Abstract: A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.

Abstract: An aircraft includes cruise propellers, lifting propellers, an energy battery and a power battery. The energy battery is electrically connected to the cruise propellers, and the power battery is electrically connected to the lifting propellers.

Abstract: A transverse fan propulsion system includes a first transverse fan configured to rotate in a first direction, and a second transverse fan configured to rotate in a second direction. The second direction is opposite to the first direction. The second transverse fan is located coaxially with and radially inward of the first transverse fan.

Abstract: An information processing method includes the following steps performed using a processor: obtaining first region information indicating a first region; obtaining first position information indicating the position of an unmanned aerial vehicle tethered to a mobile tethering body using a tether; determining, using the first region information and the first position information, a first destination which is a destination of the mobile tethering body; and moving the mobile tethering body to the first destination. The first destination is a position located at least a predetermined distance from a point which is on the boundary of the first region and located the shortest distance from the position of the unmanned aerial vehicle, in the direction from the point on the boundary of the first region to the position of the unmanned aerial vehicle.

Abstract: A control device includes a processor which: obtains first region information indicating a first region; obtains first position information indicating the position of an unmanned aerial vehicle tethered to a tethering device using a tether; and controls the tethering device using the first region information and the first position information to cause the tether to have tension corresponding to a specified distance which is at least one of the shortest distance between a boundary of the first region and the position of the unmanned aerial vehicle and a distance included in a predetermined range from the shortest distance.

Abstract: One embodiment of a vertical take-off and landing aircraft held aloft by way of one or more powered assemblies of wing type elements capable of generating aerodynamic lift by means of rotation. A main body having an integrated means for directing air impelled from an inlet, by way of one or more powered impellers, through a cavity, acting as a duct, to an outlet. At least one movable surface located in sufficient proximity to the outlet to direct expelled air in a vectored manner providing a means of affecting the motion of the aircraft.

Abstract: Method and apparatus for unmanned aerial maritime float vehicle that sense and report relevant data from physical and operational environment. The apparatus is comprised of an unmanned aerial vehicle and cabled unmanned underwater vehicle. The method wherein a end-user's controller is coupled wirelessly to the unmanned aerial vehicle transceiver to allow relevant live data to be collected from sky and ground, Upon landing on a water's surface the cable is repelled and control signals and data are transmitted to the cabled unmanned underwater vehicle transceiver, thus high speed feedback and sensor signals can be transmitted from the cabled UUV back to the UAV then both the UUV and UAV high speed feedback and sensor signals are wirelessly sent back to the user's controller through the UAV.

Abstract: A system for controlling an unmanned aerial vehicle (UAV) to switch between different flight modes during operation. The system includes one or more processors configured to determine, based on sensor data received from one or more sensors carried by the UAV, a change in environment of the UAV from a first environment type to a second environment type. In response to determining the change in environment, the one or more processors configured to switch a flight mode of the UAV from a first flight mode to a second flight mode, and effect operation of the UAV in accordance with a second set of operating rules for operating in the second environment type.

Abstract: An aircraft pylon is provided, configured for mounting to the underside of an aircraft wing projecting from a fuselage and for carrying an external payload suspended therefrom. The pylon comprises an attachment mechanism configured for facilitating mounting of the pylon to the aircraft wing, and a carrying arrangement configured for carrying the payload and being pivotally articulated to the attachment mechanism. The pylon is configured to selectively pivot the carrying arrangement about a pylon axis between a vertical position in which it is suspended in a substantially vertical orientation, and a tilted position in which it is tilted toward the fuselage.

Abstract: A gatebox system for delivering fire retardant fluid from a firefighting aircraft. A first and second gate opening are formed through a lower portion of a gatebox. The gates are hingedly connected along edges of the openings. A drive shaft in the gatebox is rotatable in gates-closing and gates-opening directions. Crank arms are fixed to the drive shaft and coupled to the gates by connecting links, which define an over-center geometry while the gates are at a closed position, such that weight of the fluid on the first gate induces torque on the drive shaft in the gates-closing direction. Rotation of the drive shaft in the gates-opening direction enables control of the fluid flow from the hopper according to an angular position of the drive shaft.

