A probing system includes a device-under-test, a probe device, and a die bonder. The device-under-test includes test patterns. The probe device includes tilt angle sensors. The tilt angle sensors include spikes that protrude from the probe device. The die bonder is operational to mount the device-under-test, mount the probe device facing the device-under-test, compress the probe device and the device-under-test together to causes a subset of the spikes to contact the test patterns, measure a number of connections formed between the tilt angle sensors and the test patterns, determine a first offset angle and a second offset angle between the device-under-test and the probe device based on the number of connections, adjust the spherical positioner in one or more rotational axes in response to the first offset angle and the second offset angle to change a parallelism between the device-under-test and the probe device.
G01B 7/00 - Measuring arrangements characterised by the use of electric or magnetic techniques
G01B 21/22 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for testing the alignment of axes
2.
CONTINUOUS COMPRESSION MOLDING MACHINES AND METHODS OF CONTINUOUS COMPRESSION MOLDING A CONSOLIDATED THERMOPLASTIC MATRIX COMPOSITE MATERIAL
Continuous compression molding machines (CCMMs) and methods of continuous compression molding a consolidated thermoplastic matrix composite material are disclosed herein. The CCMMs include a mold, a heat zone heating structure, a consolidation zone heating structure, and a stress relaxation zone heating structure. The CCMMs also include a press structure, a demold structure, and a supply structure. The methods include providing a thermoplastic matrix composite material (TMCM) that includes a thermoplastic material to a CCMM. During the providing, the methods also include heating the TMCM within a heat zone of the CCMM, cooling and consolidating the TMCM within a consolidation zone of the CCMM, relaxing stress within the TMCM within a stress relaxation zone of the CCMM, demolding the TMCM within a demold zone of the CCMM at a mold temperature that is greater than a glass transition temperature of the thermoplastic material, and periodically compressing the TMCM.
B29C 43/26 - Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of indefinite length in several steps
B29C 43/44 - Compression means for making articles of indefinite length
B29C 70/50 - Shaping or impregnating by compression for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
A manufacturing system includes a stator base, a plurality of movers, one or more end effectors, and a controller. The stator base has a planar stator surface covering an array of electrical coils configured to generate an electromagnetic field. The movers each contain multiple permanent magnets configured to cause the movers to levitate and move relative to the stator surface in response to the electromagnetic field. The end effectors are coupled to the movers, and each end effector perform one or more functions in relation to a material sheet. The controller activates the electrical coils in a manner causing independent, coordinated movement of the movers over the stator surface, and causing the end effectors to engage with and operate on the material sheet.
B25J 15/06 - Gripping heads with vacuum or magnetic holding means
B25J 5/04 - Manipulators mounted on wheels or on carriages travelling along a guideway wherein the guideway is also moved, e.g. travelling crane bridge type
An example system includes at least two transceivers configured to be coupled to an interior of a cargo compartment of an aircraft, and to detect radio frequency identification (RFID) signals from an RFID tag coupled to baggage stored in the cargo compartment. The system also includes a processor configured to perform operations including receiving the signals detected by the transceivers. The operations also include based on runtimes of the signals, determining a respective distance from the baggage to each transceiver, where the respective distance defines a boundary centered at a known location of the transceiver and along which the baggage is estimated to be located relative to the transceiver. The operations also include identifying locations at which the boundaries of the transceivers intersect and, based on the locations, detecting an estimated storage location of the baggage. The operations also include controlling a display device to display the estimated storage location.
G06Q 10/08 - Logistics, e.g. warehousing, loading or distribution; Inventory or stock management
G06K 7/10 - Methods or arrangements for sensing record carriers by corpuscular radiation
G06K 19/07 - Record carriers with conductive marks, printed circuits or semiconductor circuit elements, e.g. credit or identity cards with integrated circuit chips
A system and a method include a control unit configured to monitor one or more values of one or more aircraft at one or more airports, and compare the one or more values with one or more attributes of one or more airport maps associated with the one or more airports to determine accuracy of the one or more airport maps.
A system and method include a hydraulic system onboard an aircraft, a first temperature sensor, a second temperature sensor, and a controller. The first temperature sensor measures a first temperature of hydraulic fluid upstream of an inlet of a pump of the hydraulic system. The second temperature sensor measures a second temperature of the hydraulic fluid within a cooling flow stream downstream of an outlet of the pump. The controller determines a value of a temperature rise of the hydraulic fluid across the pump as a difference between the first temperature and the second temperature, and obtains an expected range for the temperature rise across the pump based on a speed of the pump. In response to the value of the temperature rise being outside of the expected range, the controller generates a maintenance message for communication off-board the aircraft, indicating the pump is degraded.
A system and method for removing a backing from a ply of composite material is disclosed. The system includes a roller having a roller axis and a roller surface that circumscribes the roller axis. The system also includes an adhesion feature disposed on the roller surface. The system further includes a roller drive to move the roller along a travel path that is perpendicular to the roller axis and to rotate the roller about the roller axis.
Wing assemblies (100) comprise one or more wing support structures (24), an inboard-most flap (32), one or more flap supports (28) that operatively couple the inboard-most flap (32) to the one or more wing support structures (24), and one or more flap actuators (31) configured to operatively move the inboard-most flap (32) relative to the one or more flap supports (28). The flap support(s) (28) comprise at least an inboard-most inboard-flap support (106), the flap actuator(s) (31) comprise at least an inboard-most inboard-flap actuator (108) that is outboard of the inboard edge (102) of the inboard-most flap (32), and the inboard-most inboard-flap actuator (108) is spaced-away from the inboard-most inboard-flap support (106).
TRANSDUCER ASSEMBLIES THAT SELECTIVELY MEASURE A FUEL PRESSURE WITHIN A FUEL SUPPLY SYSTEM OF AN AIRCRAFT, AIRCRAFT THAT INCLUDE THE TRANSDUCER ASSEMBLIES, AND METHODS OF UTILIZING A TRANSDUCER ASSEMBLY TO TEST PERFORMANCE OF A FUEL BOOST PUMP ASSEMBLY OF AN AIRCRAFT
Transducer assemblies that selectively measure a fuel pressure within a fuel supply system of an aircraft, aircraft that include the transducer assemblies, and methods of utilizing a transducer assembly. The transducer assemblies include an electronic pressure transducer, which is configured to measure the fuel pressure and to generate a fuel pressure signal indicative of the fuel pressure, and an electronic pressure display, which is configured to receive the fuel pressure signal and to display the fuel pressure responsive to receipt of the fuel pressure signal. The transducer assemblies also include a power supply structure and an attachment structure, which is configured to operatively interconnect the electronic pressure transducer to the aircraft. The attachment structure includes a fitting, which is configured to interface with a pressure switch receptacle of the aircraft, and a valve actuation structure, which is configured to selectively actuate a receptacle valve of the pressure switch receptacle.
G01L 19/00 - MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE - Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
G01L 19/08 - Means for indicating or recording, e.g. for remote indication
10.
ADAPTABLE LIGHTING SYSTEMS AND METHODS FOR AN INTERNAL CABIN OF A VEHICLE
A system and a method include a lighting sub-system including one or more light fixtures configured to be disposed within a cargo area of an internal cabin of a vehicle. A control unit is in communication with the one or more light fixtures. The control unit is configured to control the one or more light fixtures. The control unit is configured to selectively adjust light emitted from the one or more light fixtures based on the cargo within the cargo area. The system and the method can also include one or more temperature control devices configured to one or both of adjust or maintain a temperature within the cargo area of the internal cabin of the vehicle. The control unit can be configured to control the one or more temperature control devices based on the cargo within the cargo area.
