A system configured to assist an operator that is inserting wires into terminal block cavities that are connected to electrical equipment. The system includes a computing device that accesses one or more data tables. The data tables identify the wires and the corresponding terminal block where the wires are to be connected. The computing device is configured to create a plug map based on the one or more data tables. The plug map is a digital visualization that replicates the configuration of terminal blocks. The plug map is configured to be displayed as a graphical user interface on a monitor. During use, the computing device highlights the cavity to enable the operator to connect the wire to the correct terminal block.
H01R 43/00 - Apparatus or processes specially adapted for manufacturing, assembling, maintaining, or repairing of line connectors or current collectors or for joining electric conductors
2.
METHODS AND SYSTEMS FOR GENERATING POWER AND THERMAL MANAGEMENT HAVING DUAL LOOP ARCHITECTURE
Methods and apparatus for power generation and/or thermal management on a high speed flight vehicle include circulating a power generation loop working fluid through a power generation loop, which absorbs heat associated with the flight vehicle. A generator operably coupled to the power generation loop generates electrical power. Additionally, a heat transport loop working fluid may circulate through a heat transport loop to provide thermal management through heat transfer.
F01K 7/32 - Steam engine plants characterised by the use of specific types of enginePlants or engines characterised by their use of special steam systems, cycles or processesControl means specially adapted for such systems, cycles or processesUse of withdrawn or exhaust steam for feed-water heating the engines using steam of critical or over-critical pressure
F01K 25/10 - Plants or engines characterised by use of special working fluids, not otherwise provided forPlants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
3.
OPERATIONAL SIMULATIONS OF PLANNED MAINTENANCE FOR VEHICLES
Implementations for operational simulations of planned maintenance effects for a plurality of vehicles are provided. One aspect provides a computing system comprising processing circuitry configured to provide a plurality of operational models that comprises a route model, a preparation model, and a planned maintenance model. The processing circuitry is further configured to, using the plurality of operational models, execute an operational simulation that generates interactions between a route simulation and a planned maintenance simulation for a plurality of routes in a route schedule, wherein executing the operational simulation comprises simulating performance of a scheduled maintenance task for a vehicle of the plurality of vehicles and determining an effect of the simulated performance of the scheduled maintenance task on the route simulation. The processing circuitry is further configured to output the effect of the simulated performance.
A tailorable composite material longitudinal radius filler made from harvested, recycled dry fiber material and a composite material assembly a longitudinal radius filler cavity filled with the tailorable composite material longitudinal radius filler and methods of manufacture are presently disclosed herein.
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 63/00 - Use of epoxy resins as moulding material
B29K 105/12 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of short lengths, e.g. chopped filaments, staple fibres or bristles
Methods and apparatus for determinant assembly manipulation are disclosed. A disclosed apparatus to manipulate a panel component for assembly thereof includes a cam rotatably coupled to a jig, the cam having a first interface portion, and a support frame to hold the panel component, the support frame having a second interface portion to contact the first interface portion in at least one rotational orientation of the cam.
A pressure diffuser to accommodate changes in pressure of a fluid within a fluid supply. The pressure diffuser includes a housing with an interior space and with an inlet and an outlet. A diverting member is positioned within the interior space. The diverting member is configured to divert the fluid within the interior space away from the outlet. An elastic membrane is positioned radially within the interior space between the housing and the diverting member. The elastic membrane is configured to receive the fluid from the diverting member and to expand and contract dependent on a pressure of the fluid.
Methods and an induction curing system for curing a composite panel. The induction curing system comprises; a rigid curing tool configured to hold a composite material; a vacuum bagging material sealed to the rigid curing tool; and a dimensional control structure having a lattice and an open casing formed of a rigid material, the lattice positioned within a concavity of the open casing, the dimensional control structure sealed to at least one of the vacuum bagging material or the rigid curing tool.
B29C 35/08 - Heating or curing, e.g. crosslinking or vulcanising by wave energy or particle radiation
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 controls taxiing of an aircraft. A first laser beam and a second laser beam are emitted from the aircraft using a wavelength configuration. A first backscatter light and a second backscatter light are received at the aircraft in response to emitting the first laser beam and the second laser beam. First backscatter data is generated using the first backscatter light. Second backscatter data is generated using the second backscatter light. A first signal to noise ratio is determined using the first backscatter data. A second signal to noise ratio is determined using the second backscatter data. The wavelength configuration is controlled for the first laser beam and the second laser beam emitted by the lidar system using the first signal to noise ratio and the second signal to noise ratio. A taxiing operation is performed for the aircraft using the first backscatter data and the second backscatter data.
A method and apparatus for distributing a number of utilities. The number of utilities may be coupled between a number of utility sources and a utility fixture. The number of utilities may be coupled between the utility fixture and a mobile system.
B25J 11/00 - Manipulators not otherwise provided for
B29C 39/02 - Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressureApparatus therefor for making articles of definite length, i.e. discrete articles
B29C 39/10 - Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressureApparatus therefor for making articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. casting around inserts or for coating articles
B29C 39/12 - Making multilayered or multicoloured articles
B29C 39/22 - Component parts, details or accessoriesAuxiliary operations
B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mouldApparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
B29C 65/70 - Joining of preformed partsApparatus therefor by moulding
B60G 3/14 - Resilient suspensions for a single wheel with a single pivoted arm the arm being essentially parallel to the longitudinal axis of the vehicle the arm being rigid
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS] or computer integrated manufacturing [CIM]
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G05D 3/12 - Control of position or direction using feedback
B23P 21/00 - Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
A manufacturing system including a manufacturing device that includes one or more integrated sensors. The manufacturing system further includes an edge computing device including an edge device processor configured to receive integrated sensor data measured during production of a manufactured part using the manufacturing device. The edge device processor transmits the integrated sensor data to a remote computing device. During the production of the manufactured part, the edge device processor receives a remote processing result from the remote computing device. The remote processing result includes a quality control result notification. The edge device processor, in response to receiving the quality control result notification, programmatically performs one or more auxiliary measurements of the manufactured part and/or manufacturing device to obtain auxiliary sensor data. The edge device processor outputs the quality control result notification and the auxiliary sensor data to a graphical user interface (GUI) displayed at the edge computing device.
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS] or computer integrated manufacturing [CIM]
13.
SYSTEM AND METHOD FOR IDENTIFICATION OF NAVIGATION SIGNAL INTERFERENCE
A system includes one or more processors configured to obtain navigation system quality information from multiple data sources. The one or more processors are further configured to generate navigation signal interference map information based on the navigation system quality information. For example, the one more processors may be configured to aggregate, based on one or more parameters, first data from a first data source of the multiple data sources, and identify one or more areas associated with low quality navigation signals based on second data from a second data source of the multiple data sources. A portion of the aggregated first data may be discarded based on the one or more areas to generate the navigation signal interference map information. The one or more processors may also be configured to output the navigation signal interference map information.