Abstract: The aircraft seat dress covers with massage features are tailored specifically to provide more comfortable flight experience and accommodate unique airline seat requirements. Massage system include encapsulated vibration motors with massage functions to provide a relaxation massage that can help alleviate sore and tight muscles, improve circulation, and relieve tension during a few hours flight. Alternatively, the aircraft seat covers can have a heat massage therapy as well. The seat massage system is equipped with overheating protection system and auto shut off timer for safe use.

Abstract: An aircraft divan includes a lateral bracket connecting between front and rear legs with lateral bracket front and rear ends, a first track defined by the lateral bracket between the lateral bracket front and rear ends, an upright, having upright top and bottom ends, a second track defined by the upright between the upright top and bottom ends, a seat pan having seat pan front and rear ends, the seat pan being slidingly connected to the first track adjacent to the seat pan rear end, and a backrest having backrest top and bottom ends, the backrest being slidingly connected to the second track adjacent to the backrest top end. The seat pan rear end is pivotably connected to the backrest adjacent to the backrest bottom end such that movement of the seat pan is transmitted to the backrest so as to move together between upright and berth positions.

Abstract: A seat for an aircraft may comprise a seat pan and a back support coupled to the seat pan. An upper thoracic support may be located proximate an end of the back support opposite the seat pan. The upper thoracic support may be configured to rotate relative to the back support. A headrest may be coupled to the upper thoracic support.

Abstract: An unmanned aerial vehicle (UAV) includes a vehicle body and a flight control circuit. The vehicle body includes a housing and a fan. The housing includes two vents arranged at two ends of the housing and in communication with an internal space of the housing. The two vents and the internal space form a heat dissipation air passage. The fan is arranged at one of the two vents, and is configure to drive external air into the heat dissipation air passage and expel internal air from the heat dissipation air passage. The flight control circuit is arranged inside the housing and is configured to control flight parameters of the UAV. The heat dissipation air passage is configured to dissipate heat generated by the flight control circuit.

Abstract: An aircraft pressurized air system and method is disclosed. The system includes a compressor that receives and compresses outside air, and an air cycle machine that receives compressed air from the compressor and directs conditioned air to an aircraft pressurized zone. The system also includes a contaminant sensor disposed along an air flow path between the compressor and the aircraft pressurized zone, comprising an optical guide, a metal organic framework on an exterior surface of the optical guide in operative fluid communication with air from the air flow path, a light source in communication with the optical guide at a first end of the optical guide, and a light detector in communication with the optical guide at a second end of the optical guide.

Abstract: An aircraft air conditioning system comprising an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer. A first compressor is arranged in the ambient air supply line and is configured to compress the ambient air flowing through the ambient air supply line. A bleed air supply line allows a flow of bleed air bled off from an engine or an auxiliary power unit therethrough. A bleed air turbine is driven by the bleed air flowing through the bleed air supply line and is coupled to the first compressor so as to drive the first compressor.

Abstract: An environmental control system (ECS) for an aircraft includes at least one cooling turbine, and a turbine bypass valve disposed fluidly upstream of the at least one cooling turbine. The turbine bypass valve is configured to direct a first portion of an ECS output airflow to a first air load at a first pressure via a first outlet passage, and direct a second portion of the ECS output airflow across a cooling turbine of the at least one cooling turbine and to a second air load at a second pressure lower than the first pressure for cooling thereof.

Abstract: A softcover for an evacuation system may comprise a fabric panel. The fabric panel may define a plurality of apertures located proximate a first end of the first fabric panel. A plurality of straps may extend from a second end of the fabric panel. The straps may be configured to secure the fabric panel to a housing configured to receive an inflatable slide.

Abstract: This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.

Abstract: An rear fairing for a pylon supporting an aircraft turbojet engine forms an aerodynamic surface covering the base of the pylon. The rear fairing is elongated in a longitudinal direction and includes a floor arranged opposite the hot gases exiting the turbojet engine and side walls constituting aerodynamic surfaces. The floor and the side walls include ceramic matrix composite materials made from preforms formed by layers of superimposed warp and weft yarns, the preforms have interlayer weaving yarns connecting the layers to one another.

Abstract: Systems and methods for controlling a crossing threshold used in determining a rotational speed of a propeller of an aircraft engine. An initial value for the crossing threshold is set. A sensor signal is received that comprises a first series of pulses indicative of passage of position markers about a circumference of a propeller shaft. A detection signal is generated that comprises a second series of pulses indicative of within the first series of pulses that have a zero-crossing transition and a magnitude that exceeds the crossing threshold. The rotational speed of the propeller is determined from the detection signal. The crossing threshold is adjusted as a function of the rotational speed.

