Boeing Patente

A nacelle inlet for an engine. The nacelle inlet includes an inner flow surface, an outer flow surface, and a turbulator segment positioned along the inner flow surface. The turbulator segment extends outward beyond the inner flow surface and is configured to transition laminar airflow along the inner flow surface upstream from the turbulator segment to turbulent airflow downstream from the turbulator segment.

There is provided a leading edge protection system for a leading edge of a composite structure of an air vehicle. The leading edge protection system includes an automated brush plating system having a metal electrode plating brush, a wear-resistant metallic plating solution, and a direct current power supply. A leading edge surface has exposed carbon filaments that are conductive. The wear-resistant metallic plating solution is applied to the leading edge surface to obtain a wear-resistant metallic coating on the leading edge surface. The leading edge protection system further includes an automated cold spray system having a cold spray gun with a chamber for a conductive metallic sprayable powder, and having a supersonic spray nozzle. The automated cold spray system further includes an electrically heated process gas, and an electrical power supply. The conductive metallic sprayable powder is sprayed directly over the wear-resistant metallic coating, to obtain a conductive metallic coating.

A regulated power supply system, an integrated system, and a method are disclosed for providing regulated electrical power to an electrical load from a battery group. In an example, the regulated power supply system includes a buck regulator operable to regulate an unregulated voltage provided at an unregulated high-side interface of the battery group to a regulated voltage at a regulated high-side interface to which an electrical load can be connected. The buck regulator is configured to command a high-side driver to pass electrical energy to an inductor via the unregulated high-side interface during an on phase of a duty cycle during which the inductor is charged. The buck regulator is further configured to discontinue passing the electrical energy to the inductor during an off phase of the duty cycle.

A locking assembly to position one or more arms that are configured to be mounted to a work station to selectively lock a service cart at the work station in a cabin area of an aircraft. The locking assembly has an actuator with a body configured to connect to and move relative to the work station. A visual indicator is mounted to the work station with the visual indicator having a first visual appearance when the actuator is at a first position and a second visual appearance when the actuator is at the second position. A linkage has an elongated shape with a first end section connected to the one or more arms and a second end section connected to the actuator with the linkage configured to transfer force from the rotating actuator to the one or more arms and sized to space the actuator away from the one or more arms.

Reversible metal deposition devices are presented. A reversible metal deposition device comprises a transparent conductive electrode, a counter electrode, an electrolyte between the transparent conductive electrode and the counter electrode, a stripping additive in the electrolyte, and metal salt in the electrolyte that supplies metal to be reversibly deposited onto the transparent conductive electrode. The electrolyte contains less than 5 atomic percent water. The stripping additive comprises at least one of an acid or a base.

A system and a method include a control unit configured to receive a flight plan for an aircraft. The flight plan is in a first data standard. The control unit is further configured to convert the flight plan in the first data standard into the flight plan in a second data standard. The second data standard differs from the first data standard.

Systems and methods of determining taxiing of an aircraft (20) with multiple engines (30). The systems can include a database (52) operational to store collected historical data (61) about conditions that affect one or more engine characteristics with the one or more engine characteristics comprising fuel usage, engine wear, noise, emissions, and effect on related aircraft systems. A computing device (51) is in communication with the database and is operational to: train a machine learning model (53) using the historical data; determine an expected outcome of the engine characteristics for each of the engines; and determine which of the one or more engines to not use during taxiing of the aircraft.

Methods for analysis and process control during fabrication of workpieces are disclosed. For example, the method includes: (1) obtaining access to a historical database relating to the fabrication of the workpiece; (2) collecting interim as-built data for an interim version of the workpiece using a quality detection device during the fabrication of the workpiece; (3) processing the interim as-built data and the historical database to identify at least one inconsistency in the interim version of the workpiece; (4) processing the at least one inconsistency and the historical database to identify a probability for each inconsistency; and (5) determining whether each probability is unacceptable or acceptable based at least in part on the historical database. Automated systems for analysis and process control during fabrication of workpieces are also disclosed. For example, the automated system includes an analytical computing device, manufacturing equipment, tooling equipment and an interim as-built data monitoring device.

An attendant module configured to be mounted to a monument within a fuselage of an aircraft and configured to enable charging of a personal electronic device. The attendant module has a first compartment extends into a first side of the body. A first door is connected to the body at the first compartment. One or more holsters are mounted to the inner face of the first door with each of the holsters configured to hold the personal electronic device. A second compartment extends into a second side of the body. One or more electrical ports are positioned in the second compartment. A second door is connected to the body at the second compartment and movable between open and closed positions with the second door sized to extend across the second compartment in a closed position.

