therefore both upper and lower skin structures, such that the camber of the trailing edge section is changed. An aircraft wing section assembly, an aircraft and methods of operating an aircraft are disclosed.

An airfoil member includes an airfoil skin, a trailing edge member, a spar member extending in a lateral direction within the airfoil skin, and an airfoil member morphing device configured to modify a shape of the airfoil skin. The device includes at least one motor or actuator, an airfoil skin support sheet attached to the spar member and corrugated to define alternating upper and lower lines of contact with inner surfaces of the rearward upper skin and rearward lower skin. Actuating bands extend from the spar member through alternating upward and downward sections of the airfoil skin support sheet and are operably connected to the at least one motor or actuator. The airfoil member morphing device is configured to independently adjust a camber, twist, and chord length of the airfoil member.

An airfoil member includes an airfoil skin, a trailing edge member, a spar member extending in a lateral direction within the airfoil skin, and an airfoil member morphing device configured to modify a shape of the airfoil skin. The device includes at least one motor or actuator, an airfoil skin support sheet attached to the spar member and corrugated to define alternating upper and lower lines of contact with inner surfaces of the rearward upper skin and rearward lower skin. Actuating bands extend from the spar member through alternating upward and downward sections of the airfoil skin support sheet and are operably connected to the at least one motor or actuator. The airfoil member morphing device is configured to independently adjust a camber, twist, and chord length of the airfoil member.