Abstract: Flasher fishing lures are disclosed that include a fin pivotably attached to a rear portion of the flasher. In a closed configuration, the fin may be secured within a fin recess to form a substantially flat, continuous surface with the rear portion of the flasher. And, in an open configuration, the fin may extend substantially perpendicular to the surface of the rear portion. Accordingly, a user may select a fin configuration that provides optimal side-to-side, tail kicking and/or spinning motion of the lure through the water when trolled at various speeds and in any number of fishing conditions.

Abstract: A system is provided that guides aircraft driven with landing gear wheel-mounted electric taxi drive systems without reliance on airport ground personnel to park the aircraft parallel to an airport terminal with connections to multiple passenger loading bridges, automatically docks the aircraft, and connects the multiple loading bridges to multiple forward and rear doors. Cooperative on-aircraft monitoring systems, airport docking systems, loading bridge and terminal monitoring systems, and processors are integrated to use real time information and guide the aircraft to safely maneuver into and automatically dock in a parallel orientation at a parking location with multiple aircraft forward and rear doors connected to multiple loading bridges. The system may automatically undock the aircraft and retract the loading bridges and guide the electric taxi drive system-driven aircraft out of the parking location without reliance on airport ground personnel.

Abstract: An aircraft includes at least one passenger room (3). The room has a passenger chair (5) and a bed (7). These are separate units and can be used at the same time without one unit interfering with or restricting the full range of operations of the other unit and vice versa.

Abstract: An integrated pushback guidance system and method is provided for guiding pushback travel of electric taxi system-driven aircraft. The pushback guidance system may be integrated with existing ramp monitoring systems to monitor reverse pushback travel of pilot-controlled electric taxi system-driven aircraft along an optimum pushback path from a stand to a pushback end location. Visual signals relating to pushback travel safety as the pilot drives the aircraft along the pushback path are generated in real time by the system and transmitted to a range of display devices viewable by the aircraft pilot and airport personnel responsible for guiding aircraft pushback. The pilot may be guided by visual signals on only display devices or with guidance from airport personnel also viewing the visual signals on display devices to drive the aircraft safely in reverse with the electric taxi system along the pushback path to the pushback end location.

Abstract: Example implementations may relate to door-enabled loading and release of payloads in an unmanned aerial vehicle (UAV), which could be a type of UAV in a group of UAVs that is assigned to carry out certain transport tasks. In particular, the UAV may include a fuselage having a first side and a second side, as well as a chamber formed within the fuselage and arranged to house a payload. A first door may be arranged on the first side of the fuselage, such that an opening of the first door enables loading of the payload into the chamber. And a second door may be arranged on the second side of the fuselage, such that an opening of the second door enables release of the payload from the chamber. Moreover, the UAV may include a control system configured to control flight of the UAV, and possibly opening and/or closing of door(s).

Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.

Abstract: Reactive spoilers for aircraft and associated methods. In one embodiment, a wing of an aircraft includes a leading edge, a trailing edge, and an upper surface and a lower surface between the leading edge and the trailing edge. The wing further includes a reactive spoiler disposed on the upper surface between the leading edge and the trailing edge. The reactive spoiler comprises one or more turbines configured to raise in relation to the upper surface into an airflow passing over the upper surface, and to reduce lift of a wing section behind the turbines. The turbines are configured to convert kinetic energy from the airflow into electrical energy.

Abstract: A rotorcraft including a first power plant, at least one main rotor participating at least in providing lift for the rotorcraft in the air, and at least one tail rotor carried by a tail boom, the first power plant including at least one engine. In accordance with the invention, the rotorcraft includes: at least one pusher or puller propeller independent from the at least one main rotor, the at least one pusher or puller propeller participating at least in providing propulsion or traction for the rotorcraft; a second power plant including at least one electric motor; and at least one control member configured to generate a control setpoint or instruction for controlling the at least one electric motor.

Abstract: Provided is a multicopter providing a high level of freedom in compact design, and consuming a relatively small amount of energy. The multicopter (10) includes a machine body (12), an N number of first lift generators (30) arranged on a first concentric circle (C1) centered substantially around a gravitational center (G) of the machine body (12) and in a front part and a rear part of the machine body in a bilateral symmetry, and an M number of second lift generators (70) arranged on a second concentric circle (C2) centered substantially around the gravitational center (G) of the machine body (12) and having a larger diameter than the first concentric circle (C1), and in a front part and a rear part of the machine body (12) on a central axial line (X) extending in a fore and aft direction of the machine body (12), N being greater than M.

Abstract: A fishing lure is disclosed herein with a fishing line attachment structure comprising a hook structure, and a body structure mounted on the hook structure. The body structure has a body, a threaded neck having a cylindrical portion defining a first connector, and a head defining a second connector. The head and neck define the attachment structure. The neck includes a port for receiving the fishing line and external circumferential screw threads. The head having an aperture and internal screw threads. The fishing line is adapted to pass through the aperture of the head and the port of the neck and rest on a gripping surface from where the neck integrally mounted to the body, and the head is screwed over the neck while clenching the fishing line between the gripping surface of the body and the head. The fishing lure further comprises a weed guard and bite depth control.

