Abstract: A helicopter has a fuselage, a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing extending from the fuselage on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system.

Abstract: A box frame hub arm structure is provided and includes a body having an outboard surface, which is disposable to abut with an inboard surface of an outboard arm of an aircraft rotor head, and lead/lag sides. The body is formed to define a first cavity, an aperture communicative with the first cavity through the outboard surface and second and third cavities. The second and third cavities extend outwardly in opposite lead/lag directions from the first cavity to the lead/lag sides.

Abstract: A rotor blade includes an elongated body having a leading edge, a trailing edge, a proximal end, and a distal end; a fluid inlet; a fluid outlet arranged near the distal end of the elongated body; and a fluid duct contained within the elongated body, the fluid duct being substantially open between the fluid inlet and the fluid outlet, the fluid duct having a shape to reduce fluid velocities C generated by the interaction of fluid exiting the fluid duct and external fluid at the distal end.

Abstract: An expendable rotary wing unmanned aircraft capable of storage in a cylindrical housing includes a longitudinally extending body having an upper end and a lower end; and a pair of counter-rotating coaxial rotors each located at respective ends of longitudinally-extending body, wherein each rotor includes two or more blades, each blade rotatably coupled to a remainder of the rotor at a hinged joint and thereby extending along a length of the body in a storage configuration and extending radially outward from the body in a flight configuration.

Abstract: A servo actuator (1) comprises an actuator housing (4); an actuator member (2) located within the actuator housing (4) and at least one spool (8) located in a cavity (6) formed within the actuator housing (4). The housing (4) also comprises a first set of internal ports including an inlet port (P), an outlet port (T) and a pair of control ports (SI, S2), the inlet port (P) being arranged for connection to a first pressurised supply and a second set of internal ports comprising an inlet port (P?), an outlet port (T?) and a pair of control ports (SI?, S2?), the inlet port (P?) being arranged for connection to a second pressurised supply. In use, movement of the spool (8) alters the flow path of fluid through the first and second set of internal ports to control the movement of the actuator member (2).

Abstract: Various embodiments include a drone capable of operating as an airplane, a quad-copter, or a hybrid aircraft using a versatile flight performance envelope enabled by six elements of control. The drone may include a monolithic wing with a propulsion/lift module connected to each wing tip. Each propulsion/lift module may include a pivotal support structure configured to pivot around a longitudinal axis of the monolithic wing, with two pylons extending radially outwardly from the pivotal support structure and at least partially away from one another, and a propulsion units positioned on a distal end of each pylon. The pivotal support structures may be coupled to the monolithic wing via a servo motor enabling a processor to individually control rotation of each propulsion/lift module to provide roll and pitch control. Thrust and rotation of the propulsion units may be individually controlled by the processor to provide yaw, roll and pitch control.

Abstract: A flying wing vertical take-off and landing (VTOL) aircraft is provided and includes an empennageless-fuselage from which foldable wings extend outwardly, an empennageless-nacelle supported on each of the wings and a rigid rotor propeller disposed on each empennageless-nacelle, each of the propellers being drivable to rotate about only a single rotational axis defined along a longitudinal axis of the corresponding empennageless-nacelle and being fully cyclically controllable.

Abstract: In some embodiments, a pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a pod assembly; upload a flight plan to a flight control system of a flying frame including an airframe and a distributed propulsion system coupled to airframe; dispatch the flying frame by air to the current location of the pod assembly; couple the pod assembly to the flying frame; transport the pod assembly by air from the current location of the pod assembly to the destination of the pod assembly including transitioning the flying frame between a vertical takeoff and landing mode and a forward flight mode; and decouple the pod assembly from the flying frame at the destination of the pod assembly.

Abstract: A personal air vehicle may feature an air module that may be attached to a ground module. The air module may be equipped with exit vanes or vectored engine exhaust to provide redundant control effectors to the cyclic or collective pitch of at least one rotary wing under the control of a control system.

