Abstract: A tiltrotor aircraft includes a fuselage, a wing member extending from the fuselage, an engine disposed relative to the wing member and a proprotor mechanically coupled to the engine. The proprotor includes a plurality of proprotor blade assemblies each including a spar and a sheath extending spanwise along the spar forming the leading edge of the proprotor blade assembly. The spar has a root section, a main section and a tip section. The spar has a generally oval cross section at radial stations along the main section and a first edge having a structural bias relative to a generally oppositely disposed second edge at the radial stations along the main section.

Abstract: An apparatus for chordwise folding and locking of rotor systems includes a grip assembly and a harness disposed at least partially within and coupled to the grip assembly. A rotor blade is rotatably coupled to the grip assembly and the harness. The rotor blade has a radially extended orientation and a stowed orientation. A linkage assembly has a first end, a second end and a pivot joint therebetween. The first end of the linkage assembly is rotatably coupled to the harness and the second end of the linkage assembly is rotatably coupled to the rotor blade. A first lock assembly selectively secures the rotor blade to the grip assembly and the harness when the rotor blade is in the radially extended orientation. A second lock assembly selectively secures the rotor blade relative to the harness when the rotor blade is in the stowed orientation.

Abstract: A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to alleviate a load on the wingtip device. The flow disrupter may comprise an edge that extends into a boundary layer at a threshold angle of attack that may disrupt the boundary layer and cause a flow to separate from the wingtip device. This separated flow may reduce stresses experienced by the wingtip device and wing during various flight conditions where a transverse flow is encountered.

Abstract: A method for actuating a landing gear arrangement may include supplying a first pressure to an actuator, applying, by the actuator, a moment on a latch to rotate the latch in a first rotational direction, disengaging a first roller pin, engaging a stopper on a link, rotating the link in the first rotational direction about a pivot, the link coupled between a trailing arm and a shock strut, rotating the shock strut about a second end of the shock strut, rotating the trailing arm about a first end, and engaging a second roller pin.

Abstract: The invention relates to an aircraft landing gear (2) comprising: —a leg (6) that can be pivotably connected to a load-bearing structure of the aircraft (1) in order for the landing gear (2) to be deployed and retracted; —a wheel (13, 14) that is rotatable in relation to the leg (6), and an electric motor (15, 16) that can rotate the wheel (13, 14) in relation to the leg (6); —a transmission mechanism (17) designed to selectively transmit torque generated by the electric motor (15, 16) to the wheel (13, 14) in order to rotate the wheel in relation to the leg (6) or to the leg (6) in order to rotate the leg (6) in relation to the load-bearing structure of the aircraft (1) in order to deploy or retract the landing gear (2).

Abstract: A system and method for measuring, or otherwise determining pitch length adjustments to a pitch link coupled to a rotor blade in a rotorcraft includes vertical track adjustment indicators machined onto an exterior of the tube of the pitch link and a vertical reference indicator machined onto an exterior of the upper or the lower rod of the pitch link. A metric of a pitch length adjustment can be determined by tracking or counting how many track adjustment indicators pass the reference indicator while the tube of the pitch link is being turned in either direction for increasing or decreasing the pitch length. The track adjustment indicators can be relied upon to track one or a series of adjustments for tracking a rotor blade installed in a rotor assembly.

Abstract: In some embodiments, an actuator includes a chamber, a piston disposed within the chamber, and a tube. The chamber has a first port and a second port. The piston comprises a first surface, a second surface, and an elongated conduit coupling the first surface to the second surface. The first surface is disposed between the first port and the second port. The second surface is offset from the first surface. The tube is disposed at least partially within the elongated conduit of the piston. The tube comprises a third port disposed within the elongated conduit of the piston and a fourth port disposed outside of the elongated conduit of the piston.