Abstract: An electric propulsion unit (102) for an aircraft is shown. A fan (202) produces a pressured airflow (P) by raising the pressure of an incident airflow (I). An electric machine (201) is arranged to drive the fan and is located within a casing (204). A primary cooling circuit (205) is located within the casing, and includes the electric machine and a first pass of a fluid-fluid heat exchanger (208), thereby placing the electric machine and the fluid-fluid heat exchanger in thermal communication. A secondary cooling circuit includes a second pass of the fluid-fluid heat exchanger and an air-fluid heat exchanger (210) located within the pressurised airflow produced by the fan, thereby placing the fluid-fluid heat exchanger and the air-fluid heat exchanger in thermal communication.

Abstract: An aircraft includes a battery, an airfoil and heat conducting elements, and the heat conducting elements connect the battery thermally to the airfoil in such a way that heat which is produced in the battery is distributed to the airfoil.

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: A method and device for detecting conditions conducive to the onset of pumping that can affect a low-pressure compressor of an aircraft turbine engine. The turbine engine including a high-pressure compressor. The method including measuring a speed variation of the aircraft and measuring a speed variation of the high-pressure compressor. The method including a preliminary step of measuring an altitude of the aircraft. The conditions conducive to the onset of pumping being detected when the following conditions are jointly obtained: (a) the speed variation measured over a predetermined time interval corresponds to an acceleration greater than a first positive threshold, (b) the measured speed variation corresponds to a deceleration less than a second negative threshold, and (c) the altitude is greater than a third predetermined threshold.

Abstract: A stop device includes a first shift lever including a first shifting part configured to rotate around a rotation axis to form a first motion trajectory, and a second shift lever including a second shifting part partially within the first motion trajectory. The first shifting part drives the second shifting part to rotate around the axis of the rotating shaft to form a second motion trajectory. The stop device further includes a stopping boss located on a periphery of the first motion trajectory and partially within the second motion trajectory. The second shift lever rotates to drive the second shifting part to contact a first side of the stopping boss when rotating in a first direction and to contact a second side of the stopping boss facing away from the first boss when rotating in a second direction opposite to the first direction.

Abstract: An engine exhaust-stack plug for sealing an exhaust stack of an aircraft engine is provided. The exhaust-stack plug includes a desiccant and a flexible plug adapted to slide into an outlet of an engine exhaust-stack. The flexible plug includes a front panel that is substantially impermeable to water vapor and is accessible from the outlet of the engine exhaust-stack. An outer wall, which is also substantially impermeable to water vapor, is sealed with the front panel and shaped to fit snuggly within the outlet of the engine exhaust stack. A backside is coupled with the outer wall, opposite the front panel, for facing internal to the engine exhaust stack. The front panel, the outer wall, and the backside form an enclosure adapted to contain the desiccant. The backside is substantially air permeable such that the desiccant reduces humidity and prevents condensation inside the aircraft engine.

Abstract: The present invention is directed to a drone based delivering system comprising a drone and a portable landing pad for landing and take-off of the drone. The portable landing pad comprising GPS guided lasers for guiding the drone to safely land on the landing pad, and wherein the drone is having GPS guided laser electronic receivers for receiving the laser beams from the GPS guided lasers. The drone further comprises a battery replacement system, wherein the drone swaps its discharges battery with a charges battery already docked in the portable landing pad.

Abstract: A positioning mechanism includes a base including a landing area and a guide member movably arranged at the landing area and configured to guide a moving object. The landing area includes a positioning portion. The guide member is configured to be in a non-operating state or an operating state relative to the base. A form of the guide member in the non-operating state is different from the form of the guide member in the operating state.

Abstract: A secure terminal for the aerial transport of passengers whose technical and operational infrastructure makes it possible to ensure the physical security of the building, of the aircraft, of the goods, of the passengers and of the flight, technical and administrative personnel and the confidentiality of the passengers and of their goods, noteworthy in that it comprises at least one building having a globally V-shaped horizontal section and comprising two branches extending from a mid-zone, constituting parking hangars for aircraft and determining between them an uncovered central zone.

Abstract: A transport jig includes: a frame member; and a support section that is installed on the frame member and that supports a plurality of elongated members. The elongated members are each entirely housed inside the frame member in a lengthwise direction and the support section supports the plurality of elongated members in parallel with one another in one direction.

