Abstract: A versatile door system for a vehicle having a frame with an opening. The door system includes a door assembly including a hingeable door and a slidable door. The hingeable door is hingeably coupled to the frame proximate the opening. The slidable door is slidably coupled to the hingeable door. A rail system includes a segmented upper rail having a first portion coupled to the frame and a second portion formed on an exterior side of the hingeable door. The slidable door includes a slider bearing configured to sequentially engage the first and second portions of the segmented upper rail along a path of travel of the slidable door. In a closed configuration, the hingeable door and the slidable door are securably disposed within the opening. The hingeable door and the slidable door are configured to collectively provide access to selectable portions of the opening.

Abstract: Aircraft, aircraft wings and associated shear ties are disclosed. An example apparatus includes a first panel coupled to a second panel to define a wing box; a rib disposed chordwise within the wing box; and a stringer disposed spanwise within the wing box immediately adjacent at least one of the first panel or the second panel, the rib including a shear tie including first and second legs extending in opposite directions, the first and second legs to be coupled to at least one of the first panel, the second panel, or the stringer.

Abstract: A privacy panel assembly for a passenger seat includes a vertically extending panel attached to a lateral surface of the passenger seat such that the vertically extending panel includes a forward edge and an aft edge and at least one sliding mechanism attached to an interior surface of the vertically extending panel. The vertically extending panel includes a stowed configuration and a deployed configuration. In the stowed configuration, the aft edge of the vertically extending panel is disposed on an aft side of a rear surface of a seatback of the passenger seat. In the deployed configuration, the aft edge of the vertically extending panel is approximately aligned with a seating surface of the seatback on a forward side of the passenger seat.

Abstract: A network system for monitoring and storing data of aircraft intelligent windows or windshields to provide useable life of, provide real life performance of, and/or measure characteristics and/or properties of, the windshields forwards the data from sensors mounting the windshield to a window sensing hub having a microprocessor programed to receive and process the data to determine the performance of the windshield and formatting the data in accordance to a preset program, wherein the program includes providing data from the sensors that measures characteristics and properties of the windshield that are active during the period in which the data is taken. An aircraft central maintenance system connected to the window sensing hub receives the formatted information from the window sensing hub and unfiltered or unformatted information, wherein the unfiltered information from the windshield is acted on by the central maintenance system to provide an estimated useable life of the windshield.

Abstract: A traction kite anchoring device for attachment to a harness worn by a user to transfer force from a traction kite to the user. The traction kite anchoring device comprising a first member at an end of at least one line connected to a said kite and a chicken loop for attachment to a said harness and releasably connected to said first member, wherein the chicken loop has a first end comprising an anchor able to be received and secured at an anchor receiver of the first member in a releasable and tool-less manner.

Abstract: An aircraft launching system and method include a first lifting sub-system including a first tether that removably couples to an aircraft, and a second lifting sub-system including a second tether that couples the first lifting sub-system to the second lifting sub-system.

Abstract: A method of detecting the presence of insects, including larvae, in an indoor environment, which includes the steps of (a) obtaining a sample of volatile organic compounds (VOCs); (b) separating the sampled VOCs; (c) detecting the presence or absence of “target” VOCs from at least one category: “category 1 VOCs”—VOCs emitted independently of the support on which the insects develop and emitted only in an insect infestation VOCs, “category 2 VOCs”—VOCs emitted independently of the support but may have biological origins other than insects, and “category 3 VOCs”—VOCs emitted depending on the support and emitted only in an insect infestation; (d) calculating both an insect infestation index (“3I”) and a limit value (“VL”) based on the presence or absence of the target VOCs; and (e) comparing the “3I” and “VL” values. The environment is infested for a “3I” value strictly greater than the “VL” value.

Abstract: Systems and methods for vertical farming that reduce the deployment cost, operational costs of human labor, and overall use of energy intensive processes, such as lighting, heating and cooling, and ventilation, while increasing crop quality and yield. This reduction is achieved through a hybrid system that alternates natural light, temperature, and ventilation sources with system-controlled lighting, temperature, and ventilation means. The system includes a germination module that allows seeds to germinal on a horizontal substrate, a growth module that provides optimal growth conditions to the germinated seed on the substrate in a vertical position, and a dosing module that controls the micronutrient mixture supplied to the growing plants.

Abstract: A modular quadcopter is provided for vertical flight. The quadcopter includes a housing, a quadrilateral set of extensions, and a quadrilateral set of arms. The housing contains flight control and sensor equipment, and has a relative vertical orientation. The housing is configurable for either stowage or deployment. The extensions are disposed on each corner of the housing. Each extension has a hinge that pitches outward and upward. Each arm is disposed on the hinge and contains an electric motor and a speed controller. The configurable below the housing for the stowage and extends radially from respective the extension in relation to the orientation for the deployment.

