Abstract: Fishing lures, and more particularly, attachable floats for artificial fishing lures that include a buoyant body having a first end, a second end opposite the first end, and an outer wall connecting the first and second ends. The float includes a keeper extending from the body. The keeper is configured to attach the body to a polymeric artificial lure.

Abstract: An aircraft wing with a moveable leading edge device mounted towards the leading edge of the wing. The leading edge device is moveable between a first configuration, a second configuration and a third configuration. In the first configuration, the leading edge device is retracted fully within the wing profile. In the second configuration, a portion of a surface of the leading edge device is extended away from the wing profile and into the oncoming airflow on the lower surface of the wing as the wing moves through the airflow to increase lift produced by the wing. In the third configuration, a portion of the surface of the leading edge device is extended away from the wing profile into the oncoming airflow over the upper surface of the wing to impair lift produced by the wing.

Abstract: A method for mounting a vortex generator on an aerodynamic panel of an aircraft, including, before the step of assembling the vortex generator and the aerodynamic panel, a step of installing at least one shim interposed between the base of the vortex generator and the aerodynamic panel, the shim including a first face, oriented towards the aerodynamic panel during operation, that is shaped like the inner surface of the aerodynamic panel, and a second face, oriented towards the base during operation, that is shaped like the upper face of the arm of the base. This solution makes it possible to manufacture the vortex generator without taking into account the curvature of the aerodynamic panel. An aircraft is provided including at least one vortex generator mounted in this way.

Abstract: An aircraft having a fixed structure, an engine pylon, and a cowling system, a slider bearing a rear cowl and able to move in translation from an advanced position to a retracted position, a displacement system having, on either side of a median plane of the engine pylon, a guide as one with the fixed structure, a sliding element as one with the slider and sliding along each guide disposed on the same side, and a support as one with the fixed structure and having a blade parallel to the translation direction and on which a surface parallel to the translation direction of the slider rests. The presence of the mobile cowl ensures, inter alia, easy access to the inside of the engine pylon and to the systems that are housed therein.

Abstract: An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy derived from the gas turbine engine used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide forward propulsion of the aircraft and a respective electrical machine each configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.

Abstract: An actuator assembly includes an actuator drive source and a gust lock. The actuator drive source is operable to supply an actuator drive torque to drive a component. The gust lock is movable between a locked position, in which rotation of the drive source is prevented, and an unlocked position, in which rotation of the drive source is not prevented. The gust lock includes a lock shaft, a lock rotor, a lock motor, and a linear actuator. The lock shaft is rotatable with the drive source when the gust lock is in the unlocked position. The lock rotor is rotatable with the lock shaft. The lock motor is configured to supply a lock drive torque. The linear actuator is coupled to receive the lock drive torque and is configured, upon receipt of the lock drive torque, to move between an engaged position and a disengaged position.

Abstract: The present application discloses an aircraft configured for vertical take-off and landing and horizontal flight. The aircraft includes a valve configured to control the permitting or restricting of a release of gas from different regions of a fuel tank when the aircraft is in a vertical take-off and landing orientation and when the aircraft is in a horizontal flight orientation.

Abstract: Proposed are a composition for production of cat litter, cat litter, and a method for production of cat litter, the composition including: 45% to 58% by weight of coffee grounds; 40% to 50% by weight of natural polymer; 0.03% to 3% by weight of polymer gum; and 0.5% to 5% by weight of sodium alginate.

Abstract: A convertible aircraft with an airframe defining a first longitudinal axis is described; a pair of half-wings; a first, a second, a third, a fourth, a fifth and a sixth rotor rotatable about respective first, second, third, fourth, fifth and sixth axis, and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value independent of each other; said fifth and sixth rotor being carried by respective said half-wings and inclinable with respect to said airframe; the aircraft being switchable between a first hovering flight configuration wherein the sixth and seventh axis are arranged orthogonal to the first axis; and a second forward flight configuration wherein the sixth and seventh axis are arranged parallel to or inclined with respect to the first axis; the aircraft comprises first supports adapted to support the fifth and sixth rotor with respect to the respective half-wings; the first supports being arranged spaced apart from respe

Abstract: A satellite constellation (100) includes a plurality of artificial satellites (111 to 116) that number a multiple of 6. Each of the plurality of artificial satellites orbits in an inclined circular orbit a plurality of times a day. Normals to a plurality of orbital planes corresponding to the plurality of artificial satellites are shifted by an equal angle from each other in an azimuth direction. The plurality of orbital planes make up one or more orbital plane sets each consisting of six orbital planes. Timings at which the six artificial satellites orbit on the six orbital planes of each orbital plane set are synchronized with each other.

