Abstract: A drogue bridle attachment assembly may comprise a housing, a lock pin, jackscrew gear pin, and a drive gear pin. The housing may define a bridle opening. The lock pin may be configured to translate into the bridle opening. The jackscrew gear pin may include a threaded portion and a gear portion. The threaded portion may engage a threaded opening in the lock pin. The drive gear pin may include a drive gear portion intermeshed with the gear portion of the jackscrew gear pin.

Abstract: An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.

Abstract: A method for integrating and fitting at least one item of equipment and/or at least one line in a technical bay of an aircraft, comprising the steps comprising attaching the equipment and/or the line(s) on an integration module outside the fuselage of the aircraft, introducing the integration module into the fuselage of the aircraft via an opening of a baggage hold, and securing the integration module to a structure of the aircraft. An integration module is provided which comprises a chassis bounding a volume in which are positioned and attached at least one item of equipment and/or at least one line and having a cross section that is approximately identical to that of a baggage container and a length which is less than or equal to that of a baggage container.

Abstract: A wing assembly includes a center wing structure and a pair of outer wing structures. The center wing structure includes a center wing front spar, a center wing rear spar, and an engine mounting location on each side of a wing centerline. Each outer wing structure includes an outer wing front and rear spar configured to be coupled respectively to the center wing front and rear spar to define a wing joint coupling the outer wing structure to the center wing structure. The center wing structure is configured such that the spar terminal ends of the center wing front and rear spars at each wing joint are located no further inboard than an engine centerline associated with the engine mounting location, and no further outboard of the engine centerline than ten percent of a distance between the engine centerline and the wing centerline.

Abstract: An example system includes a first plurality of nacelles located on a first side of an aircraft, wherein each nacelle of the first plurality of nacelles includes an electric motor coupled to a propulsor, wherein an outboard nacelle of the first plurality of nacelles includes an electrical energy storage system (ESS) coupled to a first electrical bus; and a second plurality of nacelles located on a second side of the aircraft, wherein each nacelle of the second plurality of nacelles includes an electric motor coupled to a propulsor, wherein an outboard nacelle of the second plurality of nacelles includes an ESS coupled to a second electrical bus.

Abstract: A water movement system and method configured to eradicate and/or control mosquito or insect populations that lay eggs in treated, stagnant water environments. The system is comprised of a water pump configured to function in cooperation with an underwater insect attractant device. The insect attractant device is suitably constructed to generate carbon dioxide for attracting insects to a water extermination zone or trap. In one embodiment, the underwater insect attractant device contains organisms such as mycelia for generating the carbon dioxide. Insects are attracted by the carbon dioxide generation device to reproduce in the water extermination zone, using the treated water to lay eggs, and grow larvae and pupae for the subject insects. A solar-powered water pump device is configured to direct the flow of water from the water extermination zone toward filters of the water pump device to trap and kill insect progeny including eggs, larvae, and pupae.

Abstract: Method for assembling a slat, for an aircraft wing, comprising providing a skin and a plurality of stiffeners; assembling the stiffeners to the skin obtaining a skin sub-assembly; providing a spar and a plurality of lugs; assembling the lugs to the spar obtaining a spar sub-assembly; assembling the spar sub-assembly to the skin sub-assembly to obtain the slat.

Abstract: A method of providing torque protection and/or thrust protection for the or each propeller of a hybrid helicopter. The hybrid helicopter includes a control system connected to the blades of each propeller and a thrust control configured to generate an order for modifying a pitch of the blades, which order is transmitted to the control system, the propeller(s) being driven in rotation by a mechanical transmission system of the hybrid helicopter. The method includes a step of having the control system keep the pitch of the blades of a propeller within at least one control envelope relating to a thrust generated by the propeller or to a torque exerted in the mechanical transmission system. In this way, the pitch of the blades of each propeller is kept between a lower limit and an upper limit of the control envelope.

Abstract: An aircraft convertible between fixed-wing and hovering orientations includes a fuselage. The aircraft includes a main wing pair comprising two opposing wings attached to the fuselage, where each wing of the two opposing wings includes a fixed wing section attached to the fuselage and a movable wing section rotatably mounted to the fixed wing section. The aircraft includes at least a first propulsor mounted to the movable wing section of each of the two opposing wings. The aircraft includes at least a first rotation mechanism attached to the fixed wing section and movable wing section of each of the two opposing wings, the at least a first rotation mechanism configured to rotate the movable wing section between a first movable wing section position parallel to the fixed wing section and a second movable wing section position perpendicular to the fixed wing section.

Abstract: Described herein is a fishing flasher. The fishing flasher may comprise a main body portion which may comprise a passage. A fin may extend from a surface of the main body portion proximate to the trailing end of the main body portion. The fishing flasher may also comprise a removable panel which is sized and shaped to fit within the passage and may be held within the passage by at least one fastener. It is also described herein a fishing flasher kit comprising a main body portion comprising a passage, a fin, and a plurality of removable panels. Each removable panel may have a different surface feature on one or both of the first surface and/or the second surface.

Abstract: A method for converting a conventional manually monitored capture-and-release rodent trap of a type having a box-shaped container with opposed one-way entry corridors communicating with a capture chamber into a remotely-monitored rodent trap. In one aspect, the method includes attaching a smart-sensor to the lid of the trap and press-fitting a bracket having a rodent opening into the space between the one-way entry corridors such that the rodent opening in the bracket restricts movement of a rodent into the capture chamber to a pathway in sufficient proximity for detection by the smart-sensor and signaling to a remote monitoring location.