A method for layup and analysis of composite material during fabrication of a composite workpiece includes laying up a layer of the composite material for the composite workpiece based on design data for the layer and detecting as-built data for the layer using a quality detection device. Next, processing the as-built data for the layer to determine as-built fiber volume fill characteristics of the layer. Then, the method includes comparing the as-built fiber volume fill characteristics to as-planned fiber volume fill characteristics based on the design data for the layer to determine projected fiber volume fill ratios for the layer. An automated system for layup and analysis of composite material during fabrication of a composite workpiece includes at least one analytical computing device, a robotic manipulator, a layup mandrel and a quality detection device.

Methods for layup and analysis of composite materials during fabrication of composite workpieces are disclosed. For example, the method includes: (1) receiving design data for the layup of the composite material, the composite workpiece decomposed into multiple design zones, the design data including localized zone data for the multiple design zones; (2) processing the design data for multiple layers of the composite workpiece to determine as-planned fiber volume fill characteristics for the design zones of each layer individually and for the multiple layers collectively; (3) laying up a layer of the composite material for the composite workpiece based on the localized zone data; and (4) detecting as-built data for the layer using a quality detection device, the as-built data divided into an as-built grid structure that includes as-built grid cells. Automated systems for layup and analysis of composite materials during fabrication of composite workpieces are also disclosed.

Induction welding monitoring systems and methods of use are presented. The induction welding monitoring system comprises an electromagnetic field (EMF) sensor array extending the length of a weld interface, the EMF sensor array comprising a plurality of sets of sensors, a multichannel oscilloscope, and a switching system connecting the EMF sensor array to the multichannel oscilloscope and configured to switch between sets of sensors of the plurality of sets of sensors.

A method for aircraft (1110, 1202) management. Image data (1132) is received for areas of an aircraft (1110, 1202) that include deployment zones (1102) for overhead bins (151, 1101) in the aircraft (1110, 1202). The deployment zones (1102) are physical volumes that each overhead bin (1104, 1221, 1222, 1223, 1224) moves through and occupies as the overhead bin (1104, 1221, 1222, 1223, 1224) is opened. At least one of an opening or a closing of the overhead bins (151, 1101) is identified using the image data (1132) to form overhead bin usage data (1171). The overhead bin usage data (1171) is stored in a data collection (1134). The data collection (1134) is analyzed to determine a number of actions (1126) to perform for the aircraft (1110, 1202).

Examples are disclosed that relate to arranging a plurality of conductors (102) into a 2-dimensional (2D) spatial arrangement for insertion into a connector (112). One disclosed example provides a method of arranging the plurality of conductors (102). The method comprises positioning the plurality of conductors (102) within a plurality of gate stages (104) and closing each gate stage (104A) of the plurality of gate stages (104) to progressively move the plurality of conductors (102) into the 2D spatial arrangement.

An airplane wing comprises a wing substructure, an upper wing skin assembly and a lower wing skin assembly. The wing substructure comprises a composite front spar, a composite rear spar and a plurality of composite ribs extending between the composite front spar and the composite rear spar. The upper wing skin assembly comprises a composite upper wing skin and a first plurality of composite stringers co-bonded to the upper wing skin assembly by a low temperature thermoplastic bonding film. The lower wing skin assembly comprises a composite lower wing skin and a second plurality of composite stringers co-bonded to the lower wing skin by a low temperature thermoplastic bonding film.

A system and method for dynamically controlling a display of a graphical user interface (GUI) of a computer system includes receiving, via the GUI, one or more user inputs, and automatically changing a magnification of plural graphical icons displayed on the GUI between plural different levels of magnification responsive to receiving the one or more user inputs. Changing the magnification of the plural graphical icons changes a size of one or more of the graphical icons and a number of the plural graphical icons displayed on the GUI.

A mission management system (MMS) of a robot includes a plurality of mission management system computers (MMSCs). Each MMSC includes a plurality of processors. Each processor includes a conflict detection and resolution module that is configured to identify conflicts associated with the robot and to determine conflict resolutions, a communication module that is configured to communicate with a supervisor system not included in the robot, and a flight plan management (FPM) module. The FPM module includes a mission update module and a behavior management module. The mission update module is configured to generate a nominal trajectory and one or more contingency trajectories for the robot. The behavior management module is configured to control a behavior of the robot.

