Boeing Patente

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.

A method (1000) for manufacturing a composite structure (2000) comprising a carbon-reinforced composite component (2010) and a glass-reinforced composite component (2020), the method (1000) including contacting (1200) a glass-reinforced composite material (2200) with a carbon-reinforced composite material (2100) to yield a composite layup (2300), the glass-reinforced composite material (2200) comprising a glass reinforcement material (2220) and a polymeric matrix material (2210), wherein the glass reinforcement material has a silica content of at least 60 percent, and co-curing (1300) the composite layup (2300).

A system (100) and a method include a seat system (106) including a frame (110), a mobile platform (124), and a seat configured to removably secure to both the frame (110) of the seat system (106) and the mobile platform (124). The seat secured to the frame (110) provides a passenger seating location (142). The seat secured to the mobile platform (124) provides a transfer wheelchair (160).

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 method for manufacturing a non-crimp fabric includes providing a plurality of layers of continuous fibers (10, 20) held together by stitch threads (30) and applying a binder (40, 50) 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.

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.

A control system and method measures vibrations during operation of an engine connected with rotating accessories. A high vibration condition is identified responsive to a vibration amplitude exceeding a threshold and a vibration frequency being in a frequency band extending around an operating frequency of one rotating accessory. The system and method decide whether operating frequencies of the rotating accessories are within a crosstalk band from each other and, if so, the system and method shift the operating frequency of another rotating accessory to determine which rotating accessory is causing the vibrations.

Method of monitoring motion of an aircraft (100) during flight. The method includes determining sensed motion of the aircraft (100) about an axis during the flight and determining predictive motion of the aircraft (100) about the axis during the flight (based on a digital model (200)). An error is determined based on the sensed motion and the predictive motion. An effector (110) on the aircraft (100) is determined that controls the motion of the aircraft about the axis. The error is converted into an amount of necessary movement of the effector (110) to correct the error.

Polymer matrix composite joints (200) include a first contact area (202) of a first polymer matrix composite structure (204), a second contact area (206) of a second polymer matrix composite structure (208) and a resistive film heating element (210). The resistive film heating element (210) includes a lignin-based carbonaceous material (212). The resistive film heating element (210) defines a longitudinal form and is disposed between the first contact area (202) and the second contact area (206). The resistive film heating element (210) sized and shaped based on the first contact area (202) and the second contact area (206). The resistive film heating element (210) for joining the first polymer matrix composite structure (204) and the second polymer matrix composite structure (208) at the first contact area (202) and the second contact area (206) using a resistive welding process. Systems (600) for processing polymer matrix composite joints (200) and methods (1000) for processing polymer matrix composite joints (200) are also disclosed.

A support system is configured to couple to a radio frequency identification device (RFID) printer. The support system includes a tray having a support ledge configured to abut against the RFID printer below a media outlet of the RFID printer. The support ledge is configured to support a portion of an RFID component configured to be output by the RFID printer through the media outlet. The tray also includes a guide ramp connected to the support ledge at an angle. The guide ramp is configured to slidably support the RFID component after the RFID component pivots off the support ledge.

A method (1000) for bonding materials (202) includes steps of: (1) enclosing (1002) at least a portion of a first material (204) and a second material (206) within an interior volume (116) of a constraining container (110); (2) expanding (1008) an expandable medium (120) disposed within the interior volume; (3) applying (1010) a positive pressure (124) 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 (1012) the first material and the second material together.

A system and a method include a housing, an ultrasonic transducer secured within the housing, and one or more barriers secured within the housing. The one or more barriers are formed of a solid material. A liquid retention chamber is within the housing between the ultrasonic transducer and the one or more barriers. The liquid retention chamber retains a liquid.

A radio frequency (RF) reflector (100) includes a non-metallic substrate (102) shaped to reflect RF energy in a specific direction and a cold-sprayed RF-reflective layer (104) on the non-metallic substrate (102). A method (400) for manufacturing an RF reflector includes providing the non-metallic substrate (402) and cold spraying the RF-reflective layer onto the substrate (406). An antenna system (10) includes an antenna (200) for transmitting and receiving RF energy (300) and a radio frequency reflector (100) positioned to direct RF energy (300) towards or away from the antenna (200).

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.

A method of transmitting data from a first Bluetooth Low Energy, 'BLE', device that has a failed Internet connection. Upon determining that Internet connectivity has failed at the first BLE device, the method includes transmitting, from the first BLE device to a second BLE device detected by the first BLE device, data via a BLE signal with the second BLE device being within a threshold distance from the first BLE device. The method further includes determining that an Internet connection is available to the second BLE device and transmitting the data to a gateway from the second BLE device.