A breather used for vacuum bag compaction of a composite laminate part is semi-permanently installed on a compaction tool. The breather is a channel member having an internal passageway that routes air and volatiles from the vacuum bag to a vacuum port in the tool.
B29C 70/54 - Component parts, details or accessories; Auxiliary operations
B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
An internal cabin of a vehicle includes a vehicle control area. A first door is coupled to the vehicle control area. The first door is moveable between a first open position and a first closed position. An aisle extends between the vehicle control area and a passenger seating area. A forward section of the aisle is disposed between a first monument and a second monument. A second door is disposed within the aisle between the first monument and the second monument. The second door is moveable between a second open position and a second closed position. A privacy vestibule is defined between the second door in the second closed position, the first monument, the second monument, and the vehicle control area.
An image capture apparatus comprises a focal plane array and a filter device. The focal plane array comprises a plurality of detectors and the filter device is coupled with and covering the focal plane array. The filter device comprises at least one set of spectral filters, comprising at least a first spectral filter, which comprising a first wavelength range, and a second spectral filter, which comprises a second wavelength range that is different from the first wavelength range. The filter device also comprises a plurality of polarization channels, each having a polarization value that is different than the polarization value of any other of the plurality of polarization channels. The filter device further comprises a plurality of sounding filters, each operable within a spectral wavelength range and each configured to determine a characterization of atmospheric conditions.
A system and a method include a control unit including one or more processors configured to receive first data associated with expected movement of a vehicle system and second data associated with actual movement of the vehicle system. The control unit is configured to compare the first and second data to determine one or more differences between the first and second data. A responsive action is initiated by the control unit responsive to determining that the one or more differences are outside a designated threshold.
An automated environment for aeronautical information services includes converting a first data set from a first data structure to a common data structure, automatically creating a common database based at least on the common data structure, converting a second data set from a second data structure to the common data structure, analyzing a difference between the first converted data set and the second converted data set to determine a relevance metric, and, if the relevance metric meets a relevance threshold, storing at least a portion of the second converted data set at a filtered database, the filtered database separate from the common database, wherein the portion is associated with the difference.
An aircraft satellite communications system that communicates using satellite frequency bands. The aircraft satellite communications system comprises a base structure, transmitters, and receivers. The base structure has connectors arranged to correspond to connection points on an aircraft. The transmitters are connected to the base structure. The transmitters are configured to transmit using a first plurality of the satellite frequency bands. The receivers are connected to the base structure. The receivers are configured to receive using a second plurality of the satellite frequency bands. A selected transmitter in the transmitters transmits using a satellite frequency band in the satellite frequency bands is positioned at a distance from a selected receiver in the receivers using the satellite frequency band in the satellite frequency bands on the base structure with a number of other transmitters and receivers located between the selected transmitter and the selected receiver on the base structure.
A method automatically distributes aeronautical information. A source dataset for the aeronautical information is identified. The source dataset is in a common data format and has changes. A destination dataset for the aeronautical information is identified. The destination dataset is in the common data format. An overlap is determined between the source dataset and the destination dataset. The changes are present in the overlap between the source dataset and the destination dataset. A destination change dataset is generated in a destination format specific to the destination dataset. The destination change dataset comprises the changes present in the overlap. The destination change dataset in the destination format is sent to a destination database storing the destination dataset in the destination format.
Lateral sleep systems for aircraft are disclosed. A first lateral sleep apparatus is positioned on a first side of a divider adjacent a first seat, the lateral sleep apparatus includes a first headrest and a first cradle. The first cradle supports the first headrest and includes a first panel mounting interface coupling the first headrest to a first support ledge of the divider. A second lateral sleep apparatus is positioned on a second side of the divider adjacent a second seat, where the second lateral sleep apparatus includes a second headrest and a second cradle. The second cradle supports the second headrest and includes a second panel mounting interface coupling the second headrest to a second support ledge of the divider.
The present disclosure provides compositions including a conductive polymer; and a fiber material comprising one or more metals disposed thereon. The present disclosure further provides a component, such as a vehicle component, including a composition of the present disclosure disposed thereon. The present disclosure further provides methods for manufacturing a component including: contacting a metal coated fiber material with an oxidizing agent and a monomer to form a first composition comprising a metal coated fiber material and a conductive polymer; and contacting the first composition with a polymer matrix or resin to form a second composition.
C09D 7/62 - Additives non-macromolecular inorganic modified by treatment with other compounds
C09D 163/00 - Coating compositions based on epoxy resins; Coating compositions based on derivatives of epoxy resins
C09D 165/00 - Coating compositions based on macromolecular compounds obtained by reactions forming a carbon-to-carbon link in the main chain; Coating compositions based on derivatives of such polymers
H01B 1/12 - Conductors or conductive bodies characterised by the conductive materials; Selection of materials as conductors mainly consisting of other non-metallic substances organic substances
21.
HIGH ISOLATION RING SLOT PATCH RADIATOR FOR PHASED ARRAY ANTENNAS
Antenna elements include a metallic square ring patch and a metallic square ring slot to transmit or receive radio frequency (RF) signals. The antenna elements use several dielectric layers that are separated by a low-dielectric foam layer upon which the square ring patch is positioned. The antenna elements may be arranged into an antenna array that is tunable to collectively generate or receive RF signals to and from airborne and mobile vehicles with an agile, electronically scanning antenna array beam, with no moving parts. The antenna array includes a top section to communicate RF signals; a bottom section to generate a desired RF signal; and a foam layer between the top and bottom sections to separate the ring patch from the ring slot. High isolation between the top section and the bottom section allows the antenna elements to be used in higher gain and high-power arrays without adverse feedback issues.
H01Q 7/00 - Loop antennas with a substantially uniform current distribution around the loop and having a directional radiation pattern in a plane perpendicular to the plane of the loop
H01Q 21/06 - Arrays of individually energised antenna units similarly polarised and spaced apart
A removable hot box is disclosed that includes a lower hot box portion, comprising: a lower housing comprising a plurality of lower clamping structures to clamp the lower housing to a press and locating structures to provide repeatable placing in the press; and a lower heating platen, received within the lower housing, wherein the lower housing or the lower heating platen comprises lower electrical connectors to provide a lower electrical connection to a heating system and lower cooling connectors to provide a lower cooling connection to a cooling system; and an upper hot box portion, positionable above the lower hot box portion and comprising: an upper housing comprising a plurality of upper clamping structures to clamp the upper housing to the press; an upper heating platen, received within the upper housing.
An aircraft includes external structures, and one or more thermal emitters integrated with one or more of the external structures. The one or more thermal emitters are configured to generate heat to deice the one or more external structures. The one or more thermal emitters are configured to receive electrical power from one or more of an auxiliary power unit of the aircraft, a power distribution system of the aircraft, one or more engines of the aircraft, or an external power cart that is separate and distinct from the aircraft.
A system and a method include a resource scheduling control unit configured to receive inputs including information regarding pilots and pilot training resources, generate schedules for the pilots based on the inputs, and output the schedules to one or more user interfaces.
