Abstract: An assembly comprising a wing with lower spars, a mounting pylon having an upper spar and two lateral panels, a front fixing system and a rear fixing system, each comprising a beam pierced with a principal bore and, for each beam, an upper bore traversing the upper spar and a shear pin positioned in the upper bore and in the principal bore. The assembly also comprises, for each fixing system, bolts, the nut of which is accommodated in a secondary hole of the beam and the screw of which traverses the upper spar and the beam in order to be screwed into the nut.

Abstract: A mounting pylon comprising a structure that comprises two C-shaped semi-structures and comprising an upper spar, a lower spar and a lateral flank, an upper panel, a lower panel, a reacting attachment point, two bars attached between the reacting attachment point and a jet engine, and a front wing attachment point attached to a wing box. The lateral flank comprises joists that are aligned between the front wing attachment point and the reacting attachment point, and where the angles between two successive joists are equal.

Abstract: Retractable guide assemblies are provided to guide cargo load pallets onto a cargo deck of a cargo aircraft, the guide assembly having a support subassembly comprising a recessed housing box, a moveable guide subassembly pivotally connected to the support subassembly so as to be pivotally moveable relative thereto, and an actuator subassembly operatively interconnecting the moveable guide subassembly and the support subassembly. The actuator subassembly may thereby allow the moveable guide subassembly to be pivotally moveable between (i) a releasably locked stowed condition, (ii) a releasably locked deployed condition and (iii) a freely moveable unlocked maintenance condition.

Abstract: A seal plate (201) for maintaining a continuous aerodynamic surface between a fixed part (302) of an aerostructure such as an aerofoil (103) and a movable surface such as a spoiler (304) is provided. The seal plate (201) includes a resilient material such as fiberglass and has an aerodynamic surface (203). It is configured to be mounted to the fixed part (302) of the aerofoil along one edge (205) and to slidably seal with the control surface (304) at a second edge (207). The seal plate (201) is stepped and has a rigid lever (217) to engage behind the control surface (304) to bend the seal plate precisely according to movement of the control surface (304) and maintain the continuous aerodynamic surface.

Abstract: An assembly with an aircraft fuel tank is disclosed having a captive nut with an internal thread, a secondary structure, and a fastener which secures the secondary structure to the fuel tank. The fastener has a shaft which passes through the secondary structure and has an external thread coupled to the internal thread of the captive nut. The fuel tank has a fuel tank element with a hole, and the captive nut has a sleeve which is located in the hole with an interference fit between an outer surface of the sleeve and an inner surface of the wall of the hole.

Abstract: A combined seat/stair arrangement for a multi-deck vehicle, in particular a multi-deck aircraft or spacecraft, include a foldable passenger seat; a stair which is designed to connect an upper deck to a lower deck via a stair hatch and at least one floor flap which movable between a use position of the stair with the stair hatch open and a use position of the foldable passenger seat with the stair hatch closed, wherein, in the use position of the foldable passenger seat, the at least one floor flap closes at least a partial region of the stair hatch, and wherein the floor flap is designed with a seat attachment, to which the foldable passenger seat is attached.

Abstract: The present invention relates to a maintenance apparatus for a shock absorber of a landing gear, comprising a liquid reservoir which can be connected to an interior space of the shock absorber via a liquid line, a gas reservoir which can be connected to the interior space via a gas line, a coupling member for sealingly coupling the liquid reservoir and the gas reservoir, wherein the maintenance apparatus is configured to allow an exchange to occur of liquid and gas between the liquid reservoir and gas reservoir, respectively, and the interior space, the maintenance apparatus comprising control means for determining that a partial volume of the interior space occupied by the gas reaches a reference level as a result of the exchange and for bringing the partial volume of the interior space of the shock absorber respectively occupied by the gas and the liquid to a target level. The invention also relates to a maintenance method.

Abstract: Method and system for determining a condition of at least one pig in a pen provided with a feed unit. The pen is provided with a sensor system. For carrying out the method, a step a., step b. or a combination of steps a. and b. is possible. In step a., with the aid of the sensor system a reaction of the at least one pig is measured. This is done when with the feed unit feed is made available in the pen to the at least one pig to determine on the basis of the measured reaction a condition of the at least one pig. In step b., with the aid of the sensor system it is measured that the at least one pig ‘demands’ feed to determine a condition of the at least one pig.

Abstract: “Battery operated flying car with enclosed motors for human transportation” is machine that can carry humans and looks like a real flying car. The current problem with implementing this is resolved by using ducted motors with grilles around it. By covering top and bottom of car with grilles we are able to negate effect of completely covered motors. By providing grilles around motors we ensure safety of humans around it, this not only avoids direct contact but also provides continuous air flow into motors to push out from the other side. Loss of efficiency due to covered grilles are countered by use of two additional front and two rear motors. Vertically mounted front motors push air into bottom motors which significantly improves the lift capacity of the flying car. Vertically mounted rear motor pumps air out of the car and thus aids in forward movement of the flying car.

Abstract: A transportable launch and landing pad for drones includes a round surface member for supporting a drone on a ground surface. The surface member includes an endless flexible weighted ground surface contacting, engaging and conforming perimeter disposable on the flat or undulating topography of the ground surface. The endless flexible weighted ground surface contacting, engaging and conforming perimeter is formed of a stranded carbon steel wire rope. The surface member has a diameter establishing an area of the pad that is greater than any linear distance across an area of downwardly moving air of the drone when operated. The pad maintains a position on the ground surface without any separate securing member inserted into the ground, and the pad is not lifted from the ground surface by air from the thrust of the drone during approach and departure of the drone relative to the pad.

Abstract: A ground manoeuvering device comprises a housing with a fastening device for the skid, a hydraulic apparatus as well as an outer wheel and an inner wheel on two aligned horizontal axles on the hydraulic apparatus, respectively one on the inside and one on the outside beside the skid. The hydraulic apparatus comprises an extendable piston and an engagement shaft with a lever attached in a swivellable manner. When the lever is rocked, the piston is extended from the hydraulic apparatus and thereby lifts the housing vertically upwards. The engagement shaft is aligned in the wheel running direction and the lever extends, in the operating state, in the wheel axle direction of the outer wheel. In addition, the lever comprises a tread section, in order to raise the fastened skid onto the two wheels using the hydraulic apparatus while standing conveniently beside the helicopter repeatedly stepping with the foot on the tread section.

Abstract: An aircraft undercarriage carrying at least two wheels (4) and for mounting on an aircraft structure to be movable between a deployed position and a retracted position, the undercarriage being characterized in that the wheels are rotatably mounted on axles (3) carried by arms (2) hinged to a bottom portion of a strut-leg (1) of the undercarriage, each arm being associated with a shock absorber (5) coupled firstly to the arm and secondly to a collar (6) that extends around the strut-leg and that is mounted to slide on the strut-leg between a high position in which the collar bears against an abutment (7) of the strut-leg when the undercarriage is in the deployed position and a low position into which the collar is taken when the undercarriage is moved from the deployed position to the retracted position, so as to bring the wheels closer together.

Abstract: An unmanned aerial vehicle (UAV) includes a UAV body including a first mounting member, a gimbal, and a plurality of stands. The gimbal includes a second mounting member connected to the first mounting member, and a gimbal body connected to the second mounting member. The plurality of stands are fixedly attached to the gimbal body and configured to rotate together with the gimbal body around a yaw axis of the gimbal body.

Abstract: A hovering aerial vehicle is provided, comprising an airborne unit and an auxiliary unit. The airborne unit is configured to carry the auxiliary unit during flight and comprises a flight system configured to facilitate providing aerodynamic lift to facilitate hovering of the vehicle. The auxiliary unit comprises an electrical power source in electrical communication with the flight system to provide electrical power for its operation. The hovering aerial vehicle further comprises a decoupling system configured to facilitate selectively switching the vehicle between a detached configuration thereof wherein the airborne and auxiliary units are remote from each other, and an attached configuration thereof wherein the airborne and auxiliary units are secured to one another, and to maintain the electrical communication when the vehicle is in its detached configuration.

Abstract: An upward, vertically extending agricultural gas distribution system is disclosed. The gas distribution system is useable for orchards, plantations, and other permanent or semi permanent crops. The gas delivery system includes a gas supply, a flexible tube, and a rigid tube. The gas supply is adapted to be disposed proximate the bottom of a plant. The flexible tube is connected to the gas supply and has a lumen for communication of gas from the gas supply. The flexible tube is adapted to be oriented vertically along the vertical length of the plant. The rigid tube is connected to the flexible tube and also has a lumen for communication of gas from the flexible tube. The rigid tube has at least one gas emitter for release of gas from the rigid tube lumen to the exterior environment. The rigid tube is adapted to be oriented vertically along the vertical length of the plant, above the flexible tube. Tree couplers, gas wands, gas flow indicators, and gas flow control valves are also disclosed.

Abstract: An apparatus to electrically kill a plant or at least attenuate plant growth is disclosed herein, wherein the apparatus comprises at least an electrical energy processing unit and an electrical continuity system. Also disclosed are methods of producing and using same.

Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan driven by the power source; and a wing extending from the fuselage. The vertical thrust electric fan is positioned on or within the wing, the wing including a diffusion assembly movable between a first position and a second position and positioned at least partially downstream of the vertical thrust electric fan when in the second position, the diffusion assembly including a first member and a second member, the second member movable generally along the vertical direction relative to the first member such that the first member and second member together define at least in part an exhaust flowpath for the first vertical thrust electric fan when the diffusion assembly is in the second position.

Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly extending along the length of the wing and moveable between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the plurality of vertical thrust electric fans when in the vertical thrust position.

Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly moveable generally along a horizontal direction between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering at least one vertical thrust electric fan of the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the at least one vertical thrust electric fan when in the vertical thrust position.

Abstract: The force feedback device includes a stationary housing intended to be secured to an understructure of an aircraft, at least one spring opposing movement of a side-stick of the aircraft relative to the housing, and a transmission mechanism, which is supported by the housing movably and which is suitable for transmitting a rotational movement, around a first rotation axis, between the side-stick and said at least one spring, by applying a force law according to which a resistive force, opposed by said at least one spring, via the transmission mechanism, against the rotational movement of the side-stick around the first rotation axis, depends on an angular position of the side-stick around the first rotation axis.