Abstract: A composite component (16) for a vehicle (10) includes a laminate (18) made from a composite material, a first pad-up area (22) applied to the laminate (18), where the first pad-up area (22) includes a plurality of first tows laid next to one another in a side-by-side arrangement and where the first pad-up area (22) defines a first fiber orientation, and a second pad-up area (24), where the second pad-up area (24) includes a plurality of second tows laid next to one another in a side-by-side arrangement and where the second pad-up area (24) defines a second fiber orientation that differs by a predetermined angle from the first fiber orientation. The first pad-up area (22) and the second pad-up area (22) intersect at an intersecting area and together form a first pad-up ply on the laminate (18).

Abstract: A structural assembly including a first member having an external side and an internal side, the first member defining a first member through-bore, a second member having an external side and an internal side, the second member defining a second member through-bore aligned with the first member through-bore, and a mechanical fastening system including a bushing at least partially received in the first member through-bore, the bushing defining a bushing through-bore and including a flange, wherein the flange is positioned in a gap between the internal side of the first member and the external side of the second member, a nut plate connected to the internal side of the second member, the nut plate defining a clearance bore aligned with the second member through-bore and the bushing through-bore, the nut plate including a nut, and a bolt extending through the bushing through-bore and into threaded engagement with the nut.

Abstract: In one embodiment, a wing for an unmanned aerial vehicle is described. The unmanned aerial vehicle includes a first body of the wing with a first end proximate a body of the vehicle. A second end is opposite the first end. A first joint is on the first end of the first main body of the wing. The joint rotatably couples the wing to the vehicle. A second joint is on the second end of the vehicle. A second body of the wing is rotatably coupled to the first body via the second joint.

Abstract: A method of configuring a wing tip device (7) on an aircraft (1), including: undertaking ground-based operations at an airport with the wing tip device (7) in a ground configuration, in which the span of the aircraft is within an airport compatibility limit, moving the wing tip device (7) to a take-off configuration in which the wing tip device (7) is moved away from the ground configuration such that the span of the aircraft is increased and such that the wing tip device (7) has a first lift coefficient; taking-off with the wing tip device (7) in the take-off configuration; moving the wing tip device from the take-off configuration to a flight configuration, in which the wing tip device has a second lift coefficient, the second lift coefficient being lower than the first lift coefficient. The lift coefficient may be changed by adjusting the sweep of the wing tip device (7).

Abstract: The present disclosure is directed to an aerodynamic stabilizer assembly for stabilizing an aft fan mounted to a fuselage of an aircraft. For example, the stabilizer assembly includes one or more generally horizontal stabilizers for mounting to a nacelle of the aft fan and the fuselage so as to stabilize the aft fan. Each of the generally horizontal stabilizers includes an inner portion and an outer portion. As such, the inner portions are mounted to a nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion.

Abstract: A turbomachine including at least two unducted propellers, one of which is an upstream propeller and one a downstream propeller, the upstream propeller including a plurality of blades, at least one first blade of which has a different length from that of a second blade.

Abstract: Systems and methods are provided for an irreversible clutch to prevent back-drive. The irreversible clutch may transfer torque and/or rotation received at a first end to a second end, but may not transfer torque and/or rotation received at the second end to the first end. The irreversible clutch may prevent unintended adjustment of one or more rudder pedals and/or a rudder pedal assembly.

Abstract: A flight management system (FMS) including a plurality of FMS components that can include a civil FMS component and a tactical FMS component. Each FMS component can have a processor programmed to execute an FMS software product. The FMS can also include a multi core FMS manager configured to control a plurality of flight management systems and coupled to the plurality of FMS components. The multi core FMS manager can include a plurality of FMS managers, each coupled to one of the FMS components, and a platform interface manager coupled to an avionics system. Each FMS manager can be adapted to transmit flight management data to, and to receive flight management data from, the FMS component to which it is coupled. The platform interface manager can be adapted to provide each FMS component access to the avionics system, such that an aircraft operator can control each FMS component via the FMS.