A clip system includes a base, a first cantilevered arm extending from the base, and a second cantilevered arm extending from the base. The base, the first cantilevered arm, and the second cantilevered arm are configured to cooperate to secure to an edge portion of a panel. A wire retainer outwardly extends from one of the base, the first cantilevered arm, or the second cantilevered arm. The wire retainer is configured to retain a portion of a wire.

A multi-agent LLM system includes multiple non-generative executive LLM agents trained on different sets of maintenance information, and a generative orchestration LLM agent coupled with the executive LLM agents. The orchestration LLM agent can receive a maintenance inquiry related to the powered system from personnel, and assign one or more of the executive LLM agents to examine the maintenance inquiry based on which of the different sets of the technical information that the executive LLM agents were trained. The executive LLM agents can examine the set of the technical information used to train the respective one or more of the executive LLM agents for relevant information to be output responsive to the maintenance inquiry and to provide the relevant information to the orchestration LLM agent. The orchestration LLM can present the relevant information from the executive LLM agents to the personnel for maintenance of the powered system.

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.

A tooling assembly for forming and curing a composite preform in a single process step and a method of forming and curing the composite preform includes a composite material blank disposed on a platform. The tooling assembly includes a shape memory alloy (SMA) structure incorporated into the platform and configured to move in response to heating which changes a shape of the platform. The SMA structure is disposed in an initial state at a first threshold temperature when unheated and is disposed in a secondary state when heated via a heater to a second threshold temperature. The composite material blank is movable with the platform to a transformed state in response to the SMA structure moving to the secondary state to form and cure the composite material blank into the composite preform relative to the secondary state of the SMA structure.

A process (400) for distributing automated machines (240) between a plurality of tools (225, 235, 265, 295) located in a plurality of respective stations (220, 230, 260) on a production line (210) for the continuous flow manufacturing of large workpieces (217), such as spars, fuselage sections, wing structures, and other aircraft structures, and/or composite parts by identifying and accurately locating non-fixed-base tooling throughout the continuous manufacturing process is provided. The process (400) comprises: defining (410) automated machines (240) dedicated to a specific station (220, 230, 260), based on a minimum number of automated machines (240) or workload requirements (254); defining (420) automated machines (240a) among a plurality of automated machines (240) configured to travel between stations (220, 230, 260) while workpieces (217) are moving from one station (220, 230) to another (220, 230) in a single sequential flow along the production line (210) to complete the workload requirements (254) based on a maximum difference in workload requirements (254) between two or more adjacent stations (220, 230, 260); assigning each of the said automated machines (240a) to a particular zone location (280) on a workpiece (217); measuring (430) statistics (432) of each station (220, 230, 260) and tool (225, 235, 265), including measuring total required time (434), time completed (436), time remaining (438), and zone location (280); communicating (440) the statistics (432) to a controller (250); measuring (450) variables (455) from a numerical control program (258) in each automated machine (240); compiling data (460) measured of a total machine capacity (252) and total workload requirements (254) across each station (220, 230, 260); and reallocating (470) and moving one or more automated machines (240a) of the plurality of automated machines (240) to a new zone location (280) on the same workpiece (217) or on a different workpiece (217) located in a different station (220, 230) that has unmet workload requirements (254) once an efficiency threshold (256) is met, to balance out the workload requirements (254) of the plurality of automated machines (240).

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.

A method for forming composite parts includes loading an uncured composite material into a middle cavity of a chamber between an upper membrane and a lower membrane, wherein a lower cavity is defined below the lower membrane, and wherein an upper cavity is defined above the upper membrane, wherein a forming tool is disposed within the upper cavity. A vacuum is applied to the upper cavity, the middle cavity, and the lower cavity to remove at least a portion of gas entrapped within the uncured composite material. The vacuum is released from the upper cavity and the lower cavity, and the chamber is heated to a forming temperature of the uncured composite material. Pressure is controlled in the upper cavity and the lower cavity to form the heated composite material, wherein a greater pressure is applied to the lower cavity than to the upper cavity such that a pressure differential between the lower cavity and the upper cavity causes the heated composite material to form around the forming tool. The chamber is heated to a curing temperature to cure the heated composite material. (Fig. 1)

A method and a variable roller assembly (10) for forming one or more radii along a composite material blank includes a roller die configured to form the one or more radii along the composite material blank (12) to form a filler (14). A first actuator (38) is operably coupled to the roller die (32) and configured to move the roller die (32) in a linear direction along a y-axis, and a second actuator (40) operably coupled to the roller die and configured to move the roller die in a linear direction along a z-axis. A controller (50) is in communication with the first actuator and the second actuator to selectively activate the first actuator and/or the second actuator to variably move the roller die relative to the composite material blank to maintain engagement of the roller die with the composite material blank to form the one or more radii along the composite material blank to form the filler (14).

