Abstract: Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has an elastically deformable skin defining a first surface. The trailing edge has a first end to be fixed to the wing and a second end opposite the first end that is to move relative to the first end. A flap is movably coupled to the second end of the trailing edge. The flap is movable between a stowed position and a deployed position. The trailing edge is to elastically elongate when the flap moves from the stowed position to the deployed position and the trailing edge is to elastically collapse when the flap moves from the deployed position to the stowed position.

Abstract: An aircraft emergency landing stability system includes an aircraft, including a fuselage and landing gear, and a blister projecting downwardly from a fuselage-underside surface of the fuselage proximate to a nose of the fuselage. The blister locates a secondary contact surface of the aircraft forward of a center of gravity of the aircraft to mitigate a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

Abstract: An aircraft emergency landing stability system includes an aircraft, including a fuselage and landing gear, and a blister projecting downwardly from a fuselage-underside surface of the fuselage proximate to a nose of the fuselage. The blister locates a secondary contact surface of the aircraft forward of a center of gravity of the aircraft to mitigate a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

Abstract: An aircraft emergency landing stability system includes an aircraft a fuselage and landing gear, and a landing stability apparatus coupled to the fuselage, wherein the landing stability structure mitigates a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

Abstract: An improved performance propeller employs a single propeller blade having an axis of rotation and a centripetal force about the axis. A pitch control unit is mounted opposite the single propeller blade and has a compensating centripetal force with respect to the single propeller blade about the axis.

Abstract: An aircraft emergency landing stability system includes an aircraft a fuselage and landing gear, and a landing stability apparatus coupled to the fuselage, wherein the landing stability structure mitigates a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

Abstract: Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has an elastically deformable skin defining a first surface. The trailing edge has a first end to be fixed to the wing and a second end opposite the first end that is to move relative to the first end. A flap is movably coupled to the second end of the trailing edge. The flap is movable between a stowed position and a deployed position. The trailing edge is to elastically elongate when the flap moves from the stowed position to the deployed position and the trailing edge is to elastically collapse when the flap moves from the deployed position to the stowed position.

Abstract: An airfoil may include a leading edge and a shape control mechanism. The leading edge may include a flexible leading edge skin having a first end, a second end, and an arc length defined therebetween. The shape control mechanism may be attached to the flexible leading edge skin at a plurality of support locations and may transition the flexible leading edge skin from a first shape having a first curvature profile to a second shape having a second curvature profile different than the first curvature profile without a change in the arc length.

Abstract: Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has a flexible skin defining a first surface. The example apparatus also includes a flap movably coupled to the trailing edge. The flap defines a second surface. The first surface and the second surface form a substantially continuous surface when the flap is in a stowed position and when the flap is in a deployed position.

Abstract: A mechanism for changing a shape of a leading edge of an airfoil may include a first rib and a second rib. The first rib may include a plurality of first rib segments. The first rib may move between a first folded shape and a first extended shape. The second rib may include a plurality of second rib segments. The second rib may move between a second folded shape and a second extended shape. An actuator may be coupled to the first rib, the second rib, or both, to move the first rib, the second rib, or both, between their respective folded and extended shapes.

Abstract: A mechanism for changing a shape of a leading edge of an airfoil may include a first rib and a second rib. The first rib may include a plurality of first rib segments. The first rib may move between a first folded shape and a first extended shape. The second rib may include a plurality of second rib segments. The second rib may move between a second folded shape and a second extended shape. An actuator may be coupled to the first rib, the second rib, or both, to move the first rib, the second rib, or both, between their respective folded and extended shapes.

Abstract: An improved performance propeller employs a single propeller blade having an axis of rotation and a centripetal force about the axis. A pitch control unit is mounted opposite the single propeller blade and has a compensating centripetal force with respect to the single propeller blade about the axis..

Abstract: An airfoil may include a leading edge and a shape control mechanism. The leading edge may include a flexible leading edge skin having a first end, a second end, and an arc length defined therebetween. The shape control mechanism may be attached to the flexible leading edge skin at a plurality of support locations and may transition the flexible leading edge skin from a first shape having a first curvature profile to a second shape having a second curvature profile different than the first curvature profile without a change in the arc length.

Abstract: A three-dimensional vision system, device, and methods using the same are disclosed. The system or device includes an image device capable of capturing a plurality of sequential individual or scanned images of a field-of view, a buffer that stores the images for a predetermined time delay, first and second image stabilizers coupled to the buffer, and a display. The predetermined time delay signals the buffer to transmit an older image and a newer image, sequentially separated in time by the predetermined time of the predetermined time delay. The display is coupled to the first and second image stabilizers to present the images to a viewer in a format that enables the viewer to see a three-dimensional image. At least one of the first and second image stabilizers adjust the orientation of either the older image or the newer image to correspond to the orientation of the other image.

Abstract: An aircraft may include a pair of wings. A forward swept winglet may be attached proximate to a wing tip of each wing. The forward swept winglet may include a leading edge and a trailing edge. The leading edge of each winglet may extend from the wing at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the aircraft.

Abstract: A system and method for cargo handling is provided. The system includes a transport vehicle including a cargo bay capable of housing a plurality of cargo containers, and a loading dock for coupling to the cargo bay. The system also includes at least one railcar and pylons positioned along a floor of the cargo bay. A predetermined number of pylons are operable to elevate and lower a cargo container within the cargo bay. The present invention also provides a railcar for transporting cargo containers, as well as an apparatus for positioning at least one cargo container within a transport vehicle. The present invention also provides a system for aligning a loading dock and a transport vehicle that includes a mechanism for adjusting the height of the transport vehicle or loading dock, or a plurality of engagement members that are capable of aligning the loading dock and transport vehicle.

Abstract: A rotor blade including a root attachable to a rotor hub. The blade includes a tip and one or more channels aligned within the blade generally between the root and the tip. Each channel has a sealed first end and a second end vented to outside the blade. The channel(s) are vented to one or more exterior surfaces of the blade through one or more apertures in the exterior surface(s).

Abstract: An aircraft may include a pair of wings. A forward swept winglet may be attached proximate to a wing tip of each wing. The forward swept winglet may include a leading edge and a trailing edge. The leading edge of each winglet may extend from the wing at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the aircraft.

Abstract: An aircraft including a space frame fuselage structure. A plurality of panels are connected with the structure and configured to form a skin over the structure. The panels are movable relative to one another so as to prevent loading of the structure from inducing loading in the skin.

Abstract: A method to control a device may include forming an integrated simulation model of an actual environment in which the device is or will be operating. The integrated simulation model may be formed using pre-existing data and real-time data related to the actual environment. The method may also include presenting a simulation including a representation of the device operable in the integrated simulation model of the actual environment and allowing control of operation of the simulation of the device in the integrated simulation model of the actual environment. The method may further include controlling operation of the device in the actual environment using the simulation of the representation of the device in the integrated simulation model of the actual environment.