Abstract: An apparatus for deploying the wings of a movable-wing aircraft includes a spherical four-bar mechanism. The spherical four-bar mechanism has a first bar to which a first wing is attached, a second bar to which a second wing is attached, a third, movable bar rotatably or movably linking the first bar to the second bar at a first respective point on each bar, and a fourth bar grounding the first and second bar at a second respective point on each bar. The spherical four-bar mechanism may be mathematically optimized for space, size, and movement by a system of kinematic equations to allow the first and second wing to open at substantially the same time without colliding with one another. The wings of the aircraft may further include a mid-wing hinge with a movable stiffening spar to allow the wings to fold to a more compact size during storage.

Abstract: The present disclosure defines a morphing airfoil having a dynamic flexible skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and deflect in response to control inputs to change a lift force without separate movable control surfaces. The anisotropic skin is attached to underlying structure that is both actively controlled and passively supported. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift profile along a span of the airfoil.

Abstract: A morphing airfoil includes a dynamic flexible skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and bend in response to control inputs to change a lift force without separate movable control surfaces. A plurality of standoff mounts are attached to an inner surface of anisotropic skin. The standoff mounts include through apertures for receiving a flexible stringer. The anisotropic skin is attached to underlying structure through the flexible stringers. The flexible stringers interface with actuated position control ribs and passive compliant support ribs. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift and drag distributions along a span of the airfoil without separate control surfaces.

Abstract: The present disclosure defines a morphing airfoil having a dynamic flexible skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and deflect in response to control inputs to change a lift force without separate movable control surfaces. The anisotropic skin is attached to underlying structure that is both actively controlled and passively supported. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift profile along a span of the airfoil.

Abstract: A morphing airfoil includes a dynamic flexible skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and bend in response to control inputs to change a lift force without separate movable control surfaces. A plurality of standoff mounts is attached to an inner surface of anisotropic skin. The standoff mounts include through apertures for receiving a flexible stringer. The anisotropic skin is attached to underlying structure through the flexible stringers. The flexible stringers interface with actuated position control ribs and passive compliant support ribs. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift and drag distributions along a span of the airfoil without separate control surfaces.

Abstract: The present disclosure defines a morphing airfoil having a dynamic flexible anisotropic skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and bend in response to control inputs to change a lift force without separate movable control surfaces. The anisotropic skin is attached to underlying active and compliant structures. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift profile along a span of the airfoil.

Abstract: A morphing airfoil includes a dynamic flexible skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and bend in response to control inputs to change a lift force without separate movable control surfaces. A plurality of standoff mounts are attached to an inner surface of anisotropic skin. The standoff mounts include through apertures for receiving a flexible stringer. The anisotropic skin is attached to underlying structure through the flexible stringers. The flexible stringers interface with actuated position control ribs and passive compliant support ribs. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift and drag distributions along a span of the airfoil without separate control surfaces.

Abstract: An aircraft having an empennage rotatable about a longitudinal axis via an electric motor drive is disclosed herein. A pair of horizontal stabilizers extend from opposing sides of the rotatable empennage and are independently rotatable via electric motor drives. The rotatable empennage is operable for controlling yaw, pitch and rolling moments without a traditional vertical stabilizer and rudder system which can reduce weight as well as the radar cross section of the aircraft. This technology can also be applied to a weapon control system such missile such as a missile.