Abstract: A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.

Abstract: A method (600) for testing control logic for a propeller driven by a gas turbine engine of an aircraft includes overriding (602) a signal indicating the aircraft is operating in a ground mode. The method can further include testing (604) minimum pitch protection logic when the signal is overridden; determining (606) the gas turbine engine is operating at a ground fine setting; restoring (608) the signal to an original state in which the signal indicates the aircraft is operating in the ground mode; modifying (610) pitch protection logic; determining (614) the propeller is operating at an overspeed condition; and testing (616) the propeller overspeed protection logic. In addition, the method can also determine (612) the propeller is operating at a low pitch condition when the gas turbine engine is operating at the ground fine setting.

Abstract: A self-mating modular satellite bus includes a plurality of side panels each having a front surface flanked by a first longitudinal edge and a second longitudinal edge, wherein the first longitudinal edge of each side panel is nested with the second longitudinal edge of an adjacent side panel. The longitudinal edges, when superimposed, form a joggle. A method of producing the modular satellite bus includes forming a plurality of the panels, aligning the first longitudinal edge of each side panel with the second longitudinal edge of an adjacent side panel, such that the first longitudinal edge of each side panel is nested with the second longitudinal edge of the adjacent side panel, and securing the first longitudinal edge of each side panel to the second longitudinal edge of the adjacent side panel.

Abstract: A satellite configuration includes a plurality of individual satellite buses each having a number of side panels that form a polygonal shape, where the individual satellite buses collectively fit together to form the satellite configuration having a regular polygon shape. A method of producing the satellite configuration includes forming a plurality of individual satellite buses each having a polygonal shape, and fitting the individual satellite buses together to form the satellite configuration in a regular polygonal shape.

Abstract: An attitude control apparatus for a satellite includes: at least three electric motors, wherein the at least three electric motors are arranged in such a way that a torque may be generated with any orientation of an associated torque vector, and a controller, wherein the controller is configured to drive the at least three electric motors based on a torque controller. The torque controller is adapted to operate the at least three electric motors outside a rest state only when an acceleration torque and a braking torque are required to execute an agile attitude change maneuver. There is also described an associated method.

Abstract: The invention relates to a device and a method for the connection and linear separation of two elements, such as the two stages of a spacecraft, consisting in using a tube containing a pyrogenic-type material and a glue arranged around the tube, particularly in contact with the elements. The pyrotechnic triggering of the pyrogenic material causes heating and the melting or carbonisation of the glue and the separation of the two elements.

Abstract: To provide a judgement supporting system being able to support the judgement work of the pharmacist who judges the results of the package processing and a medicine dispensing apparatus. A judgement supporting system 1 comprises a packaging unit 504 performing a package processing for packaging one or a plurality of tablets in a wrapping material for every administration timing based on formulation data; and a shifted-back detection part 510 for determining occasion of a shifted-back defect when at least a part of the tablets to be charged in a first wrapping material in the package processings is wrapped in a second wrapping material being next to the first wrapping material.

Abstract: The operation handle includes a link portion engaged with the main handle on one side as viewed from the rotation fulcrum and a lever operation portion on the other side as viewed from the rotation fulcrum. The clincher arm is configured to rotate in a closing direction with respect to the main handle when the lever operation portion and the main handle are gripped. The binding machine for gardening further comprises a cover member configured to cover the link portion.

Abstract: A packaging machine to make an airtight wrapper (12) comprising a wrapping sheet (112) wrapped airtight around a structured assembly (11) consisting of an organized group of smoking articles (14) associated with a reinforcement insert (16) comprises, in working sequence on one or more cyclical conveyor devices (39, 71) of the wheel or carousel type: a structured assembly formation unit (30), a combination unit (31) suitable to combine the structured assembly (11) with said wrapping sheet (112), a wrapping sheet work unit (32) and a welding unit (34).

Abstract: The invention relates to a dosing apparatus for dosing bulk material into block forming elements, and for arrangement on a filling car of a filling apparatus of a block-making machine for manufacturing patterned blocks, in particular paving blocks. The filling car may be pushed forward and backward over block forming elements in a displacement direction, and a first bulk material component may be filled into the block forming elements with this car. The dosing apparatus comprises at least one filling box that has a lower outlet that may be opened and closed by means of a closure. A second bulk material component may be filled from the filling box into the block forming elements via the lower outlet.

