Abstract: In one embodiment, a vertical stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a vertical orientation. The airfoil structure comprises a leading edge and a trailing edge, wherein the trailing edge is configured to form a blunt shaped edge. The airfoil structure further comprises a root end and a tip end, wherein the airfoil structure is tapered from the root end to the tip end. The airfoil structure is also cambered. Finally, the airfoil structure is further configured to be mounted with a rotor, and is also further configured to house one or more internal components associated with the aircraft.

Abstract: A hierarchical integrated trust assessment system features nested subsystems. Each subsystem utilizes a trust module for validating input data to the subsystem, validating output data from the subsystem, and validating the operation of the subsystem itself. The trust module verifies the format, the authenticity, the content of the inputs to the subsystem. The scope of each trust module is minimized to the associated subsystem. Minimizing the scope of the trust module results in increased reliability of the trust module's decisions.

Abstract: According to one embodiment, an aircraft component is manufactured from a plurality of separate materials comprising a first material. The first material is physically associated with a tracking device comprising a first storage medium featuring line-of-sight accessible information and a second storage medium featuring non-line-of-sight accessible information. The line-of-sight accessible information and the non-line-of-sight accessible information each comprise information regarding the first material physically associated with the tracking device.

Abstract: A decentralized trust assessment system, comprising a neural network, a trust module, and a local subsystem, wherein the trust module controls whether a plurality of inputs to the local subsystem are trustworthy. The decentralized trust assessment system provides rotorcraft and tiltrotor aircraft with airborne systems able to detect bad and spoofed data from a wide variety of data streams.

Abstract: A cable reel restraint device comprises a cable reel, a retractable cable, first and second springs, first and second attachment interfaces, and a preload selection control. The retractable cable is configured to extend from and retract onto the cable reel. The first spring is configured to exert force for preloading the second spring, and the second spring is configured to exert force for retracting the retractable cable. The first attachment interface is coupled to the cable reel by a first spherical bearing, and the second attachment interface is coupled to the retractable cable by a second spherical bearing. Moreover, the first and second attachment interfaces are configured for being fastened to first and second attachment points. The preload selection control is configured to select a particular preload magnitude and cause the first spring to preload the second spring with a load of the particular preload magnitude.

Abstract: In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.

Abstract: In one embodiment, an apparatus may comprise: a floor panel for a rotorcraft; one or more puck fasteners in the floor panel, wherein each puck fastener comprises an attachment fitting and a plurality of internal flanges, wherein the plurality of internal flanges within each puck fastener are adjacent; and one or more seating fixtures coupled to the floor panel using the one or more puck fasteners.

Abstract: A system for image guided assembly of a structure, the structure defining an interior area accessible through at least one access opening, the interior area including at least one fastener hole. The system including a first fastening tool including an arm with first and second ends; and a support plate on the first end, the support plate including at least one connection member to securely retain a fastener therein, the at least one connection member configured to facilitate alignment of the fastener with the at least one fastener hole; an image capturing device disposed on the arm first end configured to generate a captured image of the interior area; a light source associated with the arm first end, the light source configured to generate light at the first end of the arm; and a display device located outside the interior area for displaying the captured image of the interior area.

Abstract: A component equipped with a high-visibility impact detection system. The component includes a composite layer with a minimum impact energy level known to potentially cause damage to the composite layer, a high-visibility layer covering at least a portion of the composite layer, and a top layer covering the high-visibility layer. The top layer is configured to fracture, and expose the high-visibility layer, when subjected to an impact energy level greater than or equal to the minimum impact energy level known to potentially cause damage to the composite layer.

Abstract: An aircraft comprising a pair of ducted thrusters. Each of the ducted thrusters comprises a duct surrounding a rotor assembly with a rotor hub having a plurality of rotor blades extending therefrom, wherein the plurality of rotor blades have a modulated angular distribution about a central longitudinal axis of the duct. Each of the ducted thrusters further comprises a stator assembly having a stator hub with a plurality of stator vanes extending from the stator hub to an interior surface of the duct, wherein each of the plurality of the stator vanes are angularly modulated around the stator hub such that angular spacing between pairs of adjacent vanes of the plurality of stator vanes varies for each pair of the adjacent vanes.