Abstract: A collision load distribution structure of a fuselage includes a front unit configured to be located at front ends relative to wings attached to the fuselage, a rear unit configured to be located at rear ends relative to the wings attached to the fuselage, a support unit configured to be located between the front unit and the rear unit, and a wing unit. The support unit is configured to transfer loads applied to the fuselage in case of a crash of the fuselage. The wing unit is configured to be located in the support unit, and connected to the support unit so as to transfer the loads in case of the crash of the fuselage. Loads in a length direction of the fuselage are passed through to the front unit, and are distributed to the wing unit through the support unit.

Abstract: The present specification provides an animal restraining apparatus comprising a foreleg constraining leash and a support strap comparing a loop connector, the loop connector configured to couple the foreleg constraining leash to the support strap in a manner that forms a foreleg humerus loop while allowing the foreleg constraining leash to freely slide through the loop connector to permit constriction or expansion of the foreleg humerus loop. Once donned on an animal, a handler simply applies minimal force on a leash connected to the leash end of the foreleg restraining leash in a manner that causes a reduction in loop size of the foreleg humerus loop around a foreleg of the animal. This reduction in loop size impedes the foreleg of the animal to freely move forward causing the animal to instinctually cease its movement.

Abstract: An electrical power supply system for a tethered small unmanned aerial vehicle has a ground station (1) connected to a universal aerial power supply (13) by a tether (10). The universal aerial power supply is capable of installation into the battery dock of a conventional free flying small unmanned aerial vehicle to deliver power to the small unmanned aerial vehicle systems during flight. The universal aerial power supply is compatible with a range of different small unmanned aerial vehicles and a range of classes of small unmanned aerial vehicles.

Abstract: A delivery device that travels along rails and delivers a package is provided. The rails include at least first and second rails. The delivery device includes: a main body; a connector that is configured to be connected to the rails, with the main body hanging from the connector, and with the rails being spaced apart from a ground surface; at least one actuator that drives the connector; a lift motor that is capable of taking up a wire for unloading the package; and a control circuit. When the delivery device is slidably hung from the first rail, the control circuit: switches from the first rail to the second rail by controlling the actuator; and lets out the wire and lowers the package by controlling the lift motor.

Abstract: An aircraft comprising a plurality of modules is disclosed. The aircraft in includes a blended wing body (BWB) aircraft. The blended wing body aircraft comprises a main body, a transition, and wings with no clear demarcation between the wings and the main body along a leading edge of the BWB aircraft. The blended wing aircraft additionally comprises a cabin containing a plurality of modular receptacles. A plurality of modules is configured to be removably attached to the plurality of modular receptacles. Additionally, at least a propulsor is mechanically attached to the blended wing body aircraft.

Abstract: The system includes a countertop portion, a barrier section, and one or more trays. The countertop portion has a front side and a back side. The barrier section is coupled to a bottom side of the countertop portion along the front side of the countertop. The barrier section is configured to support the countertop portion in use. The barrier section defines one or more openings therethrough. Each tray is aligned with one of the one or more openings and slidable relative to the barrier section between a retracted position and an extended position. Each of the trays is closer to the back side of the countertop in the extended position than it is in the retracted position. Each of the trays passes at least partially through its respective opening when sliding between the retracted position and the extended position.

Abstract: A convertible multi-mode vehicle capable of motorized travel in the air, on land, on water, and under water. The multi-mode vehicle is capable of controlled aerial flight, movement on the ground in terrestrial environments, on an aquatic surface, as well as underwater by changing between the different modes. Pivoting propulsion motors enable a convertible configuration from one vehicle locomotion mode to another.

Abstract: A variable fairing for covering a hydrogen duct system installation on the outside of an aircraft part, wherein the fairing comprises at least one fairing body to be mounted on the aircraft part, an air inlet and an air outlet and at least one movable closure mechanism configured to open and close a top portion of the fairing.

Abstract: An aircraft wing including: a wingbox; a fuel tank; a fuel cell system with a fuel cell; a fuel line configured to deliver fuel from the fuel tank to the fuel cell system; a propulsion system carried by the wingbox; and an electrical power line configured to deliver electrical power from the fuel cell system to the propulsion system. The fuel tank and the fuel cell system are located inside the wingbox, and the propulsion system is located outside the wingbox.

Abstract: An air vehicle has a body, more than one wing located on the body creating a lifting force, at least one control surface located on the wing and movable along the direction in which the wing extends, an open position in which the control surface moves out of the wing in the direction in which the wing extends and increases the lifting force acting on the body, a closed position in which the control surface is moved from the open position and brought to the wing, a main actuator moving the control surface between the open and closed positions, at least one shaft enabling the control surface to be moved with the triggering of the main actuator and having one end connected to the control surface, and at least one additional actuator enabling the attack angle of the wings to be changed by rotating the wings on the body.