Example implementations are directed to a method and system for collision avoidance for an aircraft traversing a flight path. The method and system described herein provides an architecture to address the full gamut of complexity that arises when dealing with possible conflicts during aircraft flight. The collision avoidance method and system disclosed herein first receives multiple streams of potential conflict information that not only considers direct obstacles on the flight path of the aircraft, but also considers contextual obstacles that are within a perimeter of the flight path. Once the possible objects are considered, a plurality of alternate flight paths are calculated and the alternate flight path with an acceptable miss distance with a possible obstacle (and minimized deviation from the original flight path) is selected and the aircraft traversing the flight path deviates from the original flight path to the alternate flight path to avoid the collision(s).
A method for detecting defects includes steps of: (1) calculating an average value for intensity of CT image voxels in a neighborhood; (2) calculating a difference value for the intensity of the voxels in the neighborhood; (3) calculating a standard deviation for the intensity of the voxels in the neighborhood; (4) calculating a z-score for each one of the voxels; (5) identifying a cluster of neighboring ones of the voxels; (6) determining a cluster-boundary parameter of the cluster; and (7) classifying the cluster as a defect when the cluster-boundary parameter of the cluster is above a parameter threshold.
A method for shaping a composite structure includes steps of: (1) holding a composite member in an initial contour along a length of the composite member; and (2) forming a final contour along the length of the composite member by: (3) sequentially shaping formed portions of the composite member while holding unformed portions of the composite member in the initial contour to form portions of the final contour; and (4) sequentially shaping the unformed portions of the composite member to form other portions of the final contour.
A retroreflective sign comprising a rigid substrate with a pattern of cell walls formed of a polyurethane adhesive or two-part polyurea adhesive, and a polymeric sheet having a front face and a rear face, the rear face facing the substrate, the rear face comprising microprismatic reflective elements is disclosed. The polymeric sheet is adhered directly to the cell walls formed of the polyurethane adhesive or two-part polyurea adhesive while leaving an air gap between the microprismatic retroreflective elements and the rigid substrate in the cells. A method of making the retroreflective sign includes applying a polyurethane adhesive or two-part polyurea adhesive to a front side of a rigid substrate in a pattern defining cell walls; and prior to full curing of the polyurethane adhesive, laminating the front side of the rigid substrate a rear side of a polymeric sheet via the cell walls, the polymeric sheet comprising microprismatic elements.
A permeable pavement and cured fiber composition and a related method are provided. The permeable pavement composition includes a quantity of pavement material, and a quantity of cured carbon fiber composite material (CCFCM) configured to be added to the pavement material to produce a reinforced composition having improved characteristics. An example of pavement material includes a pervious concrete material. The method includes providing a quantity of pavement material and adding a quantity of cured carbon fiber composite material to the pavement material to produce a reinforced composition having improved characteristics.
C04B 20/00 - Use of materials as fillers for mortars, concrete or artificial stone according to more than one of groups and characterised by shape or grain distribution; Treatment of materials according to more than one of the groups specially adapted to enhance their filling properties in mortars, concrete or artificial stone; Expanding or defibrillating materials
B28B 3/02 - Producing shaped articles from the material by using presses; Presses specially adapted therefor wherein a ram exerts pressure on the material in a moulding space; Ram heads of special form
B28B 11/24 - Apparatus or processes for treating or working the shaped articles for curing, setting or hardening
C04B 18/167 - Recycled materials, i.e. waste materials reused in the production of the same materials
C04B 28/02 - Compositions of mortars, concrete or artificial stone, containing inorganic binders or the reaction product of an inorganic and an organic binder, e.g. polycarboxylate cements containing hydraulic cements other than calcium sulfates
A diagnostic circuit includes an input port configured to receive an input current and a first superconducting quantum interference device (SQUID) inductively coupled to the input port. The first SQUID is configured to generate a first output in the form of: a first voltage in response to the input current being less than a first threshold current and a second voltage in response to the input current being greater than the first threshold current. The diagnostic circuit also includes a second SQUID inductively coupled to the input port. The second SQUID is configured to generate a second output in the form of: a third voltage in response to the input current being less than a second threshold current and a fourth voltage in response to the input current being greater than the second threshold current.
H01L 39/02 - Devices using superconductivity or hyperconductivity; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof - Details
G01R 33/035 - Measuring direction or magnitude of magnetic fields or magnetic flux using superconductive devices
H01L 39/22 - Devices comprising a junction of dissimilar materials, e.g. Josephson-effect devices
31.
METHODS AND SYSTEM FOR DETERMINING FIBER PLACEMENT START LOCATIONS FOR MANUFACTURING A LAMINATED COMPOSITE COMPONENT
The present disclosure is directed to methods and system for determining fiber placement start locations for manufacturing a laminated composite component. The method includes one or more processors accessing a computer geometric model of the laminated composite component, which includes various characteristics of the component that will be generated. Then, the processors break individual plies of the model into different groups. For each of the groups of plies, stagger requirements are determined and an algorithm (e.g., an integer optimization algorithm or other method described herein) for resolving the stagger requirements is executed. A three dimensional fiber placement start location for each ply in the group is then calculated based on the output from the executed algorithm, a reference curve determined on a definition surface, and a geodesic curve on the surface that is normal to the definition surface.
An aircraft, a method of controlling the aircraft, and a control system for the aircraft has a fuselage and tilt-wing movable relative to the fuselage. A plurality of main propulsors coupled to main propellers that is coupled to the tilt-wing, which are configured to provide a first maximum amount of thrust. A plurality of auxiliary propulsors coupled to auxiliary propellers that are spaced apart from the tilt-wing, which are configured to provide a variable amount of thrust. A controller signals the main propulsors to operate at the first maximum amount of thrust when the tilt-wing moves from the cruise position to the transition position, and signals the auxiliary propulsors to operate at the variable amount of thrust when the tilt-wing is in the transition position in which the first maximum amount of thrust and the variable amount of thrust together provide an overall thrust to descend and land the aircraft.
A missile system wherein a missile carrier delivers a plurality of submissiles over a target area. A passive or active scanner on the missile carrier repeatedly scans the target area as the missile carrier descends by drag brake over the target area. Submissile assignment to identified targets is performed at a selected altitude. A data processor controls the launching of the submissiles and actively guides the submissiles for substantial portions of their flights via optical fiber or wire links separately connecting each submissile to the missile carrier. Each submissile includes either passive or active identification devices enabling the data processor to track the submissiles individually. A missile assignment table stores a correspondence between identified targets and submissiles assigned thereto. Submissile assignment is effected on the basis of the strength of target signature. Alternatively, the most closely spaced group of targets equal in number to the number of submissiles will be assigned submissiles.
An aerial vehicle includes a wing body, a first wingtip, a second wingtip, a first edge, and a second edge. The aerial vehicle includes a pair of coaxial rotors configured to rotate in opposite rotational directions about a vehicle axis and a drive assembly configured to rotate the coaxial rotors. A controller is configured to selectively control thrust produced by the coaxial rotors. Selective control of the thrust produced by the coaxial rotors induces a pitch motion of the aerial vehicle to transition between a horizontal flight state and a vertical flight state. In the horizontal flight state, a collective thrust from the coaxial rotors is directed forward. In the vertical flight state, the collective thrust from the coaxial rotors is directed upward.
