Abstract: A plurality of propellers generate vertical thrust at least some of the time. An attachment sub-system detachably couples to a vertical connector, where a plurality of vertically-stacked multicopters are configured to detachably couple to the vertical connector in order to transport a load at a bottom end of the vertical connector. There is an opening in a vehicle frame that is configured to: (1) receive the vertical connector prior to the attachment sub-system detachably coupling to the vertical connector and (2) hold the vertical connector while the attachment sub-system is detachably coupled to the vertical connector.

Abstract: Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle ? of at least one of the plurality of engine-mounting links.

Abstract: An electrical energy processing unit of an apparatus to kill a plant or at least attenuate plant growth is disclosed. The electrical energy processing unit includes a converter and a control circuit. Also disclosed are an apparatus that includes the electrical energy processing unit and a method of utilizing the apparatus. Further disclosed are a computer program for a processor of the control circuit of the electrical energy processing unit and a non-transitory computer readable medium that includes the computer program.

Abstract: A rotary wing aircraft with a fuselage that forms an aircraft interior region, the fuselage comprising an upper primary skin that separates the aircraft interior region from an aircraft upper deck arranged above the fuselage, wherein the aircraft upper deck comprises an engine accommodating region with a firewall arrangement, the engine accommodating region accommodating at least one aircraft engine within the firewall arrangement, wherein the firewall arrangement comprises at least one gasket for tightening pass-through of a torque tube that connects the at least one aircraft engine to a main gear box of the rotary wing aircraft, and wherein the at least one gasket comprises at least two fire proof shells and a ring-shaped flexible fire proof bellows.

Abstract: A nacelle for an aircraft, including a structure, a cap attached to the structure and a seal system including an arch forming a channel which extends beneath a rear edge of the cap and which has a bottom, the arch being attached to the structure, a seal in the form of a solid block in the channel and beneath the rear edge of the cap, a spring system arranged to move the seal away from the bottom, and a retaining arrangement configured to prevent the seal from leaving the channel under the action of the spring system. With an arrangement of this kind, it is not necessary to oversize the bead, this being replaced with a solid seal mounted on a spring system.

Abstract: A convex reflective surface, such as mirror (1) or an equivalent deflector of radiation, designed to suit a FIG. 5 particular location or type of location, fixed in position and requiring no adjustment, can re-direct solar radiation (2,3) downwards onto a chosen target area throughout the calendar year or such lesser period of operation as may be chosen, benefitting the growth of plants in a greenhouse or the open air, and other human activities, at minimal expenditure including of fossil fuel.

Abstract: An improved vertical takeoff aircraft of the type having a set of pads that are in contact with the ground when the aircraft is at rest on the ground and a controllable lift and propulsion system. The aircraft includes an array of force sensors coupled to the set of pads. The array has an output providing measurements over time of forces exerted on the pads along at least two independent axes. The aircraft also includes a controller, coupled to the lift and propulsion system and to the array of force sensors. The controller is configured to control the lift and propulsion system in a manner to counteract forces exerted externally on the aircraft that would cause undesired motion of the aircraft when on the ground and transitioning from the ground to flight.

Abstract: Compliant mounting systems, devices, and methods for mounting a vehicle engine to a vehicle structure or base include a top mount, a lower mount, a center trunnion mount, and an aft mount which are configured to react forces transmitted by the engine to the vehicle structure. Metallic and elastomeric elements can provide vibrational and force isolation characteristics. Stops (e.g., snubbing elements) allow for a specific range of motion before internal mount structures contact each other to act as a conventional hard mount. Fluid elements and compressible gas-filled spaces/bladders may be incorporated to provide fluid damping behaviors to complement the metallic and elastomeric elements.

Abstract: An engine pylon has a primary structure fastened between an engine and an aircraft wing and a cowling system having a front set of fixed cowls, a rear cowl, a displacement system having a first structure as one with the rear cowl and having a first slide mechanism, and a second structure fastened to a fixed structure of the wing and having second slide mechanism. The slide mechanisms cooperate so as to realize a sliding connection and to move the rear cowl in translation from an advanced position to a retracted position. An immobilizing system locks the rear cowl in the advanced position.

Abstract: A system for mounting a gas turbine engine to a pylon and for detecting a failure within the system, the gas turbine engine comprising a first case, is disclosed. In various embodiments, the system includes a first mount connecting the first case to the pylon; and a first sensor configured to detect a first relative motion between the first case and the first mount.