Abstract: An aerial vehicle is includes a wing, first and second rotors, and a movement sensor. The first and second multicopter rotors are rotatably coupled to the wing, the first multicopter rotor is rotatable relative to the wing about a first lateral axis, and the second multicopter rotor is rotatable relative to the wing about a second lateral axis. Each multicopter rotor is coupled to each other multicopter rotor, wherein the multicopter rotors are restricted to collective synchronous rotation relative to the wing between a multicopter configuration and a fixed-wing configuration. The movement sensor is coupled to the multicopter rotors, wherein the movement sensor is positioned to rotate relative to the wing when the multicopter rotors rotate relative to the wing between the multicopter and fixed-wing configurations.

Abstract: An automated commissioning and floorplan configuration (CAFC) device can include a CAFC system having a transceiver and a CAFC engine, where the transceiver communicates with at least one device disposed in a volume of space, where the CAFC engine, based on communication between the transceiver and the at least one device, commissions the at least one device.

Abstract: A mobile, powered monitoring system includes an array of solar panels, a battery bank of at least one battery electrically connected to the array of solar panels, a landing and connection platform electrically connected to the battery bank, a cable electrically connected to the landing and connection platform, a drone electrically and mechanically connected to the cable, the drone having at least one camera, and a transmitter to allow images captured by the camera to be sent to a base station.

Abstract: Embodiments relate to a client-facing application for interacting with a transport service that transports items via unmanned aerial vehicles (UAVs). An example graphic interface may allow a user to order items to specific delivery areas associated with their larger delivery location, and may dynamically provide status updates and other functionality during the process of fulfilling an aerial vehicle transport request.

Abstract: A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled.

Abstract: Systems, apparatuses, and methods are provided herein for providing package release for an unmanned aerial system. An apparatus for releasing packages for retrieval by an unmanned aerial system comprises a plurality of arms configured to surround a plurality of packages stacked vertically in an extended position, a plurality of powered hinges at a base of each of the plurality of arms, and a control circuit coupled to the plurality of powered hinges. The control circuit being configured to: determine a height for a first lowered position for the plurality of arms at which the plurality of arms do not obstruct an unmanned aerial vehicle from coupling with a coupling structure on a first package of the plurality of packages positioned at a top of the plurality of packages, and cause the plurality of powered hinges to pivot the plurality of arms from the extended position to the first lowered position.

Abstract: An oxygen box is secured in an oxygen box hole through a panel of an aircraft cabin by fasteners that are positioned in an interior volume of the oxygen box and are inserted through holes in a back wall of the oxygen box that are aligned with fastener openings in an exterior bracket positioned behind the panel and behind the oxygen box opening where the fasteners are received by the fastener openings in the exterior bracket and the fasteners removably attach the oxygen box to the exterior bracket.

Abstract: An apparatus for controlling airflow in a duct of an aircraft galley chiller includes first and second legs having ends connected together to form a vane, and free ends configured to be attached within the duct. A free end of one first leg may have a beveled edge, and the free end of the other leg may have a flat edge, and each leg may have one or more score lines to aid cutting lengths of the first and second legs. The legs are connected together at a predetermined fixed angle, or at an adjustable angle, such as by an adjustable hinge. A pair of opposing vanes may be attached within opposing sides of the duct to form a venturi within the duct.

Abstract: An airplane seat device includes at least one airplane seat, and at least one console arranged, viewed in a flight direction, in front of the airplane seat, and at least one airbag element which is configured to protect in a crash event a passenger sitting in the airplane seat from crashing onto the console. At least one airbag element features, in a fully deployed state, at least in a head-impact zone, a thickness which is smaller than a thickness in at least one shoulder-impact zone.

Abstract: A networked suite of aircraft-seat devices is disclosed, wherein the devices receive both power and network communications via the same terminal. The devices may be connected by a two-wire connection and may be configured in a daisy chain. Various aircraft seat devices, such as actuators, may be directly connected to the network or connected via control modules connected to the network. One device on the network may be designated as a master device for controlling network configuration. A method of automatically addressing network devices includes measuring a first quiescent current through the network, enabling an addressing current in unaddressed devices, and measuring the change in current at each device after enabling the addressing currents to determine the last device in the chain.