Abstract: A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

Abstract: A composite metallic joint assembly may include a composite metal rod having a metal liner and a composite material disposed around the metal liner. A first portion of the composite metal rod may comprise the composite material and the metal liner and a second portion of the composite metal rod may comprise the metal liner exposed at a radially outer surface of the composite metal rod. The metal liner may have a first radial thickness at a first axial position corresponding to the first portion of the composite metal rod and a second radial thickness at a second axial position corresponding to the second portion of the composite metal rod. The second thickness may be greater than the first thickness.

Abstract: Systems and methods for landing gear arrangements are provided. In various embodiments, a landing gear arrangement may comprise a first composite layer, the first composite layer having a cylindrical geometry, a metallic ring comprising an inner surface and an outer surface, the metallic ring perimetrically surrounding at least a portion of the first composite layer, the inner surface being in contact with the first composite layer, a metallic connecting tab extending away from the outer surface, and a second composite layer at least partially perimetrically surrounding the metallic ring and at least partially perimetrically surrounding the first composite layer, the outer surface being in contact with the second composite layer.

Abstract: A rotary wing aircraft with a fuselage and a non-retractable skid-type landing gear that is mounted to the fuselage, the non-retractable skid-type landing gear comprising at least one landing box, the at least one landing box being provided with a skid-type landing base member and an associated box shell that delimits an internal volume of the at least one landing box.

Abstract: A method of automating entry of an aircraft into autorotation includes detecting a loss of engine power, analyzing a sensed height and sensed airspeed of the aircraft, determining an adjusted position of one or more control surfaces of the aircraft in response to the sensed height and sensed airspeed, and automatically moving the one or more control surfaces to the adjusted position.

Abstract: A multi-mode aerial vehicle hybrid wing includes a fixed wing configured to extend from a side of an elongated fuselage and double over its longitudinal axis, a tilt wing attached at a first side to a free end of the fixed wing wherein the tilt wing is rotatable ninety degrees about its axis, and a duct attached to a second side of the tilt wing. The duct includes a plurality of pivotal control surfaces positioned at a top entrance of the duct, dual counter-rotating rotors positioned at an underside of the duct, a plurality of cross stators positioned at a back entrance of the duct, and a plurality of stator pivotal control surfaces within each of the cross stators of the duct. The multi-mode aerial vehicle hybrid wing also includes a winglet attached to the duct opposite to the tilt wing.

Abstract: A multi-mode unmanned aerial vehicle includes an elongated fuselage, a right and left fixed wing extending from a respective right and left side of the elongated fuselage, a right and left tilt wing attached at a first side to a free end of the respective right and left fixed wing, a right and left duct attached to a second side of the respective right and left tilt wing, a right and left winglet attached to the respective right and left duct opposite to the right and left tilt wing, a tilt tail located within a curved guide slot at a rear end of the elongated fuselage, a rear duct attached to the tilt tail, a tilting mechanism, and an integrated autonomous flight control system.

Abstract: An aircraft having a fixed wing is operative to perform vertical takeoff and landing while positioned in a nose-down orientation. The aircraft has a fixed wing having a leading edge and a trailing edge; a propulsion system operative to selectively provide forward propulsion and rearward propulsion; and a controller operative to control operation of the propulsion system. The propulsion system provides rearward propulsion during takeoff of the aircraft to move the aircraft in a direction of the trailing edge of the fixed wing, and provides forward propulsion during flight of the aircraft to move the aircraft in a direction of the leading edge of the fixed wing. The aircraft maintains the wing substantially vertical with the trailing edge facing upwards during takeoff, and transitions to having the wing substantially horizontal during flight. A vertical landing procedure is also provided.

Abstract: An unmanned aerial vehicle UAV comprising a base, four extendible arms, a motor attached to each extendible arm, with a rotor coupled to each motor, the UAV further comprising a processor for controlling the motors, and a radio receiver for receiving control signals, wherein the UAV folds flat and is configured to clip onto a back of a mobile phone.