Abstract: A forward secondary structure for a mounting pylon for a turbomachine, the forward secondary structure extending from upstream to downstream along a longitudinal axis and having a chassis clad with an aerodynamic fairing. The aerodynamic fairing includes two adjacent cowls each having an upstream portion, where each of the cowls extends lengthwise along the longitudinal direction and includes in its upstream portion a system for articulating the cowl to the chassis, by which system the cowl can pivot with respect to the chassis about an axis of rotation normal to the longitudinal axis, between a closed position in which all of an inner face of the cowl is pressed against the chassis and an open position in which the cowl frees up an opening in the forward secondary structure.

Abstract: The invention concerns a suspension system (7) for a turbomachine, comprising a beam (10) intended to be attached to a pylon of an aircraft, and a cylindrical part (15) articulated on a ball joint housing, the ball joint housing comprising a body (11), and a ball joint nut (16) articulated on the body (11), the cylindrical part (15) being mounted so as to pivot about its axis in the ball joint nut, characterized in that the cylindrical part (15) is intended to be integral with a fixed part (8) of the turbomachine (1), the body (11) of the ball joint housing being integral with the beam (10).

Abstract: An assembly including a connecting device, connecting first and second parts, including first and second links positioned on respective opposite sides of the first and second parts and an interleaved stiffener, positioned between the first and second links, having a first contact face oriented toward the first link and a second contact face oriented toward the second link, parallel to the first face, the first and second contact faces being separated by a distance equal to that separating the first and second links. This interleaved stiffener makes it possible to limit the risks of bending of the links when they are loaded in compression.

Abstract: An assembly for reacting a thrust load from an engine, the assembly comprising a frame, a pin, an evener bar, and left and right thrust links. The frame includes an upper pin interface and a lower pin interface. The pin extends through the upper pin interface and the lower pin interface and includes an upper end and a lower end. The evener bar engages the lower end of the pin below the lower pin interface and connects the left and right thrust links to the pin. The pin is configured to react the thrust load at the lower pin interface and the upper pin interface thereby forming a distributed force couple between the lower pin interface and the upper pin interface.

Abstract: A computer-implemented method of targeting grower fields for crop yield lift is disclosed. The method comprises receiving, by a processor, crop seeding rate data and corresponding crop yield data over a period of time regarding a group of fields associated with a plurality of grower devices; receiving, by the processor, a current seeding rate for a grower's field associated with one of a plurality of grower devices; determining, whether the grower's field will be responsive to increasing a crop seeding rate for the grower's field from the current seeding rate to a target seeding rate based on the crop seeding rate data and corresponding crop yield data; preparing, in response to determining that the grower's field will be responsive, a prescription including a new crop seeding rate and a specific hybrid to be implemented in the grower's field.

Abstract: An animal bed for supporting an animal includes a body having a bottom member and a bolster forming an outer wall of the body. The outer wall is positioned about a perimeter of the bottom member and extends outwardly therefrom to define a recessed area for accommodating the animal. A plurality of straps is coupled to and extending at least partially across the bottom member opposite the recessed area. Each of the plurality of straps includes a degree of elasticity configured to hold a rigid member in contact with the bottom member.

Abstract: An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

Abstract: An aircraft pylon comprising a structure covered by a fairing. The structure includes at least one void bounded by a peripheral edge. The fairing includes at least one removable panel connected to the structure around the void and having an inner face oriented towards the structure. The structure includes at least one seal connected to the structure so as to be slightly compressed against the inner face of the removable panel. The seal extends over at least a lower portion of the peripheral edge so as to retain a fluid located below a sealing horizontal plane while ensuring ventilation beneath the fairing.

Abstract: A composite aircraft engine pylon comprising a frame, an aircraft attachment component, and an engine support. The frame includes an outer structural section and an inner structural section configured to at least partially nest with the outer structural section. The outer structural section and the inner structural section sandwich the airframe attachment component and the engine support to form double shear connections between the frame and the aircraft attachment component and between the frame and the engine support.

Abstract: A cargo loading system includes a drive unit extending along a length of a cargo area of an aircraft. The drive unit is configured to couple to a modular cargo structure via a handling member and to convey one or more cargo items coupled to the modular cargo structure. The cargo loading system further includes a rotation device and a driver. The rotation device is in contact with the drive unit. The driver is configured to apply torque to the rotation device to cause the drive unit to move the modular cargo structure within the aircraft.