An aircraft includes a memory configured to store flight mode data and one or more processors coupled to the memory. The one or more processors are configured to receive an indication of conclusion of a Resolution Advisory (RA) of a Traffic alert and Collision Avoidance System (TCAS) event. In response to receiving the indication of conclusion of the RA, the one or more processors are configured to automatically initiate a Post-Avoidance Maneuver (PAM). The PAM includes retrieval of at least a portion of the flight mode data associated with a time period before detection of the RA. The PAM further includes identification of a pre-RA flight mode from the retrieved at least a portion of the flight mode data. The PAM further includes adjustment of control settings of the aircraft based on the pre-RA flight mode.

A multi-layered electrical display assembly and method includes a display having a mounting side and a viewing side. The mounting side is coupled with a mounting surface and the viewing side displays a first image with one or more display elements. A panel assembly includes a substrate having a first side and a second side. The panel assembly includes one or more conductive traces and plural electrical components disposed on the first side of the substrate. The plural electrical components are controlled to display a second image. The second side of the substrate is coupled with the viewing side of the display to cover a portion of the viewing side of the display.

A computer-implemented method for aircraft fault diagnosis and maintenance recommendation includes receiving (850) fault reports associated with at least one fault message and receiving (852) maintenance action data associated with the fault message. The method includes determining (854) a fix effectiveness based on the maintenance action data and computing (856) a recommendation confidence for one or more recommendation actions based on the fix effectiveness. The method includes assigning (858) a concurrent fault (CF) factor to the fault message based on the number of other concurrent fault messages. The method includes computing (860) a service issue composite (SIC) factor for each of the recommendation actions using at least the recommendation confidence and the CF Factor and displaying (862) the recommendation actions and the SIC factors in a graphical user interface.

An apparatus for drilling a workpiece includes a robotic manipulator and an end effector. The end effector is coupled to the robotic manipulator. The end effector includes a base. The end effector includes a nose that is coupled to the base. The end effector includes a drill that is movable relative to the nose along a processing axis. The end effector includes a foot that is coupled to the base. One of the nose or the foot is movable relative to the base along the processing axis and another one of the nose or the foot is fixed relative to the base. The robotic manipulator positions one of the nose or the foot in contact with the workpiece. The end effector clamps the workpiece between the nose and the foot.

An electronically-controlled method is provided for manufacturing a ceramic matrix composite structure with a desired shape. The electronically-controlled method comprises picking a first ceramic matrix composite ply that is sandwiched between a first bottom backing film and a first top backing film, and peeling away the first bottom backing film from the first ceramic matrix composite ply. The electronically-controlled method also comprises placing the first ceramic matrix composite ply on a tool surface with the first top backing film facing away from the tool surface, and positioning a vacuum membrane against the first ceramic matrix composite ply that is on the tool surface to provide a vacuum-tight seal against the first ceramic matrix composite ply. The electronically-controlled method further comprises drawing a vacuum to pull the vacuum membrane against the first ceramic matrix composite ply and thereby to form the first ceramic matrix composite ply to shape of the tool surface, and releasing the vacuum. The electronically-controlled method also comprises after the vacuum is released, peeling away the first top backing film from the first ceramic matrix composite ply and thereby to provide the ceramic matrix composite structure with the desired shape.

Examples are disclosed that relate to a computer-automated, vision-based approach for inspecting an aircraft structure to track a condition of assembly. In one example, a build plan for an aircraft structure is received. Images of the aircraft structure are received. A stitched image of the aircraft structure is generated based on the images and the build plan. Regions of interest (ROIs) of the stitched image are determined. For each of the ROIs, the ROI is input into an object detection machine learning model to identify actual locations of actual holes, tacks, and/or fasteners on the aircraft structure in the corresponding ROI. A condition of assembly report is generated that includes discrepancies between the actual locations and expected locations specified in the build plan. Event notification(s) that indicate remedial action(s) to be taken based on the discrepancies are generated based on the condition of assembly report. The event notification(s) are output.

A system for an aircraft includes a shock strut of a landing gear. The system includes one or more excitation devices coupled to the shock strut. The one or more excitation devices are configured to vibrate the shock strut to enable the shock strut to transition from a first static state where an outer cylinder of the shock strut is stationary relative to an inner cylinder of the shock strut to a dynamic state where the outer cylinder moves relative to the inner cylinder and to transition from the dynamic state to a second static state. The system also includes a resonance system coupled to the one or more excitation devices. The resonance system is configured to provide a first signal to the one or more excitation devices to activate the one or more excitation devices to vibrate the shock strut.

