Abstract: A chum delivery device having a body with a plurality of openings, at least one open end, at least one removable cap, and one or more hook attachments. The plurality of openings of the body are configured to allow chum housed within the body to be released. The removable cap(s) is/are configured to seal the open end(s) of the body.

Abstract: A gimbal having a split design, which can be used in an assembly for actuating an aerodynamic high lift device, is described. The gimbal enables a rotating load path when a force is transferred from the actuator to the high lift device via the gimbal. In particular, the split design can include two receivers which can be coupled to posts extending from a nut. The nut can be secured to a shaft which receives a force generated by the actuator. In one embodiment, the actuator can rotate the shaft to cause the gimbal to translate along the shaft. The split design provides a more compact form factor and is lighter in weight than traditional gimbal designs.

Abstract: An example charging station for an unmanned aerial vehicle (UAV), the charging station generally including a nest and a charging device. The nest includes an upper portion and a lower portion. The upper portion defines an upper opening sized and shaped to receive a landing apparatus of the UAV, and a diameter of the nest reduces from a first diameter at the upper opening to a second diameter at the lower portion. The charging device is mounted in the nest, and includes a first contact pad and a second contact pad. The charging device is configured to apply a voltage differential across the first contact pad and the second contact pad such that the charging station is operable to charge a power supply of the UAV via the landing apparatus.

Abstract: An inner middle rotor is rotated while an inner front rotor, an inner back rotor, and an outer rotor are not rotated. The inner middle rotor is surrounded by the inner front rotor, the inner back rotor, the outer rotor, and a fuselage. After rotating the inner middle rotor while not rotating the inner front rotor, the inner back rotor, and the outer rotor, the inner middle rotor, the inner front rotor, the inner back rotor, and the outer rotor are simultaneously rotated.

Abstract: A method for assembling at least two parts includes using transparent welding using an energy input beam which travels a trajectory in a closed loop. The trajectory of the energy input beam and/or at least one parameter of the energy input beam is configured so that the weld bead has mechanical and/or geometrical characteristics that are substantially constant over all its length. A method for assembling a primary structure of an aircraft pylon which uses this assembly method to link the panels of the primary structure to one another, a primary structure of an aircraft pylon thus obtained, as well as an aircraft comprising at least one such primary structure is also described.

Abstract: An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.

Abstract: A method for deploying an inflatable slide includes increasing pressure within the inflatable slide, increasing a load in a force releasing member and a dampener, both of which are attached to the inflatable slide, in response to the increasing pressure within the evacuation slide, the load being increased at a slower rate than would occur if the dampener were not present, separating the force releasing member, and inflating the inflatable slide.

Abstract: A UAV with vertical takeoff and landing (VTOL) function having a plurality of lift propellers; a cabin engaged with a plurality of lift propellers; a water propulsion system engaged with the cabin to push the cabin in a forward direction when the cabin is at least partially immersed in water; at least one water inlet engaged with the water propulsion system; the cabin is a cargo hold or a passenger cabin. The UAV provided by the disclosure can realize vertical takeoff and landing in the water area, and fly, drive and navigate freely in the whole area.

Abstract: Aircraft spars with integrated power cells, and associated systems and methods are described. A representative aircraft wing spar includes a spar body extending in a spanwise direction, and having a plurality of apertures also extending in a spanwise direction, with individual apertures positioned to receive multiple electrical power cells.

Abstract: A support arrangement for an inflatable evacuation system may comprise an inflatable member configured to be elongated and stiffened in a longitudinal direction in response to being in an inflated condition, a protrusion extending orthogonal to a surface of the inflatable member, a tensile member attached at at least two locations to the inflatable member on opposing sides of the protrusion and being slidably engagable over the protrusion so as to maintain about equal tension in the tensile member on opposing sides of the protrusion, and a sleeve attached to the protrusion configured to maintain the tensile member laterally relative to the protrusion even as the tensile member is able to slide longitudinally.

Abstract: A device for adding a scent to a fishing lure, the device including: at least one electrode; and (i) a conductive element configured to place the fishing lure in conductive communication with the at least one electrode; and a control unit configured to activate the at least one electrode to cause the at least one electrode to impart a charge on the fishing lure via the conductive element, or (ii) a source of scented liquid; a heating mechanism; and a control unit configured to (a) activate the at least one electrode to cause the at least one electrode to impart a charge on the fishing lure, and (b) create steam from the scented liquid, wherein ions from the steam are attracted to the fishing lure when the charge is imparted on the fishing lure by the at least one electrode.