Abstract: A moving device includes an imaging unit, an acquiring unit, a determining unit and an imaging control unit. The acquiring unit is configured to acquire a state at a time when the moving device is released from a user. The determining unit is configured to determine an imaging manner to control the imaging unit after the time of being released, based on the state acquired by the acquiring unit. The imaging control unit is configured to control the imaging unit in the imaging manner determined by the determining unit.

Abstract: A rotorcraft in which lift and thrust can be supplied by rotors, and specifically a drone comprising a camera that is used for making optical and/or sound recordings, especially during (live) events, such as concerts, gatherings, dance events, etc. The camera gives an impression of the events and is capable of recording specific details thereof, such as individual people.

Abstract: Embodiments relate to methods and apparatus to swiftly and accurately deliver a medical treatment kit via an Unmanned Aerial Vehicle and mechanisms and systems for monitoring a medical emergency via an Emergency Control Center and providing live remote support to on location care givers.

Abstract: An unmanned aerial vehicle for scent analysis. The unmanned aerial vehicle includes a sensor array to sample ambient air in a location to detect an odor, a pattern recognition unit coupled to a database to identify the odor, wherein the odor is compared to identification information stored in the database, and a mapping unit to estimate an assessment value associated with the odor and to generate an instruction to one or more components of the unmanned aerial vehicle to perform a function when the assessment value exceeds a predetermined threshold value, wherein the function includes activating one or more feedback outputs on the unmanned aerial vehicle.

Abstract: The present invention relates to an unmanned aerial vehicle system having a multi-rotor type rotary wing. The unmanned aerial vehicle system having a multi-rotor type rotary wing includes a first unmanned aerial vehicle, at least one second unmanned aerial vehicle, and a bridge that connects the first unmanned aerial vehicle and the at least one second unmanned aerial vehicle to be separable from each other, wherein the at least one second unmanned aerial vehicle is moveable by the first unmanned aerial vehicle in a state where the at least one second unmanned aerial vehicle is coupled to the first unmanned aerial vehicle by the bridge without being driven, and the at least one second unmanned aerial vehicle is separable from the first unmanned aerial vehicle which is in flight.

Abstract: An arrangement in a cabin of a vehicle has a plurality of cabin monuments, placeable in rows, of which the lateral surfaces are in laminar contact, said cabin monuments having a front side and a rear side and a wall surface of the aircraft fuselage, at least sections of which face toward the cabin of the vehicle and are not aligned parallel with a lengthwise axis of the cabin. The cabin monuments are arranged in rows parallel to the lengthwise axis of the cabin, so that the front sides and the rear sides are each aligned parallel to the lengthwise axis of the cabin. The rear sides of at least two cabin monuments, each of which include storage space for cabin trolleys, are positioned with an offset relative to each other in a direction transverse to the lengthwise axis of the cabin.

Abstract: A seating arrangement for use in a cabin of a vehicle includes a first column set, a second column set, and an aisle between the first and second column sets. The first column set includes a first column of seats, a second column of seats, and a third column of seats. The first column set additionally includes an egress path of a first seat of the first column defined between a first seat and a second seat of the second column and between a first seat and a second seat of the third column. The egress path allows for direct unimpeded access from the first seat of the first column to the aisle, and the egress path is perpendicular to the aisle.

Abstract: Described are consoles for use in a passenger seat row. The console may include a base of a support material. The base may include a top surface, a first side wall, and a second side wall opposite the first side wall. A tray may be configured to be releasably affixed to the top surface of the base. The tray be manufactured as a piece of molded plastic. The molded plastic may be molded to include one or more storage compartments. A bottom of the molded plastic may be configured to fittingly mate with the top surface of the base. The base may further include one or more straps configured to secure the base to a passenger seat cushion, passenger seat support structure, or a passenger seat restrain system. The one or more storage compartments may be a cupholder.