A lavatory system is configured to be disposed within an internal cabin of a vehicle. The lavatory system includes a floor. One or more walls upwardly extend from the floor. A passage is formed in the one or more walls. An interior chamber is defined between the floor, the one or more walls, and a ceiling. A door is moveably coupled to the one or more walls. The door is configured to be moved between a closed position, in which the passage is closed, and an open position, in which the passage is open. The door in the open position is outside of the interior chamber. The door is configured to move away from the interior chamber from the closed position to the open position. A toilet is within the interior chamber. A countertop is within the interior chamber. A sink and a faucet are secured to the countertop.

Example ram-air turbine (RAT) systems for aircraft are disclosed herein. An example RAT system includes a fan (106); a fan output shaft (218) coupled to the fan (106); a first face gear (206, 402) operatively coupled to the fan output shaft; a second face gear (208, 404); and a first pinion gear (210, 406) enmeshed with the first face gear and the second face gear.

Methods and systems of determining propagation of a crack within a structure made of a bonded or layered material. In some examples, the method comprises performing experimental testing on one or more test coupons of the material and determining an R-curve and a Paris law curve. The method also comprises performing a computer simulation that applies a cycle of loads to a computer model of the structure, for each of the loads: determining strain energy release rates and a crack length of the applied load; applying the strain energy release rates and crack lengths to the R-curve and determining an effective strain energy release rate; applying the effective strain energy release rate to the Paris law curve and determining a change in the crack length for the cycle; and advancing a crack that is simulated in the computer model.

An optical waveguide system (104, 210, 300, 500, 700, 800, 900) comprising a primary optical waveguide (120, 220, 301, 501, 701, 801) and a color center generation optical waveguide (121, 221,302, 502, 702, 802, 902). The primary optical waveguide (120, 220, 301, 501, 701, 801) comprises a material at a location (222, 307, 507, 704, 804, 904) in the primary optical waveguide (120, 220, 301, 501, 701, 801) that can support formation of a color center (203, 309, 509, 709, 809, 909). The color center generation optical waveguide (121, 221,302, 502, 702, 802, 902) has an output (223, 304,) positioned substantially perpendicular to a direction of light travel at the location (222, 307, 507, 704, 804, 904) in the primary optical waveguide (120, 220, 301, 501, 701, 801). The output (223, 304,) is directed at the location (222, 307, 507, 704, 804, 904).

Methods of reproducibly determining a beam size parameter of a laser beam utilizing a calibration standard and additive manufacturing systems that perform the methods. The calibration standard includes a calibration body that includes an aperture and defines a plurality of distinct aperture dimensions. Each distinct aperture dimension is measured along a corresponding dimension vector. The method includes, for each distinct aperture dimension, scanning the laser beam across the calibration body and along the corresponding dimension vector and, during the scanning, measuring a resultant energy of the laser beam as a function of position along the corresponding dimension vector. The method also includes generating an energy-dimension correlation between a characteristic of the resultant energy of the laser beam for each distinct aperture dimension and the distinct aperture dimension. The method further includes determining the beam size parameter based, at least in part, on the energy-dimension correlation.

A system configured to be operatively connected to a turbine engine of an aircraft and to an accessory of an aircraft. The system is configured to selectively transfer power between a first pressure spool of the turbine engine and a second pressure spool of the turbine engine and to power the accessory to deliver air to an aircraft system of the aircraft. (Fig. 3)

A predictive maintenance system and method for predictive maintenance of an aircraft system using machine learning-based models includes accessing privately stored data for a plurality of clients from a central server. A surrogate model can be applied to the privately stored data to identify one or more anomalies within the privately stored data and/or a large language model (LLM) can be applied to the privately stored data to identify one or more records within the privately stored data associated with a component of an aircraft system. The method includes determining a relationship between the one or more anomalies and the one or more records within the privately stored data to predict operational anomalies of the aircraft system.

A method (500) for conditional predictive maintenance in aircraft systems (100) using machine learning-based surrogate models (210) is disclosed. The described method (500) addresses the challenge of accurately detecting anomalies and predicting maintenance needs amidst complex operational and environmental variables. The method (500) involves receiving operational data from aircraft sensors (102), aircraft devices (104), and/or a memory (212), training a surrogate model (210) to predict aircraft device operations, and predicting operational outputs. Deviations (406) between predicted and actual outputs (400, 402) are analyzed to identify potential anomalies, distinguishing between noise and actual faults. This approach enables real-time monitoring and proactive maintenance scheduling, reducing reliance on scheduled inspections and enhancing aircraft reliability. The system (100) is adaptable to various environmental conditions and operational modes, ensuring consistent performance across different flight profiles. This method (500) is particularly useful for improving the efficiency and accuracy of aircraft maintenance operations.

A transmission operatively connected to a turbine engine of an aircraft to selectively transfer power from a first pressure spool of the turbine engine to a second pressure spool of the turbine engine and to power an accessory. The transmission is configured to selectively operate in one of a first configuration and a second configuration. The first configuration transfers power from the turbine engine to the accessory and the second configuration transfers power from the first pressure spool to the second pressure spool.

Disclosed herein is a system comprising a first apparatus and a second apparatus. The first apparatus comprises a first syntactic-foam part comprising low-density spheres at least partially embedded in a first resin, and a first elongated member partially embedded in the first resin and comprising a first end and a second end. At least the first end is located relative to the first syntactic-foam part such that the first end is exposed to an exterior of the first syntactic-foam part at a first exterior surface of the first syntactic-foam part. The second apparatus comprises a second syntactic-foam part comprising low-density spheres at least partially embedded in a second resin, and a second elongated member partially embedded in the second resin and comprising a first end and a second end. At least the first end is located relative to the second syntactic-foam part such that the first end is exposed to an exterior of the second syntactic-foam part at a second exterior surface of the second syntactic-foam part. The second elongated member of the second apparatus is coupled to the first elongated member of the first apparatus.

Disclosed is a syntactic-foam part comprising low-density spheres, at least one inner distribution media layer positioned within the low-density spheres at a predetermined height and defining an infusion interface, and a resin encapsulating the low-density spheres and the at least one inner distribution media layer. The at least one inner distribution media layer comprises at least one lower-resistance flow region. Regions of the least one inner distribution media layer other than the at least one lower-resistance flow region comprise a higher-resistance flow region. The at least one lower-resistance flow region has a lower resistance to a flow of the resin compared to the higher-resistance flow region, such that the resin flows faster through the at least one lower-resistance flow region.

A method for reinforcing an additively manufactured structure includes adding one or more reinforcement fibers to a carrier substrate to form a textile substrate. The one or more reinforcement fibers distributed about the textile substrate. The textile substrate is draped over the additively manufactured structure. A resin is applied to the textile substrate on the surface of the additively manufactured structure to form a resin-based composite bonded to the surface. A system for reinforcing an additively manufactured structure includes a fabrication tool set with first and second fabrication tools. A fiber-reinforced additively manufactured structure includes an additively manufactured structure and a resin-based composite. The additively manufactured structure includes a surface. The resin-based composite is bonded to the surface. The resin-based composite includes a textile substrate and a resin.

A lavatory system for an internal cabin of a vehicle comprises a monument defining an internal chamber. The monument comprises a contoured wall configured to conform to at least a portion of a shape of one or more passenger seats. First and second toilets are within the internal chamber. The first and second toilets can be staggered in relation to one another. A stowage chamber is within the internal chamber. The stowage chamber is configured to retain emergency equipment. A pedestal has one or more portions that are shaped to provide additional space within the internal chamber.

A device includes a memory (342) configured to store vehicle data (356, 358) and one or more processors (344). The one or more processors are configured to receive, from a first augmentation source, first augmentation data corresponding to a first Global Navigation Satellite System (GNSS) constellation; to receive, from a second augmentation source, second augmentation data corresponding to a second GNSS constellation; to select or derive augmentation data by comparing a confidence value (352) of the first augmentation data to a confidence value (354) of the second augmentation data; to generate aggregated data (332) for the vehicle, wherein the aggregated data (332) includes the selected augmentation data and navigation data from the corresponding GNSS constellation; and to send the aggregated data to the vehicle.

A machine and process configured to control bleed-off from an airflow and/or reduce a drag of an inlet. The machine may include: a panel that may include a porous section that comprises: a length; a flow side; and a channel side; a channel that surrounds the porous section and contains a carriage adjacent to the panel, wherein the carriage comprises: a flow side; a translation component; a channel side connected to a first rigid link and to a second rigid link; a bleed gap; and a number of pressure taps; a cylinder that comprises: a forward end; an aft end; a piston connected to: a forward rod that extends out of the forward end of the cylinder; and an aft rod that extends out of the aft end of the cylinder; a number of chambers; and a bias device connected to: the aft rod; and the channel.

A computing system for cataloging software code is provided. The computing system comprises at least one code repository storing a plurality of code projects each having a natural language description, code project, and location. The computing system further comprises processing circuitry configured to, for each of the plurality of code projects, determine the location and a name of the code project and store the location and the name in a search table; receive a prompt from a user requesting a list of matching code projects from the plurality of code projects; generate, via at least one generative language model trained on the natural language descriptions of the plurality of code projects, and in response to the prompt, an output including the list of matching code projects; and return the output to the user.