Sonic fatigue analysis is provided. The method comprises developing a finite element model of a structure and calculating, from the finite element model, a number of eigenvalues representing fundamental frequencies and mode shapes for the structure. The eigenvalues are mapped to pressure loads applied to the structure in the finite element model. Frequency responses from the pressure loads are analyzed according to pressure spectral density requirements for the structure, and a critical element in the structure is identified according to the frequency responses. A frequency response function is plotted for the critical element, and an applied stress is calculated according to the frequency response function, wherein the applied stress represents total cumulative stress at the critical element.
G06F 30/13 - Architectural design, e.g. computer-aided architectural design [CAAD] related to design of buildings, bridges, landscapes, production plants or roads
G06F 30/23 - Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
36.
AIRCRAFT DE-ICING DETERMINATION SYSTEMS AND METHODS
A system and a method include a control unit for determining a probable de-icing status for one or more aircraft scheduled to depart from one or more airports. The control unit is configured to determine the probable de-icing status based on a current date at the one or more airports, current weather at the one or more airports, and the actual de-icing status of a plurality of prior aircraft scheduled to depart from the one or more airports before the one or more aircraft.
A fastening end effector is presented. The fastening end effector comprises a hammering insertion die translatable into and out of a housing of the fastening end effector along a longitudinal axis of the fastening end effector; and grippers positioned circumferentially around the hammering insertion die to hold a head of a fastener against the hammering insertion die, the grippers independently moveable relative to the hammering insertion die.
An end effector for confined space manufacturing operations and methods of use are presented. The end effector comprises a pair of kinematic machines connected in series, and an operational head connected to a first platform of a first kinematic machine of the pair of kinematic machines, the operational head configured to perform number of manufacturing operations on a structure.
B25J 19/00 - Accessories fitted to manipulators, e.g. for monitoring, for viewing; Safety devices combined with or specially adapted for use in connection with manipulators
The present disclosure includes a method and apparatus for ink jet printing an exterior surface of a vehicle including a reversibly moveable crossbeam mounted above an open pit; a first track located above the reversibly moveable crossbeam, a first reversibly moveable monument including a first serial robotic manipulator including a first end effector defining a first end effector range of motion based on fully extended reversible movement of the first serial robotic manipulator; a second track located in the open pit beneath the reversibly moveable crossbeam; a second reversibly moveable monument coupled to the second pair of rails, the second reversibly moveable monument including a second end effector defining a second end effector range of motion based on fully extended reversible movement of the second serial robotic manipulator. The first end effector range of motion overlaps the second end effector range of motion.
B41J 25/304 - Bodily-movable mechanisms for print heads or carriages movable towards or from paper surface
B41J 3/407 - Typewriters or selective printing or marking mechanisms characterised by the purpose for which they are constructed for marking on special material
The present disclosure includes a method and apparatus for changing livery on a vehicle. A method of inkjet printing an exterior surface of a vehicle, includes preparing at least a portion of the exterior surface of the vehicle in a first bay using crossflow or downflow air handling and using explosion protected equipment. That method includes inkjet printing at least the portion of the exterior surface of the vehicle in a second bay. This method includes clear-coating at least the portion of the exterior surface of the vehicle in a third bay using downflow or crossflow air handling, using air filtration and using explosion protected equipment.
B05C 5/02 - Apparatus in which liquid or other fluent material is projected, poured or allowed to flow on to the surface of the work from an outlet device in contact, or almost in contact, with the work
B05D 7/00 - Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
B05D 7/14 - Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials to metal, e.g. car bodies
41.
Instance Graph Database and Model Graph Database for Data Management of a Platform
A coupled graph database pair for management of a platform is presented. The coupled graph database pair comprises a model graph database managed in a manufacturer environment, an instance graph database managed in a customer environment, and a plurality of relationships between the nodes of the model graph database and the nodes of the instance graph database. The model graph database comprises nodes of assemblies, sub-assemblies, and parts for a designed configuration of a model of the platform. The instance graph database comprises nodes of assemblies, sub-assemblies, and parts for a real-time configuration of the platform.
A wing structure having a unitary body formed by a plurality of tubular sections that are arranged side-by-side and configured such that adjacent internal walls of the tubular sections create internal spar structures that substantially reduce or eliminate the need for non-integral spars, or for fasteners to attach conventional spars and ribs into the wing skins. The unitized structure formed by the plurality of tubular sections can be further overwrapped with a composite material to provide additional strength to the wing structure.
Chamfer-cutting tool kits comprise a cutter, a bushing, an upper-edge guide block, and a lower-edge guide block, and are configured to be selectively assembled into an upper-chamfer configuration for cutting an upper chamfer and into a lower-chamfer configuration for cutting a lower chamfer.
Fastener storage is presented. The fastener storage comprises a disc with a plurality of apertures through a first face of the disc and arranged in a plurality of rings concentric with the disc, and a plurality of machine-readable identifiers on the first face of the disc.
A device includes a processor configured to obtain flight data of one or more aircraft of an aircraft type. The processor is configured to identify a first portion of the flight data as first phase flight data associated with a first phase of one or more flights of the one or more aircraft, and to apply a first aircraft performance model to the first phase flight data to determine first parameter values. The processor is configured to identify a second portion of the flight data as second phase flight data associated with a second phase of the one or more flights, and to apply the first aircraft performance model to the second phase flight data to determine second parameter values. The processor is configured to generate, based on the first parameter values and the second parameter values, a second aircraft performance model of a particular aircraft of the aircraft type.
A vehicle includes an internal cabin. One or more areas are within the internal cabin. The one or more areas include one or more water-drawing components. A water supply system is within the internal cabin. The water supply system is configured to provide water to the one or more water-drawing components. A water leak detection system includes one or more sensing devices configured to detect water flow from the water supply system to the one or more water-drawing components. One or more shut-off valves are disposed on or within the water supply system. A control unit is in communication with the one or more sensing devices, the one or more shut-off valves, and the one or more water-drawing components. The control unit is configured to operate the one or more shut-off valves to stop the supply of water to the one or more water-drawing components in response to the one or more sensing devices detecting the water flow when the one or more water-drawing components are not in use.
G01M 3/26 - Investigating fluid tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
B64F 5/60 - Testing or inspecting aircraft components or systems
A method of monitoring controls of a vehicle includes receiving, at a computing device, sensor data from a ranging system. The ranging system monitors a space associated with one or more vehicle controls. The method also includes, in response to a determination by the computing device that one or more objects are introduced into the space based on analysis of the sensor data, causing the computing device to save state data to a first memory onboard the vehicle. The state data includes position data indicating a position of the one or more objects in the space.
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G07C 5/00 - Registering or indicating the working of vehicles
A composite skin is attached to an underlying structure by fasteners that are countersunk into the structure. The composite skin comprises a thermoplastic material that has been melted and formed into a countersink in the structure using a heated tool.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
B32B 7/08 - Interconnection of layers by mechanical means
A computing system receives sensor data that includes, for a reporting aeronautical vehicle of a set of one or more reporting aeronautical vehicles, one or more images captured by the reporting aeronautical vehicle. For the image of the sensor data, the computing system identifies one or more candidate landing zones within the image. For the candidate landing zone identified, the computing system estimates a geographic position of the candidate landing zone; and associates an identifier of the candidate landing zone with the geographic position. The computing system receives, from a client device, a request for a landing zone for an aeronautical vehicle. Responsive to the request, the computing system selects from among the one or more candidate landing zones, a target candidate landing zone; and sends the geographic position estimated for the target candidate landing zone to the client device.
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
G05D 1/10 - Simultaneous control of position or course in three dimensions
G06T 7/70 - Determining position or orientation of objects or cameras
G06V 10/62 - Extraction of image or video features relating to a temporal dimension, e.g. time-based feature extraction; Pattern tracking
G06V 10/764 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using classification, e.g. of video objects
G06V 20/17 - Terrestrial scenes taken from planes or by drones
Methods and apparatus for manufacturing a thermoplastic structure include laying a first plurality of braided plies on a mandrel, and laying one or more unidirectional plies on the plurality of braided plies. A second plurality of braided plies is laid on the one or more unidirectional plies. The layup thereby forms a thermoplastic structure having combined braided and unidirectional plies.
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
51.
SYSTEMS AND METHODS FOR REFINING ADDITIVELY MANUFACTURED COMPONENTS
An additive manufacturing system and method include an additive manufacturing head including an energy emitter that is configured to emit energy into a material to form one or more portions of a component. An ultrasonic laser emitter is configured to emit ultrasonic laser energy onto a portion of the material to generate ultrasonic waves in relation to the portion of the material. The ultrasonic waves control development of one or both of microstructure or size of grains in relation to the portion of the material.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
B29C 64/268 - Arrangements for irradiation using electron beams [EB]
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
52.
DRONE COORDINATED SATELLITE COMMUNICATIONS, ENERGY HARVESTING, AND CAMOUFLAGE
A device to assemble a skin and a frame of an aircraft fuselage. The device includes first and second brace members that extend along opposing sides of a gap. Arches are spaced apart and fixedly connected to the first and second brace members and that extend across the gap. A strongback is attached to and movable along the first and second brace members with the strongback having a curved shape that matches the plurality of arches. The strongback includes clamps configured to engage with the frame. First and second tension devices apply tension to the skin at the strongback.
A coated powder for use in additive manufacturing includes a base polymer layer formed of a base polymer material and a coating polymer layer formed of a coating polymer material. At least the coating polymer material is susceptible to dielectric heating in response to electromagnetic radiation, thereby promoting fusion between adjacent particles of coated powder that are deposited during the additive manufacturing process. Specifically, when electromagnetic radiation is applied to at least an interface area between adjacent particles of coated powder, the polymer coating layer melts to diffuse across the interface area, thereby preventing formation of voids. The base polymer material and the coating polymer material also may have similar melting points and compatible solubility parameters to further promote fusion between particles.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B01D 67/00 - Processes specially adapted for manufacturing semi-permeable membranes for separation processes or apparatus
B05D 5/08 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures to obtain an anti-friction or anti-adhesive surface
B22F 10/00 - Additive manufacturing of workpieces or articles from metallic powder
B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
B22F 12/00 - Apparatus or devices specially adapted for additive manufacturing; Auxiliary means for additive manufacturing; Combinations of additive manufacturing apparatus or devices with other processing apparatus or devices
B22F 12/82 - Combination of additive manufacturing apparatus or devices with other processing apparatus or devices
B29C 64/00 - Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
B29C 64/176 - Processes of additive manufacturing specially adapted for manufacturing multiple 3D objects sequentially
B29C 64/182 - Processes of additive manufacturing specially adapted for manufacturing multiple 3D objects in parallel batches
B29C 64/20 - Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering - Details thereof or accessories therefor
B29C 64/307 - Handling of material to be used in additive manufacturing
B29C 64/386 - Data acquisition or data processing for additive manufacturing
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B29C 64/40 - Structures for supporting 3D objects during manufacture and intended to be sacrificed after completion thereof
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
Disclosed are hierarchical buoyant materials comprising porous components having multiple length scales that provide reduced density, higher strength, and improved buoyancy. The hierarchical buoyant materials include components having at least two length scales including a first porous material having elements characterized by a first linear length scale and a second porous material having elements characterized by a second linear length scale. The first porous material includes hollow microspheres, and the second porous material provides low effective density via geometrical arrangements. The second linear length scale is substantially different than the first linear length scale in terms of size, e.g., diameter, length, or distance. The second porous material is packed between the first porous material resulting in a combined material having a higher packing fraction than either the first porous material or the second porous material alone to provide reduced density, higher specific strength, and improved buoyancy per unit volume.
A method, apparatus, system, and computer program product for managing flight leg data for flight legs flown by a plurality of aircraft. A computer system receives the flight leg data for the flight legs flown by the plurality of aircraft in real-time. The computer system associates aircraft operation data and airport data with the flight leg data such that the aircraft operation data and airport data associated with the flight leg data forms flight activity data for the flight legs. The computer system displays a selected view of the flight activity data in real-time in a graphical user interface on a display system in response to a query for the flight activity data using the selected view.
A testing system and methods of testing interfaces of a subsystem are presented. The testing system is configured to test a subsystem prior to assembly into a system, the testing system comprising a test rig comprising electrical wiring and a mechanical restraint configured to emulate at least one physical specification of the structure; and a virtual software environment developed to emulate operating software for of the system.
A method includes calculating a gradient vector of a property of a framework with respect to first components of a first vector and second components of a second vector. The first components correspond to first structures available for a first location of the framework and the second components correspond to second structures available for a second location of the framework. The method includes identifying, based on the gradient vector, first values for the first components and second values for the second components that yield a third value of the property that satisfies a criterion, selecting a first selected composite sandwich structure of the first composite sandwich structures and a second selected composite sandwich structure of the second composite sandwich structures, and providing output indicating (a) the first values and the second values or (b) the first selected composite sandwich structure and the second selected composite sandwich structure.
G06F 30/15 - Vehicle, aircraft or watercraft design
G06F 30/12 - Geometric CAD characterised by design entry means specially adapted for CAD, e.g. graphical user interfaces [GUI] specially adapted for CAD
A wing lock and deployment apparatus for an air launched vehicle includes a driver acted on by a single linear actuation event. The disclosed wing lock and deployment apparatus is capable of unlocking deployable wings of an air launched vehicle, deploying deployable wings of the air launched vehicle from a stored position, and locking deployable wings of the air launched vehicle in a deployed position in sequential order with the one single linear actuation event.
A wing lock and deployment apparatus for an air launched vehicle includes a ball screw and driver acted on by a single actuation event. The disclosed wing lock and deployment apparatus is capable of unlocking deployable wings of an air launched vehicle, deploying deployable wings of the air launched vehicle from a stored position, and locking deployable wings of the air launched vehicle in a deployed position in sequential order with the one single actuation event.
System and methods obtain ontology and contextual data for a plurality of domains, and generate an ontological knowledge graph using the ontology and contextual data. The ontological knowledge graph includes a plurality of nodes with links between the plurality of nodes, wherein the plurality of nodes are contained within a spherically represented data structure. The plurality of nodes with the links are displayed in a curvilinear orthography world metaphor digital view within the spherically represented data structure.
The present disclosure provides a system that includes an ingress module arranged to receive flight data comprising a descent rate value and an altitude value; a data store comprising descent rate threshold values of at least one aircraft model, the descent rate threshold values associated, in the data store, with pressure altitude values; a descent classification module that is operably coupled to the ingress module and the data store and adapted to compare the descent rate value with the descent rate threshold values; an alert module adapted to provide, in response to the descent classification module comparing the descent rate value that exceeds at least one of the descent rate threshold values, an alert signal to a graphic user interface that is operably coupled to the alert module.