Abstract: Various systems and methods for providing and deploying a power harvesting drone are described herein. A power harvesting drone includes a motor assembly; an energy replenishment coupler; a processor communicatively coupled to the energy replenishment coupler; and a memory storing instructions, which when executed by the processor cause the processor to: operate the power harvesting drone to navigate a predetermined path; determine that a power supply used to operate the power harvesting drone is below a threshold of remaining power; identify an opportunistic energy source; and deviate from the predetermined path to replenish at least a portion of the power supply from the opportunistic energy source using the energy replenishment coupler onboard the power harvesting drone.

Abstract: Systems and methods for authorizing drones with access to airborne fulfillment centers (AFCs) and other warehouse facilities are described. For example, the systems and methods perform multiple authentication processes, including a physical authentication process and a virtual or electronic authentication process, when determining whether a drone is authorized to access an AFC. Once authorized, the drone may access the AFC to pick up and/or deliver packages or other products, to recharge, to seek repairs, to be housed, and so on.

Abstract: There is provided an electric apparatus including a battery (6); a first pair of motors (3a, 3d) coupled with a first pair of wings and a second pair of motors (3b, 3e) coupled with a second pair of wings; and a first motor control circuitry (12ad) configured to control, the first pair of motors and a second motor control circuitry (12be) configured to control the second pair of motors. The battery (6) is configured to supply power to the first motor control circuitry (12ad) via a first power line, and the battery (6) is configured to supply power to the second motor control circuitry (12be) via a second power line.

Abstract: A method and system for designing a cooperatively-driven aircraft system. A cooperatively-driven aircraft system comprises an aircraft, a movable ground monitor station or a fixed ground monitor station, a data link of a composite data chain, and a relay communication device. A flight management system is disposed inside the aircraft. The aircraft is connected to the movable ground monitor station or the fixed ground monitor station by means of the radio data link of the composite data chain. Telemetering data information about the flight management system is issued to the movable ground monitor station or the fixed ground monitor station by means of the composite data chain. A manned aircraft technology and an unmanned aerial vehicle system technology are combined, cooperative air and ground driving is constructed, and a new technology aircraft system integrating easy flight and safe flight is provided.

Abstract: A rotor assembly for a multirotor aircraft, and a multirotor aircraft, are disclosed herein. The rotor assembly has a first motor having a first axis of rotation and a first propeller connected to the first motor. The rotor assembly has a second motor having a second axis of rotation, and a second propeller connected to the second motor. The second propeller is smaller in length than the first propeller. The first motor and the first propeller produce a greater proportion of a total lift thrust of the rotor assembly than the second motor and the second propeller. The multirotor aircraft includes an airframe and a plurality of the rotor assemblies mounted to the airframe.

Abstract: A head mounted display capable of controlling maneuver of an unmanned vehicle, the head mounted display including a display section that allows visual recognition of an outside scene, a GNSS information acquisition section that acquires a GNSS information, a communication section capable of performing communication using wireless communication with the unmanned vehicle, and a control section, wherein the control section evaluates whether or not the unmanned vehicle has entered a visual field visually recognizable through the display section in a case where the unmanned vehicle travels in an automatic navigation mode in which the unmanned vehicle moves toward a position indicated by the GNSS information and causes the unmanned vehicle to terminate the travel in the automatic navigation mode but travel in a specific navigation mode different from the automatic navigation mode in a case where the control section determines that the unmanned vehicle has entered the visual field.

Abstract: An unmanned aerial vehicle for aerial transportation of delivery items. The unmanned aerial vehicle includes an attachment device to fasten and unfasten one or more delivery items to the unmanned aerial vehicle, a motor to aerially transport the one or more delivery items along a delivery route, a sensor mounted on the unmanned aerial vehicle to detect at least one environmental variable during the delivery route, and an alert system to generate a status associated with the unmanned aerial vehicle along the delivery route to an observer when the environmental variable exceeds a predetermined threshold.