Abstract: The invention relates to a processing apparatus for packaging machines having at least one upper processing unit for processing upper package sides and at least one lower processing unit for processing lower package sides, and having a common adjustment axle for the processing units along which the processing units are adjustable manually or by means of a drive in an adjustment direction that extends in parallel with a direction of transport of the packaging machine.

Abstract: A plural-mode automatic medicament packaging system. In embodiments, the system may include an automatic dispensing machine including an automatic medicament dispensing unit and may further include pouch packaging and blister package packaging units. The medicament dispensing unit may include one or more storage and dispensing units which store and dispense medicaments. Medicaments output from the medicament dispensing unit may be packaged in a pouch package by the pouch packaging unit. Alternatively, a diverter may direct medicaments output from the medicament dispensing unit to the pouch package packaging unit for packaging in a blister package. A single automatic medicament packaging system can package medicaments in different types of packaging providing a pharmacy with the opportunity to package medicaments in the form of packaging most appropriate to meet patient needs.

Abstract: A sticker placing device is provided for placing stickers and/or patches onto a surface. The sticker placing device comprises: a cylindrical guiding body having an upper opening, a lower opening and a guiding channel extending therebetween; a sticker cartridge for holding a stack of stickers and/or patches, which sticker cartridge is insertable into the guiding channel via the lower opening; and a sticker placer which is moveable connected to the guiding body and which comprises a pusher which extends at least partly into the sticker cartridge and the guiding body for pushing onto the stack, wherein the sticker cartridge comprises first coupling members and the sticker placer comprises second coupling members. The first and second coupling members are configured to form a one-way coupling. The one-way coupling allows movement of the sticker cartridge in the insert direction and blocks movement in a direction opposite to the insert direction.

Abstract: A plastic box sealing structure includes a plastic box body formed by bending a plastic plate, box bottom long, short side plates and box top sealing long, short plates, wherein the long side plate is configured with indented V-shaped notch on a sealing center position thereof, a bottom side of the notch is exactly positioned on a sealing center line of a bottom plate face, a sealing plate is respectively configured at two sides of the notch, left, right side plates of the opposite long side plates are formed with different symmetrical hole faces, the two opposite short side plates has opposite left, right cut edges, a plate face of the short side plate is configured with through holes corresponding to the through holes configured on the long side plate, allowing the side plates to be naturally stacked and assembles together.

Abstract: Variations for flat-folding box covers with four distinct design configurations: one piece; two piece; flat-folding structural frames and clear, rigid box covers with decorative inserts. Construction techniques comprise a variety of methods including use of cutout stock sheet materials; use of stiffening panels; use of structural frame elements; use of lamination; use of clear plastic panels; and the use of coatings. Fastening techniques comprise a variety of methods including; magnets, snaps, structural frames, hinges, and adhesives. The end user may purchase finished box covers or components or select from a set of design options offered by a manufacturer; or supply custom decorative images to a manufacturer to apply to the box cover; or purchase a kit in order to make or embellish a box cover themselves. Some designs allow for the end user to update and reconfigure the design elements of the box cover after it is purchased.

Abstract: The present disclosure relates to a storage container and, more particularly, to a foldable packaging system and methods of assembly. The foldable packaging system includes: a main body; a front flap section; and an intermediate body portion connecting to both the main body and the front flap section at a first fold line and a second fold line along upper and lower edges of the intermediate body portion, respectively, wherein the first fold line has a length “x”, the second fold line has a length “x?”, and x>x?.

Abstract: A package assembly suitable for use in storing and shipping a plurality of product containers includes a shipping configuration and a display configuration. In the shipping configuration the package assembly is constructed from a single blank of packaging material and formed into a case into which a plurality of product containers are inserted. In the display configuration a top portion of the case is removed from a bottom portion of the case along one or more tear lines on the blank.

Abstract: The invention describes a secondary packaging box for pharmaceutical products, comprising at least two separable compartments wherein the box comprises perforation to enable separation of the compartments. The box includes means for keeping the primary package stable and also detection of tampering owing to its design.

Abstract: Example aspects of a storage box and a method for assembling a storage box are disclosed. The storage box can comprise a sidewall enclosure, the enclosure defining a top edge and an opposing bottom edge, a fastener extending from the bottom edge, and a tray, the fastener coupling the tray to the sidewall enclosure.