Abstract: An outflow valve is provided. The outflow valve includes a frame and a first door rotatably coupled to the frame. The first door has a first side opposite a second side and a bellmouth. The bellmouth is defined by a super-ellipse, with a major axis of the super-ellipse substantially parallel to the second side and a minor axis of the super-ellipse substantially perpendicular to the second side. The outflow valve also includes a second door rotatably coupled to the frame. The first door and the second door are substantially simultaneously movable between at least a first position and a second position.

Abstract: An aircraft air conditioning system including a process air line having a first end connected to a process air source to allow a flow of process air therethrough. A ram air channel of the air conditioning system allows ambient air flow therethrough. A heat exchanger unit is disposed in the process air line and arranged within the ram air channel to thermally couple process air flowing through the process air line to ambient air flowing through the ram air channel. A water extractor disposed in the process air line downstream of the heat exchanger unit extracts water from the process air. A water supply system supplies extracted water into the ram air channel. The water supply system has a control arrangement to control a fluid connection between the water extractor and the ram air channel in dependence on an operating state of the aircraft air conditioning system.

Abstract: An aircraft includes a thermal management system that is configured to cool portions of the aircraft. The thermal management system includes at least one reverse air cycle machine (RACM) mounted on an engine of the aircraft, and a vapor cycle system (VCS) that is configured to cool the portions of the aircraft. The VCS circulates a refrigerant therethrough. A condenser couples the RACM(s) to the VCS. The RACM(s) coupled to the condenser provides a heat sink for the VCS.

Abstract: An ozone converter includes an outer housing having an inlet and an outlet, a first channel disposed between the inlet and the outlet, and a bypass channel disposed between the inlet and the outlet and separated from first channel. The converter also includes a core disposed within the first channel and a bypass control mechanism that includes one more blocking elements that causes inlet air to pass through the first channel or the bypass channel based on an altitude of the ozone converter. The control mechanism includes a piston that moves between at least a first position and a second position and a bellows that controls a flow a pressurized air to the piston.

Abstract: An arrangement for supplying heated air to a wing anti-icing system on an aircraft propelled by a jet engine includes, but is not limited to, an ejector that is configured for coupling to a wing anti-icing system. The ejector is further configured to receive a first flow of air, to entrain a second flow of air with the first flow of air, the second flow of air having a lower temperature than the first flow of air, to mix the first flow of air with the second flow of air to form a combined flow having a temperature and a volume suitable for use by the wing anti-icing system, and to exhaust the combined flow into the wing anti-icing system.

Abstract: An aircraft engine unit comprising an engine, a mast and an engine connection connecting the engine and the mast. The aircraft engine unit includes a front engine attachment of the engine connection which comprises at least one front rod connecting the primary structure of the mast and the core of the engine and which assures the take-up of vertical forces, and at least one connection connecting the primary structure of the mast and the fan casing of the engine and which assures the take-up of forces that are horizontal and perpendicular to the axis of rotation of the engine and/or a torque about the axis of rotation of the engine.

Abstract: A nacelle for an aircraft propulsion system includes a first nacelle door, a second nacelle door and a plurality of latch assemblies. Each of the nacelle doors extends along and partially about a centerline. The latch assemblies are arranged along the centerline in an array, and configured to secure the nacelle doors together. A first of the latch assemblies includes a first latch mechanism and a first pin that pivotally mounts the first latch mechanism. A second of the latch assemblies includes a second latch mechanism and a second pin that pivotally mounts the second latch mechanism. An axis of the second pin is non-parallel with an axis of the first pin. The latch assemblies may be substantially identical to one another given the arrangement of the latch assemblies with the nacelle doors.

Abstract: A method for recycling motor power includes controlling a first motor of an unmanned aerial vehicle (UAV) in a decelerating state to work in concert with a second motor of the UAV in an accelerating state to effect rotation of the UAV, receiving power from the first motor at a power bus in electrical connection with the first motor and the second motor, and providing a portion of the received power to the second motor through the power bus during the rotation of the UAV.

Abstract: A system ensures the correct type of fuel is dispensed in an aircraft while removing the introduction of human error in the refueling process. The system includes an RFID tag disposed at one or more aircraft that electronically stores data such as engine type, engine hours, fuel type, tail number, and pilot/subscriber data for the aircraft on which the RFID tag is disposed. An RFID reader is disposed at or near a fuel dispensing mechanism, such as a fuel truck or tank. A signal indicative of fuel type is emitted from the RFID tag to the RFID reader. RFID tags on aircraft that are enrolled in the system's subscription service enable aircraft to be recognized by a module operating the fuel dispensing mechanism. Based on a comparison performed by the module, authorization to begin fueling is either permitted or declined.

Abstract: A system and method for an aircraft receptacle. The aircraft receptacle comprises an actuator connected to a number of latches and a tension spring connected to the number of latches. The actuator is part of an actuation system. The elastic member holds the number of latches in a disengaged position after failure of the actuation system.

Abstract: A system and method for controlling an inlet door of an auxiliary power unit (APU) are provided. It is determined whether a condition to inhibit a start of the APU is present. If no condition to inhibit the start of the APU is present, a door-opening signal comprising instructions to cause the inlet door to be commanded to an open position in advance of a prospective command to start the APU is output. If the condition to inhibit the start of the APU is present, a door-closing signal comprising instructions to cause the inlet door to be commanded to a closed position is output.

Abstract: A flexible flight control system enables conversion from one architecture using one type of inceptor to another architecture using another type of inceptor, through the usage of modular software and hardware pieces with common interfaces among the different types of inceptors. Longitudinal and lateral directional control laws are adapted to be compatible with the specific aspects of the operation of each configuration/architecture, giving the option to the aircraft operator to choose any one of a number of inceptor architectures at time of manufacture.

Abstract: An illuminated keypanel includes an input device. The input device has control symbology. The illuminated keypanel also includes an organic light emitting diode (OLED) sheet. The OLED sheet provides illumination to the control symbology of the input device.

Abstract: A method for balancing an aircraft turbofan engine using a respective artificial neural network for each flight of multiple reference aircraft to predict the engine vibrations that would be produced in response to input of flight parameter and balance weight data acquired from a flight of a test aircraft of the same type. The resulting sets of predicted vibrations are then processed to identify and collect those engine vibration predictions which match or nearly match the engine vibration measurements acquired from the test aircraft during its flight test. For each matching modeled flight of the reference aircraft, the magnitude and phase angle of the mass vector for any commonly used balance weight configurations are determined and included in a list of recommended balance weight configurations. A technician can then reconfigure the balance weights attached to the engine on the test aircraft in accordance with a selected recommendation.

Abstract: A method for manufacturing a panel made of composite material incorporating a lightning protection arrangement which comprises strips with a conductive layer. The method comprises a step of laying the strips in an automated manner, the strips having a width of less than 20 mm and being distributed in a first set of mutually parallel strips that are laid in a first laying direction and a second set of mutually parallel strips that are laid in a second laying direction that intersects the first laying direction. A panel made of composite material manufactured by way of this method is also disclosed.

Abstract: The use of shielded material in a deployable vehicle arresting and containment device that, when used for the interception of an unmanned vehicle, effectively achieves RF isolation of that vehicle, breaking all external communications with that vehicle. This apparatus, which may have internal and external antennas, could enable a variety of advanced effects such as localized GPS and command and control link spoofing and jamming as well as providing a vehicle for signal intercept and intelligence solutions. Additionally, due to the shielding properties of the arresting and containment device, semi-destructive means such as localized EMPs could be used to damage the encapsulated unmanned vehicle electronics.

Abstract: Described herein are apparatuses that provided various features related to unmanned aerial vehicles (UAVs). An example apparatus may include, among other features, (i) a launch system for a UAV, (ii) a landing feature that is arranged on the apparatus so as to receive the UAV when the UAV returns from a flight, and (iii) a mechanical battery-replacement system that is configured to (a) remove a first battery from the UAV, and (b) after removal of the first battery, install a second battery in the UAV.

Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV having an exterior surface, an aerial vehicle (AV) tab extending from the exterior surface, a tube containing the UAV, the tube including a tab stop configured to controllably hinder travel of the AV tab past the tab stop, and a pair of opposing tab guides configured to position the AV tab for travel over the tab stop.

Abstract: Predictive aircraft maintenance systems and methods are disclosed. Predictive maintenance methods may include extracting feature data from flight data collected during a flight of the aircraft, applying an ensemble of related classifiers to produce a classifier indicator for each classifier of the ensemble of classifiers, aggregating the classifier indicators to produce an aggregate indicator indicating an aggregate category of a selected component for a threshold number of future flights, and determining the performance status of the selected component based on the aggregate indicator. The classifiers are each configured to indicate a category of the selected component within a given number of flights. The given number of flights for each classifier is different. The threshold number of future flights is greater than or equal to the maximum of the given numbers of the classifiers.

Abstract: Systems and methods for high-speed non-destructive inspection of a half- or full-barrel-shaped workpiece, such as a barrel-shaped section of an aircraft fuselage. Such workpieces can be scanned externally using a mobile (e.g., translating) arch gantry system comprising a translatable arch frame disposed outside the fuselage section, a carriage that can travel along a curved track carried by the arch frame, a radially inward-extending telescopic arm having a proximal end fixedly coupled to the carriage, and an NDI sensor unit coupled to a distal end of the telescoping arm. The stiffeners of the fuselage sections can be scanned using a mobile scanner platform disposed inside the fuselage section, which platform comprises a radially outward-extending telescopic arm rotatably coupled to a mobile (e.g., holonomic or linear motion) platform and an NDI sensor unit coupled to a distal end of the telescoping arm.

Abstract: A roll-out solar array includes a first mandrel having first and second ends and a second mandrel having first and second ends. A hinge extends between the first and second mandrels, such that the roll-out solar array can transition between a stowed position where the mandrels are in a substantially parallel configuration and a deployed position where the mandrels are in a series configuration. A latch may be provided to lock the roll-out solar array in the stowed configuration.

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 vertical form fill and seal system supports a sheet of material having material segments and a tube sized for drawing edges of the elongated sheet of material together in an overlapping configuration to form the sheet into a substantially tube shape. The VFFS also includes a sealer that seals the edges of the material to one another and a gusseting mechanism sized for forming a gusseted tuck in each of a left panel portion of the material and a right panel portion of the material. A cutting mechanism removes a first portion and a second portion of a first segment of the material segments in order to form a first cut and a second cut in the first segment and a sealing mechanism folds and seals the first segment at the first cut and at the second cut to provide an end wall with a substantially flat, rectangular-shaped footprint.

Abstract: Packaging material may be profiled to generate an incremental containment force per revolution (ICF) attribute that is represented by a function that is variable as a function of wrap force. Moreover, the performance of different packaging materials, e.g., in terms of speed or cost, may be compared for a particular load through simulation of wrap operations based upon dimensions of the load and a desired load containment force requirement for the load.

Abstract: Provided is a glove picking, organizing, and stacking apparatus, belonging to the field of equipment for producing PVC, nitrile, and latex gloves, and comprising a glove-picking apparatus (2), a correcting conveying apparatus, a conveying and placing apparatus, and a front/back stacking, conveying, and taking apparatus; the glove-picking apparatus (2) is connected to the front/back stacking, conveying, and taking apparatus by means of the correcting conveying apparatus or the conveying and placing apparatus; a system control apparatus is connected to the described apparatuses and controls their switching and operation, thereby automatically carrying out the entire process of picking, transporting, stacking, and counting the gloves, and the quality of and efficiency in the completion of the tasks is very high.