Abstract: An armrest table has an armrest casing, a frontward-moving stand, an upward-moving stand, and at least one table panel. The frontward-moving stand is front and rear movably mounted in the armrest casing. The table panel is up and down moveably mounted in the frontward-moving stand. The table panel can be rotated to be horizontal when moved to a highest position of its movement route. The frontward-moving stand and the table panel can be received in the armrest casing when the table panel is moved to a lowest position of its movement route. The armrest table is mounted beside the seat, and thus the passenger can adjust the height of the table panel.

Abstract: An aircraft comprising a turbine engine, an atomizer, a reservoir, a conduit connecting the reservoir to the atomizer, and a unit for controlling the flow of liquid in the atomizer. The turbine engine, the atomizer, the reservoir, the conduit and the control unit are fixed to the aircraft. This allows cleaning in flight of at least some parts of the turbine engine.

Abstract: A probe portion of an air data probe is provided. The probe portion includes an endoskeleton structure having an outer surface, a heater cable disposed along the outer surface of the endoskeleton structure, a porous cover, surrounding the endoskeleton structure and heater cable, and a braze filler that substantially fills gaps between the heater cable and the endoskeleton structure and that substantially fills gaps in the porous metal cover.

Abstract: Apparatus and associated methods relate to determining, based on a spatial extent of ice accretion, a maximum size of super-cooled droplets contained in an atmosphere and/or if an atmosphere contains super-cooled water droplets that equal and/or exceed a predetermined size. A testing region on an exterior surface of an aircraft is monitored for ice accretion by an ice detector. A boundary calculator determines a specific location to be tested within the testing region. The determined specific location corresponds to a calculated boundary that separates an ice-accretion region from an ice-free region if the atmosphere contains super-cooled water droplets of no larger than the predetermined size. If the ice detector detects ice accretion at the determined specific location, an alert is generated. The alert can advantageously inform a pilot of the aircraft that the atmosphere contains super-cooled water droplets that equal or exceed the predetermined size.

Abstract: Apparatus and associated methods relate to determining, based on a spatial extent of ice accretion, whether an atmosphere contains super-cooled water droplets that equal and/or exceed a predetermined size. A convex-shaped housing is mounted to an aircraft and exposed to an airstream. The convex-shaped housing has a testing region that is monitored for ice accretion by an ice detector. A boundary locator determines a specific location to be tested within the testing region. The determined specific location corresponds to a calculated boundary that separates an ice-accretion region from an ice-free region if the atmosphere contains super-cooled water droplets up to the predetermined size. If the ice detector detects ice accretion at the determined specific location, an alert is generated. The alert can advantageously inform a pilot of an atmosphere containing super-cooled water droplets that equal or exceed the predetermined size.

Abstract: An aircraft is provided and includes a fixed frame including a ledge and a seat pan on which seating elements for seating an aircraft crewperson are disposable. The seat pan includes a hinge about which the seat pan is pivotable relative to the fixed frame and a flange disposable on the ledge to establish a first pivot position for the seat pan relative to the fixed frame and a seat pan lifter coupled to the fixed frame and selectively interposable between the flange and the ledge to establish a second pivot position for the seat pan relative to the fixed frame.

Abstract: An aircraft gas turbine engine (110) comprises first and second non-coaxial propulsors (113a, 113b), each propulsor (113a, 113b) being driven by a common gas turbine engine core (176) comprising a propulsor drive turbine (143) arranged to drive the first and second propulsors (113a, 113b) via a propulsor drive coupling (127). The core (176) further comprises a first core module (190) comprising a first compressor (129) and a first turbine (131) interconnected by a first shaft (177), and a second core module (191) comprising a second compressor (128) and the propulsor drive turbine (143) interconnected by a second shaft (127), the first and second core modules (190, 191) being axially spaced.

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: A method and a device for detecting that a rotorcraft is approaching a vortex domain. After previously determining a limit advance speed threshold and a limit vertical speed threshold defining a limit for said rotorcraft entering into a vortex domain, a predictive advance speed and a predictive vertical speed for said rotorcraft are calculated, said predictive vertical speed being calculated differently depending on the value of said instantaneous advance speed. Thereafter, said predictive advance speed and said predictive vertical speed are compared with said thresholds, which may be thresholds with hysteresis, in order to determine whether said rotorcraft is approaching a vortex domain, and if so to signal this situation to a pilot of said rotorcraft.

