Boeing Patente

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.

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.

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 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.

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 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 first cut and kitted material is held against a first flange face of a first die. A second cut and kitted material is held against a second flange face of a second die. The method simultaneously forms the first cut and kitted material against a first blade face of the first die and the second cut and kitted material against a second blade face of the second die. The first cut and kitted material and the second cut and kitted material are clamped between the first die and the second die after forming the first cut and kitted material and the second cut and kitted material. A composite stringer preform comprising the first cut and kitted material, the second cut and kitted material, a noodle, and a base material is cured while the composite stringer preform is against the first forming surface and the second forming surface.

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 device includes a receive antenna configured to receive a radar signal. The device includes a return signal generator configured to generate a return signal based on the received radar signal. The return signal includes at least a first component at a first frequency offset from a carrier frequency of the received radar signal and a second component at a second frequency offset from the carrier frequency. The device also includes a transmit antenna configured to transmit the return signal.

A method of using a fastener assembly includes aligning a first opening having a first diameter in a first component with a second opening having a second diameter in a second component and inserting a shaft having an outer diameter surrounded by a sleeve through the first opening and the second opening. The sleeve includes a proximal end, a distal end, an inner diameter, and an outer diameter. The method also includes compressing the proximal end and distal end of the sleeve to deform the sleeve and increase a wall thickness of the sleeve within at least one of the first opening or the second opening.

Hinge mechanisms for a door of a fuselage of an aircraft, doors for a fuselage of an aircraft, aircraft that include the doors, and related methods. The hinge mechanisms include a plurality of components operatively attached to the fuselage via a body fitting. The doors include a hinge mechanism, an outer door panel, and an inner door panel and are configured to be selectively transitioned between a closed configuration, in which the door seals a door opening of the fuselage, and an open configuration, in which the door permits access to an interior of the fuselage via the door opening. The methods include methods of testing operation of the door and methods of actuating the door.

Tracking a maintenance compliance window of opportunity is provided. The method comprises receiving an alert in response to an aircraft system exceeding an operational threshold or failing to transmit a report. A lead time countdown to a compliance deadline is started in prescribed units. Elapsed and remaining units, out of a total number of allotted units in the lead time, are calculated based on reports from sources defining an operating cycle of the aircraft system. The countdown is displayed in a user interface as a normalized sliding scale of elapsed percentage of total number of allotted units in the lead time. The remaining units out the total number of allotted units are also displayed in the user interface. The countdown is ceased in response to the first of: resolution of the alert or the countdown reaching the compliance deadline, wherein the lead time has completely elapsed.

An aircraft maintenance user interface is provided. The interface comprises an alert indicator that displays an alert related to an aircraft system that must be addressed for maintenance compliance of an aircraft. A compliance window indicator displays a normalized sliding scale of elapsed percentage of a lead time between the alert and a maintenance compliance deadline. A remaining units indictor displays a number of used units out of a total number of allotted units that measure the remaining lead time.

A seal boot includes a base and a toe that extends from the base. The seal boot includes a fillet surface that is formed by the base and the toe. The seal boot includes a first fay surface that is at least partially formed by the base. The seal boot includes a second fay surface that is at least partially formed by the toe.

A module interface device for a multi-cell battery module comprises a cathode bus connectable to a cathode terminal and an anode bus connectable to an anode terminal of the battery module, and a set of one or more inter-cell taps connectable to respective inter-cell electrical interconnectors that interconnect neighboring pairs of cells of the battery module. The module interface devices comprises a cell balancing circuit that includes: an electrically conductive pathway that joins the cathode bus with the anode bus, a set of multiple resistive-capacitive elements arranged along the electrically conductive pathway, and a set of one or more switches in which a respective switch is located along each inter-cell tap. Each inter-cell tap joins the electrically conductive pathway at a respective location between a different neighboring pair of resistive-capacitive elements.

A captive fastener system and methods of installing captive fasteners are presented. A captive fastener system comprises an expandable opening with an initial diameter connected to a channel; and the channel. The channel has an internal diameter larger than the initial diameter and an exit diameter configured to retain a head of a fastener inside the channel.

A device includes a memory and one or more processors coupled to the memory. The processor(s) are configured to obtain historical flight data that represents a plurality of flights associated with a plurality of airports and to generate a directed graph, based on the historical flight data, that includes a plurality of nodes and a plurality of edges connecting pairs of nodes. The plurality of nodes correspond to the plurality of airports and the plurality of edges correspond to the plurality of flights. The processor(s) are configured to perform a ranking operation on the directed graph to identify one or more target nodes of the plurality of nodes. The one or more target nodes correspond to one or more airports of the plurality of airports. The processor(s) are configured to output a graphical user interface that indicates the one or more airports as recommended airports for modeling predicted traffic flow.

Manifolds and methods of connecting corrugated conduits are presented. A manifold to connect corrugated conduits is presented. The manifold comprises a first half, a second half removably connected to the first half to form a volume within the manifold, a first number of openings on a first end to access the volume, and a second number of openings on a second end to access the volume. Removing the first half from the second half cleaves each of the first number of openings and each of the second number of openings.