A cavitation nozzle is disclosed, including a plate, a hollow body, and a cap removably engaged with the hollow body and holding the plate against a distal end of the hollow body. The plate may have a central aperture and a distal surface, wherein the distal surface is bisected by a groove and the hollow body is configured to deliver high pressure fluid through the central aperture. The delivered high pressure fluid may be discharged as a cavitating jet.

Resin infusion tooling systems and methods of resin infusion are presented. A resin infusion tooling system comprises a heating tool bed comprising a plurality of cavities formed between a plurality of bed segments movable relative to each other, and a plurality of seals configured to seal the plurality of bed segments together for resin infusion of a plurality of dry stringer preforms in the plurality of cavities. The plurality of cavities is expandable by movement of the plurality of bed segments relative to each other.

A method of forming a composite preform includes transforming a composite blank material into the composite preform via a two-stage process. The composite blank material is disposed between first and second membranes during a first stage. The first membrane and the second membrane are disposed across first and second mold bodies in the first stage. A vacuum is activated to expel a gaseous fluid out of a space between the first membrane and the first mold body and the second mold body to form a first radius of the composite blank material during the first stage. A third membrane is disposed at least partially over the composite blank material during a second stage. The vacuum is activated to expel a gaseous fluid out of an area between the third membrane and the first mold body to form a second radius of the composite blank material during the second stage.

A mold assembly for a vacuum forming process and a method of elongating membranes of the mold assembly for the vacuum forming process. A permeable layer is disposed across a surface of a mold body such that the permeable layer overlaps a groove defined in the surface of the mold body. Membranes are disposed across the permeable layer and the mold body. A vacuum is activated to expel a gaseous fluid out of a space between the mold body and one of the membranes which creates compaction pressure during compaction that causes the membranes to elongate and transform the composite blank material into the composite preform. A pump is activated to inject a flow of fluid between the permeable layer and one of the membranes via the groove to control the compaction pressure during elongation of the membranes as the gaseous fluid is expelled out of the space.

An aeronautical navigation data standardization method comprising: receiving data sets of aeronautical navigation data from aeronautical navigation source providers "ANSPs"; identifying one or both of a type of the aeronautical navigation data in the data sets or the countries in which the ANSPs are located; selecting one or more data standardization cases for one or more of the data sets to change the aeronautical navigation data in the one or more of the data sets based on one or more previous detections of the type of the aeronautical navigation data or the countries for one or more previous changes to one or more previous data sets; and changing the aeronautical navigation data according to the one or more data standardization cases that are selected, one or both of a format or a syntax of the aeronautical navigation data being changed in the one or more of the data sets.

The present disclosure provides techniques for localizing RF interference devices and identifying impacted RF receiver paths or positions. A plurality of RF interference events are collected from one or more data sources. A group of RF interference events that indicate interference from a common RF interference source are identified from the plurality of RF interference events. An RF receiver location is estimated from each RF interference event. A plurality of RF interference source location constraint regions are created, each region being a volume referenced to an estimated RF receiver location. An overlapping volume that the plurality of RF interference source location constraint regions intersect is identified. An RF interference influence volume is defined by expanding the overlapping volume based on an interference range of the RF interference device as a function of direction.

Single use and replaceable self-powered aircraft compartment thermal indicators that deliver a localized visually detectable signal that can be perceived by personnel at the exterior of an aircraft component and that can be activated on demand to signal the presence of a temperature within an aircraft compartment that exceeds a threshold temperature and that can be tested in situ, and methods of use are disclosed.

An inlet assembly for a nacelle includes an inlet cowl and a plenum back wall of a fluid ice protection system (FIPS). The inlet cowl extends a length from a front end of the inlet cowl to a rear end of the inlet cowl. The inlet cowl includes a lipskin that defines a leading edge of the inlet cowl at the front end, and an acoustic panel coupled to the lipskin at an interface along an inner side of the inlet cowl. A seam is defined between the acoustic panel and the lipskin. The plenum back wall is affixed to an interior surface of the lipskin to define a plenum between the interior surface and a front surface of the plenum back wall. The plenum receives an anti-ice liquid. The plenum back wall is disposed in front of the seam along the length of the inlet cowl.

