The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to flow control system involving different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The active flow control device or activatable flow effectors of these various embodiments are adapted to be activated, controlled, and deactivated based on signals from the sensors to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to flow control system involving different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The active flow control device or activatable flow effectors of these various embodiments are adapted to be activated, controlled, and deactivated based on signals from the sensors to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) including: a fuselage; a first pair of airfoils rotatable between a retracted position and a deployed position, the deployed position extending out from the fuselage and the retracted position extending substantially along a first portion on an exterior of the fuselage; a second pair of airfoils rotatable between a second retracted position and a second deployed position, the second deployed position extending out from the fuselage and the second retracted position extending substantially along the first portion on the exterior of the fuselage; and a rudder foldable against the fuselage in a pre-deployment position.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) including: a fuselage; a first pair of airfoils rotatable between a retracted position and a deployed position, the deployed position extending out from the fuselage and the retracted position extending substantially along a first portion on an exterior of the fuselage; a second pair of airfoils rotatable between a second retracted position and a second deployed position, the second deployed position extending out from the fuselage and the second retracted position extending substantially along the first portion on the exterior of the fuselage; and a rudder foldable against the fuselage in a pre-deployment position.

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 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.

An embodiment is an aircraft, including at least a fuselage, a tail rotatably coupled to the fuselage, the tail coupled at an aft of the fuselage, and a tail actuator coupled to the fuselage and the tail, the tail actuator to transition the tail between an extended position and a retracted position.

An embodiment is an aircraft, including at least a fuselage, a tail rotatably coupled to the fuselage, the tail coupled at an aft of the fuselage, and a tail actuator coupled to the fuselage and the tail, the tail actuator to transition the tail between an extended position and a retracted position.

A chine spoiler system enhances aircraft wing stall recovery characteristics while optimizing a maximum lift coefficient (CLMAX) of an aft-swept wing on an aircraft having an engine nacelle mounted below the wing. The system includes a chine located on a surface of the nacelle; the chine is configured to generate a vortex at high angles of attack. The vortex passes over an upper surface of the wing, favorably influencing inboard wing aerodynamics to delay airflow separation from the wing, in advance of a stall. The vortex increases CLMAX, but also creates a nose-up pitching moment on an aft-swept wing, which degrades stall recovery. A chine spoiler system module is configured to render the chine ineffective at predetermined wing flap configurations and angles of attack (typically post CLMAX) to balance the objectives of achieving high pre-stall CLMAX, while providing a nose-down pitching moment increment for improved stall recovery.

A chine spoiler system enhances aircraft wing stall recovery characteristics while optimizing a maximum lift coefficient (CLMAX) of an aft-swept wing on an aircraft having an engine nacelle mounted below the wing. The system includes a chine located on a surface of the nacelle; the chine is configured to generate a vortex at high angles of attack. The vortex passes over an upper surface of the wing, favorably influencing inboard wing aerodynamics to delay airflow separation from the wing, in advance of a stall. The vortex increases CLMAX, but also creates a nose-up pitching moment on an aft-swept wing, which degrades stall recovery. A chine spoiler system module is configured to render the chine ineffective at predetermined wing flap configurations and angles of attack (typically post CLMAX) to balance the objectives of achieving high pre-stall CLMAX, while providing a nose-down pitching moment increment for improved stall recovery.