Systems, apparatuses, and methods provide for a tool to support components on a common hinge line axis. The tool includes a first pin and a second pin coupled in coaxial alignment with each other, defining the common hinge line axis. A first shouldered hinge pin is slidably disposed on the first pin and a second shouldered hinge pin is slidably disposed on the second pin. The first and second shouldered hinge pins allow translation along the common hinge line axis of the supported components when coupled to the first and second shouldered hinge pins. The first and second pins are disposed within a ball and socket joint, which enables pivotal adjustment of the common hinge line axis while maintaining the first and second pins co-axial to each other during adjustment of the common hinge line axis, to aid fit and assembly of the supported components to a mating structure.
Methods of peeling a protective film from the composite material are presented. A second protective film on a second face of the composite material sheet is held against a plurality of gripping points of an end effector. The composite material sheet is positioned at an angle relative to the manufacturing floor using the end effector. A first protective film on a first face of the composite material sheet is gripped by a film removal end effector. The first protective film is peeled away from the first face of the composite material sheet by movement of the film removal end effector.
A method includes obtaining first humidity data indicative of a first humidity value at an origin airport of a flight. The method also includes obtaining second humidity data indicative of a second humidity value at a destination airport. The method also includes determining, based on the first humidity data, a first fuel flow rate adjustment for a first phase of flight from a first altitude of the origin airport to a threshold altitude. The method also includes determining, based on the second humidity data, a second fuel flow rate adjustment for a second phase of flight from the threshold altitude to a second altitude of the destination airport. The method also includes estimating total fuel flow for the flight based on the first fuel flow rate adjustment and the second fuel flow rate adjustment.
A method includes comparing a first field of a first data record to a first field of a second data record to determine a first similarity metric based on a number of single character changes used to convert a value of the first field of the first data record to a value of the first field of the second data record and comparing a second field of the first data record to a second field of the second data record to determine a second similarity metric based on whether the second field of the first data record is identical to a value of the second field of the second data record. The method includes determining an aggregate similarity metric based on at least the first similarity metric and the second similarity metric and assigning the second data record to a calibration reliability group based on the aggregate similarity metric.
An elastomer component comprised of an elastomer material having an air volume fraction (AVF) of greater than 5%, and the elastomer component is a three-dimensional solid. An assembly comprises an outer barrier, at least one elastomer component, and a curable material. A method comprises inserting an elastomer component and a curable material into an outer barrier to form an assembly and heating the assembly.
A fluid reservoir comprises a reservoir body and a passage. The reservoir body is configured to be arranged within an aerodynamic component. The passage is configured to operatively couple the reservoir body to an exterior surface of the aerodynamic component. The passage is further configured to flow fluid from the reservoir body to the exterior surface when a pressure differential exceeds a threshold pressure differential. The threshold pressure differential is a difference between a pressure at a terminal end of the passage and a pressure of an interior of the reservoir body. An apparatus comprises an aerodynamic component and a reservoir. The passage is configured to flow fluid from the reservoir body to the exterior surface when a pressure differential exceeds a threshold pressure differential. A method comprises flowing fluid from a reservoir to an exterior surface of an aerodynamic component at a threshold pressure differential.
A ceramic matrix composite part and methods of locating a composite ply on a layup tool are presented. A composite ply comprising a fiducial is placed onto the layup tool. A position of the fiducial of the composite ply is determined relative to the layup tool. An actual position of the composite ply on the layup tool is determined. A difference between the actual position of the composite ply and a designed position for the composite ply is determined.
Rapidly generated tooling and methods for rapidly generating tooling for composite layup and cure are presented. A foam block is formed into a tool body with a forming surface having a near net shape. A low CTE material is additively deposited onto the forming surface to form a metal cover
A forming area for automated composite processing and methods of maintaining workability of a ceramic matrix composite material in a forming area are presented. It is determined if a humidity within the forming area is in a desired range. In response to a determination that the humidity is not in the desired range, at least one of a heater or a humidifier is activated by an environmental controller to maintain a desired humidity for forming the ceramic matrix composite material within the forming area.
A method includes determining, based on historical data associated with a reliability group, a model fit metric for each reliability model of a plurality of reliability models. The method also includes selecting a particular reliability model based on the model fit metrics. The method also includes estimating calibration interval parameters for the reliability group based on the particular reliability model. The method also includes generating a calibration interval recommendation for the reliability group based on the calibration interval parameters and a reliability target associated with the reliability group.
A method is presented for determining a likelihood of an ignition hazard. The method comprises receiving a current waveform for a lightning strike event at a conductive member that forms an interface with a decomposable member. Material parameter inputs for the conductive member and the decomposable member are received. Based at least on one or more of the received material parameter inputs and an energy from the current waveform, a heating of the decomposable member is resolved, and a quantity of volatiles within the interface volume are determined. A total pressure generation within the interface volume is determined. A probability of ignition hazard by the lightning strike event is output based on a comparison of the total pressure generation and a containment pressure threshold for the interface volume.
There is provided an airflow system for a building. The airflow system includes at least one air purification system providing purified air and receiving recirculated air; at least one air supply assembly supplying the purified air from the air purification system to at least one interior airflow space including one or more of, an office cubicle, a conference room, and an auditorium; at least one air return assembly returning the recirculated air from the at least one interior airflow space to the at least one air purification system; directional airstream(s) formed between the air supply assembly and the air return assembly, including first directional airstream(s) forming one or more air barriers between occupants, to provide respiratory isolation, and second directional airstream(s) forming an airflow field around each occupant; and at least one control system controlling the airflow system. The airflow system provides a contamination mitigation for each occupant.
A system for removing a cap seal from a fastener, includes a seal remover including fingers outwardly extending from a base. The fingers include one or more first fingers and one or more second fingers. The one or more first fingers are sized, shaped, or configured differently than the one or more second fingers. Passages are defined between the fingers. The seal remover is configured to be coupled to a distal end of an operative portion of a tool. The tool is configured to be operated to rotate the seal remover in relation to the cap seal so that the fingers remove the cap seal from the fastener. Removed portions of the cap seal are discharged through and out of the passages.
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 deformationTools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
F16B 41/00 - Measures against loss of bolts, nuts, or pinsMeasures against unauthorised operation of bolts, nuts, or pins
28.
DETERMINATION OF ONE OR MORE MAXIMAL CLIQUES IN AN UPDATED CONNECTIVITY GRAPH
A computing device may determine, based on first information identifying one or more maximal cliques in a first connectivity graph, a set of potential cliques in a second connectivity graph that is an updated version of the first connectivity graph. The computing device may determine a set of valid cliques, of the set of potential cliques, in the second connectivity graph and may determine, based on the set of valid cliques, a first set of maximal cliques in the second connectivity graph. The computing device may determine, based on a set of nodes of the second connectivity graph that are not included in the first set of maximal cliques, a second set of maximal cliques in the second connectivity graph. The computing device may determine second information identifying the first set of maximal cliques and the second set of maximal cliques.