Abstract: The unit (10) uses a resiliently biased electrical connector assembly (16) and/or resiliently biased feet (50) pivotally attached to adjustable sway brace legs (20) to apply an ejection impulse to a store (not shown) after release from a suspension hook (102). A safety latch mechanism comprises a pawl (130) which engages a nib (108) on the suspension hook assembly to prevent inadvertent release of the store if the suspension hook assembly becomes jammed e.g. due to ice formation.

Abstract: A precision delivery vehicle having a vehicle body assembly, a fixed wing system, a rotor system and a guidance system. The vehicle body assembly can retain a payload. The fixed wing system includes first and second wings coupled to the vehicle body for fixed wing flight. The rotor system includes a mast structure, a rotor hub rotatable about the mast structure and at least two rotor blades coupled to the rotor hub and rotatable with the rotor hub relative to the mast structure. The at least two rotor blades are movable between a collapsed configuration and a deployed configuration. In the collapsed configuration, the precision delivery vehicle is in fixed wing flight. Upon placement of the at least two rotor blades into the deployed configuration, the precision delivery vehicle is placed into rotative flight. The guidance system is structurally configured to direct the precision delivery vehicle to a target.

Abstract: In some embodiments, systems, apparatuses and methods are provided herein that enable delivery of retail products. Some embodiments provide delivery systems comprising: a package support frame comprising first and second package supports, and a pivot coupler pivotably securing the first package support with the second package support; and a first release plate positioned across a separation between the first and second package supports, and comprising: a set of at least one angled locking grooves; a set of at least one groove pins slidably positioned within a respective one of the locking grooves; and a release tab configured to contact a surface and cause an unlocking of the first release plate such that the release plate moves with the locking grooves sliding along respective groove pins such that the base of the package support pivots away from the base of the second package support enlarging a package release aperture.

Abstract: An load adaptive lift assist for a pivoting stowage bin includes an assembly housing having an interior and a pair of opposing end fittings. A piston rod is disposed within the assembly housing and operatively coupled to one of the end fittings, the piston rod being configured to move between extended and retracted positions based on the movement of the pivoting stowage bin. A spring retainer is attached to a structure that retains at least one lift assist spring and a latch mechanism is operatively coupled to the other of the end fittings. The latch mechanism includes at least one mechanical feature for retaining the spring retainer until a predetermined load has been exceeded in the stowage bin. The load adaptive lift assist automatically resets itself and does not require use of sensors or feedback controls.

Abstract: An overhead stowage compartment of a passenger aircraft includes a carrier and a pivoting part being pivotable about a pivot axis and rotatable in a pivoting range at least between an open position and a closing position. A resetting device brings about a closing force in the direction of the closing position at a gripping point of the pivoting part. The closing force is greater than and opposed to the gravitational force, which is effective at the gripping point, by using the unloaded pivoting part. The stowage compartment has a holding device through the use of which the pivoting part can be held at the open position.

Abstract: A solid state liquid-chilled bar unit for an aircraft galley includes a multilevel frame dimensioned to fit the galley and including stacked slots, each slot configured to fit a compartment. Warmer compartments include a liquid thermoelectric device (LTD) with “cold” and “hot” sides and a liquid heat exchanger (LHE) connected to the cold side. Scroll fans circulate air over a finned heat exchanger (on the LTD's hot side) to heat the compartment. Chiller compartments include LTDs with an LHE connected to the “hot” side, and may be bottle coolers or chiller drawers. Bottle coolers chill bottles or other containers via conductive contact with the LTD “cold” side, while chiller drawers chill air by circulating it over a finned heat exchanger on the “cold” side. Unchilled drawers store food, drink, or supplies at or near the ambient cabin temperature.