Abstract: A reusable food pouch having a removably insertable one-way valve is disclosed herein. The one-way valve may be used with the reusable food pouch if food product having a water-like consistency is being stored in the reusable food pouch to prevent spills if the reusable food pouch is inadvertently laid on its side. Conversely, the one-way valve may be removed from the reusable food pouch if the food product has a consistency more like thick oatmeal and/or applesauce to allow for free flow of the food product through a spout of the reusable food pouch.

Abstract: An apparatus and method of forming a metallic cup that is subsequently reformed into a container body. More specifically, an apparatus and methods used to form a metallic cup with a reformed bottom having an inwardly oriented projection are disclosed. The inwardly oriented projection reduces a height of the metallic cup but utilizes the same amount of metallic stock material as a taller cup with substantially the same diameter that does not have an inward projection. The inwardly oriented projection thus allows the use of a conventional bodymaker and other can manufacturing tools to convert the cup into a container body of a preferred size and shape.

Abstract: A double container includes: an inner container having a cylindrical barrel portion the upper circumferential edge of which is formed to have a curled portion, and a bottom portion provided on a lower end of the barrel portion so as to close the lower face thereof; and a exterior sleeve) which covers the barrel portion, and is secured thereto, so as to form a thermal insulating space between itself and the outer side of the barrel portion. The outer surface of the barrel portion of inner container is provided over the entire circumference thereof with a plurality of elongated projections, which consist of thermoplastic resin, arranged in a row and spaced apart in the circumferential direction, the projections extending in elongated fashion circumferentially and each having an amount of projection of 1.0 to 2.0 mm.

Abstract: A packaging box, cutouts, method and device for producing corrugated cardboard boxes comprising walls, a base (6) and a cover (7), the inner face of the base being provided with at least two recesses (33) and the cover comprising at least two tabs (38) adhered to the upper face thereof, directly above the recesses of complementary shape. The recesses and/or the tabs are situated fully inside the corresponding face or faces (31, 32).

Abstract: A carton for holding at least one article includes a plurality of panels that extends at least partially around an interior of the carton. The plurality of panels includes a front panel, a first side panel, a second side panel, and a back panel. A plurality of end flaps includes a first end flap foldably connected to the front panel and a second end flap foldably connected to the back panel. A first gusset is foldably connected to a portion of the first side panel and a second gusset is foldably connected to a portion of the second side panel. At least the first end flap, the first gusset, and the second gusset cooperate to form a first closure of the carton, and the second end flap forms a second closure of the carton. The second closure at least partially overlaps the first closure.

Abstract: Disclosed is a glove container that comprises a top portion, bottom portion, first and second side portions, and first and second end portions. When one of the end portions is torn away to reveal the contents of the container, at least one tab or flap containing visual indicia that indicates a characteristic of the contents of a container will remain attached to the container. The visual indicia may convey information such as the size or material of the gloves. The container is deemed particularly to suitable for use in emergency vehicles, where glove boxes are often stored in compartments with the end being exposed.

Abstract: A container having both a one-dimensional configuration before it is formed into its three-dimensional configuration. A blank is used to form the container and is initially flat with a plurality of fold lines. The container includes a base portion with a plurality of edges along its perimeter, a lid portion which is distanced from and parallel to the base portion, and a wall projecting orthogonally from each edge forming a plurality of walls. At least one wall is integrally connected to both the base portion and the lid portion.

Abstract: A packing box includes first and second sidewall parts spaced apart and facing each other, first and second connecting parts, a third connecting part attaching the second connecting part to the first sidewall part, a bottom part connecting lower portions of the first and second sidewall parts and the first and second connecting parts, and a top part facing the bottom part and connecting upper portions of the first and second sidewall parts and the first and second connecting parts to form a receiving space. The top part includes first to fourth upper paperboards folded and extended from the upper portions of the first and second sidewall parts and the first and second connecting parts to form a handle, and a fifth upper paperboard folded from the third connecting part and disposed under the first to fourth upper paperboards to prevent withdrawal of contents from the receiving space.