Northrop Grumman Systems Corporation

Lockheed Martin Corporation

Kendall G Young

Steven Louis Pauletti

David Eugene Sherrill

Douglas William Leggett

Joseph A Simon

Brent N McCallum

Robert S Cascella

Chris A Frangos

Kevin D Edge

Phil S Zimmerman

Ron L Stroud

Todd A Williams

George Louis Conway, Jr

A method for maintaining a dynamic reference repository within an enterprise architecture domain, comprises discovering pertinent input(s) to the dynamic reference repository. These newly discovered pertinent inputs are then retrieved to the dynamic reference repository. After retrieval, the pertinent input(s) to the dynamic reference repository are managed and distributed within the enterprise architecture domain.

Dynamic reference repository

A contra-bevel driven control mechanism repositions a control surface in a fluid environment such as an aerodynamic or hydrodynamic environment. This involves mechanically coupling an airfoil and a control surface. The control surface may pivot about a spanwise axis between upwardly deflected and downwardly deflected positions. A forward beveled rotor mounted to the airfoil and an aft beveled rotor mounted to the control surface counter rotate. The forward beveled rotor rotates about a forward chordwise axis within the airfoil while the aft beveled rotor rotates about an aft chordwise axis within the control surface. The angular rotation between the forward beveled rotor and the aft beveled rotor deflects the aft beveled rotor and the aft chordwise axis within the control surface. Additionally, this method allows the control surface to be deflected with maximum mechanical advantage when the control surface is fully deflected.

Contra-bevel driven control surface

Amethod for constructing a composite structure is disclosed. The method comprises four steps. Step one calls for coupling a flexible layer to a base, where the flexible layer has a working surface and an underside surface. Step two requires coupling at least one support element to the underside surface of the flexible layer. The next step calls for coupling at least one adjustable element to the support element for adjusting the position of the flexible layer. The last step requires configuring the flexible layer to a configuration suitable for constructing the composite structure. More specifically, the flexible layer may have internal reinforcing elements for added strength and durability.

Method for constructing a composite structure

A subdermally-reinforced elastomeric transition is provided in which an elastomeric skin is attached to a plurality of subdermal supporting members that engage subdermal reinforcing members. The reinforcing members may be rods or support rails which the supporting members engage. The supporting members may be attached to the elastomeric skin in an orientation that is perpendicular to a direction of strain of the skin and may have a plurality of holes or slots for receiving the reinforcing members. Alternatively, the supporting members may be oriented to be parallel to the direction of strain of the skin, the reinforcing members being located substantially within the supporting members.

Subdermally-reinforced elastomeric transitions

A conformal aircraft bay having a single aperture or gap formed by doors with abutting edge portions being located side-by-side while the doors are in a closed position, the doors are structured to open to access the bay with the abutting edge portions moving apart from each other, and each door having an elastomeric transition closing the gaps between the abutting edge portions when the doors are closed.

Single aperture conformal aircraft bays

A flexible structural frame ( ) includes a structure ( ) having a passage ( ), the walls ( ) of the passage ( ) defining an opening ( ). The flexible structural frame ( ) also includes a piece of elastomeric material ( ) that has a first surface ( ) and a second surface ( ). The first surface ( ) of the elastomeric material ( ) is coupled to at least one of the walls ( ) of the passage ( ). The flexible structural frame ( ) further includes at least one rigid member ( ) coupled to the elastomeric material ( ) and at least one tension bearing member ( ) coupled to the rigid member ( ), such that the elastomeric material ( ) is compressed when the tension applied to the tension bearing member ( ) increases.

