Abstract: An unmanned aerial system for transporting and delivering packages, comprises an unmanned motorized aircraft and a non-motorized aerostatic device having aerostatic lift and being able to be coupled to the motorized aircraft, for transporting at least one package from a take-off site to a delivery site. This aerial system cooperates with a site for storing and distributing aerostatic modules each having a predetermined modular aerostatic lift, the storage and distribution site being located in the vicinity of the take-off site and being configured to deliver a set of j aerostatic modules on demand, which modules are secured by coupling means, so as to supply an aerostatic device with static lift that is substantially greater than or equal to the overall weight of the package to be transported and of the aerostatic device.

Abstract: A compartment system for a vehicle cabin includes a framework assembly for attachment to a vehicle structure, and a container bin. The framework assembly includes a flat bottom section, a top part and a lateral stiffening element. The bottom section has a rear edge for attachment to the structure and a front edge opposite to the rear edge. The top part is spaced from and parallel to the bottom section front edge. The lateral stiffening element is connected to the top part and the bottom section to create the framework assembly having a front opening between the top part and the bottom section front edge. The container bin has a box-like shape and an open front side. The framework assembly and the container bin are configured to detachably attach the container bin in the framework assembly with the open front side arranged in the framework assembly front opening.

Abstract: An overhead luggage bin includes: a bucket including side walls and a belly wall defining a luggage bin interior, a door displaceable between open and closed positions, and a bullnose extending along a forward edge of the belly wall; a hinge bracket fixedly mounted to one of the side walls, the hinge bracket extending between a lower portion mounted to the bullnose and an upper portion having a pivot; and a door displacement mechanism mounted to the door and mounted to the pivot of the hinge bracket, to displace the door to the open position. The hinge bracket has a rear mounting extending between the upper portion and the lower portion, the rear mounting mounted to a forward edge of said one of the side walls of the bucket.

Abstract: There is described an aircraft configured to be able to hover, comprising a fuselage; and a support element adapted to support a load, made of elastically deformable material and constrained to said fuselage; the support element being movable in an operating position in which it is arranged at least partially outside said fuselage and supports said load; the aircraft comprises a sock surrounding the support element arranged in said operating position; the sock is configured to contain the elastic return of the support element, in case the support element arranged in said operating position is sheared off.

Abstract: Movable platforms for use with a vehicle capture assembly of a capture vehicle and related devices, systems, and methods include floors with rotatable legs extending between the floors. The rotation of the legs relative to one or more of the floors enables the movable platform to move from an initial position to a displaced position as one or more of the floors move relative to each other.

Abstract: An aircraft wing includes a wing root having a leading edge, a trailing edge, and a distal end. The wing also includes a wing tip and a wing-tip hinge that pivotally couples the wing tip to the wing root and defines a wing-tip axis that is perpendicular to a folding plane. The wing tip is pivotable about the wing-tip axis, within the folding plane, between, and inclusive of, an extended position and a retracted position, relative to the wing root. When in the extended position, the leading edge of the wing tip extends from the leading edge of the wing root in a spanwise direction of the wing root. When in the retracted position, the leading edge of the wing tip extends from the leading edge of the wing root in a chordwise direction of the wing root.

Abstract: An aircraft passenger seat unit configured for use adjacent an aisle of an aircraft cabin is disclosed. The seat unit comprises a seat, a footrest, and a movable panel. The movable panel is movable with respect to the footrest between a closed position in which the movable panel at least partially encloses a side of the footrest and an open position in which the movable panel at least partially exposes the side of the footrest such that, in use, when the panel is in the open position, a passenger can access the seat from an aisle through the partially exposed side of the footrest.

Abstract: A magnetohydrodynamic (MHD) flow control mechanism is described which substantially improves the existing processes in that smaller magnetic fields, requiring far less mass, may be placed away from the forebody of the spacecraft to produce Lorentz forces that augment the lift and the drag forces for guidance, navigation, and control of the spacecraft. The MHD flow control mechanism may also be configured to provide additional thermal protection of the electrodes therein.

Abstract: A vertical intercostal for an aircraft vehicle having a vehicle cabin and an over-monument fairing arranged in a non-flex zone area of the vehicle cabin. The intercostal includes a frame member that includes an upper frame attachment region, a lower frame attachment region, and an intermediate frame attachment region to provide lateral structural support for the over-monument fairing to the airframe of the aircraft.

Abstract: Convertible monuments for aircraft cabins that house at least one lavatory can comprise moveable wall sections that can be reversibly deployed from a stowed configuration to a deployed configuration to form a temporary convertible monument having a monument footprint that overlaps at least a portion of an aircraft interior egress pathway during flight, and efficiently uses previously unused aircraft interior space during aircraft flight.

