A variable area fan nozzle actuation (VAFN) system is disclosed. The VAFN system may include an electrohydrostatic actuator (EHA) arranged to translate a VAFN panel relative to a translating sleeve. An electrical coupling may extend between a translating sleeve associated with the VAFN system and the fixed structure. The electrical coupling may be movable so that as the translating sleeve and fixed structure move relative to each other, power may be provided to the EHA by a wiring harness extending across the space between the translating sleeve and the fixed structure and connecting the EHA to an EHA power source.

A variable area fan nozzle actuation (VAFN) system is disclosed. The VAFN system may include an electrohydrostatic actuator (EHA) arranged to translate a VAFN panel relative to a translating sleeve. An electrical coupling may extend between a translating sleeve associated with the VAFN system and the fixed structure. The electrical coupling may be movable so that as the translating sleeve and fixed structure move relative to each other, power may be provided to the EHA by a wiring harness extending across the space between the translating sleeve and the fixed structure and connecting the EHA to an EHA power source.

Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.

Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.

A control system for a missile includes a plurality of control surfaces that can be arrayed across a surface of the missile body, and a controller connected to the control surfaces to selectively move the control surfaces between an aerodynamic stowed position where the control surfaces conform to the surface of the body, and a deployed control position removed from the aerodynamic stowed position where the control surfaces extend from the surface of the body to interact with airflow over the body. The control surfaces are made of a material that includes a shape-memory alloy. Heating the control surfaces causes the shape-memory alloy to move the control surfaces from the aerodynamic stowed position to the deployed control position. By selectively extending and retracting the control surfaces, the control system provides the ability to control the missile's direction of travel or to reduce roll about a longitudinal axis of the body.

A control system for a missile includes a plurality of control surfaces that can be arrayed across a surface of the missile body, and a controller connected to the control surfaces to selectively move the control surfaces between an aerodynamic stowed position where the control surfaces conform to the surface of the body, and a deployed control position removed from the aerodynamic stowed position where the control surfaces extend from the surface of the body to interact with airflow over the body. The control surfaces are made of a material that includes a shape-memory alloy. Heating the control surfaces causes the shape-memory alloy to move the control surfaces from the aerodynamic stowed position to the deployed control position. By selectively extending and retracting the control surfaces, the control system provides the ability to control the missile's direction of travel or to reduce roll about a longitudinal axis of the body.

An actively stabilized refueling drogue including a drogue canopy, drogue straits extending from the drogue canopy, a coupling body, a coupling shroud, a system of fins, and actuators. The coupling body is for connecting a flexible refueling hose to a receiver aircraft fuel intake, so that in-air refueling may occur The drogue struts terminate at the coupling body. The coupling shroud covers the coupling body. The system of fins is for stabilization of the drogue and is attached to the coupling shroud. The actuators are for actuating the fins to achieve aerodynamic stabilization. The actuators are manufactured from a solid state shape memory alloy, such that the fins may be actuated by applying thermal energy to the actuators.

An actively stabilized refueling drogue including a drogue canopy, drogue straits extending from the drogue canopy, a coupling body, a coupling shroud, a system of fins, and actuators. The coupling body is for connecting a flexible refueling hose to a receiver aircraft fuel intake, so that in-air refueling may occur The drogue struts terminate at the coupling body. The coupling shroud covers the coupling body. The system of fins is for stabilization of the drogue and is attached to the coupling shroud. The actuators are for actuating the fins to achieve aerodynamic stabilization. The actuators are manufactured from a solid state shape memory alloy, such that the fins may be actuated by applying thermal energy to the actuators.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A torque tube door and related method steps may include a door coupled to an inboard wing flap, such that the door is movable with the flap to selectively cover and uncover a torque tube opening in an aircraft fuselage.