Abstract: A sensor for detecting relative movement between two adjacent components includes a first member, a second member rotatable about an axis relative to the first member, and a fuse element including a first electrical contactor connected to the first member and a second electrical contactor connected to the second member. When the first member and the second member are skewed, the first electrical contactor and the second electrical contactor are not in electrical contact.

Abstract: A navigation security module of an unmanned aerial vehicle (UAV) receives a combination of signals from a location technology, each signal comprising at least a signal identification and location data. The combination of signal identifications is processed against known identifications. If the identification is not found, or if the combination of signal identification is not possible, the signal may be a rogue signal, resulting in a quarantine protocol.

Abstract: An unmanned aerial vehicle (UAV) system, location and method, for operation with a flight management system, has a controlled access UAV zone for at least one of: UAV landing, UAV loading, and UAV take-off. A sensor can be in communication with a control panel and/or a lock to govern access to the UAV zone. The zone can have a barrier with closure secured by the lock, and controlled by a flight management system. Separate access codes can be provided for departure and destination locations, to enable personnel associated with a delivery request to access those locations, to effect delivery of an article. The codes can be generated and supplied when the flight management system receives a valid delivery request.

Abstract: Locking line capture devices for unmanned aircraft, and associated systems and methods are disclosed herein. A representative system includes a line capture body having a line slot with an open end and closed end, and a retainer positioned proximate the line slot and movable between first position in which the retainer blocks access to the line slot and a second position in which the retainer allows access to the line slot. A locking device is operably coupled between the capture body and the retainer and is movable between an unlocked position to allow movement of the retainer between the first and second positions, and a locked position to block such movement. A release device is operably coupled to the locking device and movable between a secured position with the locking device secured in the locked position, and a released position with the locking device movable between the locked and unlocked positions.

Abstract: The object is to provide an aircraft component positioning device, an aircraft assembly system, and an aircraft assembly method with which it is possible to precisely dispose components on a planar member of an aircraft without using a positioning jig. A positioning device (2) includes a detection unit (5) that detects positions of a plurality of first components installed on a planar member of an aircraft, a virtual position creation unit (6) that creates a virtual position between the plurality of first components on the basis of the positions of the plurality of first components that are detected, and a position determination unit (7) that, on the basis of the virtual position that is created, determines an installation position of a second component, different from the plurality of first components, that is installed on the planar member.

Abstract: A method of repairing or, in certain cases, strengthening a metallic substrate at a damage site is provided and includes removing material from the substrate around the damage site to form a recess, and cold spraying particulate material into the recess to form a bead of deposited material.

Abstract: An engine monitoring system for an aircraft engine having a nacelle extending annularly thereabout and a sensor positioned radially inward therefrom. The system includes an engine control device coupled communicatively to the sensor and configured to receive engine data from the sensor and/or receive instruction data from a transmitter device positioned radially outward from a nacelle radially outward surface. The system also includes a composite panel including at least a portion of the nacelle and a ground plane positioned radially inward from the nacelle radially outward surface, the composite panel including an antenna coupled communicatively to engine control device and a radome positioned radially outward from ground plane. The antenna is configured to at least one of receive engine data from the engine control device and transmit engine data to a receiver device, and receive instruction data from the transmitter device and transmit instruction data to the engine control device.

Abstract: An engine communication system for aircraft engines having a nacelle with two cowlings extending annularly about the aircraft engine and defining a radially outward surface thereof, and at least one sensor positioned radially inward from the nacelle. The system includes a cowling gap positioned between the two cowlings when coupled together, and an engine control device communicatively coupled to the sensor and configured to at least one of receive engine data from the sensor and receive instruction data from a transmitter device positioned radially outward from the cowling gap. The system also includes a linearly polarized antenna communicatively coupled to the engine control device and positioned radially inward from the cowling gap and extending radially outward toward the cowling gap. The antenna is configured to at least one of receive and transmit the engine data and the instruction data through the cowling gap.