Shipping containers for batteries are described herein. An example shipping container includes a base defining a cavity, a lid to be coupled to a top of the base to substantially seal the cavity, and an absorbent pad disposed within the cavity to absorb liquid from the battery if the battery leaks.
B65D 81/26 - Adaptations for preventing deterioration or decay of contents; Applications to the container or packaging material of food preservatives, fungicides, pesticides or animal repellants with provision for draining away, or absorbing, fluids, e.g. exuded by contents; Applications of corrosion inhibitors or desiccators
B65D 81/05 - Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents specially adapted to protect contents from mechanical damage maintaining contents at spaced relation from package walls, or from other contents
B65D 85/30 - Containers, packaging elements or packages, specially adapted for particular articles or materials for articles particularly sensitive to damage by shock or pressure
B65D 85/84 - Containers, packaging elements or packages, specially adapted for particular articles or materials for corrosive chemicals
Methods of recovering and/or recycling expanded polymer tooling, the methods including collecting expanded polymer tooling, reducing the collected expanded polymer tooling into smaller particles, treating the reduced expanded polymer tooling in order to yield an at least partially purified recovered polymer composition, and then collecting the at least partially purified recovered polymer composition. The at least partially purified recovered polymer composition can then be used to form new expandable polymer tooling.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
A method for repairing a crack in a structure includes mounting a manifold to the structure around the crack. The structure has a nonplanar surface contour that surrounds the crack. The manifold has a base portion, a cover portion, and a plug. The base portion has a grip surface configured to conform to the nonplanar surface contour of the structure. The cover portion is connected to the base portion, and has an injection port and a vent port in fluid communication with a channel aligned to the crack. The injection port transfers a bonding material into and out of the channel. The plug closes and opens the vent port. The method includes filling the channel with the bonding material to direct the bonding material into the crack, and draining the bonding material from the manifold.
B23P 6/04 - Repairing fractures or cracked metal parts or products, e.g. castings
B23K 20/00 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
B29C 73/04 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements
A navigation system for one or more vehicles includes: a first camera configured to observe the vehicle(s) and first and second reference points within a first field of view, wherein the first and second reference points have first and second known spatial positions, respectively, the first camera being further configured to produce a first output signal from observation of the observed vehicle(s) and reference points; a second camera configured to observe the vehicle(s) and reference points within a second field of view, the second camera being further configured to produce a second output signal from observation of the observed vehicle(s) and reference points; and a processor operatively connected with the first and second cameras and configured to determine a respective spatial position for each vehicle(s) from the first and second output signals and from known first and second camera spatial positions of the first and second cameras.
Systems, methods, and apparatus for processing a signal using a non-uniform antenna array are disclosed. In one aspect, a receiver apparatus for processing high frequency signals is provided. The receiver apparatus may comprise an antenna array including a plurality of antenna elements. The plurality of antenna elements may include a first antenna element and a remainder of the plurality of antenna elements. The remainder of the plurality of antenna elements may be uniformly spaced apart from one another by a first distance and arranged in a substantially linear orientation. The remainder of the plurality of antenna elements may include a second antenna element spaced apart from the first antenna element by a second distance. The second distance may be different than the first distance.
G01S 3/46 - Systems for determining direction or deviation from predetermined direction using antennas spaced apart and measuring phase or time difference between signals therefrom, i.e. path-difference systems
A computer-implemented method for matching material names from one or more material sources with safety data sheet material names from one or more safety data sheets. The method includes: extracting the material names from the one or more material sources; preprocessing the material names and removing extraneous data from one or more of the material names; selecting one of the material names; comparing the selected material name with the safety data sheet material names; identifying the safety data sheet material names that match the material name; and transmitting an output to a user device to display the material name and the matching safety data sheet material names.
A method for recycling an aluminum alloy scrap includes performing selective oxidation roasting and washing treatment on the aluminum alloy scrap to obtain an uncoated aluminum alloy scrap; melting the uncoated aluminum alloy scrap in a refining furnace to obtain aluminum alloy melt liquid, online-detecting components of the aluminum alloy melt liquid and adding a metallic copper, a copper alloy, a magnesium alloy or a zinc alloy to the aluminum alloy melt liquid according to the requirements of target alloy components, performing pressure-controlled and oxygen-controlled melting through regulating pressure intensity and oxygen partial pressure in the refining furnace and coupling an external-field stirring mode to obtain refining aluminum alloy melt liquid; filtering the refining aluminum alloy melt liquid, to obtain an aluminum alloy melt with the target alloy components; and casting the aluminum alloy melt.
B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
A masking tool includes a body portion; a masking portion supported by the body portion, the masking portion having an engagement surface sized to fit a periphery of the opening; and a retention member extending from the body portion, the retention member being positioned to engage a surface of the recess to retain at least a portion of the body portion within the recess and to maintain the engagement surface of the masking portion against the periphery of the opening.
A stamp-forming system includes a lower die formed of elastomeric material and having lower die lateral sides. In addition, the stamp-forming system includes a die wall configured to encircle the lower die lateral sides, and move vertically relative to the lower die. Also included in the stamp-forming system is an upper die configured to move between an open position in which the upper die is separated from the die wall and the lower die, and a clamped position in which the upper die is in contact with the die wall and applying clamping pressure to a blank against the lower die, to thereby form the blank into a formed article. The die wall is sized and configured to prevent lateral expansion of the lower die when the lower die is vertically compressed by the clamping pressure applied by the upper die.
A method of generating an infill geometry of a body, comprises providing a driver mesh comprised of tetrahedral elements, and providing a reference unit cell mesh configured to fit exactly within a regular tetrahedron having triangular faces. The reference unit cell mesh is symmetric with respect to the arrangement of cell mesh nodes on the triangular faces. The method includes mapping the reference unit cell meshes respectively into the tetrahedral elements of the driver mesh, through the use of basis functions defined on each of the tetrahedral elements in a manner causing adjustment of the reference unit cell meshes to conform respectively to the tetrahedral elements, and resulting in an infill geometry comprised of mapped unit cell meshes. The method additionally includes stitching together the mapped unit cell meshes to result in a stitched mesh, and optionally smoothing the stitched mesh through one or more mesh smoothing operations.
A method of generating a panel infill geometry of a sandwich panel, includes providing a driver mesh representing a panel mid-surface of a sandwich panel. The driver mesh is comprised of a plurality of quadrilateral elements. The method further includes providing a reference unit cell mesh configured to fit exactly within a cube. The reference unit cell mesh is comprised of a unit infill mesh interconnecting a pair of unit face sheet meshes. The method additionally includes mapping a plurality of the reference unit cell meshes respectively onto a plurality of hexahedral elements respectively associated with the plurality of quadrilateral elements, through the use of basis functions defined on each of the plurality of quadrilateral elements in a manner causing adjustment of the size and shape of the plurality of reference unit cell meshes to conform respectively to the plurality of hexahedral elements.
A method for manufacturing a tool having one or more internal channels includes forming one or more channel cores by additive manufacturing, coating a metal onto the one or more channel cores to form a metal tube on each of the one or more channel cores, positioning the one or more metal tubes into a casting mold having a shape of a tool, and casting a molten metal into the casting mold to form the tool having the one or more internal channels corresponding to the one or more channel cores.