Abstract: Disclosed is a docking station for use with an unmanned aerial vehicle (UAV). The docking station has a retractable guide apparatus having a retracted state in which the retractable guide apparatus is retracted within the docking station and an expanded state in which the retractable guide is expanded outward from the docking station for physically guiding the UAV into the docking station. Given that the guide apparatus is retractable, the retractable guide apparatus is provided with some protection from environmental factors such as exposure to ice, snow and high winds.

Abstract: An inflatable partition includes a flexible membrane, an inflatable frame, and a support member coupled to the inflatable frame. The inflatable frame extends along a periphery of the flexible membrane and has an inner edge adjacent to the flexible membrane and an outer edge. The inflatable frame further includes a sealing mechanism extending along at least a portion of the outer edge and the inflatable frame is inflatable between a first state and a second state. The inflatable partition includes a first structural member and a second structural member. Each of the first and second structural members is coupled to the inflatable frame and extends vertically from the upper portion to the bottom portion of the inflatable frame and the first and second structural members define an opening in the inflatable partition.

Abstract: An aerial vehicle according to the present invention includes: at least one rotor configured to generate an air flow for lifting; and at least one sound producing structure having an opening and configured to produce sound for scaring birds and animals when the air flow generated by the rotor causes air to flow into the opening.

Abstract: A rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition.

Abstract: An aircraft interior unit with a detachable panel. The aircraft interior unit comprises a wall comprising a hollow panel, and a door mounted to the wall. The door is slidable between a closed position in which it covers an entrance to the aircraft interior unit, and an open position in which the entrance to the aircraft interior unit is uncovered. In the open position, the door is at least partially disposed within the hollow panel of the wall. The hollow panel can be detached from the rest of the aircraft interior unit, and the door, when moved from the open position, can be detached from the wall.

Abstract: There is provided a strut assembly for a wing of an aircraft. The strut assembly has a strut having an outboard end, an inboard end, and an elongate body. The outboard end is coupled to the wing of the aircraft, and the inboard end is coupled to a fuselage of the aircraft. The strut assembly further has at least one tensioner member having a first end coupled to the strut. The strut assembly further has a first fitting element having a through opening receiving a first portion of the strut and a bearing surface facing inboard. The strut assembly further has a second fitting element having a through opening receiving a second portion of the strut and a bearing surface facing outboard. The at least one tensioner member maintains tension in the strut, to keep the strut taut and in tension, to prevent or to minimize drooping of the strut.

Abstract: The embodiments is an unmanned aerial vehicle. The unmanned aerial vehicle includes: an airframe; and a fixed-wing assembly and a rotor assembly, both replaceably connected to the airframe. The fixed-wing assembly is connected to the airframe to form a vertical take-off and landing fixed-wing unmanned aerial vehicle and the rotor assembly is connected to the airframe to form a multi-rotor unmanned aerial vehicle, thereby implementing an unmanned aerial vehicle that can switch between the vertical take-off and landing fixed-wing unmanned aerial vehicle and the multi-rotor unmanned aerial vehicle.

Abstract: According to one aspect of the present disclosure, an apparatus for shortening a wingspan of an aircraft is disclosed. The apparatus comprises a first track affixed to a fixed wing of the aircraft. A first roller assembly is affixed to a wingtip of the aircraft, with the first roller assembly moveably captured within the first track. A second track is also affixed to the fixed wing. A second roller assembly is affixed to the wingtip and is moveably captured within the second track. A wingtip actuation assembly is configured to translate the first roller assembly within the first track and the second roller assembly within the second track to move the wingtip between an extended position and a stowed position under the fixed wing.

Abstract: An aircraft includes a fuselage and an airframe supporting the fuselage. The airframe includes a pair of longitudinally-extending beams. The aircraft further includes a battery assembly including a cold plate secured to the pair of longitudinally-extending beams, and a battery mounted to the cold plate.

Abstract: Apparatuses, systems, and methods for towing an aircraft mid-flight are disclosed. The apparatuses include a tow line receiver that is configured for releasably mechanically joining to an aircraft connector on an aircraft to be towed. The aerial vehicle towing system includes an aircraft connector on the aircraft to be towed, a tow line receiver, a tow line, and a winch. Several methods are also provided. These include: a method of towing or retrieving an aircraft in flight; a method of recharging an electrically-powered aircraft in flight; methods of towing and refueling aircraft in flight; a method of communicating between a tow aircraft and an aircraft being towed; and combinations of these methods.