A transfer assembly to transfer power within an aircraft. The transfer assembly includes a low pressure drive mechanism operatively connected to a low pressure spool, a high pressure drive mechanism operatively connected to the high pressure spool, an accessory drive mechanism operatively connected to the accessory, and a differential operatively connected to each of the low pressure drive mechanism, the high pressure drive mechanism, and the accessory drive mechanism. The differential is configured to operate in a first mode configured to transfer power from the accessory to one of the low pressure spool and the high pressure spool, a second mode configured to transfer power from one of the low pressure spool and the high pressure spool to the accessory, and a third mode configured to transfer power from the low pressure spool to the high pressure spool.

An aircraft includes an internal cabin, and a lavatory system within the internal cabin. The lavatory system is convertible between a standard configuration and an expanded configuration. The lavatory system includes a first lavatory unit, and a second lavatory unit. One or more doors of one or both of the first lavatory unit or the second lavatory unit are moveable between different positions to provide the standard configuration and the expanded configuration.

Described herein is a robotic laser ablation system that comprises a robot and processing circuitry. The robot has an end effector with laser componentry and a camera mounted thereto. Processing circuitry is configured, in response to stored instructions, to perform operations including: receiving the input image of a workpiece from the camera; segmenting the input image to produce an image segment that depicts at least a portion of the workpiece; applying a surface-fitting algorithm to generate a polynomial surface that is fit to the surface in the image segment; computing a set of surface normal vectors across the polynomial surface to generate a set of waypoints offset from the polynomial surface by an offset length; programmatically generating a motion path linking a plurality of the waypoints; and performing laser ablation of the surface of the portion of the workpiece based on the motion path.

A projector includes a housing, a display controller, a display engine, and a drive assembly. The display controller is coupled to the housing. The display engine is enclosed in the housing and is coupled to the display controller. The drive assembly is coupled to the housing and is configured to selectively position the housing.

A system for constructing a composite stringer package includes a tray, a lid, a deformable membrane, and a vacuum rig. The tray includes a receptacle. The lid is configured for moving relative to the tray between an open state and a closed state. The deformable membrane is configured for positioning over the tray. The vacuum rig is coupled to the tray. With the lid in the closed state, the lid and the tray are sealed together to form a sealed chamber. With the lid in the closed state, the deformable membrane is positioned in the sealed chamber between the tray and the lid. With the lid in the closed state, the vacuum rig is configured for applying vacuum to the sealed chamber.

A test stand in operative communication with a source of conveyed air and configured to position thereon an air cycling machine (ACM) having a compressor and a turbine includes a support structure. The test stand also includes wheels mounted to the support structure and configured to facilitate mobility of the test stand. The test stand additionally includes a duct assembly moveably mounted to the support structure and configured to receive a flow of the conveyed air from an outlet of the source, supply the air to a compressor inlet of the ACM, and exhaust air from a turbine outlet of the ACM to atmosphere. The test stand also includes a pressure transducer configured to detect pressure of the conveyed air in the duct assembly and communicate the detected pressure to an electronic controller. The detected pressure is used by the electronic controller to regulate the source of conveyed air.

A thermal expansion absorbing coupler configured to join individual pipes includes a multi-segment retaining shell having a V-shaped cross-section inner surface configured to draw together adjoining pipe ends. The coupler also includes a hightemperature material sealing ring configured to be arranged between the retaining shell and outer diameter of the adjoining pipes and block leakage of airflow from between the adjoining pipe ends. A test stand configured to position thereon an air cycling machine (ACM) having a compressor and a turbine may employ such a thermal expansion absorbing coupler. On the test stand, the coupler connects the ACM to a duct assembly and/or joins individual pipes of the duct assembly and absorbs thermal expansion of the duct assembly.

A system and a method include a lower support, an upper support, a first coupler connected to the lower support and the upper support at a first point of contact and a second point of contact, respectively, and a second coupler connected to the lower support and the upper support at a third point of contact and a fourth point of contact, respectively. The first coupler and the second coupler are configured to retain a test article therebetween.

A testing arrangement includes an air heating and routing system (AHRS) system configured to receive and convey a flow of air and having a three-stage pressure adjusting subsystem for adjusting pressure of the conveyed air. The AHRS system also includes an air heater configured for regulating temperature of the conveyed air and plumbing for fluidly connecting the air heater and the three-stage pressure adjusting subsystem and convey the flow of air. The testing arrangement also includes a pressure transducer for detecting pressure of the conveyed air and an electronic controller. The electronic controller is configured to regulate the three-stage pressure adjusting subsystem, using the pressure detected by the pressure transducer, and the air heater to output the pressure and temperature regulated air via the AHRS plumbing. The testing arrangement may further include a test stand in operative communication with the AHRS. A testing method employs such a testing arrangement.