Flexible structural frame

A flight control system provides a maximized mechanical advantage when the load of the airstream on the airfoil is also at a maximum. A control surface is pivotally mounted for movement through a range of positions between a neutral position at which airstream load thereon is a minimum and upwardly and downwardly deflected positions, the airstream load being a maximum in either of the deflected positions. An operator mechanism for moving the control surface between the upwardly and downwardly deflected positions includes a rotor mounted on the airfoil for rotation about a chordwise extending rotary axis and has a horn member with a terminal end offset from the rotary axis. The terminal end of the horn member is slidably engaged with the guide track and an actuator rotates the rotor and by reason of the slidable engagement of the horn member with the guide track moves the control surface.

Aerodynamic control surface system

An apparatus (,) for constructing a composite structure (,) is disclosed. The apparatus (,) comprises a flexible layer (,), which has a working surface (,) and an underside surface (,), coupled to a base (,). At least one support element (,) is coupled to the underside surface (,) of the flexible layer (,), and at least one adjustable element (,) is coupled to the support element (,) for adjusting the position of the flexible layer (,). More specifically, the flexible layer (,) may have internal reinforcing elements (,) for added strength and durability.

Apparatus for constructing a composite structure

In accordance with the present invention, there is provided an aerodynamic control device for use with an aerodynamic lifting member. The lifting member is defined by a horizontal reference plane disposed therethrough. The control device is provided with at least one support rotor extending from the lifting member. The support rotor is sized and configured to rotate about a rotor axis of rotation which is disposed generally parallel to the horizontal reference plane. The support rotor has an inboard segment which is disposed along the rotor axis of rotation and in rotational communication with the lifting member. The support rotor has an outboard segment disposed off-set from the rotor axis of rotation. The control device is further provided with a control device body which is engaged with the outboard segment of the support rotor. The control device body is sized and configured to translate generally orthogonal to the horizontal reference plane in response to rotation of the support rotor.

Rotor driven edge

In accordance with the present invention, there is provided a structural transition system for use between an aerodynamic lifting member and an aerodynamic control device attached thereto. The aerodynamic lifting member has an indenture formed therein which is defined by a first shoulder portion. The control device has a first end and is disposed within the indenture with the first end adjacent the first shoulder portion. The control device is sized and configured to rotate about a control device axis of rotation for deflecting the control device relative to the lifting member. The structural transition system is provided with a torque transfer element disposable between and in mechanical communication with the first shoulder portion and the first end. The torque transfer element is sized and configured to deform in response to deflection of the control device. The structural transition system is further provided with at least two of support elements distributed between the first shoulder portion and the first end. The support elements are in mechanical communication with the torque transfer element. The support elements are sized and configured to incrementally rotate generally about the control device axis of rotation in response to deformation of the torque transfer element.

Low density flexible edge transition

In accordance with the present invention, there is provided an aerodynamic control surface apparatus for use with a wing assembly having a wing trailing edge. The control surface apparatus has an inboard section defined by a cordwise inboard side, a first trailing edge side, and a first tapering edge side disposed between the inboard and the fist trailing edge sides. The inboard section has an axis of rotation generally about the cordwise inboard side. The control surface apparatus further has an outboard section defined by a cordwise outboard side, a second trailing edge side, and a second tapering edge side disposed between the outboard and the second trailing edge sides. The outboard section has an axis of rotation generally about the cordwise outboard side. The control surface apparatus further has at least one adjustable spanwise member rotatably attached to the first and second tapering edge sides of the inboard and outboard sections. The spanwise member is movable relative to the wing assembly in response to rotation of the inboard and outboard sections.

Adaptive control surface apparatus

A deformable aircraft door which is movable between open and closed positions and is adapted to substantially maintain contact with the door frame for reducing a perimeter gap between the door and the door frame. The aircraft door comprises an edge portion which is formed to engage the door frame, and an elastic portion which is attached to the edge portion. The elastic portion is selectively expandable and contractible for permitting movement of the edge portion relative to the door frame when the aircraft door is in the closed position so as to substantially maintain contact between the edge portion and the door frame despite changes in the geometry of the door frame.

Growing community of inventors

Crowley, TX, United States of America

Kendall G Young