Systems, methods, and other embodiments described herein relate to providing time synchronization between devices in a network. In one embodiment, a method includes synchronizing a plurality of remote interface units (RIU) to a single network time. The RIUs are connected in the network. The method includes receiving, by a first of the RIUs, a one pulse-per-second (1PPS) signal. The method further includes determining a 1PPS receive time and a 1PPS period based on the 1PPS signal and with respect to the single network time. The 1PPS receive time refers to when the 1PPS signal is received by the first of the RIUs. The method includes transmitting, by the first of the RIUs, a message to a second of the RIUs. The message includes the 1PPS receive time and 1PPS period. The second of the RIUs is one of the RIUs other than the first of the RIUs.
A rigidizable insertion tool includes a first segment having a pin extension and a second segment having a pin slot that is elongated. The first segment and the second segment are connected via a joint comprising the pin extension of the first segment and the pin slot of the second segment. The pin extension is movable between a proximal end and a distal end of the pin slot with movement of the first segment relative to the second segment.
The present disclosure relates to a system and method for adjusting a tool with a plurality of segments for inserting into a cavity of a machine. The method includes determining an initial alignment measurement of at least a portion of the tool; comparing the initial alignment measurement to a target alignment measurement to determine an adjustment amount; and adjusting at least one of the plurality of segments based on the adjustment amount. The tool includes a plurality of segments moveably coupled, where one or more of the plurality of segments comprises a unique dimensional measurement affecting a fit tolerance.
G01B 5/25 - Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of mechanical techniques for testing the alignment of axes for testing the alignment of axes
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
A system for compensating for a relative motion between a probe and an apparatus. The system includes a probe assembly, a sensor, and a computer. The probe assembly includes an actuator pack positioned exterior to the apparatus and a probe insertable into the apparatus. The probe includes a first end coupled to the actuator pack, a second end, and an elongated body extending therebetween. The sensor senses data indicative of a relative motion between the apparatus and the probe assembly. The computer is operably coupled with the sensor and the probe assembly to move the probe of the probe assembly in response to the sensor sensing the data indicative of the relative motion between the apparatus and the probe assembly.
A method of fabricating a radio-frequency multi-layer circuit includes perforating a silicon wafer to form a plurality of perforations, forming a plurality of vias spaced apart by the plurality of perforations, oxidizing the silicon wafer to provide a silicon oxide wafer, after forming the plurality of vias, filling the plurality of perforations with a fused silica layer to convert the silicon oxide wafer into a fused silica wafer, depositing within the plurality of vias and between the plurality of vias a metal layer connector to electrically connect the plurality of vias, and bonding two or more fused silica wafers together such that the vias of the two or more fused silica wafers are electrically connected to each other to form a radio-frequency circuit.
H01L 21/70 - Manufacture or treatment of devices consisting of a plurality of solid state components or integrated circuits formed in or on a common substrate or of specific parts thereofManufacture of integrated circuit devices or of specific parts thereof
H01L 23/00 - Details of semiconductor or other solid state devices
6.
ONBOARD MAINTENANCE SYSTEM CONFIGURATION GENERATION
Systems, methods, and other embodiments described herein relate to developing a comprehensive set of rules for evaluating the health of an aircraft system. In one embodiment, a method includes receiving text from one or more sources. Each of the sources describes operation of at least a portion of a system. The method includes generating, using at least one natural language processing model, one or more sets of rules based on the text. The method includes generating, using at least one generative model, one or more formatted sets of rules based on at least the sets of rules, a relationship between the sets of rules, and a selected format. The method also includes outputting at least a portion of the formatted sets of rules to an aircraft maintenance system. The aircraft maintenance system is being operated based on at least the portion of the sets of formatted rules.
G07C 5/00 - Registering or indicating the working of vehicles
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
7.
FAULT DETECTION SYSTEM AND POWER DISTRIBUTION SYSTEM HAVING SAME
A fault detection system for detecting an electrical fault in a component includes an optical conductor with a first end and a second end, and configured to optically face the component. A first sensor and a second sensor can be operably coupled to the first end and the second end, respectively. The first sensor and the second sensor are each configured to detect electromagnetic radiation propagating through the optical conductor.