Abstract: A power control arrangement for an aircraft galley including a power control unit and an interface unit. A power input of the power control unit includes a main switch and connects to a power feed. Each of a power outlets of the power control unit includes an outlet switch and connects to a galley insert. A main switch interface on the interface unit is provided for switching of the main switch. Each outlet switch interface of the interface unit is associated with one of the outlet switches for switching the outlet switch. The interface unit is arranged remote from the power control unit and the switch interfaces are connected to the corresponding switch via an electrical, radio or optical connection for controlling switching of the switches. Further, an aircraft galley and an aircraft are disclosed.

Abstract: The present invention relates to a seat array (100), comprising a first (1) and a second (2) seat, arranged with their backrests opposite one another, said first (1) and second (2) seats being able to move from a sitting position to a lying position, possibly with possibility of stopping at each of the intermediate positions, a portion of dividing wall (respectively 3, 4) being arranged laterally with respect to said seats (1, 2), said portion of dividing wall (3, 4) being provided extending laterally at one side of said first and second seats (1, 2) and ending, on one side, in a portion containing a footrest (5, 6), arranged in front of the respective seat (1, 2), and on the other side at a distance from the respective side of the dividing wall (3, 4) of the seat (2, 1), in such a way as to leave an entry/exit passage (7), and thus access, to the seats (1, 2), said entry/exit passage (7) leading to a lane (respectively 8, 9) for reaching the first (1) or the second (2) seat, said dividing walls (3, 4), on th

Abstract: An airline seatbelt arrangement (10) includes an airline seat frame (5) with a seat base (3) connected to the airline seat frame (5). The seat base has a cushion upper surface (30). A seatbelt retractor (11) is connected to the seat frame (5). A seatbelt retractor (11) has a seatbelt (20) with a seatbelt tongue (12) connected to the seatbelt (20). A seatbelt guide (36, 36?, 36?, 35, 35?, 35?) is connected to the seat base. The seatbelt guide guides the seatbelt and seatbelt tongue from a retracted position to a deployed position within an angular range relative to the seatbelt connection location, whereby the seatbelt and seatbelt tongue may be positioned in the angular range relative to the cushion upper surface in the deployed position. The seatbelt guide may include a recess formed in the seat base and extending from a seatbelt retractor location to the cushion upper surface.

Abstract: An passenger cabin of an aircraft including a floor (108) on which are mounted a front seat (104a), a rear seat (104b) and a partition wall separating the front and rear seats, wherein the front seat (104a) pivots about an axis perpendicular to the floor (108) through an angle of at least 180 degrees, and the partition wall (106) has a fixed lower portion (106a) and a removable upper portion, and wherein a securing means has a securing position which secures the upper portion to the lower portion (106a), and a release position which allows the upper portion to detach from the lower portion (106a). The pivoting front seat and partition wall with detachable upper portion provide a first configuration seating configures that provides confidentiality between two passengers seated one behind the other, and a second configuration that permits communication between the seated passengers.

Abstract: A tray table configured to transition between a stowed position within a stowage module to a deployed position outside of the stowage module by way of an arced rail having rail heads, and a plurality of tray table wheels and stowage module wheels arranged to mesh with the rail heads. The tray table follows an arcuate path between the stowed and deployed positions and remains horizontal in all positions of the tray table.

Abstract: A panel door assembly for providing access to an aircraft passenger suite includes a stationary panel with a side portion extending between upper and lower ends of the panel door assembly. A lower portion of the stationary panel may extend across a width of the panel door assembly and slide along a rail between open and closed positions. A removable panel may connect to the stationary panel and may include a first latching mechanism connecting the removable panel to an upper portion of the stationary panel and a second latching mechanism connecting the removable panel to the lower portion of the stationary panel. An emergency handle may be connected on an inner side of the removable panel, that when actuated, engages the first latching mechanism and the second latching mechanism, disconnecting the removable panel from the stationary panel and providing an egress path from the suite.

