Abstract: A manufacture and process for a winglet formed as a unitary structure by laying up and co-curing three ply-sets in a bifurcated configuration, without metal and fasteners, comprising three continuous surfaces: a first ply-set comprising a first continuous surface forming: an outboard surface of an upper blade; an outboard portion of a root region; and an outboard surface of a lower blade; a second ply-set forming a second continuous surface forming an inboard surface of the upper blade and an upper skin of the root region; and a third ply-set forming a third continuous surface forming an inboard surface of the lower blade and a lower skin of the root region . . . continuous surface. The root region being integral in the bifurcated configuration, matching a shape of an airfoil of a tip of a wing, and comprising two supports that comprise an additional ply-set shaped to receive an attachment system.

Abstract: Adjustment mechanisms, systems and methods allow for a moveable aerodynamic surface to be positionally adjusted relative to a stationary adjustment surface so as to ensure smooth aerodynamic transition between such surfaces. The adjustment mechanisms may include a base structure adapted for fixed connection to the moveable aerodynamic surface, a fixed-position receiver opposing the base structure and adapted for positionally fixed connection to the support structure of the moveable aerodynamic surface and an adjustment bolt having a head and a threaded shaft extending from the head through an elongate slot of the base structure, the slot defining an elongate axis which is aligned with an adjustment axis for the moveable aerodynamic surface, and being threadably coupled to the receiver to operably interconnect the base structure and the receiver.

Abstract: An example aircraft includes (i) a landing gear having a chassis, an axle, and wheels mounted to ends of the axle; (ii) a hydraulic actuator including a cylinder, a first piston coupled to the chassis, and a second piston coupled to the axle; and (iii) a directional control valve including: inlet ports configured to be fluidly coupled to a source of pressurized fluid, tank ports configured to be fluidly coupled to a tank, and workports configured to be fluidly coupled to the hydraulic actuator.

Abstract: A multirotor aircraft with an airframe and at least one wing that is mounted to the airframe, the at least one wing being provided with at least four thrust producing units that are arranged in spanwise direction of the at least one wing, wherein each one of the at least four thrust producing units comprises at least one rotor assembly that is accommodated in an associated shrouding, the associated shrouding being integrated into the at least one wing, wherein the associated shrouding defines an air duct that is axially delimited by an air inlet region and an air outlet region, wherein the air inlet region exhibits in circumferential direction of the air duct at least two different aerodynamic profiles.

Abstract: A centrifugal force (CF) bearing for a rotorcraft rotor assembly includes an inner-member, an outer-member, and an elastic member interposed between the inner- and outer-members. The outer-member includes an upper flange extension and a lower flange extension for location to and engagement with a grip. The upper flange extension is disposed over an upper surface portion of the elastic member, and the lower flange extension is disposed under a lower surface portion of the elastic member. The CF bearing is configured for attachment to a grip of the rotor assembly. The outer-member is configured to communicate mechanical loads (e.g., centrifugal force, lateral shear, vertical shear) from the grip to the yoke during operation of the rotor assembly.

Abstract: The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

Abstract: A rotor actuation system includes a swashplate assembly comprised of a stationary swashplate and a rotating swashplate operatively connected together for relative rotation about a rotor axis. A cyclic actuator is operatively connected to the stationary swashplate to tilt the swashplate assembly off axis from the rotor axis for cyclic control. A collective actuator is operatively connected to the swashplate assembly to move the swashplate axially along the rotor axis for collective control. The cyclic actuator and the collective actuator are operatively connected to the swashplate assembly to respectively actuate cyclic and collective control independent of one another.

Abstract: An example rotating swashplate ring to rotor mast connection includes a polygon-shaped drive tube secured to the rotor mast and a gimbal joint connected between the rotating swashplate ring and the polygon-shaped drive tube, wherein the gimbal joint rotates with the rotor mast and can translate axially along the polygon-shaped drive tube.

Abstract: Method and apparatus for a flight vehicle including a wing having a high aspect ratio and first and second rotors having a high aspect ratio, with a ratio of the rotor diameter to wing length ratio is equal to or greater than about 0.25. In embodiments, the flight vehicle can include a first and second motor, each less than about one thousand HP, to drive a respective rotor and a second motor. The flight vehicle can include a cruise mode and a VTOL mode.