G01R 31/08 - Locating faults in cables, transmission lines, or networks
G01R 31/58 - Testing of lines, cables or conductors
H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
8.
INSPECTION SYSTEMS AND METHODS FOR DAMAGE MEASUREMENT
A system may include a sensor comprising a sensor configured to capture data from a part of an engine. The system being configured to form a three-dimensional (3D) surface model of the part of the engine based on signals received from the sensor system, determine a nonplanar reference surface based on the 3D surface model of the part, and measure a characteristic of a damaged portion of the part of the engine based on the 3D surface model and the nonplanar reference surface.
A system may include an image sensor. A system may include an actuator configured to cause a controlled movement of the image sensor relative to a target element, the controlled movement being based on an operating velocity of the target element relative to an initial position of the image sensor. A system may include a controller communicatively coupled to the image sensor, the controller configured to: identify the operating velocity, determine an activation time to activate the image sensor for a designated exposure time based on the operating velocity and the controlled movement; and activate the image sensor at the activation time.
A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
Systems and methods for engine imaging are provided. An imaging system includes an optical sensor coupled to an insertion tool and a light source configured to output alight projection onto a component of the engine assembly. The system includes a processor configured to: receive data comprising a plurality of frames from the optical sensor captured while the component of the engine assembly is rotating, determine an angular displacement of the component between frames, and form a 3D point cloud of the component based on combining the data in the frames based on the angular displacement of the component between the frames.
A rigidizable insertion tool includes a first segment having a pin extension and a second segment having a pin slot that is elongated. The first segment and the second segment are connected via a joint comprising the pin extension of the first segment and the pin slot of the second segment. The pin extension is movable between a proximal end and a distal end of the pin slot with movement of the first segment relative to the second segment.
An apparatus and method to detect and locate electrical faults in an insulated supply conductor sheathed in a conductive screen is disclosed. The apparatus is positioned along the supply conductor between a power supply and an electrical load. The conductive screen is coupled to an electrical ground via a first resistive element. A voltage on the conductive screen is sensed and compared to a threshold to determine whether a fault condition exists. The apparatus is configured to inject a voltage pulse to the conductive screen and detect a reflected pulse therefrom. The location of the fault condition is determined based on an elapsed time between the injection of the voltage pulse and the detection of the reflected pulse.
A computer implemented method for servicing an engine including receiving information including an initial condition profile, CP1, of the engine; forming a workscope associated with a servicing operation of the engine in view of the initial condition profile, CP1; servicing the engine in view of the workscope; determining at least in part an updated condition profile, CP2, of the engine in view of information acquired during the service; and storing the updated condition profile, CP2, for use in a subsequent service operation.
B60S 5/00 - Servicing, maintaining, repairing, or refitting of vehicles
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
A contactor apparatus and method for operating the contactor apparatus can include a contactor assembly with a contactor coil operably coupled to a contactor switch. One or more sensors can be provided in the contactor assembly adapted to measure one or more aspects of the contactor assembly. Based upon the measured aspects, a controller can initiate operation of the contactor switch to effectively toggle the contactor switch at a zero-crossing point along an alternating current waveform.
H01H 9/56 - Circuit arrangements not adapted to a particular application of the switching device and for which no provision exists elsewhere for ensuring operation of the switch at a predetermined point in the AC cycle
H01H 33/59 - Circuit arrangements not adapted to a particular application of the switch and not otherwise provided for, e.g. for ensuring operation of the switch at a predetermined point in the AC cycle
H01H 47/00 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current
H01H 47/18 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current for modifying the operation of the relay for introducing delay in the operation of the relay
H01H 47/26 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current for supplying energising current for relay coil having thermo-sensitive input
H02H 3/02 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection Details
An aircraft component inspection system is provided. The system includes an image capture system including: an image sensor system, a positioning system, and a processor configured to determine an inspection recipe based at least on an identifier associated with a component of an aircraft being inspected, identify a plurality of locations for performing image capture during an inspection workflow based on the inspection recipe, provide machine instruction to the positioning system to position the image sensor system relative to the component based on the plurality of locations, cause the image sensor system to capture images at the plurality of locations, and store the images with capture location data in an inspection data database.