Abstract: Described are examples of a seating arrangement for an aircraft with a first seat in a first accommodation space and a second seat in a second accommodation space, wherein the first and second accommodation spaces are configured to share a common floor space at a floor level of the aircraft. One seating arrangement includes a divider screen located between the first and second accommodation spaces, moveable, by sliding in a direction along the common floor space, between a stowed position permitting passenger egress between the first and second accommodation spaces across the common floor space, and a deployed position preventing passenger egress between the first and second accommodation spaces across the common floor space.

Abstract: Disclosed is a seat intended in particular for a passenger transport vehicle, the seat including a seating part, a backrest that pivots relative to the seating part, a headrest, and an active noise control device including: at least one error sensor capable of sensing a minimization acoustic field and generating a reference signal; a reference sensor able to capture an undesirable acoustic field; a processing unit able to generate a cancellation signal from the reference signal and from a signal representative of the undesirable acoustic field; and at least one speaker able to emit a cancellation acoustic field from the cancellation signal. The headrest includes a support and a first deformable casing carried by the support. The at least one error sensor is arranged on the first deformable casing.

Abstract: A passenger tray table includes at least two hingedly connected table sections, and is operable to move between at least three positions: 1) a stowed mounting position against a fore positioned monument, where the tray table stows at an angle relative to vertical, and a top portion of the tray table is closer to the passenger than a lower portion of the passenger tray table in the stowed position, 2) a first operative position, where a front table section of the tray table lowers into a horizontal position, while the rear table section remains in the angled stowed position, and 3) a second operative position, where the front table section is disposed closer to the passenger while the rear table section of the passenger tray table is lowered to a horizontal position, in line with the front table section to provide a contiguous table surface.

Abstract: An aircraft tray table assembly includes a recessed storage compartment covered by a pivoting lid which becomes an integral part of the tray table surface upon closing. A mirror may be fixedly attached to the inside of the lid. A passenger may be provided a mirror surface by flipping open the pivoting lid when positioned in a passenger seat within an aircraft. A retractor may be configured to closing of the pivoting lid when a passenger manually translates the tray table into a stowed position, thereby avoiding contact of the deployed lid with aircraft fixture surfaces proximate the stowed position of the tray table.

Abstract: A passenger seat module, a tray table deployable from within the module, and a drawer deployable from within the tray table. The tray table drawer is accessible regardless of the stowed or deployed position of the tray table to provide a stowage solution independent of tray table deployment. A module adapted to be positioned in proximity to a passenger seat and including a tray table coupled to the module through a support arm, the tray table movable between a stowed position within the module and a deployed position outside of the module.

Abstract: A seating unit (202, 204) includes a first seat (206, 210) and an adjacent second seat (208, 212), the seating unit being convertible between a first configuration in which each of the first seat (206, 210) and second seat (208, 212) can receive an occupant sitting thereon and a second configuration in which the first seat (206, 210) and second seat (208, 212) can collectively support an occupant lying thereon, and access to a space (215) in a back portion of the first seat (206, 210) being denied when the seating unit (202, 204) is in the first configuration and access to the space (215) being allowed when the seating unit (202, 204) is in the second configuration, the seating unit (202, 204) gives the passenger in the first seat (206, 210) a perception of increased spaciousness, and provides sufficient differentiation between the economy-class configuration and the business-class configuration.

Abstract: A connector for attaching a seat base cushion of an aircraft seat to an elongate frame member of an aircraft seat and for maintaining a gap between the seat base cushion and the elongate frame member includes (i) a body positionable between the seat base cushion and the elongate frame member, (ii) first and second frame fasteners for attaching the body to the elongate frame member; and (iii) a seat base cushion attachment means for removably attaching the body to the underside of the seat base cushion. The first frame fastener is provided on a frame facing surface of the body such that it is positionable between the body and the elongate frame member. The second frame fastener is for at least partially surrounding the elongate frame member. Also described is a seat frame, seat base cushion, seat and row of seats.