H04L 41/12 - Discovery or management of network topologies
H04L 41/082 - Configuration setting characterised by the conditions triggering a change of settings the condition being updates or upgrades of network functionality
A bushing configured to receive a connector to connect engine components within an aircraft to absorb forces during a fan blade out. The bushing includes an outer ring, an inner ring that is positioned within and spaced inward from the outer ring with the inner ring having a central opening sized to receive the connector, and spokes that extend between and connect together the outer ring and the inner ring. One or more of the spokes have a linear shape and one or more of the spokes have a non-linear shape.
A support system is configured to couple a leading edge of a wing to a main body of the wing. The support system includes an extender configured to secure to the leading edge and the main body. The extender is configured to extend and retract. The support system is in a retracted position when the extender is retracted. The support system is in a forward extended position when the extender is extended. The leading edge abuts the main body when the support system is in the retracted position. The leading edge is spaced apart from the main body when the support system is in the forward extended position.
A device includes a housing. a first interface on a first side of the housing, a second interface on a second side of the housing opposite the first side, and circuitry within the housing. The first interface is configured to couple to a multimode receiver (MMR) rack. The second interface is configured to couple to a MMR external to the housing. The circuitry is configured to receive, via the first interface, digital data representing navigation signals received at an antenna. The circuitry is configured to perform time, space and frequency filtering operations using the digital data to generate modified digital data. The circuitry is configured to output modified analog navigation signals, based on the modified digital data, to the MMR via the second interface.
Hybrid propulsion systems that utilize liquid natural gas solid oxide fuel cells in a manner practical for use in aircraft that avoid the use of heavy batteries, provide transient response times suitable for use in aircraft, and/or simplify reactant pre-conditioning systems using a compressor and turbine pair operatively coupled to the solid oxide fuel cell. Such hybrid propulsion systems for an aircraft may include a liquid natural gas turboshaft engine, a turbo generator operatively coupled to the turboshaft engine, a liquid natural gas solid oxide fuel cell, and an electric fan. The electric fan may be configured to generate thrust for the aircraft and may be powered by the turbo generator and/or the solid oxide fuel cell. Fuel cell reactants may be pre-conditioned using turboshaft bleed air, and the liquid natural gas may be pre-heated by fuel exhaust from the solid oxide fuel cell.
A panel comprises a panel interior surface, a foam layer, and a composite layer. A first end of the panel is oriented at a first end angle relative to a foam layer interior surface, wherein the first end angle is not 90 degrees. A foam layer interior surface is operatively arranged at the panel interior surface. The composite layer comprises a composite layer interior surface operatively engaged with the foam layer exterior surface. An aircraft assembly comprises a fuselage and at least a first panel and a second panel. A first end angle of a first panel first end corresponds to a second end angle of a second panel second end, and the first panel first end operatively engages the second panel second end. A method comprising operatively engaging a first panel interior surface of a first panel with a fuselage exterior surface of a fuselage.
A microforge system for additive metallic manufacturing includes a forge barrel with a forge head configured to move in opposite directions within the forge barrel. A metal supply device supplies metal powder into the forge barrel, and one or more inductive heaters inductively heat the metal powder within the forge barrel. The forge head oscillates within the forge barrel while the metal powder is heated and sintered onto a substrate to form a solid metal additive layer. The system may include an inert gas supply device to load inert gas into the forge barrel, allowing the metal powder to be heated and forged without a vacuum chamber. The forge head compacts the metal powder to produce a solid metal additive layer with a wrought microstructure. A translation system moves the forge barrel and inductive heaters transversely relative to the forge head's oscillation.
A panel assembly includes a plurality of panels. Each one of the panels includes a first face sheet, a second face sheet, a truss structure connecting the first face sheet and the second face sheet, and a perimeter edge. The panel assembly also includes a primary splice connector that is connected to the first face sheet and the second face sheet along at least a portion of the perimeter edge of directly adjacent ones of the panels. The primary splice connector includes a heat exchanger.
F28D 15/02 - 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
B33Y 80/00 - Products made by additive manufacturing
A fiber laser machine tool includes a mounting plate, a fiber laser probe and a rotary actuator. The mounting plate for mounting the tool to a manufacturing system for vertical and horizontal movement in relation to a honeycomb core structure. The fiber laser probe includes an inner core with a fiber optic conductor. The inner core is installed on the mounting plate to prevent rotation of the center. The probe also includes a rotational outer sheath with a mirror for reflecting laser energy from the fiber optic conductor toward walls of cells in the honeycomb core structure to perforate the walls. The rotary actuator is installed on the mounting plate and includes a shaft linked to the rotational outer sheath to enable rotation of the mirror. Various manufacturing systems and methods for modifying walls of cells in honeycomb core structures are also disclosed.
There is provided a portable conduction welding apparatus for conduction welding of thermoplastic composite parts. The apparatus has a heating system with a first heater assembly and a second heater assembly each having a machined insulation block, a machined heater block, heater element(s), and a thermocouple. The apparatus has a force application and monitoring system with a clamp assembly and a load cell. The apparatus has an indexing assembly to index the first heater assembly and the second heater assembly to the clamp assembly. The apparatus has one or more controllers having one or more power supplies. The apparatus is portable and is configured to weld together at a weldline, a first thermoplastic composite part aligned to the first heater assembly and a second thermoplastic composite part aligned to the second heater assembly, by applying force and conducting heat at the weldline during a thermal welding cycle.
B29C 65/34 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
B29C 65/00 - Joining of preformed partsApparatus therefor
B29C 65/78 - Means for handling the parts to be joined, e.g. for making containers or hollow articles
Door latching systems, apparatus, articles of manufacture, and methods are disclosed. An example door latch includes a worm gear including a worm wheel and a worm screw, the worm wheel rotatable upon rotation of the worm screw; a lever operatively coupled to the worm wheel, the lever to rotate based on rotation of the worm wheel; a cam surface, the lever to contact the cam surface between a first rotational position and a second rotational position, the second rotational position different from the first rotational position; and a pin to enable rotation of the worm gear.
There is provided an airflow system for a building. The airflow system includes at least one air purification system providing purified air and receiving recirculated air; at least one air supply assembly supplying the purified air from the air purification system to at least one interior airflow space including one or more of, an aisleway, a cafeteria, a restroom, and an elevator; at least one air return assembly returning the recirculated air from the at least one interior airflow space to the at least one air purification system; directional airstream(s) formed between the air supply assembly and the air return assembly, and comprising at least one or more of, a directed airflow field around each occupant, air barrier(s) between each occupant, and an airflow field around each occupant; and at least one control system controlling the airflow system. The airflow system provides a contamination mitigation for each occupant.
A dimmable window system includes a reveal retaining a window, a dimmable member, and an energy harvester configured to harvest energy to provide power to the dimmable member and other components of the dimmable window system. The dimmable window system can be configured for a vehicle, such as an aircraft.
Heat exchangers with integrally formed flow turbulators are disclosed. An example heat exchanger includes a plurality of fluid passages forming a fluid flow path through the heat exchanger and a plurality of flow turbulators within the fluid passages, the flow turbulators within the fluid flow path and being integrally formed with a body of the heat exchanger.
F28F 1/40 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only inside the tubular element
42.