Propeller control systems and methods for controlling the pitch of a plurality of propeller blades of a variable pitch propeller assembly operatively coupled with an engine is provided. In one exemplary aspect, the propeller control system includes features for combining overspeed and feathering protective functions in a protective control valve communicatively coupled with a controller. In such an event the controller controls the protective control valve to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted based at least in part on the condition of the engine.
An inspection system is provided. The inspection system includes a light source and a surface profile compensator. The light source illuminates a contoured surface of a part. The surface profile compensator causes light emitted from the light source to be distributed over an inspection area of the contoured surface according to a target light distribution.
A selectively flexible extension tool includes a line assembly; and a plurality of sequentially arranged links, the line assembly operable with the plurality of sequentially arranged links to move the plurality of sequentially arranged links between a slacked position and a tensioned position, the plurality of sequentially arranged links spaced from one another when in the slacked position to allow the plurality of sequentially arranged links to pivotably move relative to one another, the plurality of sequentially arranged links pressed against one another when in the tensioned position to rigidly fix the plurality of sequentially arranged links to one another.
A pulse illumination imaging system is provided. The system includes an image sensor, a light source, and a controller. The image sensor includes a plurality of light sensitive pixel elements that are activatable for a designated exposure time to capture one or more images. The controller is configured to determine an activation time to activate the image sensor based on motion of a target element relative to the image sensor; activate the image sensor at the activation time; and activate the light source during the exposure time of the image sensor to produce a pulse having a preconfigured time duration that is less than the exposure time of the image sensor.
Systems and methods for authenticating data transmissions are provided, such as e.g., analog radio streams received at a vehicle. In one aspect, the vehicle includes features that allow for detection and decryption of an encrypted source identifier embedded or introduced into a data transmission transmitted to the vehicle. The source identifier may be used to determine whether the source is authorized to transmit data transmissions to the vehicle and the data transmission may be authenticated accordingly. In another aspect, the vehicle includes features that determine the location of the transmitting device used to transmit the data transmission to the vehicle. The location is then used to determine whether the data transmission should be authenticated.
A modular power distribution apparatus and method includes a frame defined by a first set of parallel supports and a second set of parallel supports, the second set of parallel supports connecting the first set of parallel supports, the frame defining a generally planar assembly, as well as a set of components extending from a side of the frame. The set of components includes a set of power modules.
An insertion tool is provided for an engine defining an access opening and including a component defining at least in part a cavity. The insertion tool includes: an insertion tool arm having a plurality of segments, the insertion tool arm configured for insertion through the access opening into the cavity and the plurality of segments configured to be in a fixed position relative to one another within the cavity; and a base coupled to the insertion tool arm and configured to be positioned outside the cavity and to move the insertion tool arm along at least two degrees of freedom.
Systems and methods of servicing engines, an exemplary method of servicing an engine, the method including receiving, by one or more computing devices, information corresponding to one or more components of the engine; determining, by the one or more computing devices, a location of the one or more components of the engine with respect to a location of an augmented reality device; and presenting, in a current field of view display of the augmented reality device, at least a portion of the information corresponding to the one or more components of the engine, wherein the portion of the information includes a rendering of the one or more components, instructions regarding operations to be performed on the one or more components, directional arrows or contextual information associated with the one or more components, or any combination thereof.
G06V 20/20 - ScenesScene-specific elements in augmented reality scenes
G06V 40/20 - Movements or behaviour, e.g. gesture recognition
G08B 7/06 - Signalling systems according to more than one of groups Personal calling systems according to more than one of groups using electric transmission
G09B 5/06 - Electrically-operated educational appliances with both visual and audible presentation of the material to be studied
G09B 19/00 - Teaching not covered by other main groups of this subclass
A robotic assembly configured to service an engine, wherein the robotic assembly includes an environmental capture device configured to provide information associated with an environment in which the engine is disposed to one or more computing devices, and wherein the one or more computing devices are configured to use the information to inspect the engine before and after repair operations associated with the service to check for repair equipment, or parts thereof, left in the engine after the repair.