Abstract: Embodiments relate to reconfigurable unmanned vehicles (100). Such vehicles (100) comprise a fuselage (102) presenting a bay (118) for receiving a plurality of components (120-128), each of the plurality of components (120-128) relating to a respective entity for at least one of flight control or operation of the unmanned vehicle (100). The bay (118) comprising a bus to support communications between at least two of the plurality of components (120-128), the plurality of components (120-128) comprising a controller to determine a configuration or presence of one or more than one component of the plurality of components (120-128) when coupled to the bus.

Abstract: An aircraft includes an airframe, and a coaxial main rotor assembly including a static mast and an upper rotor assembly and a lower rotor assembly rotatable about a main rotor axis defined by the static mast. The upper rotor assembly and the lower rotor assembly are independently rotatable about the static mast. A propulsion system includes at least one propulsion source for directly driving at least one of the upper rotor assembly and the lower rotor assembly and a flight control system is operably coupled to the propulsion system. The flight control system is operable to independently control a rotational speed of the upper rotor assembly and the lower rotor assembly relative to the static mast.

Abstract: A cage for housing laboratory animals, said cage includes a bowl and a cap or cover which may be positioned on said bowl in a removable manner, wherein the cap and the bowl, with the cap positioned on the bowl, define an internal space which is closed and not accessible from the outside, wherein in the internal space a feeder is positioned, adapted to contain food adapted to feed the laboratory animals, wherein the cage is equipped with first means adapted to detect the presence and/or quantity of food in the feeder.

Abstract: An aircraft wing with a wing structure and a spoiler movable between a stowed configuration and a deployed configuration are disclosed. The spoiler includes an actuator configurable between an engaged mode and a disengaged mode. When the actuator is in the engaged mode, the actuator can restrict movement of the spoiler and move the spoiler between the stowed configuration and deployed configuration. In the disengaged mode, the actuator allows free movement of the spoiler, such that the spoiler may pop up due to reduced air pressure on the aircraft wing.

Abstract: A vortex generator, includes a vane, mountable on an aerodynamic surface of an aircraft, and an actuator that rotates the vane between a stowed position and a deployed position. The actuator includes a linear actuator, composed at least in part of a shape memory alloy (SMA), that when thermally activated facilitates rotation of the vane between the stowed position to the deployed position. Thermal activation of the SMA is caused via one or more of joule heating, conduction, and induction in response to one or more of an electronic command signal and a wireless command signal. The electronic command signal and the wireless command signal may be transmitted in response to ambient conditions, aircraft flight conditions, and aircraft mission.

Abstract: An aircraft including: a wing having a leading edge; an electric motor mounted on the wing; and an electric power cable in the wing for providing power to the electric motor, wherein the electric power cable runs through a duct in the wing; the duct comprises an air inlet and an air outlet; and the electric power cable is cooled by air passing through the duct between the air inlet and the air outlet.

Abstract: There is provided a method of mounting equipment to an aircraft. The method comprises attaching a mounting structure to the fuselage of the aircraft, the fuselage extending lengthwise along a longitudinal axis. This comprises irremovably attaching a plurality of substantially planar frames to the exterior of the fuselage, such that each frame is oriented orthogonal to the longitudinal axis and spaced apart from an adjacent frame; and irremovably attaching a plurality of intercostal ribs between pairs of adjacent frames of the plurality frames, such that each rib is oriented parallel to the longitudinal axis and attached to each of a pair of said adjacent frames. The method further comprises mounting equipment to or within the mounting structure; and covering the mounting structure and the equipment mounted thereon or therein with a cover. The method further comprises removably attaching the cover to the mounting structure or the fuselage. An assembly, structure, tailplane and aircraft are also provided.

Abstract: An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

Abstract: An ice fishing container and an organizer system that is useable with the ice fishing container to organize the contents within the ice fishing container. The organizer system is disposed within the interior space of the ice fishing container and is configured to neatly organize ice fishing gear and equipment within the interior space of the ice fishing container. The organizer system has a plurality of divider panels that are configured to fit within the interior space, where the divider panels of the organizer system include a plurality of longitudinal divider panels that are parallel to the side walls of the ice fishing container, and a plurality of lateral divider panels that are parallel to the front and rear end walls of the ice fishing container.

Abstract: Methods and apparatus to recover unmanned aerial vehicles (UAVs) with kites are disclosed. A disclosed example apparatus to recover a UAV during flight includes a tether line, a tensioner operatively coupled to the tether line, and a kite operatively coupled to the tether line to support the tether line for recovery of the UAV.