SYSTEMS AND METHODS FOR DETERMINING BORE CHARACTERISTICS OF A HOLE
A system for determining bore characteristics of a hole includes a measuring tool and a controller. The measuring tool is configured to measure a hole and generate data representing the hole. The controller is in communication with the measuring tool and is configured to determine at least one of the bore characteristics based on the data from the measuring tool.
G01B 11/00 - Measuring arrangements characterised by the use of optical techniques
G01B 11/03 - Measuring arrangements characterised by the use of optical techniques for measuring length, width, or thickness by measuring coordinates of points
G01B 11/12 - Measuring arrangements characterised by the use of optical techniques for measuring diameters internal diameters
G01B 11/22 - Measuring arrangements characterised by the use of optical techniques for measuring depth
G01B 11/26 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes
G01B 11/30 - Measuring arrangements characterised by the use of optical techniques for measuring roughness or irregularity of surfaces
G01D 5/00 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable
G01D 5/26 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using optical means, i.e. using infrared, visible or ultraviolet light
G01D 5/28 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using optical means, i.e. using infrared, visible or ultraviolet light with deflection of beams of light, e.g. for direct optical indication
G01N 21/954 - Inspecting the inner surface of hollow bodies, e.g. bores
A computing system is provided, including one or more processing devices configured to receive a manufacturing change specification of a proposed change to a manufacturing system. At a first trained machine learning model, the one or more processing devices are further configured to compute one or more predicted change categories of the proposed change. At a second trained machine learning model, the one or more processing devices are further configured to compute a change magnitude classification associated with the proposed change. The second trained machine learning model is configured to compute the change magnitude classification based at least in part on the one or more predicted change categories. The one or more processing devices are further configured to output the one or more predicted change categories and the change magnitude classification to a user interface.
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
METHODS FOR MANUFACTURING NON-CRIMP FABRIC AND COMPOSITE STRUCTURES COMPRISING NON-CRIMP FABRIC WITH BINDER, AND PREFORM COMPRISING NON-CRIMP FABRIC WITH BINDER
A method for manufacturing a non-crimp fabric includes providing a plurality of layers of continuous fibers held together by stitch threads and applying a binder between adjacent layers of the plurality of layers of continuous fibers and on an outer layer of the plurality of layers of continuous fibers, wherein the binder has an activation temperature below a melting temperature of the stitch threads.
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 5/06 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer needled to another layer, e.g. of fibres, of paper
B32B 5/22 - 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
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
A device includes one or more processors configured to generate an operational congestion metric associated with a particular airport, wherein the operational congestion metric is based at least on one or more usage metrics for the particular airport. The one or more processors are configured to generate an impact congestion metric non-linearly based at least on the operational congestion metric. The one or more processors are configured to determine based on the impact congestion metric, a congestion prediction for the particular airport. The one or more processors are configured to communicate a congestion alert for the particular airport, wherein the congestion alert is based at least on the congestion prediction
A method of forming a dry fiber stack, a carrier encapsulated composite, and a flexible consolidation and forming carrier are presented. The flexible consolidation and forming carrier comprises an integrated heating element arranged in a material support region, a flexible base material encompassing the integrated heating element, and a seal portion around a perimeter of the flexible consolidation and forming carrier.
B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
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
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
A computing system is provided, including one or more processing devices configured to receive a manufacturing change specification of a proposed change to a manufacturing system. At a first trained machine learning model, the one or more processing devices are further configured to compute one or more predicted change categories of the proposed change. At a second trained machine learning model, the one or more processing devices are further configured to compute a change magnitude classification associated with the proposed change. The second trained machine learning model is configured to compute the change magnitude classification based at least in part on the one or more predicted change categories. The one or more processing devices are further configured to output the one or more predicted change categories and the change magnitude classification to a user interface.
A system and a method included a control unit configured to receive wind characteristics for locations at and between a current location of an aircraft and an arrival location, and revise a flight plan at one or more of the locations based on the wind characteristics to provide a revised flight plan. The aircraft is configured to be operated to fly from the current location to the arrival location according to the revised flight plan.
Apparatus and methods for installation of optical solar reflectors are disclosed. An example method includes coupling a first side of a pressure sensitive adhesive (PSA) substrate to a polyester film; coupling a first side of an optical solar reflector to a second side of the PSA substrate; applying an adhesive material to a surface of a vehicle; coupling a second side of the optical solar reflector to the adhesive material; and after curing of the adhesive material, separating the first side of the optical solar reflector from the second side of the PSA substrate, the second side of the optical solar reflector remaining coupled to the surface of the vehicle via the cured adhesive material.
Examples are disclosed that relate to a weight detection and management system for an aircraft. In one example, the system includes a plurality of weight sensors, a communication network connected to the plurality of weight sensors, and a computing system. The plurality of weight sensors is distributed throughout the aircraft. Each weight sensor of the plurality of weight sensors is configured to output weight data that indicates a weight of a load detected by the weight sensor. The computing system includes a logic subsystem and a storage subsystem holding instructions executable by the logic subsystem to receive, via the communication network, the weight data output by the plurality of weight sensors, calculate a center of gravity of the aircraft based at least on the weight data output by the plurality of weight sensors, and output the center of gravity of the aircraft.
G01M 1/12 - Static balancingDetermining position of centre of gravity
G01G 19/07 - Weighing apparatus or methods adapted for special purposes not provided for in groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
Methods of resin transfer infusion and maintaining a clean resin infusion tool, a seal, and a resin infusion tool are presented. A resin infusion tool comprises a first mold; a second mold configured to form a resin infusion chamber with the first mold, wherein the second mold comprises at least one channel around a perimeter of the second mold; and at least one seal seated within the at least one channel of the second mold, the at least one seal is seated so as to maintain a vacuum seal between the first mold and the second mold in both a infusion position and a closed position of the resin infusion tool, wherein the seal is in contact with the first mold in the infusion position, and wherein the seal is compressed in the closed position.
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 33/00 - Moulds or coresDetails thereof or accessories therefor
52.
SYSTEMS AND METHODS FOR AUTONOMOUS VEHICLE PATH PLANNING
Systems and methods for autonomous vehicle path planning are described herein. An example vehicle includes an image sensor to obtain an image of a scene of an area surrounding the vehicle. The vehicle also includes navigation system circuitry to: analyze the image and generate a semantically segmented image that identifies one or more types of features in the image; project the semantically segmented image to a two-dimensional (2D) map projection; convert the 2D map projection into a cost map; and determine a path for the vehicle based on the cost map.
Resilient elongated tubular seals that are flexible and that can absorb compressive forces and compress to seal gaps between adjacently positioned aircraft cabin structures and that can further expand outwardly from a compressed condition as compressive forces change or abate and methods of installation of such elongated tubular seals are disclosed.
The Board of Trustees of the University of Illinois (USA)
Inventor
Kim, Jae H.
Eckhardt, Josh D.
Caesar, Matthew C.