Abstract: A fuselage is described that includes a plurality of frames and a plurality of seat rows spaced apart according to a seat pitch. Each frame includes a lateral floor beam, and each seat row of the plurality of seat rows includes a load-bearing structural base with a plurality of legs attached to a proximal lateral floor beam and a distal lateral floor beam. Each seat row also includes a seat or bank of seats attached to the load-bearing structural base, where the seat or bank of seats includes at least one seat bottom and at least one seat back. Further, each seat row includes an interface between (i) the load-bearing structural base and (ii) the seat or bank of seats to allow for attachment and detachment of the seat or bank of seats relative to the load-bearing structural base.

Abstract: A functional unit in a passenger cabin includes a support unit and a passenger seat system. The passenger seat system is formed in two parts and has an upper constructional unit and a lower constructional unit that are each separate components, the upper constructional unit arranged on the support unit and containing at least one backrest, and the lower constructional unit containing a seat frame, at least one seat element and restraint for the passenger on the seat. The seat frame is fastenable to seat rails on the floor of a passenger cabin. For the use position, the upper and lower constructional units are positioned such that a passenger seat is formed. In the use position, personal comfort for the individuals on the seats is not impaired as far as possible, and the division of the seat system into two parts cannot be seen by the user.

Abstract: A seat track cover for a passenger seat of an aircraft is positionable on a seat track. The seat track cover is mechanically coupled at a first end to a seat leg structure of the passenger seat via a pivot joint. The seat track cover is arranged substantially parallel to the seat track and takes up a covering position which covers a seat track located therebeneath when the passenger seat is in its working position. The seat track cover takes up a stowed position in a second state, wherein, in the stowed position, the seat track cover is pivotable out of the parallel plane with respect to the seat track via a pivoting movement about the pivot of the pivot joint. The transition from the covering position to the stowed position takes place via the pivoting movement about the first end of the seat track cover.

Abstract: A retractable chair for an aircraft cabin which is connected in use to a wall of the cabin, and includes an articulated frame having a back and a seat; a support which is connected to the frame, and fitted such as to be mobile on the wall around an axis of rotation; and at least one covering stretched on the frame. The fact of pivoting the support relative to the wall makes it possible to be able to incline the back, which contributes towards improving the comfort of the chair.

Abstract: An air distribution system and method for an air conditioning system in an air vehicle are provided. The air distribution system has lower lobe ducts below a cabin floor of a cabin of the air vehicle. Each lower lobe duct is in fluid communication with a mix manifold coupled to AC packs. The air distribution system further has sidewall riser ducts, outboard manifold ducts, a recirculation air duct, and either recirculation downer ducts, or branch recirculation ducts coupled to the recirculation air duct. The air distribution system has a conditioned air flow, distributed to either the lower lobe ducts, or the lower lobe ducts and then the sidewall riser ducts; has a recirculated air flow, distributed to either the recirculation downer ducts or branch recirculation ducts; and has a mixed air flow distributed to the outboard manifold ducts, and into the cabin.

Abstract: An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, a turbine coupled to the compressor via the shaft; and a heat exchanger. The compressor receives and compresses a first medium in accordance with power provided by the turbine via the shaft. The turbine receives and expands a second medium to provide the power to the compressor via the shaft. The heat exchanger is configured to cool the first medium.

Abstract: An airplane is provided. The airplane includes a motor-driven compressor assembly. The motor-driven compressor assembly includes a shaft, a motor, a compressor, and a turbine coupled to the compressor via the shaft. The motor provides a first power to the compressor via the shaft. The turbine receives and expands a second medium to provide a second power to the compressor via the shaft. The compressor receives and compresses a first medium in accordance with the first power provided by the turbine and the second power provided by the motor.

Abstract: The present invention relates to an aircraft comprising a fuselage, a lateral support wing (1) and propulsion assembly (100) mounted under the wing, the wing comprising at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream, and the propulsion assembly comprising a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans (102, 104) are attached directly to one of the said spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (?) with the axis of the fuselage, the two offset fans (102, 104) are axially offset from one another.