Abstract: Predictive aircraft maintenance methods include extracting feature data from flight data collected during a flight of the aircraft, calculating a performance classifier indicator that indicates a performance category of the selected flight control surface component within a threshold number of future flights based on the feature data, and determining the performance status of the selected flight control surface component relative to the threshold number of future flights based on the performance classifier indicator. Such methods may include classifying the feature data with an ensemble of related primary classifiers to produce a primary classifier indicator for each primary classifier and aggregating the primary classifier indicators to produce the performance classifier indicator indicating the performance category of the selected active component for the threshold number of future flights.

Abstract: Methods, systems, and apparatus for designing, constructing and using instrument landers for in situ exploration of small solar system bodies, such as asteroids and comets. In one aspect, a lander includes a CubeSat-style platform; instrument packaging, wherein the CubeSat-style platform and the instrument packaging are configured and arranged for an uncontrolled descent, hopping landing on a surface of a body in a solar system, where a descending trajectory for the lander is designed based on gravitational force and solar radiation, with no lander-based propulsion; and a mobility mechanism configured and arranged to self-orient the lander on the surface of the body in the solar system.

Abstract: A satellite comprises thrusters disposed with the firing directions each facing away from the mass center of satellite and different from each other. A control amount calculator calculates control amounts of the mean orbital elements from the mean orbital elements and the temporal change rates of the mean orbital elements set by an orbit determiner, and the target values. A distributor calculates firing timings and firing amounts of the thrusters for realizing the control amounts of the mean orbital elements by expressing a motion of satellite with orbital elements, solving an equation taking into account coupling of an out-of-plane motion and an in-plane motion due to thruster disposition angles and thruster firing amounts at multiple times, and combining one or more thruster firings controlling mainly an out-of-the-orbit-plane direction and one or more thruster firings controlling mainly an in-the-orbit-plane direction.

Abstract: Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

Abstract: A method of forming bundles of glass articles is provided. The method includes transporting individual glass articles to an insert building station using a conveying system. The glass articles are individually located within article receiving slots of a layer separation insert using the conveying system. Each slot of the layer separation insert receives a single glass article forming a glass article layer of side-by-side glass articles. Multiple glass article layers including layer separation inserts are stacked using the conveying system forming a bundle. The layer separation inserts provide a barrier between adjacent glass articles of each of the glass article layers to inhibit glass-to-glass contact.

Abstract: A cartoning machine for packaging one or more products in a respective carton includes a product conveyor for conveying the products along an advancement direction, a transport device for transporting the carton along a transport path, an insertion zone wherein the products face an aperture of the carton and are inserted into the carton. The product conveyor includes a first belt on which first edges are mounted and a second belt on which second edges are mounted, each first edge defining with a respective second edge a pair of containment edges of the products. A mutual position of the first belt and of the second belt is adjustable so as to adjust accordingly a distance between the first edges and the second edges to adapt the pair of containment edges to a dimension of the products.

Abstract: A system and method of providing a secondary means for removing thermoforming trim material from a continuous-loop clamping chain (202) having clamps (302) biased to engage a clamp grip surface (314). A cam (400), attached to a sprocket located downstream from a cutting station (114) but upstream from a forming station (102), provides an outer surface that engages a clamp release surface (306) as the link member (300) passes over the sprocket.

Abstract: There is disclosed a labelling group for advancing a series of labels to be applied onto relative articles. In one implementation, the labelling group may include a first drum adapted to convey a strip of labels along a first path and towards a transfer station; a cutting mechanism adapted to cut a sequence of single labels from the strip; a second drum fed by first drum with cut single labels at the transfer station and adapted to convey simultaneously a required number of cut single labels along a second path. The first drum may move at a first tangential speed at the transfer station, and the second drum may move at a second tangential speed at the transfer station, where the first tangential speed is different from the second tangential speed and is adjusted on the basis of required number of cut labels to be simultaneously conveyed on second drum.