Abstract: In one embodiment, a tiltrotor aircraft may comprise a fuselage; a biplane wing coupled to the fuselage, wherein the biplane wing comprises an upper wing structure and a lower wing structure; a plurality of tiltrotors coupled to the biplane wing; and at least one engine to power the plurality of tiltrotors.

Abstract: A rotorcraft comprising a fuselage, a single main rotor, and a first propeller and a second propeller. The rotorcraft has an adjustment system configured, at least during a stage of hovering flight, to position the first propeller in a first low speed configuration in order to exert a first thrust including a first horizontal component and a first vertical component, the adjustment system being configured, at least during the stage of hovering flight, to position the second propeller in a second low speed configuration so as to exert a second thrust comprising a second horizontal component and a second vertical component.

Abstract: In one possible embodiment, a system capable of a self-propagating data link includes an unmanned vehicle having a data link transceiver and at least one deployable data link transceiver. The unmanned vehicle having a deployment means for deploying the at least one deployable data link transceiver.

Abstract: An unmanned aerial robotic vehicle (UARV) that can fly to an object such as a palm tree, hover in place adjacent to the object, mount itself securely and releasably to a mounting location on the object using a mounting mechanism, and which uses an incorporated utility system for performing one or more utilitarian functions, such as use of a cutting tool to trim palm tree branches and foliage.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pushing motor and propeller assembly that is oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, the pushing motor may be engaged and the pushing propeller will aid in the horizontal propulsion of the UAV.

Abstract: A computer system for mapping the movement of a user to the controls of a drone generates, with a mixed-reality device, a simultaneous localization and mapping coordinate system of a user environment. The system then receives, from sensors within the mixed-reality device, a movement variable that comprises an indication that the user has moved a first distance in a particular direction with respect to the simultaneous localization and mapping coordinate system. The system communicates, to the drone, a movement command to move a second distance and particular direction based upon information within the movement variable.

Abstract: A drone is operated by a sky diver. The drone is interfaced to a parachute pack worn by the sky diver. The sky diver has a device (e.g. smartphone, smartwatch) that communicates with the drone to initiate launch/lift and to release the sky diver. In some embodiments, after the sky diver is released, the drone maneuvers around the sky diver to capture pictures/video of the sky diver. In some embodiments, safety features are included to assure the drone has sufficient battery power to achieve a safe jump altitude above ground level and to assure the release is not made until the drone achieves that safe jump altitude.

Abstract: A drone comprises at least one propeller for generating lift and an article containment area for containing an article to be carried by the drone. The floor of the article containment area comprises a dynamic support surface for supporting the article and allowing the article to move into, out of and through the article containment area. The dynamic support surface may be a conveyor belt forming the floor of the article containment area.

Abstract: A cabin monument for an aircraft includes a floor panel, which forms a base surface of the cabin monument, and a surrounding sidewall which defines an interior space of the cabin monument. The surrounding sidewall is assembled from a first wall part and a second wall part which is coupled to this. Provision is made on at least one of the wall parts for a fixing section which is overlapped by the floor panel. Also described is an aircraft which features such a cabin monument.

Abstract: A venting outlet (1) for a drinking water supply system of an aircraft is proposed, having an inlet opening (3) which is arranged on a rear side of the venting outlet and is intended for receiving a venting fluid, in particular air, from the drinking water supply system, and further having a venting opening (6) arranged on a front side of the venting outlet and intended for discharging at least some of the received venting fluid to an external surroundings of the venting outlet (1).

Abstract: A wall module for a cabin of a vehicle for separation of different cabin regions comprises a lower wall section having a fastener for fastening the wall module to a structurally fixed component fixed to the floor in the cabin, a surface-like rigid upper wall section converging with the lower wall section having a second fastener in a region of the wall module facing away from the lower wall section for fastening the wall module to a structurally fixed component fixed to the ceiling in the cabin. The upper wall section at least in a region comprises an arched curvature around a horizontal axis for adapting to the shape of a backrest of a seat. The wall module comprises at least one element stiffer than the upper wall section, which extends from a region adjacent the floor to a region adjacent the ceiling of the wall module.