An apparatus for inserting a wire contact into an object is disclosed. The apparatus comprising a handle portion and a trigger slidably engaged with the handle portion. The apparatus also comprises an inner tube comprising an inner-tip end that is fixed to the handle portion. The apparatus further comprises an outer tube comprising an outer-tip end that is concentric with and slidably moveable relative to the inner tube. The outer tube is fixed to the trigger. The trigger is configured to move along the handle portion between, and inclusive of, a first position and a second position. When the trigger is in the first position, the inner-tip end of the inner tube is retracted within the outer tube. Alternatively, when the trigger is in the second position, the inner-tip end of the inner tube is extended from the outer-tip end of the outer tube.
Methods and apparatus for performing repair operations using an unmanned aerial vehicle. The methods are enabled by equipping the UAV with tools for rapidly repairing a large structure or object (e.g., an aircraft or a wind turbine blade) that is not easily accessible to maintenance personnel. In accordance with various embodiments disclosed below, the unmanned aerial vehicle may be equipped with an easily attachable/removable module that includes an additive repair tool. The additive repair tool is configured to add material to a body of material. For example, the additive repair tool may be configured to apply a sealant or other coating material in liquid form to a damage site on a surface of a structure or object (e.g., by spraying liquid or launching liquid-filled capsules onto the surface). In alternative embodiments, the additive repair tool is configured to adhere a tape to the damage site.
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B05B 1/28 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means with integral means for catching drips or collecting surplus liquid or other fluent material
B05B 14/30 - Arrangements for collecting, re-using or eliminating excess spraying material comprising enclosures close to, or in contact with, the object to be sprayed and surrounding or confining the discharged spray or jet but not the object to be sprayed
B05D 5/00 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
B64D 1/18 - Dropping or releasing powdered, liquid or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
A computer-implemented method and system for identifying an object in an area of interest. The area of interest is enclosed by a boundary comprising a plurality of line segments extending between vertex points. A reference point relative to the area of interest and a reference direction from the reference point are determined and used to determine a vertex angle of each vertex point. The reference point and reference direction also are used to determine an object angle of the object from location information identifying a location of the object. The object angle and the vertex angles are used to identify a number of line segment crossings in the plurality of line segments. An indicator is generated to indicate whether the object is in the area of interest based on the number of line segment crossings.
An ultrasonic injection device and methods of use are presented. The ultrasonic injection device comprises a housing, an injection nozzle attached to the housing, an ultrasonic vibration generator attached to the housing, and a pressure applicator. The injection nozzle has a number of openings configured to dispense a fluid. The ultrasonic vibration generator is configured to apply ultrasonic energy to fluid within the injection nozzle. The pressure application is configured to propel the fluid towards and out of the number of openings.
B05B 17/06 - Apparatus for spraying or atomising liquids or other fluent materials, not covered by any other group of this subclass operating with special methods using ultrasonic vibrations
79.
Systems, apparatus, articles of manufacture, and methods for code merging in communication systems
Systems, apparatus, methods, and articles of manufacture are disclosed for code merging in communication systems. An example apparatus includes at least one memory, machine-readable instructions, and processor circuitry to at least one of instantiate or execute the machine-readable instructions to at least identify first data as line-of-sight data based on a first range of a first target object, identify second data as multipath data based on a second range of a second target object, after a determination that the second data includes a data portion not included in the first data, output communication data based on a merge of the first data and the second data, and cause movement of at least one of the first target object or the second target object based on the communication data.
Commonwealth Scientific and Industrial Research Organisation (Australia)
Inventor
Kinlen, Patrick J.
Bruton, Eric Alan
Kohl, Thomas Matthew
Espiritu, Maria
Abstract
The present disclosure generally relates to coatings and compositions comprising conductive polymers. The present disclosure also relates to thermally stable coatings and compositions comprising solution processable polyaniline conducting polymers and thermal stability agents, and to processes for preparing the coatings and compositions.
H01B 1/12 - Conductors or conductive bodies characterised by the conductive materials; Selection of materials as conductors mainly consisting of other non-metallic substances organic substances
81.
SYSTEM AND METHOD FOR DYNAMIC DISPLAY OF AIRCRAFT EMISSIONS DATA
Systems and methods are provided for dynamically modeling and depicting overall emissions of the aviation industry and changes thereto when taking into account, for example, traffic growth and introduction of sustainability strategies, such as new and/or improved technologies, an increase in operational efficiency, and carbon offsets. Using the dynamic tool described herein, users can define scenarios on how to reduce emissions through the introduction of different sustainability strategies, both statically and over time, analyze the impact of those strategies on emissions, and understand the dependencies between select strategies.
A mask forming system for protecting a structure and a method of forming a mask for protecting the structure includes a masking material having a first layer, a second layer, and a third layer sandwiched together. The masking material is unrolled across a platform and a plurality of features are generated in the masking material, wherein the features include printing, kiss cutting, and double-kiss cutting the masking material. Data is printed on the first layer of the masking material. The first layer of the masking material is kiss cut. The second layer of the masking material is double-kiss cut. The third layer remains uncut and unprinted on during the formation of the mask. The masking material remains in the same orientation during printing and kiss cutting of the first layer, and the masking material remains in the same orientation during double-kiss cutting of the second layer.
B05B 12/24 - Masking elements, i.e. elements defining uncoated areas on an object to be coated made at least partly of flexible material, e.g. sheets of paper or fabric
B05D 1/32 - Processes for applying liquids or other fluent materials using means for protecting parts of a surface not to be coated, e.g. using stencils, resists
An example system for inspecting a surface includes a laser, an optical system, a gated camera, and a control system. The laser is configured to emit pulses of light, with respective wavelengths of the pulses of light varying over time. The optical system includes at least one optical element, and is configured to direct light emitted by the laser to points along a scan line one point at a time. The gated camera is configured to record a fluorescent response of the surface from light having each wavelength of a plurality of wavelengths at each point along the scan line. The control system is configured to control the gated camera such that an aperture of the gated camera is open during fluorescence of the surface but closed during exposure of the surface to light emitted by the laser.
A lightning strike protection (LSP) apparatus includes a first layer of fiber glass. The LSP apparatus also includes a second layer positioned on the first layer. The second layer includes carbon nanotubes (CNT). The LSP apparatus also includes a third layer positioned on the second layer. The third layer includes a surfacer. The LSP apparatus also includes a fourth layer positioned on the third layer. The fourth layer also includes the fiber glass. The LSP apparatus also includes a fifth layer positioned on the fourth layer. The fifth layer includes a primer. The LSP apparatus also includes a sixth layer positioned on the fifth layer. The sixth layer includes an outer surface material.
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 15/02 - Layered products essentially comprising metal in a form other than a sheet, e.g. wire, particles
B32B 15/14 - Layered products essentially comprising metal next to a fibrous or filamentary layer
B64C 1/12 - Construction or attachment of skin panels
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
Systems and methods include determining a collision probability between a first spacecraft and a second spacecraft; responsive to a determination that the collision probability exceeds a threshold, identifying a plane that is orthogonal to a relative velocity between the first spacecraft and the second spacecraft; determining a boundary on the plane that, when intersected by the first spacecraft, reduces the collision probability to a threshold level; selecting a first test point along the boundary and a second test point along the boundary; determining a first cost associated with maneuvering the first spacecraft towards the first test point and a second cost associated with maneuvering the first spacecraft towards the second test point, the first cost and the second cost based on one or more user-defined parameters; and maneuvering the first spacecraft toward a target point along the boundary that is determined based on the first cost and the second cost.
The application is directed to methods and devices for estimating corrosion of a material. One of the methods includes obtaining data regarding corrosion. The data is obtained from various sources, such as but not limited to sensors and observational data. The data is then trained to provide for a more complete data set. The trained data is then used to estimate the expected amount of corrosion for a given situation.
The present application relates to a system comprising a processor configured to execute a digital system model based on simulated conditions to generate simulated data. The processor may also be configured to train a surrogate model using at least the simulated data to approximate the digital system model of the system and generate, using the trained surrogate model, estimated values for conditions or parameters of the systems based on operational data, wherein the operational data includes sensor data or in-service data from the system. Further, the processor may be configured to execute the digital system model of the system to generate simulation data based on the operational data and the estimated values or parameters generated by the surrogate model and synchronize or update a digital twin of the system based on the simulation data, wherein the digital twin represents a state or condition of the system.
G06F 30/27 - Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
G06F 30/15 - Vehicle, aircraft or watercraft design
G06F 30/25 - Design optimisation, verification or simulation using particle-based methods
88.
ELECTROADHESIVE PADS, ELECTROADHESIVE END EFFECTORS, AND METHODS OF PRODUCING THE SAME
The electroadhesive pad comprises a substrate, a first electrical network, and a second electrical network. The first electrical network comprises a first subset of electrodes and a first voltage source configured to apply an output voltage at a first polarity to the first subset of electrodes. The second electrical network comprises a second subset of electrodes and a second voltage source configured to apply the output voltage to the second subset of electrodes at a second polarity. The first and second voltage sources are disposed along a central region of the electroadhesive pad. The first and second subsets of electrodes are supported by the substrate and extend between the central region and a perimeter of the electroadhesive pad. The methods include producing a custom electrostatic pad by mapping a shape of the custom electroadhesive pad onto a stock electroadhesive pad and cutting the stock electroadhesive pad into the shape.
Systems and methods are provided for facilitating pick and placement of preforms. One embodiment is a method for picking and placing a preform. The method includes placing an inner surface of a first caul plate into contact with a first side of a stringer preform, such that an outer surface of the first caul plate forms a first plane that is uniform along a length of the stringer preform, placing an inner surface of a second caul plate into contact with a second side of the stringer preform, such that an outer surface of the second caul plate forms a second plane that is parallel to the first plane along a length of the stringer preform, grasping the caul plates at the first plane and the second plane along the length of the stringer preform, and lifting the stringer preform together with the caul plates while maintaining the grasp.
A support box apparatus includes longitudinal members that span forward to aft and transverse members that span inboard to outboard between the longitudinal members. The longitudinal members and the transverse members are formed of composite honeycomb sandwich panels. The support box apparatus also includes attachment components configured to couple the longitudinal members or the transverse members to structural components of an aircraft, electrical wiring attached to the longitudinal members or the transverse members, environmental control system (ECS) ducting attached to the longitudinal members or the transverse members, and life support lines attached to the longitudinal members or the transverse members.
A modeling system is provided which retrieves from memory the 3D virtual model of an object; extract an outer surface of the 3D virtual model, the outer surface including a plurality of faces; identify feature curves in each of the plurality of faces of the outer surface; generate a parameterized surface from the identified feature curves; and output the feature curves and the parameterized surface. The system may generate a list of feature curve pairs that are adjacent to one another; obtain face pairs corresponding to the feature curve pairs; obtain and add a list of faces in the outer surface to a connectivity graph mapping points in 3D space to the feature curves; for each pair of connected faces, evaluate whether an angle difference between normals of the connected faces is greater than a threshold; and then extract a feature curve based on the pair of connected faces.
A system for removing a panel insert from a panel includes a main housing. A loading cap is coupled to the main housing. A tension knob is coupled to the main housing. The tension knob is configured to couple to a puller rod. A tension spring is within the main housing. The loading cap is configured to set the tension spring at an initial tension. The tension knob is configured to set the tension spring at a subsequent tension. A heater is configured to apply heat to the panel insert.
B23P 19/02 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for connecting objects by press fit or for detaching same
B23P 19/04 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
93.
SYSTEMS AND METHODS FOR SECURING A PANEL INSERT TO A PANEL
A system and a method for securing a panel insert to a panel include a main housing, a heater within the main housing, a coupling rod extending from the main housing, and a clamp assembly coupled to the coupling rod. The clamp assembly is configured to clamp the panel insert to the panel. The heater is configured to cure an adhesive applied to the panel insert to bond the panel insert to the panel.
A cutting tool that includes an elongated body with a first end and an opposing second end. A cutting edge is positioned at the first end. A heat pipe extends within an interior space of the body and has a first end in proximity to the cutting edge and a second end in proximity to the second end of the body. The interior space is enclosed within the body and comprises walls that extend around an interior space. The walls comprise a geometric configuration for a liquid within the heat pipe to move towards the first end of the heat pipe during rotation of the body.
B23B 51/06 - Drills with lubricating or cooling equipment
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
A hybrid engine including features to meet aircraft thrust, passenger airflow, and fuel cell requirements. The engine includes a combustor burning the same fuel as the fuel cell. The engine has electric motors to utilize the power output of the fuel cell. The engine shafts have sprags to allow motors to drive the compressors and over run the turbines. The engine has variable flowpath geometry to bypass the combustor.
Commonwealth Scientific and Industrial Research Organisation (Australia)
Inventor
Kohl, Thomas
Tsanaktsidis, John
Hornung, Christian
Kinlen, Patrick
Bruton, Eric
Flack, Matthew
Zweig, Andrew
Abstract
The present disclosure relates to a continuous flow process for preparing conducting polymers, for example polyaniline. The continuous flow process can provide a controlled synthesis of a conducting polymer from an emulsion comprising a polymerizable organic monomer and a free radical initiator in flow within a temperature controlled continuous flow reactor comprising at least one mixing element. The present disclosure also relates to the conducting polymers prepared by the continuous flow process.
A method includes obtaining, at a device, a first test matrix for a first aircraft system and a second test matrix for a second aircraft system. The method also includes, during a first operational test of the first test matrix, obtaining sensor data that includes first sensor data in a range specified by the first test matrix and second sensor data that is not specified by the first test matrix. The method includes evaluating, at the device, a second operational test of the second test matrix by processing the second sensor data using a second analytic model of the second aircraft system. The method also includes determining, based at least in part on a range of the second sensor data, a test coverage metric of the second test matrix. The method further includes providing an output to a display device, the output indicating the test coverage metric.
Methods of additively manufacturing a manufactured component and systems that perform the methods. The methods include determining an energy application parameter at an addition location on a previously formed portion of the manufactured component. The energy application parameter includes an intersection area relationship that describes an area of intersection between the previously formed portion and a surface of a virtual geometric shape, which is positioned at the addition location, as a function of a size parameter of the virtual geometric shape. The methods also include supplying a feedstock material to the addition location. The methods further include delivering an amount of energy sufficient to form a melt pool of the feedstock material at the addition location. The amount of energy is based, at least in part, on the energy application parameter. The methods also include consolidating the melt pool with a previously formed portion of the manufactured component.
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
patents