B25J 11/00 - Manipulators not otherwise provided for
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
A system and method for adjusting an operator workload during a travel segment includes tracking inputs by an operator into an avionic system responsive to a request from a flight control computer during one or more flights of an aircraft, determining a rate at which the inputs by the operator are made, and determining an operator workload based on the rate. The operator workload can be adjusted when the operator workload exceeds a predetermined threshold.
A spray nozzle includes a first conduit that provides a first flow path for a first type of fluid, a second conduit that provides a second flow path for a second fluid that is different from the first fluid, a first dispensing aperture that ejects therefrom a spray that includes the first type of fluid and/or the second type of fluid, and at least one balancing outlet in fluid communication with the second conduit. The at least one balancing outlet permit the second type of fluid to exit therefrom to balance a force of ejection of the spray from the first dispensing aperture.
B05B 7/08 - Spray pistolsApparatus for discharge with separate outlet orifices, e.g. to form parallel jets, to form intersecting jets
B05B 13/04 - Means for supporting workArrangement or mounting of spray headsAdaptation or arrangement of means for feeding work the spray heads being moved during operation
B05B 15/65 - Mounting arrangements for fluid connection of the spraying apparatus or its outlets to flow conduits
B25J 9/06 - Programme-controlled manipulators characterised by multi-articulated arms
B25J 13/08 - Controls for manipulators by means of sensing devices, e.g. viewing or touching devices
A system and method of using a tool assembly is provided. The system includes a body, a first camera and a second camera fixed to the body, and a controller. The controller is configured to receive data indicative of images of a reference feature from the first camera, determine data indicative of a first spatial position of the first camera based at least in part on the received data indicative of the images of the reference feature, and determine data indicative of a second spatial position of the second camera based on the first spatial position, a known spatial relationship between the first location and the second location, or both. Further, the controller may be configured to receive data indicative of images of a target feature using the second camera, derive dimensions of the target feature based on the images, and generate a three-dimensional representation of the target feature.
An inspection system and related methods that employ directional light for enhanced imaging are provided. The inspection system includes an inspection camera and at least one directional light source positionable in an offset position from a field of view of the inspection camera. The at least one directional light source is configured to emit directional light from the offset position into the field of view of the inspection camera so as to produce shadows on a surface of interest. Further, the inspection system includes a display device coupled to the inspection camera and the inspection camera is configured to capture one or more images of the shadows produced on the surface of interest. The display device is configured to receive and display the one or more images.
An inspection system and related methods are provided. The inspection system includes an inspection camera, a plurality of light sources collocated with the inspection camera, and a post processing system. The plurality of light sources output directional light that have different respective ranges of light wavelengths. The inspection camera is configured to capture image data while a surface of interest is being illuminated with the directional light. Further, the post processing system is configured to receive the image data, process portions of the image data into a plurality of images that include distinct images corresponding to the different respective ranges of light wavelengths. The plurality of images can be reviewed to identify an abnormal region of the surface of interest.
Systems and methods of servicing engines including a method of servicing an engine, the method including navigating at least a portion of a robotic assembly to a location associated with the engine; applying, from the robotic assembly, a medium to one or more adjustable components of the engine while the engine is at an elevated temperature; waiting a duration of time; and with the robotic assembly, operating on the one or more adjustable components.
B25J 19/00 - Accessories fitted to manipulators, e.g. for monitoring, for viewingSafety devices combined with or specially adapted for use in connection with manipulators
A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.
F02K 3/08 - Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluidControl thereof
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
A method of repairing a component of a gas turbine engine in situ, wherein the component includes a deposit, includes directing a flow of gas, which may be an oxygen-containing gas, to the deposit of the component; and heating the component including the deposit while the component is installed in the gas turbine engine and for a duration sufficient to substantially remove the deposit.