Abstract: In one embodiment, a rotor hub comprises a hub body, and a plurality of blade grips configured for attaching a plurality of rotor blades. The rotor hub further comprises a plurality of centrifugal force bearings coupled to the plurality of blade grips, wherein a focus of the plurality of centrifugal force bearings is aligned with a centerline of a rotor mast. The rotor hub further comprises a plurality of drive links configured to transfer torque to the plurality of rotor blades, wherein the plurality of drive links is positioned to correspond with a leading edge side of the plurality of rotor blades. The rotor hub further comprises a plurality of pitch horns configured to adjust a pitch of the plurality of rotor blades.

Abstract: Embodiments are directed to gearbox covers, mast caps, port plugs, and other coverings or lids that can be used to protect aircraft components against corrosion and contaminants. The protective coverings may be may be manufactured using three-dimensional printing or other additive manufacturing fabrication methods. The protective coverings are ultraviolet-light resistant, weather resistant, and impact resistant. The protective coverings may include a desiccant filter to reduce an aircraft component's exposure to water. The protective coverings may attach to the aircraft components using thumbscrews and may include an O-ring or gasket that creates an airtight and watertight seal.

Abstract: Embodiments are directed to adding wing extensions outboard of the engine nacelles on tiltrotor aircraft to increase cruise efficiency. By using pivoting wing extensions, the download penalty during hover operations is decreased because the wing extensions will pivot into the downwash rather than act as a barrier. Freely pivoting wing extensions will align with the local airflow during conversion mode flight, which eliminates flow separation issues. The freely pivoting wing extensions also reduce gust response by rotating out of the way of turbulence and updrafts. A trailing edge trim flap provides simple and effective control of the incidence angle for the free-pivot wing extension.

Abstract: In a first aspect, there is a rotor system for a tiltrotor aircraft, the rotor system including an upper outboard engine in a fixed location on a wing member of the tiltrotor aircraft; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position. In another aspect, there is provided a tiltrotor aircraft including a fuselage; a wing member; an upper outboard engine in a fixed location on the wing member; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position.

Abstract: In one aspect, a spinner fairing includes a base configured to be fixed relative to a hub system; a movable spinner assembly movable relative to the base; the movable spinner assembly comprising a first movable member and a second movable member. Each first and second movable member being selectively configurable between a closed position and a contracted position, in which the movable spinner assembly has a decreased shape and/or volume. In another embodiment, a spinner fairing can include at least one static member and a moveable member. In still another embodiment, a rotor head fairing assembly includes an upper housing and a lower housing coupled to a hub system; the upper housing including an upper movable member; the lower housing comprising a lower movable member. In yet another embodiment, a rotor head fairing includes at least one moveable upper housing and lower housing.

Abstract: In one aspect, there is provided a spar member for an aircraft wing including a support beam having an interior surface, an exterior surface, and opposing ends configured for an aircraft wing, the interior surface and exterior surface disposed between the opposing ends; and a first spar flange extending generally laterally from the exterior surface, the first spar flange configured for attachment with a first wing skin. The first spar flange can be an upper or lower spar flange. In some embodiments, the first spar flange is at an acute angle relative to the exterior surface of the support beam. In certain embodiments, the first spar flange is at an angle of from about 50 degrees to about 85 degrees relative to the exterior surface of the support beam.

Abstract: There is disclosed a molding assembly including a mold having a first surface and an opposed second surface. The mold defines a cavity bounded by two side walls converging toward each other from the first surface toward the second surface. Two mandrels are each removably receivable in the cavity and have a first wall, a second wall opposed to the first wall, an inner wall, and an outer wall opposed to the inner wall. The inner walls face each other and define a gap therebetween for receiving a composite material to be cured. The outer walls are angled and each slidably engage a respective one of the two side walls. A method of co-curing a stiffener and a panel is also disclosed.

Abstract: A standpipe assembly for a rotorcraft includes a slip ring positioned within the mast of the rotorcraft. The slip ring includes a stator rotationally connected to a rotor. A flexible coupling is connected to the stator and a standpipe tube is connected to the flexible coupling. The flexible coupling is capable of angular, axial, and torsional displacement.

Abstract: The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.