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: A table apparatus includes a table device and a table support structure that is connected to the table device. The table support structure includes a carrier structure and a table support linkage. The carrier structure is connected to the table support linkage via a single pivot connection. The table device is pivotable about only the single pivot connection.

Abstract: A cable actuating mechanism that actuates through a central pivot axis of a pivoting mechanism including two articulating cable actuators that contact opposing ends of a floating pin that passes through the center of the pivot. One actuator is affixed to a stationary assembly of the pivot device and the other actuator is affixed to a rotating body of the device. A first cable pulled at one end of the device pulls a second cable at an opposing end of the device through the articulating cable actuators. The cable actuating mechanism can be used to unlock, for example, a seat recline lock device in an aircraft seat equipped with a pivoting armrest, among other applications within and outside of an aircraft cabin environment.

Abstract: Described are passenger support assemblies for a passenger seat, including an expandable inner frame that attaches the passenger support assembly with a seat frame and an expansion mechanism that allows the expandable inner frame to change in width, and an outer frame that includes two side frame elements connected with the expandable inner frame and extending beyond the expandable inner frame, the outer frame configured to change in width in response to a change in width of the expandable inner frame. A diaphragm can held in tension by the two side frame elements of the outer frame to define a seating surface.

Abstract: A seating system for a vehicle that comprises floor beams, which support floor panels that define a floor surface. The vehicle has a virtual longitudinal plane, perpendicular to the floor surface, and a virtual longitudinal axis, parallel to the floor surface and lying in the virtual longitudinal plane. The seating system comprises a primary pair of seat tracks, a secondary pair of seat tracks, one of which is positioned between seat tracks of the primary pair of seat tracks, and a first seat assembly. The first seat assembly comprises a first seat support and a first plurality of seats, attached to the first seat support. The first seat support is attached to the primary pair of seat tracks.

Abstract: Air conditioning system for a cabin 6 of an aircraft, the air conditioning system 1 including a pressurized air source 2, a ram air duct 3, an air amplifier 4 and a heat exchanger 5. The air amplifier 4 includes an inlet 41 for work air, a slot 42 suitable for letting the work air exit the air amplifier, and a main fluid zone 43. The inlet 41 is in fluid communication with the pressurized air source 2 and the slot 42 is arranged in fluid communication with the ram air duct 3, in such a way that the work air exiting from the slot 42 produces a suction effect in the ambient air in such a way that this ambient air flows along the ram air duct 3. The air amplifier 4 is arranged so that the ambient air is forced by the suction effect to pass from the inlet 51 to the outlet 52 of the cold side of the heat exchanger 5.

Abstract: An evacuation system may comprise an evacuation slide configured to be deployed from an aircraft, a first strap coupled to the evacuation slide, a second strap coupled to the evacuation slide, and a releasable restraint extending through the first strap and the second strap. The releasable restraint may comprise a first stem connected to a first bead and a second stem connected to a second bead, wherein a diameter of the second stem may be different from a diameter of the first stem.

Abstract: An apparatus and method for mounting a turbine engine to an aircraft can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section.

Abstract: An assembly between an aircraft structural pylon and an aircraft turbine engine is disclosed, with the assembly comprising a beam intended to be attached to the turbine engine and wherein a knuckle intended for the installation of a pad integral with the pylon is mounted, with the beam comprising suspension lugs each including a bore for the passage of a shaft intended to further go through a bore formed in the pylon to connect the beam with the pylon.

Abstract: A device for managing the mechanical energy of an aircraft, having an energy management auxiliary system, includes a support defining a guide, a centralized control lever for varying the energy of the aircraft, at least one position sensor detecting the position of the centralized control lever in the guide. The position sensor is configured to create position information for the position of the centralized control lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an auxiliary support; for the or each motor of the aircraft, an individual control lever for the individual propulsion of the motor, mounted movably in the auxiliary support; and at least one auxiliary position sensor detecting the position of the or each individual lever configured to generate information intended to be sent to the flight control unit of the aircraft.

Abstract: An acoustic insert comprises a sleeve and a number of wave-shaped passageways within the sleeve. A contour of the number of wave-shaped passageways is selected to provide a desired level of attenuation for a frequency of sound waves entering the sleeve.

Abstract: An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between ? and ? of the total chord between the stop point and the assembly point.