Abstract
The present disclosure provides a method of wireless communications in the presence of one or more neighboring signals on a wireless channel. The method includes receiving a first wireless signal by a receiver of an operator, the first wireless signal being influenced by a second wireless signal and a jamming signal that are transmitted on the wireless channel by the operator. The method further includes receiving, at the receiver, a key indicating one or more transmission properties of the jamming signal; generating an estimate of the jamming signal based on the one or more transmission properties; and reconstituting the second wireless signal, which comprises subtracting the estimate from the first wireless signal.
A thermoplastic part with a thermoplastic repair patch and methods of repairing a thermoplastic part are presented. The thermoplastic part with a thermoplastic repair patch comprises a composite material with a cut-out forming a repair area, and the thermoplastic repair patch in the cut-out. The composite material has a first melting temperature. The thermoplastic repair patch comprises a plurality of consolidated thermoplastic stacks, each consolidated thermoplastic stack comprising thermoplastic composite plies between low melt thermoplastic surfaces having a second melting temperature lower than the first melting temperature.
B29C 73/10 - 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 using patches sealing on the surface of the article
A method includes, during an initial approach for an approach to landing phase, determining, based on a target path and aircraft data, a state for each monitored condition of a first set of monitored conditions and a region of the monitored condition that includes the state. The method includes, during a final approach for the approach to landing phase, determining, based on the target path and the aircraft data, a state for each monitored condition of a second set of monitored conditions and a region of the monitored condition that includes the state. The method includes accessing notification content for a region of a particular monitored condition, where the state for the particular monitored condition is outside of a target region for the particular monitored condition. The method also includes sending notification signals based on the notification content from a computing system to one or more output systems.
An extended diol composition is disclosed, which includes a first component that includes α-ω hydroxyl terminated diol oligomer having a number average molecular weight Mn of from about 500 Da to about 100,000 Da, a multifunctional isocyanate species, and a multifunctional alcohol or amine species. Another extended diol composition is disclosed, which includes a first component that includes an α-ω hydroxyl terminated diol oligomer having a number average molecular weight Mn of from about 500 Da to about 100,000 Da, a multifunctional isocyanate species, and a multifunctional species including an alcohol-functional group and an epoxy-functional group.
C08G 18/64 - Macromolecular compounds not provided for by groups
C08G 18/09 - Processes comprising oligomerisation of isocyanates or isothiocyanates involving reaction of a part of the isocyanate or isothiocyanate groups with each other in the reaction mixture
C08G 18/10 - Prepolymer processes involving reaction of isocyanates or isothiocyanates with compounds having active hydrogen in a first reaction step
C08G 18/24 - Catalysts containing metal compounds of tin
59.
WATER LEAK DETECTION SYSTEMS AND METHODS FOR AN INTERNAL CABIN OF AN AIRCRAFT
A vehicle includes one or more areas, one or more water-drawing components within the one or more areas, a water supply system configured to provide water to the one or more water-drawing components, and a water leak detection system including one or more sensing devices, one or more shut-off valves, and a control unit 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 a supply of water to the one or more water-drawing components in response to the one or more sensing devices detecting (a) a water leak within the one or more areas when the one or more water-drawing components are not in use, or (b) the water leak within the one or more areas when the water-drawing components are 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
60.
MONITORING OF CHROMIUM (VI)-FREE ANODIZED SEALING PROCESSES AND METHODS THEREOF
A method for monitoring and optimizing a sealing process in situ includes sealing a surface of an anodized substrate, providing a test anodized substrate corresponding to the anodized substrate into the same sealing process as the anodized substrate, measuring an electrochemical surface potential of a test anodized substrate that represents the surface of an anodized part, collecting electrochemical surface potential measurement data, analyzing the electrochemical surface potential measurement data, and identifying one or more performance indicators related to seal quality and processing parameters. The method may include optimizing the sealing process using information obtained from analyzing the electrochemical surface potential measurement data, measuring the electrochemical surface potential using a potentiostat and a reference electrode, and measuring an electrochemical surface potential of a test anodized substrate that represents the surface of an anodized part.
METHODS FOR MONITORING FABRICATION OF WORKPIECES, ANALYTICAL COMPUTING DEVICES AND METHODS FOR TRAINING NEURAL NETWORKS TO ANALYZE ROBOT-ASSISTED DRILLING OPERATIONS
Methods for monitoring fabrication of a workpiece includes receiving a thrust force signal from a robotic manipulator during a robot-assisted drilling operation on the workpiece, filtering noise data points and filtering outlier data points from the thrust force signal to form a filtered thrust force signal, extracting a thrust feature from the filtered thrust force signal, processing the thrust feature using a neural network trained to analyze the robot-assisted drilling operation and predicting a stiffness value for the workpiece based on a regression analysis of the thrust feature by the neural network during the processing of the one or more thrust feature. Analytical computing devices associated with the methods includes a network interface, a processor, an application program storage device, a neural network and a data storage device. Methods for training the neural network to analyze the robot-assisted drilling operation are also disclosed.
G16C 60/00 - Computational materials science, i.e. ICT specially adapted for investigating the physical or chemical properties of materials or phenomena associated with their design, synthesis, processing, characterisation or utilisation
B23B 49/00 - Measuring or gauging equipment on boring machines for positioning or guiding the drillDevices for indicating failure of drills during boringCentring devices for holes to be bored
A diagnostic device includes a probe, a motor configured to scan the probe over a test circuit, a superconducting quantum interference device (SQUID) attached to the probe and configured to be coupled to the test circuit such that an electronic noise present in the test circuit induces a first current that flows through the SQUID, and a current path configured to receive a second current that flows through the SQUID. The SQUID is configured to generate an output in a form of a first voltage in response to a sum of the first current and the second current being less than a threshold current, and a second voltage in response to the sum of the first current and the second current being greater than the threshold current.
A system for testing control surface actuators of an aerial refueling boom includes a rudder test apparatus and an elevator test apparatus. The rudder test apparatus is configured to be coupled to at least one of a first rudder and second rudder. The elevator test apparatus is configured to be coupled to at least one of a first elevator and second elevator. With the rudder test apparatus coupled to at least one of the first rudder and second rudder, a constant rudder test force applied to the rudder test apparatus drives actuation of one of the first rudder or second rudder against a rudder actuator. With the elevator test apparatus coupled to at least one of the first elevator and second elevator, a constant elevator test force applied to the elevator test apparatus drives actuation of the first elevator and second elevator against an elevator actuator.
An electrical power system includes a battery system that includes multiple battery modules, and an electrical distribution network. The battery system further includes, for each battery module of the battery system, a respective module interface device having a switching circuit that is operable to connect and disconnect that battery module with respect to the electrical distribution network independent of other battery modules of the battery system. The electrical power system further includes a control system operatively coupled to each module interface device. The control system is configured to command the module interface devices of a first subset of battery modules to connect the first subset of battery modules to the electrical distribution network, and to command the module interface devices of a second subset of battery modules to disconnect the battery modules of the second subset from electrical distribution network.