Abstract: A multi-rotor unmanned aerial vehicle (UAV) comprises: a fuselage; a plurality of rotor mechanisms disposed on the fuselage, each rotor mechanism including a rotor; and a plurality of connection mechanisms disposed on the fuselage. The plurality of connection mechanisms have a one-to-one correspondence with the plurality of rotor mechanisms, each connection mechanism corresponding to one of the plurality of rotor mechanisms. Each rotor mechanism is movably connected to the fuselage through the corresponding connection mechanism; and the plurality of rotor mechanisms are configured to be rotated with respect to the corresponding connection mechanisms to cause the plurality of rotor mechanisms to overlap with each other and form a rotor mechanism assembly.

Abstract: This present invention relates to an ice fishing hole cover. The cover features a hinged door attached to the cover through mechanical attachments. The ice fishing hole cover includes a fishing line hole to allow a user to setup a fishing bait line through the cover. The hinged door enables the user to open a portion of the cover, and not the entire cover, to set up the fishing bait line or to access and land a fish caught while ice fishing. The ice fishing hole cover enhances the overall ice fishing experience of the users and eliminates the inconvenience of maintaining an open ice hole while fishing.

Abstract: A leading edge structure for an aerodynamic surface of an aircraft with an outer wall part curved in a streamlined manner around an interior compartment and having an inner surface pointing toward the interior compartment and an outer surface provided for contact with the external surrounding flow. The outer wall part has a first outer wall section extending from a leading edge point in an incident flow direction in a convexly curved manner in the direction of a first side. The outer wall part has a second outer wall section which extends from the leading edge point in the incident flow direction in a convexly curved in the direction of a second side. An inner wall part is arranged in the interior compartment opposite the inner surface of the outer wall part and extends from the first outer wall section to the second outer wall section.

Abstract: A leading edge for an airfoil of an aircraft includes a leading plate with a convex side and a concave side, and at least one container filled with a non-Newtonian fluid. The leading edge is configured to be secured to the torsion box of the airfoil. The at least one container is arranged between the concave side of the leading plate and the torsion box of the airfoil. An airfoil is also provided including such a leading edge. A method is provided for assembling such a leading edge.

Abstract: An animal tether system and method wherein the rate of extension and retraction of the tether and/or the length of the tether can be actively controlled at least in part as a function of the angular direction and/or speed and/or length of which the tether extends/retracts. The system can be used to maintain an animal in a non-circular boundary, such as a rectangular space, by controlling how far the tether can extend at certain angular positions. The system also allows a user to block off certain areas within a space from access by the animal.

Abstract: The inventive subject matter provides a device in which a pet stroller comprises at least three wheels, a battery, a motor, and a treadmill. The treadmill is positioned inside of the stroller and has a belt upon which an animal walk and run. The battery is configured to power the motor, and in at least some contemplated embodiments, movement of one or more of the wheels of the stroller can be used to directly move the belt of the treadmill, and/or indirectly power the belt by providing power to the battery.

Abstract: A quick attach bracket includes a first portion and a second portion aligned substantially perpendicular with the first portion, a retaining ridge disposed across the first portion and extending in the direction of the second portion, and a hub disposed on the second portion and extending in the direction of the first portion. The retaining ridge is configured to receive a flange of a structure. The hub includes a sidewall that extends from the second portion in the direction of the first portion, a façade aligned with the second portion, and a rounded portion connecting the sidewall and the façade to assist with installation of the hub into a recess or through-hole of the structure. The quick attach bracket is installable by hand via hooking of the retaining ridge on the flange and insertion of the hub into the recess or through-hole.

Abstract: A hybrid aerial vehicle (HAV) comprising: a fuselage of the HAV; a first mechanism within the fuselage for accepting a plurality of wings of the HAV, the first mechanism allowing coordinated contraction of the plurality of wings essentially into the fuselage such that tips of the wings are position in proximity of the fuselage and coordinated extension of the wings such that tips of each wing are positioned away from the fuselage; a first wing extending from the port side of the fuselage and connected to the first mechanism; a second wing extending from the starboard side of the fuselage and connected to the first mechanism; a second mechanism placed within the fuselage in proximity to its front end, the second mechanism allowing motion of propellers of the HAV affixed there to between a first plain and a second plain; a first set of propellers affixed at the port side of the fuselage to the second mechanism; a second set of propellers affixed at the starboard side of the fuselage to the second mechanism; a t

Abstract: A boundary layer ingestion-open rotor system for use with an aircraft having a fuselage, wings, and an empennage includes an open rotor assembly, one or more energy storage systems, and an electronic control unit (ECU). The open rotor assembly includes fan blades connected to and extending radially from a rotor hub, and a linkage assembly connecting the hub to the fuselage aft of the empennage within a predefined boundary layer of airflow around the fuselage. The energy storage systems are connectable to the rotor hub. In response to an electronic control signal, the system(s) selectively energize the open rotor assembly to cause rotation of the hub to occur within the boundary layer. The ECU selectively generates the electronic control signals to energize the open rotor assembly during one or more predetermined flight operating phases of the aircraft, e.g., cruise, takeoff, landing, and descent.