Abstract: One embodiment is a passive particle separation system including a plenum; an inlet for feeding outside air into the plenum, wherein the outside air has particles entrained therewith; a housing for enclosing the plenum; and a standpipe installed on the housing. The outside air enters the plenum via the inlet and plenum, housing, and standpipe interact to impact the outside air entering the plenum to cause the particles to be released from the outside air.

Abstract: An aircraft system includes a component configured to operate with a minimum power demand. The aircraft system also includes an auxiliary power unit including an engine. The auxiliary power unit is configured to power the component and to operate the engine in a plurality of operating modes including a power mode and a standby mode. The auxiliary power unit generates a first power output at least equal to the minimum power demand during the power mode. The auxiliary power unit generates a second power output less than the minimum power demand during the standby mode.

Abstract: An exterior aircraft light for indicating a movement of a foldable wing tip between a folded up position and a laterally extended position includes a light source; and a control unit; wherein the control unit is configured to operate the light source to emit a warning light output in response to a warning light control signal indicative of the movement of the foldable wing tip.

Abstract: An aircraft communication network comprises in-flight entertainment terminals, an addressing system, communication links and one or more cameras intended for installation inside the aircraft. A passenger can thus receive on their in-flight entertainment terminal, images captured by one of the cameras or data deduced from the images. Said images or data inform him of crowding in common access areas or shared use areas inside the aircraft.

Abstract: Devices and methods improving the ability to capture images remotely and manually with a camera integrated with or attached to a drone. A display screen on the drone body allows viewing of captured image data. Booms are configured to both support the flight components of the drone and allow manipulation. Boom handles allow a user to hold and manually aim the camera.

Abstract: Aerial launch and/or recovery for unmanned aircraft, and associated systems and methods. A representative system includes a first, carrier aircraft having an airframe a propulsion system carried by the airframe and positioned to support the carrier aircraft in hover, and a capture line carried by the carrier aircraft and deployable to hang from the carrier aircraft. The capture line is sized to releasably engage with a capture device of a second, carried aircraft. The system further includes a retrieval device positioned to support the carried aircraft for detachment from the capture line.

Abstract: A naval platform has a zone for the deck landing/take-off of an aircraft and an aircraft handler, to move the aircraft over the deck landing/take-off zone. The aircraft handler includes a body in the form of a bar for gripping and securing the main landing gear of the aircraft, provided with an anchoring hook mounted to slide in at least one rail, guiding the the aircraft on the deck landing/take-off zone. The hook is retractable, allowing the release of the body in the form of a gripping and securing bar from the rail, the body gripping the landing gear of the aircraft. The movement of the aircraft brings the body into position on the rail, and the hook into a position in which it faces the rail, and the hook back into an anchoring position in the rail in order to secure the aircraft.

Abstract: The present invention includes an apparatus for preventing aircraft rollover upon a water landing comprising: a deployable first and/or second boom affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis of the aircraft; and a first and/or second air bladder attached to a second end of the first and/or second boom, wherein the first and/or second air bladders are configured to inflate when an aircraft lands in the water, wherein deployment of the first and second boom and air bladder prevents aircraft rollover upon water landing; or a deployable keel affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis and opposite a rotor of the aircraft upon a water landing, wherein the keel is sized to prevent aircraft rollover upon deployment; or both.

Abstract: Embodiments of a spherical momentum control device are provided. In one embodiment, the spherical momentum control device includes a housing assembly bounding a cavity, a rotor support axle disposed within the cavity, and a spherical bearing interface formed between the rotor support axle and the housing assembly. The spherical bearing interface facilitates rotation of the rotor support axle within the cavity about three orthogonal axes transecting substantially at the cavity center point. A rotor is mounted to the rotor support axle (e.g., through precision bearings) for rotation about a spin axis. The spherical bearing interface can assume any form for facilitating rotation of the rotor support axle about the orthogonal axes including, for example, a low friction plane bearing interface. In one embodiment, the spherical bearing interface includes rolling element bearings embedded in the cavity walls or embedded in enlarged end caps forming part of the rotor support axle.