A maintenance tool and alignment system are provided having a first optical device and a second optical device. The tool includes the at least two optical devices such that they do not occupy the same space or interfere with the tool's function. In some embodiments, the first and second optical devices define or project a first viewing plane and a second viewing plane. The first viewing plane and second viewing plane are transverse to one another and intersect within a field of view of the first optical device creating an intersection. The intersection of the first and second viewing planes allows for the tool, via a processor or a control device, to alignment the tool within a workspace without a dependence on an estimation of a distance of the tool relative to the workspace.
B25J 13/08 - Controls for manipulators by means of sensing devices, e.g. viewing or touching devices
G01B 11/27 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes for testing the alignment of axes
35.
Turbine engine servicing tool and method for using thereof
A servicing tool for a turbine engine and a method for using thereof are provided. A method includes inserting the tool into an access opening of the turbine engine, contacting a blade of the turbine engine, and removing material from the blade. The tool may comprise a wiper mount and a wiper, including a wiper surface, configured to contact and remove material from the blades. The tool may further comprise a body, an actuator, and fluid flowpaths for deploying the wiper and providing fluid locally to the blades of the turbine engine.
During a maintenance operation and in a predetermined sequence, selected ones of a plurality of gates of a passive balancing electrical network are opened and closed. The passive balancing electrical network is coupled to the plurality of battery cells. The passive balancing electrical network includes multiple unintentional resistances and the multiple unintentional resistances inherent to the plurality of battery cells or a structure of the passive balancing electrical network. These unintentional resistances are utilized to identify location and nature of failures within the network to allow preparing the item for safe handling.
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H01M 10/46 - Accumulators structurally combined with charging apparatus
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
An apparatus comprises a tool having a first portion and a second portion that are separated by at least a first area of articulation. A first inertial measurement unit is affixed with respect to that first portion and a second inertial measurement unit is affixed with respect to that second portion. A control circuit operably couples to those inertial measurement units and receives corresponding information regarding those portions of the tool. The control circuit can then process that received information to generate positional proprioception information as regards those monitored tool portions. By one approach, the control circuit generates that positional proprioception information by first determining an absolute orientation of each of the tool portions independent of one another and then calculating a differential pose as a function of the determined absolute orientation of those tool portions.
A robotic arm is inserted into a passage of a part to be examined. Operator instructions defining a tip motion for a tip of the robotic arm, sensor readings, and an environmental map are received. The operator instructions, the environmental map and sensor readings are applied to a previously trained machine learning model to produce control signals. The control signals to an actuator on the arm to control a movement of the robotic arm allowing the robotic arm to automatically gain traction in the passage and automatically move according to the movement.
An apparatus comprises a tool having a first portion and a second portion that are separated by at least a first area of articulation. A first inertial measurement unit is affixed with respect to that first portion and a second inertial measurement unit is affixed with respect to that second portion. A control circuit operably couples to those inertial measurement units and receives corresponding information regarding those portions of the tool. The control circuit can then process that received information to generate positional proprioception information as regards those monitored tool portions. By one approach, the control circuit generates that positional proprioception information by first determining an absolute orientation of each of the tool portions independent of one another and then calculating a differential pose as a function of the determined absolute orientation of those tool portions.
A robotic arm is inserted into a passage of a part to be examined. Operator instructions defining a tip motion for a tip of the robotic arm, sensor readings, and an environmental map are received. The operator instructions, the environmental map and sensor readings are applied to a previously trained machine learning model to produce control signals. The control signals to an actuator on the arm to control a movement of the robotic arm allowing the robotic arm to automatically gain traction in the passage and automatically move according to the movement.
G01D 5/26 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using optical means, i.e. using infrared, visible or ultraviolet light
G01D 11/00 - Component parts of measuring arrangements not specially adapted for a specific variable
A tool stabilization mechanism is disclosed including a stabilizing device connected to a tool and movable between a deployed position and a non-deployed position, and an actuator for actuating the stabilizing device to move between the deployed position and the non-deployed position. In some forms the tool stabilization mechanism is integrated into a borescope unit, while in other forms it may be an accessory attachable to conventional borescope units. Related methods to the above are also disclosed herein.
An aircraft and method, including a power distribution network and a set of dischargeable power system modules. The dischargeable power system module can include a chassis, a set of replaceable dischargeable energy modules selectively interconnected within the chassis, and an energy management module having a controller module configured to operably control the power distribution from the set of energy modules during aircraft operations, based on the energy demands of the respective subset of the power-consuming subsystems.
A method of operating an energy management system for a fleet of aircraft, can include receiving a desired flight plan database for the fleet of aircraft, defining at least a desired flight plan for each of the fleet of aircraft and a location of each of the fleet of aircraft, and generating a power source inventory distribution plan for the at least a subset of the desired flight plans for the fleet of aircraft.
B60L 58/10 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
B60L 53/50 - Charging stations characterised by energy-storage or power-generation means
B60L 53/60 - Monitoring or controlling charging stations
A contactor apparatus and method for operating the contactor apparatus can include a contactor assembly with a contactor coil operably coupled to a contactor switch. One or more sensors can be provided in the contactor assembly adapted to measure one or more aspects of the contactor assembly. Based upon the measured aspects, a controller can initiate operation of the contactor switch to effectively toggle the contactor switch at a zero-crossing point along an alternating current waveform.
H01H 47/18 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current for modifying the operation of the relay for introducing delay in the operation of the relay
B64D 41/00 - Power installations for auxiliary purposes
H01H 9/56 - Circuit arrangements not adapted to a particular application of the switching device and for which no provision exists elsewhere for ensuring operation of the switch at a predetermined point in the AC cycle
H01H 33/59 - Circuit arrangements not adapted to a particular application of the switch and not otherwise provided for, e.g. for ensuring operation of the switch at a predetermined point in the AC cycle
H01H 47/00 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current
H01H 47/26 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current for supplying energising current for relay coil having thermo-sensitive input
H02H 3/02 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection Details
A method for inspecting and repairing a surface of a component of a gas turbine engine, the method including: inserting an inspection and repair tool into an interior of the gas turbine engine; inspecting the surface of the component with the inspection and repair tool; performing a repair of the surface of the component with the inspection and repair tool from within the interior of the gas turbine engine, the inspection and repair tool remaining within the interior of the gas turbine engine between inspecting the component and performing the repair of the surface of the component.
B05B 15/68 - Arrangements for adjusting the position of spray heads
B05B 15/70 - Arrangements for moving spray heads automatically to or from the working position
B05B 12/12 - Arrangements for controlling deliveryArrangements for controlling the spray area responsive to condition of liquid or other fluent material discharged, of ambient medium or of target responsive to conditions of ambient medium or target, e.g. humidity, temperature
G01N 21/88 - Investigating the presence of flaws, defects or contamination
G01N 21/954 - Inspecting the inner surface of hollow bodies, e.g. bores
46.
Systems and methods of protecting metallic engine components from corrosion
Methods of protecting a metallic substrate from corrosion include introducing an aqueous or powder-form composition including at least one corrosion inhibitor into a crevice that traverses one or more layers covering the metallic substrate to deliver the composition via the crevice into contact with a surface of the metallic substrate. The corrosion inhibitors present in the composition bond to the surface of the metallic substrate, resulting in formation of a film on the surface of the metallic substrate. This film protects the surface of the metallic substrate against corrosion.
The present disclosure relates to a system and method for adjusting a tool with a plurality of segments for inserting into a cavity of a machine. The method includes determining an initial alignment measurement of at least a portion of the tool; comparing the initial alignment measurement to a target alignment measurement to determine an adjustment amount; and adjusting at least one of the plurality of segments based on the adjustment amount. The tool includes a plurality of segments moveably coupled, where one or more of the plurality of segments comprises a unique dimensional measurement affecting a fit tolerance.
G01B 5/25 - Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of mechanical techniques for testing the alignment of axes for testing the alignment of axes
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
The present disclosure relates to a system and method for adjusting a tool with a plurality of segments for inserting into a cavity of a machine. The method includes determining an initial alignment measurement of at least a portion of the tool; comparing the initial alignment measurement to a target alignment measurement to determine an adjustment amount; and adjusting at least one of the plurality of segments based on the adjustment amount. The tool includes a plurality of segments moveably coupled, where one or more of the plurality of segments comprises a unique dimensional measurement affecting a fit tolerance.
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
G12B 5/00 - Adjusting position or attitude, e.g. level, of instruments or other apparatus, or of parts thereofCompensating for the effects of tilting or acceleration, e.g. for optical apparatus
49.
USER INTERFACE FOR AND METHOD OF PRESENTING RAW IMAGE DATA WITH COMPOSITE IMAGE
Methods and systems for presenting raw image data with a composite image are provided. For example, a method comprises displaying a composite image on a user interface; identifying an area of interest on the composite image; and displaying at least one source image on the user interface simultaneously with the composite image, the at least one source image containing at least one pixel in the area of interest. As another example, a method comprises projecting a composite image onto a representation of a three-dimensional (3D) surface displayed on a user interface to produce a 3D composite image and changing an orientation of the 3D composite image in response to a user input prior to identifying an area of interest on the 3D composite image. An image display system comprising a user interface is configured to simultaneously display the composite image and a plurality of source images.
Multi-semiconductor SSPCs that solve bus level problems affecting systems as well as controller level problems affecting individual multi-semiconductor SSPCs are disclosed. Bus level and controller level problems adversely affect multi-semiconductor SSPCs and their associated systems. The disclosed multi-semiconductor SSPCs solve both bus level and controller level problems by implementing controlled rate-change of voltage (dv/dt) ramp-on rate, to ensure that the voltage on the input bus does not collapse when a multi-semiconductor SSPC is commanded closed and that a minimum amount of power is being dissipated evenly across the switching semiconductors.
H02H 9/04 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess voltage
H02H 9/00 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection
H03K 17/0812 - Modifications for protecting switching circuit against overcurrent or overvoltage without feedback from the output circuit to the control circuit by measures taken in the control circuit
An insertion tool with a flexible spine and a method for forming thereof are provided. A method includes placing a plurality of links, a flexible spine, and a line assembly into a channel of a fixturing assembly, pulling, via the line assembly, the plurality of links into a tensioned state in the channel, and affixing the flexible spine to each of the plurality of links while in the tensioned state. An insertion tool comprising a plurality of links arranged in a sequence, a flexible spine affixed to three or more links of the plurality of links, and a line assembly inserted through line guides in each of the plurality of links, the line assembly being configured to actuate the plurality of links from a free state to a tensioned state.
B25J 9/06 - Programme-controlled manipulators characterised by multi-articulated arms
B25J 9/10 - Programme-controlled manipulators characterised by positioning means for manipulator elements
B25J 19/00 - Accessories fitted to manipulators, e.g. for monitoring, for viewingSafety devices combined with or specially adapted for use in connection with manipulators
An insertion tool with a flexible spine and a method for forming thereof are provided. A method includes placing a plurality of links, a flexible spine, and a line assembly into a channel of a fixturing assembly, pulling, via the line assembly, the plurality of links into a tensioned state in the channel, and affixing the flexible spine to each of the plurality of links while in the tensioned state. An insertion tool comprising a plurality of links arranged in a sequence, a flexible spine affixed to three or more links of the plurality of links, and a line assembly inserted through line guides in each of the plurality of links, the line assembly being configured to actuate the plurality of links from a free state to a tensioned state.
A non-transitory computer-readable medium and apparatus for restoring navigational performance for a navigational system. The apparatus including a receiver for receiving by a first navigational system and a second navigational system a collection of data points to establish a real-time navigational route for the aircraft, and a computer for comparing navigational performance values or drift ranges. The computer capable of establishing a new navigational route based on the collection of data points.
G01S 19/49 - Determining position by combining or switching between position solutions derived from the satellite radio beacon positioning system and position solutions derived from a further system whereby the further system is an inertial position system, e.g. loosely-coupled
G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation
54.