Abstract: The present invention relates to an aircraft comprising a fuselage (1), a propulsion unit (7) at the rear tip of the fuselage and at least two engines (3, 5) each driving an engine shaft (32, 52), the propulsion unit including at least one propeller (71, 73) driven mechanically by the engine shafts (32, 52), characterised in that the propulsion unit (7) includes two propellers (71, 73), each of the propellers being driven by a propeller shaft (72, 74), the two propeller shafts being driven by the engine shafts (32, 52) via a first differential epicyclic gear train (40). Specifically, the input of the first differential gear train (40) is connected to the output of a second differential epicyclic gear train (60), the second differential gear train (60) including two inputs (61c2, 62c2), each of said two inputs being connected mechanically to one of said engine shafts (32, 52).

Abstract: The invention relates to a system for suspending two modules of a propulsion unit, such as two fan modules, said system comprising a pylon (28) and a rudder bar (30). One part (30?) of the rudder bar is hinged to the pylon, while the opposing ends thereof are hinged to connecting rods (34, 36). The system also comprises a torque bar (40) which has an elongate shape and is mounted on the pylon such that it can pivot about an axis substantially parallel to an axis (13) of elongation of the torque bar, the opposing ends (42) of said bar being secured on each side of the above-mentioned part of the rudder bar.

Abstract: A method for prohibiting the propulsion of an electrical airplane when the airplane is galvanically connected to a ground station. The electrical airplane comprises a battery assembly, a low voltage electrical network provided with power contactors, at least one integrated electrical propulsion system and a processor. The method comprises steps of detection of a connection to the ground station by the battery assembly, of non-supply of the integrated electrical propulsion systems and of their switch to protection mode, and of stopping of the propulsion systems regardless of their supply of electrical energy and the user set point.

Abstract: A method and a device for controlling an aircraft propulsion assembly which mitigates the drawbacks of the application of a protection mode in which the maximum thrust is reduced (a degraded operating mode), in particular when an emergency situation occurs or the switch to protection mode is due to an incorrect analysis of the operating parameters of the propulsion assembly. The method includes a sequence of positions of the thrust control consisting in bringing the thrust control to idle then to setting it into the position corresponding to the desired thrust or a setting of the control to the maximum thrust position. Other simple sequences may include, the transition through the idling position with a transition to maximum thrust position, or through a succession of positions relative to the current position of the thrust control at the moment of the switch to degraded mode.

Abstract: A member includes a first composite member containing a plastic reinforced with a thermally conductive carbon fiber containing one or both of a metal-coated carbon fiber and a pitch-based carbon fiber, wherein one end of the thermally conductive carbon fiber is disposed in a heat-generating section, and the other end of the thermally conductive carbon fiber is disposed in a heat-radiating section in a fiber direction.

Abstract: Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of sensing three dimensional (3D) airflow by an aircraft includes: collecting measurements characterizing airflow near the aircraft; analyzing the collected measurements; creating, by a processor, a computer model predicting one or more 3D airflow patterns parameter values based on the analyzing; obtaining one or more additional measurements characterizing airflow near an aircraft of the plurality of aircraft, and evaluating an error between an airflow parameter value predicted by the computer model and the one or more additional measurement.

Abstract: A method for presenting an alert onboard an aircraft, by a computing device comprising at least system memory, a processor, and a plurality of sensors, is provided. The method identifies a status of the aircraft, by the processor, from a plurality of avionics communicatively coupled to the computing device via a wireless data connection; determines that attention of a flight crew member is required by one of the plurality of avionics, based on the status; determines that the computing device is in a state of current use, based on user input data received by the plurality of sensors; and presents an alert associated with the status and the one of the plurality of avionics, via a display device communicatively coupled to the processor, wherein the alert comprises an indication to direct the attention toward the one of the plurality of avionics and details associated with the status.