Boeing Patente

Methods and apparatus for multi-layered integrity validation of vision-based vehicle guidance are disclosed. A disclosed example system includes an image sensor carried by a vehicle, the image sensor to identify light sources of a ground-based pattern display, wherein a spatial arrangement of varying distances between the light sources defines a light pattern array, and at least one processor circuitry to perform a multi-layer integrity validation corresponding to the light pattern array based on the identified light sources for guidance of the vehicle via the light pattern array.

A system includes a toilet, and an energy harvester coupled to the toilet. The energy harvester is configured to convert vacuum force, which flushes contents from the toilet, into electrical energy. The energy harvester is further configured to provide the electrical energy to one or more components.

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 unitary composite structure and methods of forming are presented. A method of laying up a unitary composite structure comprises laying up a plurality of dome plies on a rounded end of a mandrel using a plurality of rosettes; laying up a plurality of cylindrical plies on a cylindrical surface of the mandrel using a layup rosette independent of the plurality of rosettes; and forming a transition region comprising a joint between the plurality of dome plies and the plurality of cylindrical plies by varying lengths of the plurality of dome plies and lengths of the plurality of cylindrical plies.

An environmental control system pack for an aircraft that includes a ram air circuit and a bleed flow circuit. The ram air circuit receives air from an atmosphere on an exterior of the aircraft and expels the air through an outlet back into the atmosphere. The bleed flow circuit receives bleed air and cools the air prior to the bleed air being delivered to an interior space. The environmental control system pack uses energy from the bleed air to drive a fan in the ram air circuit. This causes an increase in a compression power of the air in the ram air circuit to increase a thrust of the air exiting the ram air circuit through the outlet.

A composite material assembly (20) comprises at least one composite material assembly member (22, 24, 26) comprising a dry fiber material impregnated with an epoxy resin-containing material. Said at least one assembly member (22, 24, 26) comprises a first side (22a, 24a, 26a); a second side (22b, 24b, 26b); and a longitudinal radius filler cavity (28) bounded by the second side (22b, 24b, 26b), said cavity (28) comprising a cavity radius. The composite material assembly (20) further comprises a tailorable composite material longitudinal radius filler (30) positioned within the cavity (28), said radius filler (30) comprising a radius dimensioned to substantially match the cavity radius, said radius filler (30) comprising a recycled dry fiber material (40) impregnated with the epoxy resin-containing material (42).

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.

Systems and methods are provided for fabricating multiple segment spars for an aircraft. In one example the method includes fabricating preforms of fiber reinforced material for spar segments, hardening the preforms to form the spar segments, and bonding the spar segments together to form a completed spar detail. In addition to bonding, other examples include co-curing and fastening the spar segments. In additional examples, the spar segments include kinks or subkinks as described.

An environmental control system pack for an aircraft that includes a ram air circuit and a bleed flow circuit. The ram air circuit receives air from an atmosphere on an exterior of the aircraft and expels the air through an outlet back into the atmosphere. The bleed flow circuit receives bleed air and cools the air prior to the bleed air being delivered to an interior space. The environmental control system pack uses energy from the bleed air to drive a fan in the ram air circuit. This causes an increase in a compression power of the air in the ram air circuit to increase a thrust of the air exiting the ram air circuit through the outlet.

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.

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 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.

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.

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.

An elastomer component (10) comprised of an elastomer material (12) having an air volume fraction (AVF) of greater than 5%, and the elastomer component (10) is a three-dimensional solid. An assembly (100) comprises an outer barrier (30), at least one elastomer component (10), and a curable material (20). A method comprises inserting (202) an elastomer component (10) and a curable material (20) into an outer barrier (30) to form an assembly (100) and heating (204) the assembly (100).

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.

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.

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 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.

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 solid oxide fuel cell, a motor driven by electric power from the solid oxide fuel cell, a gearbox operatively coupled to the motor, and a turbofan engine configured to generate thrust for the aircraft. The turbofan engine may be configured to provide electric power and shaft power and may include a duct fan that is operatively coupled to the motor via the gearbox, with the duct fan being driven by mechanical power from the gearbox and by the motor.

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. (Fig. 1)

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.

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.

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.

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.

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.

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. (Fig. 3)

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.

A method (200) for software function scheduling includes, at a computing system (100), executing a scheduling service (112) to coordinate function execution for a plurality of software functions (108) of the computing system (100). The scheduling service (112) receives registration information (302) for a software function (108) of the plurality of software functions, the registration information (302) including a periodic execution rate (308) for the software function (108). The software function (108) is assigned to a rate group (312) that includes one or more other software functions (108) each having the periodic execution rate (308), wherein each software function (108) in the rate group (312) is executed in a group-specific processing thread (310). The software function (304) is executed at the periodic execution rate (308) using the group-specific processing thread (310).

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.

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. (Fig. 1)

A method for monitoring a sealing process includes sealing a surface of an anodized substrate; passing 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 using open circuit potentiometry in situ to generate electrochemical surface potential data; and analyzing the electrochemical surface potential measurement data.

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.

Bleed-air systems comprise a bleed-air turbine configured to receive at least a first portion of bleed air from a jet engine and deliver it to a cabin, a cabin-exhaust compressor operatively coupled to the bleed-air turbine and configured to receive cabin exhaust air from the cabin, and a cabin-exhaust nozzle configured to receive the cabin exhaust air from the cabin-exhaust compressor. Aircraft comprise a fuselage, a wing, a jet engine, and a bleed-air system. Methods comprise expanding at least a first portion of bleed air from a jet engine to drive a cabin-exhaust compressor, compressing cabin exhaust air from a cabin with the cabin-exhaust compressor, and nozzling the cabin exhaust air to environment.

A plurality of fiber tows (214) are laid down (102) by an automated lamination machine (200) (e.g., an automated fiber placement (AFP) machine or a contoured tape laying machine (CTLM)), each fiber tow having a cut end (218). At least one marking (222) is automatically applied within at least one marked region (224) of each respective fiber tow (214). Each marking (222) 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.

A thermoplastic part (202, 302) with a thermoplastic repair patch (204, 304) and methods of repairing a thermoplastic part are presented. The thermoplastic part with a thermoplastic repair patch comprises a composite material (206) with a cut-out forming a repair area (210, 303), and the thermoplastic repair patch in the cut-out. The composite material has a first melting temperature (208, 230). The thermoplastic repair patch comprises a plurality of consolidated thermoplastic stacks (224, 226, 310, 312, 314, 400), each consolidated thermoplastic stack comprising thermoplastic composite plies (232, 244, 322, 324, 326, 406) between low melt thermoplastic surfaces (238, 240, 250, 252, 402, 404) having a second melting temperature (208, 230) lower than the first melting temperature.

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.

A method (900) of modeling sustainability strategies (116) for an aviation industry is presented. The method (900) comprises receiving (910), at one or more processors (1010), flight traffic information (102) for a plurality of flights over a select time period. A traffic growth model (110) is applied (930) to the flight traffic information (102) to generate projected flight traffic information over a future time period. Baseline calculations (112) are performed (940) on the projected flight information to generate forecasted aviation emissions information over the future time period. User input (104) is received (950) at one or more processors (1010) indicating one or more parameters for each of one or more of a plurality of sustainability strategies (116). The one or more of the plurality of sustainability strategies (116) are applied (960) to the forecasted aviation emissions information to generate adjusted forecasted aviation emissions information. An emissions reduction potential is indicated (970) over the future time period based on the adjusted forecasted aviation emissions information.

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.