Abstract: A propulsion module of an air mobility vehicle may include a door provided in the housing and opening or closing the opening portion of the housing by a sliding motion of the door; a propeller for providing propulsion to the air mobility vehicle; a link assembly having a first end portion connected to the housing and a second end portion connected to the propeller to pull the propeller into the internal space of the housing through the opening portion or pull the propeller outside the internal space through the opening portion; and a door opening and closing portion coupled to the door and configured for providing an opening and closing force to the door according to an inward-pulling motion or an outward-pulling motion of the propeller.

Abstract: A high rise building escape drone is shown and described. The high rise building escape drone includes of a frame. The frame has a spine secured to an upper housing. The upper housing secures a motor and a CPU operably connected to the motor. The motor is rotatably coupled to at least one propeller. A seat is secured to the spine below the upper housing. A control panel is secured to the seat. The control panel is operably coupled to the CPU and is capable to control the drone. A plurality of feet are secured to a bottom of the spine such that the feet support the drone.

Abstract: A method for operating a frost treatment system including a first heating mat, covering a first zone and an intermediate zone of a second zone, operating alternately at a first energy level adjusted to maintain a first positive temperature on the first zone and a negative temperature on at least a part of the intermediate zone and at a second energy level adjusted to generate a positive temperature on the intermediate zone, a second heating mat covering the second zone apart from the intermediate zone and ensuring the defrosting function for the zone. This solution makes it possible to reduce the energy consumption of the first heating mat by reducing the energy level at which it is powered for most of the time. Also, an outer wall of an aircraft is provided including at least one frost treatment system operating according to this method.

Abstract: A planter includes an interior surface and a riser extending from a bottom of the interior surface and including a space between the riser and lateral walls of the planter. The riser includes an open-top recess formed in a top portion of the riser. A plate including a protrusion extending from a bottom side of the plate and forming an open-top reservoir on a top side of the protrusion. The protrusion is configured to be coupled with the recess to secure the plate to the riser.

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: Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.

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: A compact harmonic drive system with a motor residing within the flexspline cup. The motor may reside further into the flexspline cup than the wave generator, and the air gap of the motor may be further out radially than the interior of the wave generator bearing. The motor may use an outrunner configuration with an outboard rotor made up of magnets, allowing for a large radial distance to the air gap and resulting in higher torque. The interior stator windings are thermally well coupled to the drive system structure. The harmonic drive may be coupled to a deployment system adapted to support moment loads perpendicular to the rotation axis such that those loads are not supported by the harmonic drive.

Abstract: A system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprises: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.

Abstract: A milking system includes a milking device, a milk line, and a sampling and analysis device for the milk that includes a control unit, a tape mover to move and unwind a tape wound on a tape reel and with a base material with reagent pads, that detect a substance in the sample, and a dosing device to provide the sample onto a reagent pad, and a sensor to detect radiation from said reagent pad, and to analyse the detected radiation to indicate a presence or concentration of said substance. The reagent pad is facing downward during provision of the sample. In this way, the chance of excess liquid falling from the reagent, and possibly onto a camera, is reduced. Smaller reagent pads may be used, it reduces the chance of supplied liquid spilling over to a neighbouring reagent pad, the measures preventing this spilling may be limited, and it is easier to suck away excess fluid.

Abstract: An aircraft includes electrical components and a ducted fan with a cooling coil. The aircraft is designed to discharge heat from the electrical components to the cooling coil.

Abstract: An energy-load assembly includes an accommodating box, a power source, a load and an undercarriage. The accommodating box can be connected to a body of an unmanned aerial vehicle; the power source is arranged in the accommodating box, and can provide electric energy to the unmanned aerial vehicle; the load is arranged at the bottom of the accommodating box; and the undercarriage is connected to the accommodating box. The energy-load assembly provided integrates the power source, the load and the undercarriage. The corresponding power source and the load can be integrated according to different tasks performed.

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 method for controlling maneuver of a refueling device, that includes: a refueling device is attached by a hose to a component of an aircraft. That component maintains a reference force on the hose. The desired position and current position of the refueling device are obtained. A determination is made, based on the current and desired positions of the refueling device, whether to extend or retract the hose. Depending on the determination, a command is sent for adjusting force generating arrangements that are attached to the refueling device. This causes the component to detect a changed force and to maintain the reference force on the hose. The distance between the fueling device and the aircraft is thereby changed.

Abstract: A method of unmanned aerial vehicle (UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV using at least one electric motor, providing primary vertical lift for the UAV during the forward flight using a fixed and non-rotating wing, repositioning the at least one electric motor to provide vertical thrust during transition of the UAV to vertical flight for descent, landing the UAV on a surface using a vertical approach after the motor repositioning, and deploying an anchor to secure the UAV to a surface.

Abstract: A passenger cabin area includes at least one aisle extending along a longitudinal axis of the passenger cabin area, a seating area next to the aisle in the direction of a transverse axis, perpendicular to the longitudinal axis, of the passenger cabin area and in which at least one passenger seat is provided, and a plurality of sleeping berths arranged above the seating area in the direction of a vertical axis, perpendicular to the longitudinal axis and the transverse axis, of the passenger cabin area. Each sleeping berth is accessible from the aisle of the passenger cabin area via a stairway element assigned individually to the sleeping berth.

Abstract: A system for repositioning rails in a cargo bay of an aircraft. The system includes a base configured to be coupled to a structure in the cargo bay and having a first side and a second side. The system further includes a cradle for receiving a rail for restricting movement of a unit load device (ULD) in at least one direction, the cradle configured to position the rail between a first position and a second position in which the rail is closer to the second side of the base than when the rail is in the second position.

Abstract: Methods, systems, and apparatus for drone landing ground station. A method includes determining that a drone is landing on a ground station, based on determining that the drone is landing on the ground station, determining a magnetic field to generate at a first magnetic component at a first position in the ground station and an opposing magnetic polar at a second magnetic component at a second position in the ground station, and generating the magnetic field at the first magnetic component and the opposing magnetic field at the second magnetic component.

Abstract: A composite core assembly includes a composite core structure having internal material interfaces and an attachment rail coupled to the composite core structure. The attachment rail includes a first planar surface and a second planar surface adjoined with the first planar surface. The first planar surface is arranged parallel to an internal material interface plane of the composite core structure, and the first planar portion is at least partially integrated into the composite core structure in an internal material interface plane. At least a portion of the first planar surface extends beyond a perimeter surface of the composite core structure, and the second planar surface is configured to attach to the surrounding support member. The core material does not have net edge facets or flat edges positioned next to surrounding structure, and/or may not have a structure arranged parallel to the adjacent support structure to attach to the support structure.

Abstract: A system and a method are provided for safely and efficiently transferring cargo and freight packed in ULD containers directly between an airport freight terminal and freight aircraft. An enclosed freightway is designed to provide a direct connection between the freight terminal and aircraft cargo doors. The enclosed freightway is structured and sized to move ULD containers automatically or manually between freight aircraft and freight terminals. Different freightway configurations enable direct connection between the freight terminal and freight aircraft main cargo door when freight aircraft are driven by electric taxi drive systems or aircraft engines and parked in nose-in orientations and when freight aircraft are driven by electric taxi drive systems and parked in parallel orientations at the freight terminal. An alternative embodiment provides direct connections between freight aircraft cargo doors and interior loading docks for aircraft driven with electric taxi drive systems.