A method (200) for measuring a hole (130) comprises: driving (202) a fiber optic probe (114) into the hole; determining (204) a profile (128) by scanning walls (132) of the hole via the fiber optic probe; determining (206) whether an interface gap (140) exists at the walls of the hole based on the profile; and if the interface gap exists, identifying (220) sealant (1110) at the interface gap based on a region (1344) of the profile representing the interface gap.

A device includes a memory and one or more processors coupled to the memory. The one or more processors are configured to obtain statistics based on historical flight data for each of a plurality of historical flight paths. The historical flight paths are associated with historical flown distances between respective departure and arrival points. The one or more processors are configured to obtain an expected flown distance for an estimated flight path between a departure point and an arrival point. The one or more processors are configured to generate an airspace congestion metric associated with the estimated flight path. The airspace congestion metric is based on the expected flown distance and a set of the statistics associated with the departure and arrival points. The one or more processors are configured to output, based on the airspace congestion metric, a displayable airspace congestion indicator associated with the estimated flight path.

A battery charging station is disclosed that includes an electrical system including a charging interface, a communications system including a wireless interface, and a control system. The control system is configured to receive a charging request to initiate a battery charging operation for a battery system of a mobile platform, establish a wireless communications link with the mobile platform via the wireless interface, and receive health status data for the battery system from the mobile platform over the wireless communications link via the wireless interface. The control system is further configured to enable charging of the battery system of the mobile platform via the charging interface responsive to the health status data satisfying a first condition, and to disable charging of the battery system of the mobile platform via the charging interface responsive to the health status data satisfying a second condition indicating a fault of the battery system.

A system and a method include a component formed of a material. The component has one or more first holes. A test piece is formed of the material. The test piece has one or more second holes. A first tool is configured to insert one or more first fasteners into one or both of the first hole(s) or the second hole(s). A second tool is configured to insert one or more second fasteners into one or both of the first hole(s) or the second hole(s). One or more force sensors are coupled to one or both of the component or the test piece. The force sensor(s) are configured to detect (a) one or more first aspects of one or more first forces exerted during operation of the first tool to insert the first fastener(s) into one or both of the first hole(s) or the second hole(s), and (b) one or more second aspects of one or more second forces exerted during operation of the second tool to insert the second fastener(s) into one or both the first hole(s) or the second hole(s). A control unit is in communication with the force sensor(s), and is configured to correlate the first aspect(s) of the first force(s) with the second aspect(s) of the second force(s).

Systems, apparatuses and methods can provide for technology includes a turbofan engine subassembly having an inlet surface with a first side and a second side, and one or more flow effectors coupled to the inlet surface, wherein the flow effector(s) transition from a retracted position to an extended position on the second side of the inlet surface in response to an ambient temperature on the first side of the inlet surface exceeding a first threshold. The flow effector(s) may also transition from the extended position to the retracted position in response to the ambient temperature on the first side of the inlet surface falling below a second threshold.

An electronically-controlled method (700, 800, 900) is provided for manufacturing a ceramic matrix composite structure (500) with a desired shape, the electronically-controlled method comprising: - processing (block 802) at a first location a plurality of ceramic matrix composite plies to form a stack (400) of the plurality of ceramic matrix composite plies (212, 222), wherein the processing comprises: - picking (902) a first ceramic matrix composite ply (212) that is sandwiched between a first bottom backing film (213) and a first top backing film (211); - placing (904) the first ceramic matrix composite ply (212) on a table surface (104) at a first location; - peeling away (906) the first top backing film (211) from a top surface of the first ceramic matrix composite ply (212); - picking (908) a second ceramic matrix composite ply (222) that is sandwiched between a second bottom backing film (223) and a second top backing film (221); - peeling away (910) the second bottom backing film (223) from a bottom surface of the second ceramic matrix composite ply (222); - placing (912) the bottom surface of the second ceramic matrix composite ply (222) on the top surface of the first ceramic matrix composite ply (212) to form a stack (400) comprising at least the first ceramic matrix composite ply (212) and the second ceramic matrix composite ply (222); - transporting (block 804) the stack (400) of plurality of ceramic matrix composite plies (212, 222) from the first location to a second location which is remote from the first location, wherein the transporting comprises: - transporting (914) the stack (400) from the table surface (104) at the first location to a tool surface (112) at a second location which is different from the first location to enable the stack (400) to be manufactured as the ceramic matrix composite structure (500) with the desired shape at the second location; and - processing (block 804) at the second location the stack (400) of plurality of ceramic matrix composite plies (212, 222) to provide the ceramic matrix composite structure (500) with the desired shape.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Methods of forming a composite product are presented. A releasable gap filler (218, 402) is applied within a recess (206) of a mold (202). An uncured composite material (204) is applied directly over the releasable gap filler (218, 402) and onto the mold (202). The uncured composite material (204) is cured to form a cured composite material on the mold. The cured composite material is removed from the mold and the releasable gap filler.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …