Abstract: A hinge mechanism for hingedly coupling a flight control member having a top surface to an aircraft component having a top surface includes a first hinge member pivotably coupled to the flight control member about a first axis and slidingly coupled to the aircraft component and a second hinge member pivotably coupled to the aircraft component about a second axis and slidingly coupled to the flight control member. The first hinge member is pivotably coupled to the second hinge member about a central axis. The first hinge member and the second hinge member are configured to cooperatively facilitate movement the flight control member relative to the aircraft component between at least a stowed position and a deployed position.

Abstract: Disclosed are various embodiments for reducing or eliminating the nose-down pitching moment during water landings of amphibious aircraft when the landing gear is in the down position. Shielding struts forward of the wheels generate hydrodynamic lift and reduce hydrodynamic drag in order to alter the pitching moment about the aircraft center of mass.

Abstract: A stabilizer system for an ejection seat may comprise a collapsible support structure configured to be coupled to a seat back or a seat bucket of the ejection seat, an airfoil coupled to the collapsible support structure, and a deployment system operatively coupled to the collapsible support structure and configured to expand the collapsible support structure.

Abstract: A landing apparatus for a reusable launch vehicle is provided, including a landing leg pivotably mounted at one end to the reusable launch vehicle, for example, to a propellant tank part, and mounted at the other end to the propellant tank part by a detaching means such as a pyro bolt for example, a cover mounted to an outside of the landing leg along a longitudinal direction of the landing leg, and a leg landing plate mounted to a distal end of the landing leg and relatively pivotable with respect to the landing leg by its own weight when the other end of the landing leg is separated from the propellant tank part.

Abstract: Aircraft passenger seat device includes an aircraft seat row, comprising having a mounting unit, and three or more neighboring seat areas. In the two outer seat areas, an aircraft seat with a seat bottom and a backrest is mounted to the mounting unit. In the middle seat area a backrest base body is mounted to the mounting unit. In one or more operating states a detachable center console is detachably mounted to the mounting unit in the middle seat area forming a separation between the two outer seats. The backrest base body has one or more functional elements on its rear side provided for the use by a passenger sitting behind.

Abstract: An airfoil surface skin, comprising a network of a solid material, embedded in a base of deformable solid material. Fluid pressure applied to the interface between the network and the surrounding embedding material, opens an internal network of channels by viscous peeling of the surrounding solid from the network. The network is offset from the centerline the surround material, such that pressure driven viscous flow through the narrow channels generates two types of deformation of the skin—an in-plane elongation and a curvature of the skin plane itself. The shape of the internal solid core element and its material, and the material of the encompassing solid are chosen to achieve a desired integral structural rigidity. The injected fluid pressure determines the extent of extension and bending. Use of this skin enables shape amending airfoils having reduced drag compared with similar airfoils having conventional flap mechanisms.

Abstract: Example implementations relate to simple to manufacture flap assemblies with failsafe jam-resistant flap tracks. An example flap assembly may include a track having an elongate structure and a flap carriage configured to move along a length of the track. The track is configured to couple to an aircraft wing and the flap carriage includes a primary roller and a pair of secondary rollers configured to secure the flap carriage to the track. A top portion of the flap carriage is configured to couple to a flap such that movement of the flap carriage along the length of the track enables movement of the flap relative to the aircraft wing.

Abstract: A simple and lightweight system for discharging water that can flow out through an orifice in an insulation blanket lining the walls of a fuselage of a transport vehicle such as an aircraft. The blanket has an impermeable collection plate having at least partially the shape of a channel, container or the like for collecting and discharging condensation water under the effect of gravity through an orifice.

Abstract: A seat track assembly is disclosed. The seat track assembly includes an elongate titanium crown, an elongate carbon-fiber reinforced polymer (CFRP) flange, and an elongate CFRP base. The elongate titanium crown is configured to removably secure a plurality of seats to the seat track assembly. The elongate CFRP flange is configured to support the elongate titanium crown. The elongate CFRP base has a top, two sidewalls extending vertically from opposing sides of the top, and two bottom flanges each extending laterally outward from a corresponding sidewall of the two sidewalls. A fastener is insertable through aligned holes defined by the elongate titanium crown, the elongate CFRP flange, and the elongate CFRP base to mechanically fasten the elongate titanium crown, the elongate CFRP flange, and the elongate CFRP base to each other.

Abstract: An assembly for moving a tip of an airfoil (e.g., an aircraft wing tip) relative to a fixed body of the airfoil. The assembly includes a linear actuator configured to pivotally attach to both the fixed body of the airfoil and the movable tip of the airfoil, such that the linear actuator is configured to extend between a first pivotal attachment on the fixed body and a second pivotal attachment on the movable tip. The linear actuator is configured to repeatedly move the tip of the airfoil from an unfolded position to a folded position, wherein throughout such movement the linear actuator is configured to pivot about both the first and second pivotal attachments.

Abstract: A wing for an aircraft is disclosed having a main wing, a slat, and a connection assembly movable connecting the slat to the main wing, wherein the connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing comprising a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail, and wherein the roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track.

Abstract: A large animal lifting and moving apparatus includes a frame having a front end and a rear end, the frame, a drive shaft rotatably coupled to the frame, a drive motor coupled to the frame and operatively coupled to the drive shaft; the drive motor selectively powered by a power source, and one or more roller chains coupled to the drive shaft. The frame is structured to support a large animal between the front end and the rear end and structured to be moved during operation of the large animal lifting and moving apparatus. When the drive motor is powered by the power source, the drive motor drives the drive shaft and the roller chains coupled to the drive shaft.

Abstract: A modular unmanned aerial vehicle (UAV) system comprises a body module, a rotor module, and a wing module. The body module includes a flight controller and a power distribution device. The body module is releasably attachable to the rotor module or the wing module, and the body module is releasably attachable to the rotor module. The rotor module includes one or more motors and electronic speed controllers (ESCs), while the wing module includes a wing having a flap, elevator, aileron, or rudder. Various UAV configurations can be formed from the body module, the rotor module, and the wing module. Each configuration includes different advantages for flight time, distance, battery life, and payload capacity. A UAV can be configured to a particular configuration to optimize parcel delivery.

Abstract: A rotorcraft seating assembly includes a seat base supporting a seat bucket, the seat base having left- and right-side panel portions. Each side panel portion has a linear bucket guide channel set into its inside face (including an upper portion for adjusting the seat bucket relative to the seat base for pilots of varying heights, and a lower portion for energy attenuation (EA) stroking in response to a crash event) and a bucket guide slot set into its outside face (including a linear upper portion corresponding to the range of adjustment of the seat bucket and a curved lower portion allowing the seat bucket to translate forward and away from the seat base during EA stroking). The curved outer bucket guide slot allows for the required EA stroking distance within a minimal vertical space between the seat bucket and the flight deck floor.

Abstract: An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, a plurality of arms extending outward from the chassis, a plurality of rotors, and a support structure mounted atop the chassis. Each rotor is mounted to a corresponding arm of the plurality of arms, is in communication with the control system, and is operable to generate lift under control of the control system. The support structure includes a plurality of arched struts that connect to one another at an apex region of the support structure.

Abstract: An example carriage is configured for mounting to an unmanned aerial vehicle. The carriage generally includes a housing assembly configured for mounting to the unmanned aerial vehicle, a movable grip mounted to the housing assembly for movement between a capturing position and a releasing position, a latch device, and a driver. The latch device has a latching state and an unlatching state, is configured to retain the movable grip in the capturing position when the latch device is in the latching state, and is configured to permit movement of the movable grip from the capturing position to the releasing position when in the unlatching state. The driver is operable to transition the latch device from the latching state to the unlatching state.

Abstract: This disclosure relates to system and method for managing an insect swarm using a plurality of drones. The method includes detecting an insect swarm. The method may further include tracking a movement of the insect swarm. The method further includes communicating, with remaining of the plurality of drones, to dynamically align in a position based on the tracking so as to make a drone formation. The method further includes magnetizing, by at least some of the plurality of drones, one or more drone couplers for electromagnetically coupling the at least some of the plurality of drones with each other as per the drone formation. The method further includes casting, by each of the plurality of drones, a net to trap insects in the insect swarm. The method further includes supplying, by each of the plurality of drones, a high voltage to the net to decapacitate the insects.

Abstract: A ballistically launched foldable multirotor vehicle has a central body frame. A battery is located in an upper vertical location of the vehicle and positions a center of mass of the vehicle to provide aerodynamic stability during a launch. Fins are attached to the central body frame such that aerodynamic forces on the fins shift an aerodynamic center (AC) of the vehicle downward below the center of mass of the vehicle. Three or more foldable arms are attached to the central body frame via a hinge and exist in two states—a closed state where the foldable arms are parallel to a central body axis, and an open state (after launch) where the foldable arms extend radially outward perpendicular to the central body axis. Rotors mounted to each foldable arm are controlled by a motor to enable flight.

Abstract: A rotor system for an aircraft is described and includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast. The drive system includes at least one electric motor for providing rotational energy to a motor shaft; and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the motor shaft and providing rotational energy to the rotor mast via a rotor shaft.

Abstract: A supply drop assembly for delivering one or more payloads via an aerial vehicle, the assembly comprising a payload body configured to receive a payload; and one or more wings attached to the payload with a connector or integral to the one or more wings; wherein when the supply drop assembly is dropped from the aerial vehicle, the one or more wings start rotating thereby generating lift and slowing the rate of descent of the payload as it falls downwards to a recipient.