Abstract: The present invention relates to a Microwave Electrothermal Thruster(MET) adapted for in-space electrothermal propulsion comprising a tunable frequency Microwave Electrothermal Thruster propulsion module enabling primary propulsion and altitude control of a satellite/spacecraft wherein RF Semiconductors is introduced for the first time as microwave generator inside cavity body to increase its efficiency and respond time and to make the thruster capable of operating in two frequencies by mechanically tuning its cavity making such thruster compact and light weight. The free-floating plasma within the resonant cavity couples the incident electrical power directly to the tangentially injected propellant gas. The plasma forms by focusing the microwave energy into the first transverse magnetic mode and operates independent of the type of propellant gas used.

Abstract: A stacking device for a space vehicle comprises a plurality of hold down and release mechanisms and is configured to hold, temporarily, n space appendages, n being an integer strictly greater than 2, on one and the same support of a space vehicle using hold down and release mechanisms. The stacking device is arranged such that several space appendages are held by one and the same hold down and release mechanism. An associated space vehicle comprising at least one such stacking device is also provided.

Abstract: An inflatable pressure structure includes an airtight flexible membrane having collapsed and inflated configurations. The inflatable pressure structure includes an elongated pressure-assisted seal that is configured to selectively seal an opening in the airtight flexible membrane. The pressure-assisted seal includes first and second seal components that sealingly engage one another and prevent escape of gas from inside the airtight flexible membrane. The airtight flexible membrane, when inflated, generates a force transverse to the pressure-assisted seal tending to pull the first and second seal components apart. Pressurized gas inside the airtight flexible membrane causes the first and second seal components to more securely engage one another whereby a force transverse to the pressure-assisted seal does not disengage the first and second seal components.

Abstract: Systems, methods, and apparatus for converting a sheet material into packaging templates can include a converting machine that performs conversion functions, such as cutting, creasing, and scoring, on the sheet material. Items to be packed into boxes formed of the packaging templates can be used as the pattern for determining the location of performance of the conversion functions on the sheet material. Accordingly, no intermediate measuring of the items may be required prior to performance of the conversion functions. Instead, longheads can be positioned adjacent to opposing sides of the items and cross heads can be advanced inward to the positioned longheads.

Abstract: A conveyor receives a cardboard box formed about an article, with a first lateral flank uncovered. An inlet receives the cardboard box with the first lateral closing wall coplanar with a base wall, a second lateral closing box wall folded to cover a second lateral article flank, a third lateral closing box wall folded to cover a third lateral article flank, a fourth lateral closing box wall folded to cover a fourth lateral article flank, and an upper closing box wall folded to cover an upper article face. An arrest stops the box, a first folding component rotates and folds the first lateral closing box wall to cover the first lateral article flank, and second folding component rotates a closing tab (AC), hinged to the upper closing wall to fold and bring a closing tab against the first lateral closing wall for closing the cardboard box.

Abstract: A rigid holding container has a flexible cover sheet extending over the holding area for sealing the contents. The container has a wide, flat perimeter lip which provides a firm base for the seal between the cover sheet and the container. A breaching bubble is formed in the seal, under the cover and over the perimeter lip. The consumer breaches the bubble by pressing the bubble against the lip between the thumb and forefinger. The pressure compresses the air in the bubble causing the bubble to expand laterally. The expanding bubble breaches along the perimeter of the lip, producing a peel flap of flexible cover material. The consumer pulls the peel flap while holding the rigid container down, to remove the cover sheet.

Abstract: A kit for covering a load (18) comprising: a cargo cover (10); a deployment means comprising a base sheet (2) for containing the cargo cover (10) prior to covering the load (18), the base sheet (2) comprising releasable securement means (4) for securing it around the cargo cover (10); and a plurality of cargo cover deployment straps (12, 14).

Abstract: The present disclosure includes a method and system for collecting data from multiple measuring points within equipment. Once collected, the data may be consolidated and stored in a database remotely. The data may then be used to optimize system performance either locally or across facilities. Such optimization may include determining the proper handling of packages of objects, such as eggs, that are not ideally marked or that are not properly packed. Such optimization may also include the resetting and/or recalibrating of laser systems within one or more facilities based on the data collected.

Abstract: The present invention relates to a flow wrapper which comprises a form and/or film tube, which forms the planar film into a film tube and/or fills the film tube with a packaging item and which comprises means to provide a longitudinal- and/or cross-seal to the film tube.