Abstract: An improved fishing lure with hanging blade is provided. The lure with hanging blade comprises a body with front hook and rear hook. Between the front hook and the rear hook, a blade hangs from the floating body. The blade is shaped to impart fish-attracting motion to the floating stickbait with hanging blade. The blade attaches to the body by a blade support pin. The blade, pin, body, and hooks are sized and positioned (i) to create fish attracting sound, and (ii) to avoid interfering with hookup with a fish. The blade can be shaped asymmetrically to impart an erratic fish-attracting motion to the floating stickbait with hanging blade as it is retrieved.

Abstract: Herein provided are methods and systems for method for transmitting data from an aircraft. A communication module for transmitting data from an aircraft comprises: a physical interface for removably coupling the communication module to an aircraft communication system which obtains the data; a data interface for obtaining at least one message for transmission from the aircraft communication system, the at least one message based on the data; and at least one radio for transmitting the at least one message via at least one antenna.

Abstract: A fishing lure of the present invention includes a body component and a hook component, wherein one end of the hook component is integral with the body component and extends therefrom. In addition, the fishing lure includes an inventive through-line element wherein a fishing line can be threaded through the through-line element and attached directly to the hook component. In preferred embodiments, the inventive fishing lure can eliminate the need for an eyelet when securing a fishing line to the fishing lure.

Abstract: A fly/drive vehicle has a road riding condition and a flying condition, and is easily convertible between the road riding condition and the flying condition. The vehicle includes a body with a passenger compartment and a drive compartment, at least one steered wheel and at least one driven wheel, and a propulsion propeller. The propulsion propeller has a central propeller base projecting outside a longitudinal end of the vehicle, and two propeller blades hinged to the central base. In the flying condition, the propeller blades are in an operative spread-out position, in which they extend substantially in line with each other substantially perpendicular to the propeller's rotation axis. In the road riding condition, the propeller blades are hinged about substantially vertical hinge axes to be directed more parallel to the longitudinal direction.

Abstract: A first embodiment includes a circuit based unmanned aerial vehicle (UAV) including at least one enclosed air duct vertical z-force circuit, at least one enclosed air duct lateral y-force circuit, and at least one enclosed air duct longitudinal x-force circuit whereby each circuit includes a plurality of fans within respective fan tunnels and a plurality of rotational cylinders within archways. The UAV utilizes a magnus effect at strategic points along each respective circuit to apply navigational force thereon. A second embodiment includes a circuit based unmanned aerial vehicle (UAV) including a first and second air duct circuit joined at a medial trunk. Each circuit includes a plurality of fans within respective fan tunnels and a plurality of rotational cylinders within archways. The second embodiment also utilizes the magnus effect at strategic points along each respective circuit to apply navigational force thereon.

Abstract: A taxi drive system is disclosed that provides motive force to wheels of an aircraft. The motive force is transferred by a motor powered continuous track (e.g., belt, chain, or other flexible transmission element) directly to the wheel(s) of an aircraft. The system is carried by the landing gear of the aircraft, and is placed in engagement with an aircraft wheel with sufficient force to allow for the track to drive the aircraft wheel. The taxi drive system includes a separate motor from the main aircraft engines so that the aircraft may be taxied while the main engines are shutdown or at idle.

Abstract: The Curtis Protocol, an aircraft control interface, is provided. The Curtis Protocol standardizes the division and selection of aircraft flight regimes and flight modes within the selected flight regime.

Abstract: A fishing rod holder system for easily transporting, storing, and/or using fishing rods, including one or more rod holding members releasably mountable to receiving member affixed to a separate structure. The one or more rod holding members can be attachable/detachable and swivelable/rotatable about the receiving member. In some embodiments, the positions of the one or more rod holding members can be fixed or adjustable with respect to the receiving member. Further, the rod holding members are substantially hollow tubes for receiving the handle of a fishing rod, wherein the rod holding members may include various configurations of notches and/or slots for engaging with the fishing rod/reel.

Abstract: This disclosure is directed to an unmanned aerial vehicle (“UAV”) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a wing. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon. In this vertical flight configuration, the UAV may perform vertical flight or hover. During the vertical flight, the UAV may cause the wing to extend outward via the pivots such that the wing segments become positioned substantially parallel to one another and the wing resembles a conventional fixed wing. With the wing extended, the UAV assumes a horizontal flight configuration that provides upward lift generated from the wing.