Honeywell Patente

A system comprises a communication management function (CMF) onboard an aircraft and configured to exchange datalink messages including ACARS messages, and CPDLC messages; and an onboard data gateway device in communication with the CMF. The data gateway device includes an ACARS over IP stack and a message decoder that communicates with the ACARS over IP stack. A ground server is configured for ACARS over IP messaging, with the ground server being in communication with the CMF through the data gateway device. At least one external device is in communication with the data gateway device. The external device comprises an onboard mobile device or a private cloud server. When ACARS over IP messages are exchanged between the CMF and the ground server, through the data gateway device, the messages are also routed from the gateway device to the external device comprising the onboard mobile device or the private cloud server.

A sensing device is disclosed. The sensing device comprising a printed circuit board (PCB), a conductive port coupled to the PCB via a conductive adhesive and defining an orifice filled with a protective gel. Further, the sensing device comprises a sensing element disposed on the PCB within the conductive port and encased by the protective gel, and a conductive member disposed at least over the protective gel. The conductive member is configured to discharge static charges accumulated over the protective gel to the PCB via at least the conductive adhesive.

Devices, methods, and systems for event monitoring and detection device (100, 200, 300, 400) testing are described herein. One device includes a memory (124, 524) and a processor (126, 526) to execute instructions stored in the memory to modify a sensitivity level of a sensor (412) of the event monitoring and detection device from a first sensitivity level to a second sensitivity level, cause an air movement device (116, 216, 416) to pass air through a testing chamber (104, 204, 404) of the event monitoring and detection device, cause the sensor to take an environmental particulate matter reading of particle sizes of particulates in the air passing through the testing chamber, and transmit the environmental particulate matter reading to a remote computing device (426).

Systems and methods are provided for systems and methods for visualization of automated actions using a holographic agent. A selection of a holographic form of a holographic agent is received. An automated control notification associated with an automated control action is received at a first time. The automated control action is scheduled for implementation at a second time by an autopilot system of a vehicle. The second time is after the first time. An agent action is generated based at least in part on the automated control action. A command is transmitted to a hologram generation system to generate the holographic agent in the selected holographic form to engage in the agent action at the first time. The agent action is a visual representation of the implementation of the automated control action by the autopilot system prior to the implementation of the first automated control action at the second time.

A method of treating an at least partially unconsumed hydrogen generator cartridge including water and a metal hydride includes treating the at least partially unconsumed hydrogen generator cartridge to form a treated hydrogen generator cartridge. When subjected to testing conditions the treated hydrogen generator cartridge produces no hydrogen gas or produces hydrogen gas at a lower rate than the at least partially unconsumed hydrogen generator cartridge subjected to the testing conditions. The testing conditions include heating at less than or equal to 300 °C, agitation, exposing the metal hydride to a protic solvent, or a combination thereof.

Gas turbine engines, rotors thereof, methods for operating the gas turbine engines, and aircraft including the gas turbine engines are provided. The rotors (200) include rotor blades (202) each having an airfoil (202) extending from a root (210) to a tip (212) and having a leading edge (206) and a trailing edge (208), and a rotor disk (204) coupled to the rotor blades configured for rotation with a shaft and to receive a portion of a fluid flow from a fan. The airfoil is configured to have a first camber angle adjacent to the root that is greater than a second camber angle adjacent to the tip, wherein the difference therebetween is at least 15 degrees. The airfoil is configured to have a first stagger angle adjacent to the root that is less than a second stagger angle adjacent to the tip, wherein the difference therebetween is at least 10 degrees.

Systems provide load redistribution and reduced stress at otherwise highly loaded threads. A system for a threaded connection 162 includes a shaft 134 that rotates about an axis 136. The shaft 134 is a hollow cylinder with an inner surface 196 and a wall 194 defined around the inner surface. A fastener 154 is in threaded engagement with the shaft 134. The fastener 154 applies a compressive load holding the shaft 134 under a tensile load. The threaded connection 162 extends from a loaded end 177 adjacent a place of application of the compressive load, to an unloaded end 179 opposite the loaded end. The inner surface 196 has a contour, and the wall 194 has one thickness at the loaded end 177 and another greater thickness at the unloaded end 179, so the wall has more compliance at the loaded end 177 as compared to at the unloaded end 179 to reduce a stress resulting from the load and redistributing stress throughout the threaded connection 162.

A pressure sensor component comprising a base wafer comprising a first piezoresistive Wheatstone bridge that is configured to measure a first pressure range associated with a first pressure that is applied onto a surface of the base wafer; and a top wafer that is coupled to the surface, the top wafer comprising (i) a diaphragm that includes a pin element, (ii) a second piezoresistive Wheatstone bridge that is configured to measure a second pressure range that is associated with a force that opposes the first pressure at a base of the pin element, and (iii) a third piezoresistive Wheatstone bridge that is configured to measure a third pressure range that is associated with beam stress at a perimeter of the diaphragm.

A device and method for extracting digital data from field devices of a process control system connected to a controller on a first network supported by a first protocol for transmission of the digital data to a second network using a second protocol. A bridging device connected to the first network and to the second network includes a first transmission path coupled to the first network that provides bi-directional communication between the field devices and the controller. A second transmission path operatively couples the first network to an extraction component associated with each field device. Each extraction component extracts digital data from the first protocol from each field device connected to the first network. A conversion component operatively coupled to each extraction component is arranged to receive the digital data and convert the digital data into the second protocol for transmission of the digital data on the second network.

An aircraft avionics system of an ownship vehicle comprising: communications circuitry; a user interface (UI); and processing circuitry configured to: receive a first set of information indicating one or more first characteristics of weather formations along a planned route of the ownship vehicle; receive, via the communications circuitry, a second set of information from one or more other vehicles, wherein the second set of information indicate one or more second characteristics of the weather formations, the one or more second characteristics being different from the one or more first characteristics; determine, based on the one or more first characteristics of the weather formations, the one or more second characteristics of the weather formations, and one or more characteristics of the ownship vehicle, an alternate route; and present, via the UI, the alternate route to an operator of the ownship vehicle.

A system and method for displaying taxi guidance information includes receiving, in a processing system, taxi guidance data representative of taxi guidance information for a specific airport. Airport moving map (AMM) data for the specific airport is retrieved, via the processing system, from an AMM data source, and chart data for the specific airport is retrieved, via the processing system, from an airport chart data source. The processing system commands a display device to render an image representative of a published airport chart for the specific airport overlaid onto an airport moving map for the specific airport and with a taxi path that corresponds to the taxi guidance information overlaid onto the airport chart for the specific airport.

A system, comprises: active radar beacon(s) positioned within geographic area and comprising: first antenna(s) and first circuitry configured to encode data into artificial echo(s) by adding adjusted delay into the artificial echo(s), wherein the artificial echo(s) with adjusted delay is transmitted via first antenna(s), wherein artificial echo(s) with adjusted delay emulates return signal; and radar unit onboard vehicle and comprising: second antenna(s); transmitter communicatively coupled to second antenna(s), transmitter configured to transmit radar signals through second antenna(s) to geographic area including active radar beacon(s); receiver communicatively coupled to second antenna(s) and configured to receive return signals from geographic area, return signals including reflected signals reflected from surfaces and artificial echo(s) transmitted from active radar beacon(s); and second circuitry configured to receive and decode data encoded into artificial echo(s) to generate decoded data by detecting changes in a delay in artificial echo(s) received by receiver.

Systems (155) provide damping and centering for rotating machinery. A system includes a ring (206) encircling an axis (172) where the ring is configured to receive a bearing element (208). The ring has a first axially directed face (230)and a second axially directed face. The ring includes fluid apertures (250, 252, 254) that are axially disposed and radially located outward from the axis, the fluid apertures opening through the first axially directed face and through the second axially directed face. The ring includes arcing slits (221-226), each arcing slit beginning at one of the fluid apertures and ending at another of the fluid apertures. A fluid delivery system delivers a fluid to the fluid apertures and/or the slits, at one of the axially directed faces. The fluid delivery system delivers the fluid into the arcing slits so that the fluid in the arcing slits provides a damping action in the ring.

A gas turbine engine fuel supply system includes a fuel manifold, at least one fuel nozzle, and a hydraulic accumulator. The fuel manifold is adapted to receive fuel supplied thereto from a fuel source. The fuel manifold and the fuel have first thermal expansion characteristics. The at least one fuel nozzle is coupled to the fuel manifold and is adapted to inject the fuel supplied to the manifold into a combustor. The hydraulic accumulator is thermally coupled to, and is in fluid communication with, the manifold. The hydraulic accumulator is configured to exhibit second thermal expansion characteristics that are substantially equivalent to the first thermal expansion characteristics.

A method of forming a bonded coil is disclosed. A flat and/or rectangular wire conductor is formed into a spring. The spring is coated with ingredients using a first heat treatment to remove any organic material from the ingredients that cannot withstand temperatures above a first temperature. The spring is compressed into an edge-wound coil. A second heat treatment is performed at a second temperature to bond the edge-wound coil together and form the bonded coil. The bonded coil can operate in a temperature range up to a melting point of the insulation without degradation.

A heat exchanger assembly may include a heat exchanger stack including a plurality of tanks. Each tank of the plurality of tanks may define a tank chamber configured to house a phase change material. The heat exchanger stack may define a plurality of undulating flow paths. Each undulating flow path of the plurality of undulating flow paths may be configured to receive a working fluid between neighboring tanks of the plurality of tanks. A method may include stacking the plurality of tanks to form the heat exchanger stack.

Embodiments of the disclosure provide for improving alignment of a vehicle to a landing site. In the context of a method, the method includes generating transmission signals via a radar altimeter onboard a vehicle, the vehicle being oriented proximate to a landing site comprising a plurality of radio-reflective targets; receiving, via the radar altimeter, a plurality of reflected signals; generating a plurality of power metrics based on the plurality of reflected signals; comparing the plurality of power metrics to a threshold to determine a subset of power metrics associated with the radio-reflective targets; generating alignment correction data based on respective difference values between the subset of power metrics; and causing output of the alignment correction data to a ground station or a control system onboard the vehicle, wherein the alignment correction data comprises at least one parameter for aligning the vehicle with the landing site to minimize the difference values.

A sensing device is disclosed. The sensing device comprises a housing that defines an orifice and a gel positioned within the orifice of the housing and undergoes a change in one or more attributes based on change in temperature or pressure. Further, a membrane is positioned over the orifice and in contact with the gel. The membrane is configured to be positioned in contact with an intravenous (IV) tube carrying media. Further, at least one sensing element is operationally coupled to the gel and detects the change in the one or more attributes of the gel. Thereafter, at least one processing unit is operationally coupled to the at least one sensing element and is configured to determine a temperature output and a pressure output of the media within the IV tube based on the detected change in the one or more attributes of the gel.

A system comprises a gyrocompass unit onboard a vehicle, with the gyrocompass unit comprising an inertial measurement unit (IMU) operative to produce inertial data for the vehicle. At least one processor is in operative communication with the IMU, the at least one processor hosting a set of program modules comprising: a gyrocompassing computation module operative to process the inertial data from the IMU and determine an attitude, heading, or latitude of the vehicle; and an artificial intelligence module including a trained gyrocompassing machine learning model, which is operative to process the inertial data from the IMU and predict an attitude, heading, or latitude of the vehicle. The gyrocompassing computation module is configured to receive the predicted attitude, heading, or latitude from the machine learning model, which operates as an aiding source during initialization or start-up of the gyrocompass unit to reduce an initial alignment time of the gyrocompass unit.

A list of equipment to implement a proposed building automation system may be generated based at least in part on a sequence of operation that describes how the proposed building automation system is to operate. A master standard library of different building automation system components includes a sequence of operation and an IO table for each of the different building automation system components. The sequence of operation that describes how the proposed building automation system is to operate, along with the master standard library of different building automation system components, are provided to a Large Language Model, which is prompted to generate the list of equipment based at least in part on the sequence of operation that describes how the proposed building automation system is to operate and the master standard library of different building automation system components. The list of equipment is outputted.

A method and system is provided for capturing a modified flight descent path for an aircraft has been developed. The method first generates a descent approach path for an aircraft with a flight management system (FMS). A proposed recovery path is generated for the aircraft that rejoins the descent approach path. The proposed recovery path is generated when the aircraft deviates from the descent approach path during flight operations. Inputs for the proposed recovery path for the aircraft are received with the FMS. The inputs are aircraft flight parameters that are received from aircrew members of the aircraft. The proposed recovery path is modified to comply with the inputs from the aircrew members. The modified recovery path is then integrated into the descent approach path with the FMS.

Systems and methods are provided for water management onboard an aircraft. The water management systems include one or more storage devices onboard the aircraft, an outlet configured for rejecting water from the aircraft to an environment exterior to the aircraft, and a controller configured to, by one or more processors: receive aircraft data indicative of operating parameters of the aircraft and, optionally, environmental parameters exterior to the aircraft, determine, based on the aircraft data and one or more water management parameters, a volume of water to be rejected via the outlet, and reject the volume of water from the outlet.

Fly-by-wire vehicle systems and related actuation systems and operating methods are provided for actuating a flight control component. An exemplary method of operating a motor coupled to a flight control component involves determining a time period associated with an electrical cycle based on one or more electrical characteristics associated with a respective phase of the motor during the electrical cycle, calculating an excitation offset based at least in part on the time period associated with the electrical cycle, and thereafter operating a power conversion arrangement to apply a subsequent set of one or more voltage signals to the respective phase of the motor at a respective time within a subsequent electrical cycle corresponding to the excitation offset after a start of the subsequent electrical cycle to align excitation of the respective phase of the motor with an extremum of an electrical characteristic associated with the respective phase.

Apparatuses, systems, and methods are provided for protective assemblies for sensors. In some embodiments, a protective assembly comprises a substrate. In some embodiments, the protective assembly further comprises at least one enclosing port adhered to the substrate. In some embodiments, the protective assembly further comprises one or more electronic components disposed within a cavity of the enclosing port and wire-bonded to the substrate. In some embodiments, the protective assembly further comprises a gel material disposed within the cavity such that it covers the one or more electronic components. In some embodiments, the protective assembly further comprises a fluoropolymer polyimide film (FEP) disposed proximate to a surface of the gel material.

A moisture detecting apparatus comprising an input port; an output port; a housing that is configured between the input port at a first end and the output port at a second end; an adsorbent material that is configured in a flow path of an inner cavity within the housing; and an electrical port comprising a controller that is coupled to the adsorbent material via one or more pin bars, wherein the controller is configured to (i) measure, using the one or more pin bars, one or more voltages on the adsorbent material and (ii) determine an electrical property of the adsorbent material based on the one or more voltages.

An anti-ice/de-ice system includes a component having at least one flow channel extending therethrough, a pressurized air source, and an aerodynamic resonator. The pressurized air source is configured to supply a flow of pressurized air at a first temperature. The aerodynamic resonator includes an inlet nozzle, a resonance tube, and an outlet port. The aerodynamic resonator is coupled to receive, via the inlet nozzle, the flow of pressurized air at the first temperature and configured to discharge, via the outlet port, the flow of pressurized air at a second temperature into the at least one flow channel of the component, wherein the second temperature is greater than the first temperature.

Devices, systems, and methods for determining a change in a field of view of a camera for an apron area of an airport are described herein. In some examples, one or more embodiments include a memory and a processor to execute instructions stored in the memory to compare a ground center line (GCL) mask, generated from an image of an apron area of an airport captured by a camera, with a reference GCL mask, determine whether a field of view (FOV) of the camera has changed from a calibrated FOV of the camera based on the comparison, and generate a notification based on the determination.

A method and system for automatically determining a flight mode display for an electric vertical take-off and landing (eVTOL) aircraft has been developed. First, the flight rules and airspace type that are currently used by the eVTOL aircraft are determined. The flight mode display is automatically set to a traffic avoidance mode if the eVTOL aircraft currently uses VFR and VF are currently used in a congested airspace. The flight mode display is automatically set to an auto-pilot mode if the eVTOL aircraft is operating in an urban air mobility (UAM) corridor. The flight mode display is automatically set to a manual mode if a system failure of the auto-pilot mode occurs.

Size, weight, and cost of an atomic magnetic sensor vacuum chamber, and thus an atomic magnetometer and/or an atomic magnetic gradiometer, is reduced by using at least one photonic integrated circuit (PIC). The at least one PIC is configured to receive an optical signal, e.g., from a laser, and to distribute the optical signal to at least one set of two or more grating coupled surface emitters. Each grating coupled surface emitter is configured to collimate, direct, and emit, along a direction of emission, an optical beam, derived from a portion of the optical signal, to an optical detector.

Embodiments of the present disclosure relate to generating controller logic. Indication of a controller logic generation request associated with an asset identifier may be received. A prompt template set associated with a controller logic generation workflow may be identified based on the asset identifier. The prompt template of the prompt template set may comprise one or more instruction sets. The prompt template set may be input into a large language model comprising one or more transformer neural networks and configured to generate a controller logic configuration file for the asset identifier based on the prompt template set and intent classification associated with each prompt template. The controller logic configuration file may be received from the large language model. Performance of one or more prediction-based actions may be initiated based on the controller logic configuration file.

A method for determining a position of a vehicle-of-interest is provided. The method includes: receiving data including position, velocity, heading and integrity that is broadcast from an ADS-B system from at least two neighboring vehicles in the vicinity of the vehicle-of-interest; determining a distance to, and a direction of travel of, each of the at least two neighboring vehicles using radar on the vehicle-of-interest; receiving a current path of the vehicle-of-interest; calculating a current position and integrity of the vehicle-of-interest based on (1) the data from the at least two neighboring vehicles, (2) the distance to, and direction of travel of, the at least two neighboring vehicles, and (3) the current path of the vehicle-of-interest; checking the integrity of the position received in the data from the at least two neighboring vehicles; and broadcasting a message about the integrity of the position received.

A limit switch is provided. For example, a limit switch may include a housing assembly defining an upper chamber, a lower chamber, and a dividing plate defining a passage between the upper chamber and the lower chamber, a plunger selectively movable relative to the housing assembly, a magnet affixed to a lower portion of the plunger, and a sensor mounted within the lower chamber positioned to interact with the magnet to detect movement of the plunger. A width of the middle portion of the plunger is wider than the passage such that the dividing plate limits movement of the plunger away from its upward-most position. A length of the lower portion of the plunger is selected such that the lower portion of the plunger does not contact a bottom of the lower chamber when the middle portion is in contact with the dividing plate.

A gateway system and method for use in an industrial process control system. The control system has a first network that uses a first communication protocol and at least one second network using a second communication protocol. A network interface is coupled to the second network and to a local area network coupled to the first network. A gateway converts supervisory control and data received on the first network from the controller in the first communication protocol to the second communication protocol and couples the converted supervisory control and data over the local area network to the network interface and the second network. The gateway converts information and data received in the second communication protocol on the local area network from the network interface and the second network to the first communication protocol coupling the converted data and information to the first network.

A system and method for gradually enabling operational capabilities for a pilot returning from a rest phase during flight includes: (a) enabling, via a processing system, only cockpit equipment associated with a first predetermined set of pilot-related tasks, to thereby limit the pilot's ability to conduct only the first predetermined set of pilot-related tasks; (b) assessing, via the processing system, when the pilot is capable of conducting an additional set of pilot-related tasks and, in response, additionally enabling, via the processing system, the cockpit equipment associated with the additional set of pilot-related tasks, to thereby limit the pilot's ability to conduct only the first predetermined set of tasks and the additional set pilot-related tasks; and (c) repeating step (b) until the pilot can conduct all pilot-related tasks.

A first video camera identifies an object of interest in a video frame of a video stream captured by the first video camera. A region of interest (ROI) is cropped out in the video frame of the video stream that corresponds to the object of interest, wherein the cropped-out region including less than all of the video frame of the video stream. The cropped-out region of interest (ROI) of the video frame of the video stream is sent to a second video camera and the second video camera executes a video analytics algorithm on the cropped-out region of interest (ROI) of the video frame of the video stream, resulting in a video analytics result. The second video camera sends the video analytics result to the first video camera.

Various embodiments of optical sensors such as optical leak sensors are provided. Example embodiments of the optical sensors described herein may include an optical prism comprising a plurality of substantially semicylindrical grooves, a plurality of wires disposed within the plurality of substantially semicylindrical grooves (wherein the plurality of wires is configured to provide heat to the sensing surface of the optical prism in response to application of power), and/or a microcontroller configured to provide the power to the plurality of wires.

Various embodiments described herein relate to providing and/or employing a system and a method for tracking emissions in a facility. In this regard, inventory data associated with at least one of a product and a process is collected from a plurality of data sources. As a result, a Product Carbon Footprint (PCF) value associated with the at least one of the product and the process is determined based on the inventory data and corresponding emission factors. Based on at least one change in parameters of the inventory data, the inventory data is updated in real-time. As a result, an updated PCF value is determined in real-time based on the updated inventory data. Accordingly, the updated PCF value is displayed via a user interface of a display device.

Approaches for efficiently and accurately resolving user queries related to a particular premises are described. According to one example, one or more data repositories, associated with the premises, that are to be searched to respond to a user query are identified using a query resolution model. Further, a processing route is determined to search and analyse the one or more data repositories. The user query and the one or more data repositories are then parsed, by the query resolution model, in accordance with the processing route to retrieve and process relevant data from each of the one or more data repositories for generating a final response to the user query. The relevant data may have a context similar to the context of the user query.

An accelerometer system including an accelerometer comprising a proof mass assembly the proof mass assembly comprising: a plurality of dampening plates; at least two proof mass elements, wherein each proof mass element of the at least two proof mass elements is disposed between two dampening plates of the plurality of dampening plates; and a plurality of resonators, wherein at least two resonators of the plurality of resonators is coupled to each proof mass element of the at least two proof mass elements.

Systems and methods for a gas turbine engine (100) with a combustor liner (36) having a wall defining a combustion chamber (40). An injector module (42) extends into the combustion chamber (40) and includes an atomizer body (82). A shroud (72) extends around the atomizer body (82). The shroud (72) defines a coolant chamber (88) within the shroud (72) around the atomizer body (82) configured to receive a coolant. The shroud (72) includes an inner wall (98) configured as an impingement baffle and that defines a plural number of jet holes (202). The shroud (72) defines an outer wall (99) around the inner wall (98) with a cavity (200) defined between the inner wall (98) and the outer wall (99). The outer wall (99) defines a plural number of effusion holes (204) that extend between the cavity (200) and the combustion chamber (40).