One example provides a method for operating a verdict retriever module configured to programmatically interface with a product lifecycle management (PLM) system. The method comprises receiving a change data request for a part reference object in the PLM system. The method further comprises sending a verdict request based at least upon the change data request to the PLM system and in response, receiving a verdict response. The method also comprises sending a request to publish data to a control gate module and in response, receiving a pointer to a storage location in a data warehouse. The method additionally comprises transferring the pointer to the PLM system to record the pointer in relation to the part reference object, and sending at least the verdict response to a source of the change data request.
H04L 9/32 - Arrangements for secret or secure communicationsNetwork security protocols including means for verifying the identity or authority of a user of the system
66.
COMPOSITE FUSELAGE FRAMES AND METHODS OF FABRICATING FRAME FILLERS AND COMPOSITE FUSELAGE FRAMES FOR AIRCRAFT
A composite fuselage frame for an aircraft includes a web and a shear tie foot. The web includes a width and a first thickness. The web forms an arc between first and second ends in relation to the fuselage. The width extends from the outer side in relation to a skin on the fuselage to an inner side. The shear tie foot is disposed on the outer side of the web between first and second mouse holes and projects from the first thickness of the web. The shear tie foot has a second thickness that extends along the skin between first and second stringers. The second thickness of the shear tie foot is defined by the first thickness and second polymer matrix composite layers formed by first material polymer matrix composite plies that provide a frame filler integrated with second material polymer matrix composite plies of the first thickness.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
A method for software function scheduling includes, at a computing system, executing a scheduling service to coordinate function execution for a plurality of software functions of the computing system. The scheduling service receives registration information for a software function of the plurality of software functions, the registration information including a periodic execution rate for the software function. The software function is assigned to a rate group that includes one or more other software functions each having the periodic execution rate, wherein each software function in the rate group is executed in a group-specific processing thread. The software function is executed at the periodic execution rate using the group-specific processing thread.
A plurality of fiber tows are laid down by an automated lamination machine (e.g., an automated fiber placement (AFP) machine or a contoured tape laying machine (CTLM)), each fiber tow having a cut end. At least one marking is automatically applied within at least one marked region of each respective fiber tow. Each marking is configured to provide location information about the respective fiber tow on which the respective marking is placed. The markings are applied using a contrasting color on each respective fiber tow, with the contrasting color being chosen to contrast with a color of the fiber tows such that the markings are configured to enable visual inspection of the plurality of fiber tows. The markings may be designed for human visual inspection, or automated inspection by a machine, and individual fiber tows or plies of fiber tows may be inspected as the tows are being laid down.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
69.
LASER-BASED SYSTEM FOR MEASURING FLUID DATA OF A VEHICLE
Examples are disclosed relating to a laser-based system for measuring fluid data of a vehicle. In one example, the system includes a laser, a sensor system, and a computing system. The computing system is configured to send control signals to the laser causing the laser to emit laser light into a medium outside of the vehicle to induce a one or more plasma sparks in the medium. The computing system is further configured to receive, from the sensor system, sensor data indicating one or more properties of the one or more plasma sparks, including an orientation of the one or more plasma sparks relative to the vehicle. The computing system is further configured to calculate the fluid data of the vehicle based at least on the sensor data including the orientation of the one or more plasma sparks relative to the vehicle and output the fluid data of the vehicle.
G01N 21/71 - Systems in which the material investigated is excited whereby it emits light or causes a change in wavelength of the incident light thermally excited
B64D 43/00 - Arrangements or adaptations of instruments
G01N 21/85 - Investigating moving fluids or granular solids
70.
Locking system for a thrust reverser of an aircraft
A locking system to secure a trans cowl to a frame of a thrust reverser on an engine of an aircraft. The locking system includes an arm that is connected to the trans cowl with the arm having a receptacle. A lock includes a body and a pin with the pin movable relative to the body and with the lock positionable between a locked position and an unlocked position. In the locked position, the pin is in an extended position relative to the body that extends into the receptacle to secure the trans cowl in a stowed position. In the unlocked position, the pin is in a retracted position relative to the body that is away from the arm to enable the trans cowl to move to a deployed position.
Disclosed herein is an acoustic array and associated system and method for acoustic source localization. The acoustic array includes a plurality of microphones, each positioned along at least one of a first axis, a second axis angled relative to the first axis, or a third axis, angled relative to the first axis and the second axis. The acoustic array further includes a support assembly having a central mount and a plurality of support arms that extend outward from the central mount. Each one of the plurality of microphones are coupled to either the central mount or one of the plurality of support arms, enabling precise localization of acoustic sources within an acoustic-testing space.
A quantitative flight test data gathering system is configured to, during flight test operation of an aircraft, obtain, from one or more flight data sensors, from a flight control system, or both, one or more feedback signals indicative of a state of the aircraft. The quantitative flight test data gathering system is configured to generate, based at least in part on the feedback signals, one or more signals associated with a flight test maneuver. The quantitative flight test data gathering system is configured to provide the one or more signals as input to the flight control system to cause one or more control laws of the flight control system to generate control signals to cause the aircraft to operate according to the flight test maneuver.
A system for determining pilot cognitive states, includes one or more processors coupled to a memory configured to receive physiological data and aircraft state data, determine mental workload and mental fatigue of a pilot based on the physiological data, determine available attention resources of the pilot based on the mental workload and mental fatigue, determine attention allocation of the pilot based on the available attention resources and gaze patterns derived from the physiological data, determine situational awareness of the pilot based on the attention allocation and the aircraft state data, and generate a visualization of the available attentional resources of the pilot, the attention allocation of the pilot, the situational awareness of the pilot, and aircraft state data.
Examples of the present disclosure provide a systema and a method for testing an aircraft within a wind tunnel. The method includes integrally forming roughness components with a substrate to provide an artificial ice layer.
B33Y 50/00 - Data acquisition or data processing for additive manufacturing
B33Y 80/00 - Products made by additive manufacturing
75.
REMNANT EXTRACTION TOOLS, ROBOTIC MANUFACTURING SYSTEMS AND METHODS FOR EXTRACTING REMNANTS DURING DRILLING OPERATIONS AT ROBOTIC MANUFACTURING SYSTEMS
A remnant extraction tool includes a nosepiece assembly and a vacuum assembly. The nosepiece assembly engages with a robotic manipulator to adjustably align with an exit side of a workpiece during a drilling operation through the workpiece at a predetermined location. The drilling operation includes drilling performed by another robotic manipulator from a drilling side of the workpiece. The vacuum assembly is in fluidic communication with the nosepiece assembly and engages with the robotic manipulator to selectively apply a vacuum to the exit side of the workpiece via the nosepiece assembly and to collect remnants from the drilling operation. A robotic manufacturing system includes a machine drill tool and the remnant extraction tool. The machine drill tool engages with a first robotic manipulator. The remnant extraction tool engages with a second robotic manipulator. Methods for extracting remnants during drilling operations at robotic manufacturing systems are also disclosed.
B23Q 11/00 - Accessories fitted to machine tools for keeping tools or parts of the machine in good working condition or for cooling workSafety devices specially combined with or arranged in, or specially adapted for use in connection with, machine tools
B25J 11/00 - Manipulators not otherwise provided for
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
76.
METHODS AND APPARATUS FOR MOISTURE CHARACTERIZATION
Methods and apparatus for moisture characterization are disclosed. A disclosed apparatus to determine a characteristic of moisture corresponding to a vehicle includes a moisture sensor including first and second insulative layers, first and second electrodes between the first and second insulative layers, and a liquid transport material, wherein at least a portion of the liquid transport material is positioned between the first and second electrodes, and a resonance circuit electrically coupled to the first and second electrodes, the resonance circuit to measure a capacitance of the moisture sensor.
G01N 27/22 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating impedance by investigating capacitance
77.
SYMMETRIC CASCADE THRUST REVERSERS AND RELATED METHODS
Symmetric cascade thrust reversers and related methods are disclosed. An example apparatus includes a plurality of first cascades spaced circumferentially along a first portion of an aircraft engine with respect to a first plane and a second plane passing through a longitudinal axis of the aircraft engine extending in a fore-aft direction. The first plane is orthogonal relative to the second plane. The first cascades are positioned between a first side of the first plane and a first side of the second plane. Respective ones of the first cascades provide corresponding respective ones of first exhaust vectors. At least a first one of the first exhaust vectors is oriented toward the second plane and at least a second one of the first exhaust vectors is oriented in a direction away from the second plane.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
78.
Method of Increasing the Efficiency of a Vehicle by Utilizing Available Space in a Cargo Hold
Methods and system of transporting cargo in a vehicle. A method includes after first cargo has been loaded into a cargo hold of a vehicle at a first location, determining available space within the cargo hold of the vehicle with the available space being unoccupied by the first cargo. After the vehicle leaves the first location, determining second cargo that is sized to fit in the available space. Loading the second cargo into the available space of the vehicle at a second location. The method also includes transporting the first cargo and the second cargo to a third location.
A drill clamp tool that includes a body sized and configured to extend along a first side and a second side of a workpiece. The tool includes a sleeve at a first section of the body for positioning at the first side. The tool also includes a clamping member on a second section of the body for positioning at the second side. An opening extends through the sleeve and a corresponding opening extends into the face of the clamping member. When the tool is connected to the workpiece, the openings are colinearly aligned on opposing sides of the workpiece. During the drilling process, a user inserts a drill bit into the opening in the sleeve and then drills a hole in the workpiece. At least a tip of the drill bit moves through the workpiece and is inserted into the opening in the contact pad.
A computer-implemented method for distributed mission planning and media management for aircraft. The method includes providing a web-based architecture that allows multiple remote users to interact with a networked media station through a web interface. The networked media station contains multiple memory bays holding removable memories configured for insertion into different control systems of the aircraft. The method involves receiving user inputs via the web interface to create and manage pre-planned mission packages stored in the removable memories. The networked media station preemptively validates mission media to identify and report issues preventing successful implementation of the pre-planned mission packages. The removable memories are then loaded into the aircraft's control systems for mission execution. The method also includes simultaneous offloading of mission data post-mission, automatic report generation, and cloud-based storage for data redundancy. An artificial intelligence system analyzes mission media and pre-planned packages to provide recommendations for future missions.
G07C 5/00 - Registering or indicating the working of vehicles
G05B 13/02 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
G08G 5/32 - Flight plan management for flight plan preparation
81.
SYSTEMS, METHODS, AND APPARATUS FOR CORRELATING LOCATIONS OF REAL-WORLD OBJECTS TO THE DIGITAL WORLD
A portable electronic device for obtaining information about an area of interest of an object is disclosed. The portable electronic device may include a display, an image capture device, a measurement device, and a processor. The processor may be configured to determine one or more positions of a portable electronic device relative to a location of one or more items of the object and determine a location of the area of interest of the object relative to the one or more positions of the portable electronic device. The processor may also be configured to identify electronic or digital information associated with the location of the area of interest of the object and send the electronic or digital information or the location of the area of interest to a remote computing device.
G06F 16/587 - Retrieval characterised by using metadata, e.g. metadata not derived from the content or metadata generated manually using geographical or spatial information, e.g. location
G06F 3/01 - Input arrangements or combined input and output arrangements for interaction between user and computer
G06T 7/73 - Determining position or orientation of objects or cameras using feature-based methods
G06T 19/00 - Manipulating 3D models or images for computer graphics
An aerospace physical component inspection system comprises a mobile personal computing device; a camera system connected to the mobile personal computing device, a machine learning model running in the mobile personal computing device; and a controller. The machine learning model is trained to detect anomalies in a set of images of a physical component in an aerospace vehicle. The controller configured to control the camera system to generate a set of images of the physical component; send the set of images of the physical component to the machine learning model; and receive a result from the machine learning model indicating whether an anomaly is present in the physical component.
A method for manufacturing a composite structure that has a carbon-reinforced composite component and a glass-reinforced composite component, the method including contacting a glass-reinforced composite material with a carbon-reinforced composite material to yield a composite layup, the glass-reinforced composite material having a glass reinforcement material and a polymeric matrix material, wherein the glass reinforcement material has a silica content of at least 60 percent, and co-curing the composite layup.
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 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
A method for restoring a pseudo random noise from a received binary offset carrier pseudo random noise signal. The received binary offset carrier pseudo random noise signal is filtered using a filter system to form a filtered binary offset carrier pseudo random noise signal that comprises a range of frequencies in the received binary offset carrier pseudo random noise signal. A binary offset carrier is removed from the filtered binary offset carrier pseudo random noise signal to obtain a restored pseudo random noise. The restored pseudo random noise is correlated with a local replica of the pseudo random noise.
A system and a method include a seat system including a frame, a mobile platform, and a seat configured to removably secure to both the frame of the seat system and the mobile platform. The seat secured to the frame provides a passenger seating location. The seat secured to the mobile platform provides a transfer wheelchair.
A device includes one or more processors configured to obtain, at a primary orchestrator of a system, a notification of a change event from an authoritative source of the system and identify, based on an evaluation precedence network at the primary orchestrator, one or more evaluations to perform in response to the change event. For each identified evaluation, the processor(s) are configured to send, from the primary orchestrator, an evaluation request to a secondary orchestrator of the system to request performance of the evaluation, and receive, from the secondary orchestrator, an evaluation result based on performance of the evaluation. The processor(s) are configured to update the evaluation precedence network to indicate an updated state of evaluation executions based on one or more of the evaluation results. The processor(s) are configured to determine, at the primary orchestrator, whether to generate an additional evaluation request after the evaluation precedence network is updated.
A method for controlling a movement of a vehicle is provided. An input image is received in which stars are present from a camera system for the vehicle. A subpixel probability image is generated by a machine learning model system from the input image in which the stars are present. The input image is comprised of pixels and the subpixel probability image is comprised of subpixel coordinates describing subpixel locations having probabilities of a presence of the stars. The subpixel coordinates for the subpixel locations of the stars is generated from the subpixel probability image. An orientation of the vehicle is determined using the subpixel coordinates for the subpixel locations of the stars. The movement of the vehicle is controlled using the orientation of the vehicle.
An example locking assembly includes a first wall; an arm having a first end and a second end, the first end coupled to a pivot extending from the first wall, the second end having a magnet; and a component attached to a second wall, the arm movable about the pivot to align the magnet with the component to lock the first wall and a propeller rotor in a stationary position based on a magnetic attraction between the magnet and the component.
H02K 99/00 - Subject matter not provided for in other groups of this subclass
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
H02K 1/06 - Details of the magnetic circuit characterised by the shape, form or construction
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
89.
SYSTEM AND METHOD TO DETECT ANOMALOUS WINGTIP EXTENSION FOR A FOLDING WING TIP AIRCRAFT
An aircraft including one or more sensors configured to obtain sensor data, a wing that includes a primary portion and a wingtip, and a folding wingtip system that includes a latch pin system, a first electronic controller, and a second electronic controller. The first electronic controller configured to receive a fold command, send instructions to use the latch pin system according to the fold command, and make a first determination that a wingtip position of the wingtip is not in a folded position. The aircraft further including a flight control computer that is configured to send the fold command to the first electronic controller, in response to the first determination, set first error codes for the folding wingtip system, change a setting to indicate that the aircraft is grounded based on the first error codes, and schedule maintenance of the aircraft based on the first error codes.
A coffee making system includes a housing. A base is coupled to the housing. An internal chamber is defined between the housing and the base. The internal chamber is configured to receive a carafe. The coffee making system also includes a carafe restraining plate, and a shower head assembly coupled to the carafe restraining plate. A lever is operatively coupled to the carafe restraining plate. Movement of the lever causes synchronous motion of the carafe restraining plate and the shower head assembly.
A method for bonding materials includes steps of: (1) enclosing at least a portion of a first material and a second material within an interior volume of a constraining container; (2) expanding an expandable medium disposed within the interior volume; (3) applying a positive pressure to the constraining container and at least one of the first material and the second material in response to expanding the expandable medium; and (4) bonding the first material and the second material together.
B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
B32B 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
92.
SYSTEMS AND METHODS FOR AUTONOMOUS VEHICLE CONTINGENCY PLANNING WITH THREE-DIMENSIONAL VOLUMES
A device includes a memory configured to store data that indicates, for a region associated with a mission, a plurality of partitions in the region and, for each of the partitions, a contingency route. The device includes one or more processors and configured to, based on detection of a first contingency event, locate a particular airspace in the region corresponding to a current location of the autonomous aerial vehicle; determine a path for the autonomous aerial vehicle to travel from the current location to the contingency route for the particular airspace; and generate one or more commands to cause the autonomous aerial vehicle to travel to the contingency route.
Methods and apparatus to dispense high viscosity fluid with a forming end effector are disclosed. An example an applicator includes a tool interface couplable to an arm of a robot, and an end effector supported by the tool interface, the end effector including a contoured surface and an outlet proximate or on the contoured surface, the outlet to dispense fluid therefrom as the end effector is moved such that contact of the contoured surface with the dispensed fluid is to shape the dispensed fluid.
B25J 11/00 - Manipulators not otherwise provided for
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
Jack stand support vehicles are disclosed. A disclosed apparatus for transporting a jack stand includes a base for supporting the jack stand, sidewalls extending from the base, the sidewalls supporting wheels by which the apparatus is moved, and a gate positioned on or proximate an opening defined by the sidewalls, the gate movable between (i) an open position for loading or unloading the jack stand and (ii) a closed position for retaining the jack stand.
A terminal block module includes terminal fittings, first and second terminal blocks, and an electrically conductive element. The terminal fittings are electrically conductive and have a cylindrically shaped sleeve and a lip. The first and second terminal blocks are electrically non-conductive and have terminal recesses, each having a sleeve-receiving section and a lip-receiving section. Each cavity is configured to receive a terminal fitting in any rotational orientation, and prevent axial movement of the terminal fitting via the lip. The electrically conductive element is locatable at an interface of the mating surfaces of the block assembly and is configured to electrically couple at least two terminal fittings to each other and/or electrically couple at least one terminal fitting to an external electrical component that is separate from the block assembly.
H01R 11/12 - End pieces terminating in an eye, hook, or fork
H01R 43/26 - Apparatus or processes specially adapted for manufacturing, assembling, maintaining, or repairing of line connectors or current collectors or for joining electric conductors for engaging or disengaging the two parts of a coupling device
Antennas having selective material loading are disclosed. An example antenna includes a ground plane, a radiator layer, and a loading layer including discrete loading portions located adjacent to the periphery of the radiator layer.
H01Q 25/00 - Antennas or antenna systems providing at least two radiating patterns
H01Q 21/24 - Combinations of antenna units polarised in different directions for transmitting or receiving circularly and elliptically polarised waves or waves linearly polarised in any direction
97.
HANDS-FREE COMMUNICATION SYSTEMS AND METHODS FOR AN AIRCRAFT
A system and a method include detecting signals from the operator that are motion signals and/or audio signals. A coded datalink message is created by a first control unit by converting the signals to coded signals. Each of the signals is associated with a coded signal based on a reference table. The coded datalink message is communicated with a second control unit. The second control unit decodes the coded datalink message by converting the coded signals to the signals based on the reference table and executes the datalink message.
A conduit system and method includes a mounting bar that extends between a first end and a second end. The mounting bar includes a mating surface that extends between the first end and the second end. The mating surface includes one or more mating features. The conduit system includes one or more conduits each including an outer surface that is operably coupled with at least one of the mating features of the mounting bar. The conduits are operably coupled with the mating surface of the mounting bar via a thermal bond or an adhesive bond.
F16L 3/22 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets specially adapted for supporting a number of parallel pipes at intervals
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
A method of modeling sustainability strategies for an aviation industry is presented. The method comprises receiving, at one or more processors, flight traffic information for a plurality of flights over a select time period. A traffic growth model is applied to the flight traffic information to generate projected flight traffic information over a future time period. Baseline calculations are performed on the projected flight information to generate forecasted aviation emissions information over the future time period. User input is received at one or more processors indicating one or more parameters for each of one or more of a plurality of sustainability strategies. The one or more of the plurality of sustainability strategies are applied to the forecasted aviation emissions information to generate adjusted forecasted aviation emissions information. An emissions reduction potential is indicated over the future time period based on the adjusted forecasted aviation emissions information.
The present disclosure provides an inflation system for inflating inflatable objects, such as aircraft tires. The inflation system includes a flow sensor arranged to sense a flow rate of pressurized air supplied to an inflatable object by way of a supply path. The inflation system also includes a computing system. The computing system is configured to inflate, using feedback from the flow sensor, the inflatable object with a learned volume of pressurized air specific to the inflatable object.
B60C 23/00 - Devices for measuring, signalling, controlling, or distributing tyre pressure or temperature, specially adapted for mounting on vehiclesArrangement of tyre inflating devices on vehicles, e.g. of pumps or of tanksTyre cooling arrangements