Abstract: A pet bed including a cushioned-base defined by a body-section and a head-section; a blanket removably fastened to the cushioned-base; and fastener for removably fastening the blanket to the cushioned-base. The cushioned-base includes molded sections to provide support and comfort to the bed. In particular, the head-section includes a molded section which defines a pillow. The pet bed is useful for providing a pet, particularly a dog, with a comforting location to rest.

Abstract: An aircraft, has an airframe, a transmission, and a liquid inertia vibration elimination (LIVE) system disposed between the airframe and the transmission via spherical bearings of two legs and via a central spherical bearing.

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: An aircraft engine attachment including a beam fixed to a pylon and including a yoke with two walls, and a connecting rod with an articulation housed in the yoke, in which the connecting rod has a front flank and a rear flank which are facing inner faces of the walls. For each wall, a wearing part is disposed against the inner face of the wall and between the wall and the corresponding flank of the connecting rod. A Fixing arrangement ensures the fixing of the wearing part to the wall. Thus, the wearing parts prevent an excessive tilting of the connecting rod and the wearing of the connecting rod or of the yoke.

Abstract: An assembly for an aircraft that has a wing and an engine pylon having a primary structure with right-side and left-side panels, an upper and a lower spar and a rear rib, two sets of upper or lower shackles, one set fastening the right-side panel to the wing, and a second set fastening the left-side panel to the wing, a fastening element secured to the rear rib or to the lower spar, a rear rod connecting the fastening element to the wing, a transverse shackle connecting the upper spar to the wing, a line connecting two centers of the transverse shackle being oriented transversely relative to a longitudinal axis of the engine pylon, and a reinforcing panel, at each joint between a right-side or left-side panel and an upper or lower shackle, which is fastened along a height against the panel and to which the shackle is also fastened.

Abstract: A door arrangement for an aircraft segment, which door arrangement comprises a passenger door, a fuselage portion accommodating the passenger door, and a girt bar for arming and disarming an emergency slide. The passenger door is movable relative to the fuselage portion between a raised position and a lowered position. The girt bar is connectable by means of a connecting arrangement to the passenger door and/or to the fuselage portion. The connecting arrangement comprises a mechanism which is configured to, during arming of the emergency slide, actuate a locking mechanism of an engagement device fastened to the fuselage portion, such that the girt bar is fixed in a decouplable manner to the engagement device.

Abstract: An apparatus for inhibiting cross contamination by airborne droplets between adjacent passengers on an aircraft comprises a case in which a flexible shield can be stored, and from which the shield can be deployed in a vertical, substantially flat configuration, where it is maintained by an extension mechanism. The shield can be coiled within the case when not deployed, and can be retractable by a ratchet and spring when deployment is terminated. An attachment mechanism positions the case between the passengers by fixing the case to a structure such as an arm rest. The extension mechanism can include one or more rigid or semi-rigid rods. The case or shield can include a storage cavity for storage of the rods when not deployed. The attachment mechanism can include an arm rest clamp and/or an insertion member that can pivot downward for insertion between a seat cushion and adjacent structure.

Abstract: When the tension across the cord's 24 length reaches a predetermined threshold, an activation mechanism within the payload 16 and coupled to one of the cord's 24 ends is actuated in order to activate the payload 16. Activating the payload 16 may include deactivating a SAFU, activating a motor 32 disposed within the housing, or causing flight controls to extend from a housed position. Here, “within the payload 16” may mean part of the activation mechanism is disposed on the outer surface or housing of the payload 16.

Abstract: A restrain and release mechanism for an externally airborne load, includes at least one stiff support for suspending the load and an elastically deformable adaptive member designed to maintain the load at pressure contact against the support. The adaptive member is a three-dimensional monolithic metallic body obtained using an additive manufacturing method and having a flexural orthotropic behaviour.

Abstract: A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.

Abstract: The invention relates to an aircraft having a tailless fuselage. The fuselage has a body which includes a transverse trailing edge. The aircraft further includes a wing having two sides which protrude from opposite sides of the fuselage. The body typically has a fineness ratio of between 3 and 7. Each side of the wing has an inner section having a first dihedral angle and an outer section having a second dihedral angle, the second dihedral angle being less than the first dihedral angle. At least part of the outer section is typically swept back. The configuration of the aircraft provides it with improved flight efficiency.