Method and system for enabling component monitoring redundancy in a digital network of intelligent sensing devices
Techniques for employing a smart sensor device that has a primary sensing function for sensing a state of a physical component and can concurrently enable one or more backup functions for sensing one or more states of one or more other physicals components in response to one or more other smart sensor devices not being able to perform their primary function of sensing and/or reporting on the one or more states of the one or more other physical components.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B64F 5/60 - Testing or inspecting aircraft components or systems
F16H 57/01 - Monitoring wear or stress of gearing elements, e.g. for triggering maintenance
G07C 5/00 - Registering or indicating the working of vehicles
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
A system and method of using a tool assembly is provided. The system includes a body, a first camera and a second camera fixed to the body, and a controller. The controller is configured to receive data indicative of images of a reference feature from the first camera, determine data indicative of a first spatial position of the first camera based at least in part on the received data indicative of the images of the reference feature, and determine data indicative of a second spatial position of the second camera based on the first spatial position, a known spatial relationship between the first location and the second location, or both. Further, the controller may be configured to receive data indicative of images of a target feature using the second camera, derive dimensions of the target feature based on the images, and generate a three-dimensional representation of the target feature.
A method for inspecting an object includes determining guide image data of the object from a determined orientation, the guide image data including a guide image pixel array and a pixel property for at least one guide image pixel in the guide image pixel array. The method also includes receiving inspection image data indicative of an inspection image and associating the inspection image data with the guide image data with a processor of a computing device. Additionally, the method includes determining a property of the object based on the guide image data and the associated inspection image data.
A method for inspecting an object includes determining a first inspection package that includes a first inspection image of the object and a first designation. The method includes determining data indicative of a second inspection package that includes a second inspection image of the object and a second designation. The method includes determining a first property of the object based on the first inspection image of the object, one or more properties maps of the object, and the first designation. The method includes determining a second property of the object based on the second inspection image of the object, the one or more properties maps of the object, and the second designation. The method includes displaying the first property and the second property or displaying data indicative of a comparison of the first property with the second property.
G06T 7/564 - Depth or shape recovery from multiple images from contours
G06T 17/20 - Wire-frame description, e.g. polygonalisation or tessellation
G01B 11/25 - Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures by projecting a pattern, e.g. moiré fringes, on the object
An aircraft and non-transitory computer-readable medium for detecting the spoofing of a signal from a satellite in orbit. A receiver on the aircraft to receive an apparent satellite signal. A computer for determining at least two characteristic signatures of the signal including a power level, and indicating the apparent satellite signal is a spoofed satellite signal.
A method for inspecting an object includes receiving or determining inspection image data, the inspection image data including an inspection image pixel array with at least one inspection image pixel in the inspection image pixel array having a pixel property associated therewith. The method includes receiving via a processor a user input associated with a continuous segment of inspection image pixels in the inspection image pixel array. The method includes determining a property of the object based on the pixel properties associated with the continuous segment of inspection image pixels in the inspection image pixel array.
An aerial vehicle is provided. The aerial vehicle can include a plurality of sensors mounted thereon, an avionics system configured to operate at least a portion of the aerial vehicle, and a machine vision controller in operative communication with the avionics system and the plurality of sensors. The machine vision controller is configured to perform a method. The method includes obtaining sensor data from at least one sensor of the plurality of sensors, determining performance data from the avionic system or an additional sensor of the plurality of sensors, processing the sensor data based on the performance data to compensate for movement of the unmanned aerial vehicle, identifying at least one geographic indicator based on processing the sensor data, and determining a geographic location of the aerial vehicle based on the at least one geographic indicator.
A mechanical arm assembly including a bendable arm. In some embodiments, the bendable arm includes a body including a plurality of links and a plurality of joints movably coupling the plurality of links; and a plurality of wires including one or more control wires. For example, the body encloses at least a portion of each of the plurality of wires and defines a plurality of openings with each wire in the plurality of wires extending through at least one respective opening of the plurality of openings. The one or more control wires may be moveably positioned within at least a portion of the body enclosing the one or more control wires. In some embodiments, each control wire terminates at a corresponding link. For example, a first control wire terminates at a first link and a second control wire terminates at a second link of the plurality of links.
Systems and methods for treating a component of an installed and assembled gas turbine engine are provided. Accordingly, the method includes operably coupling a delivery assembly to an annular inlet of a core gas turbine engine. A portion of treating fluid is atomized with the delivery assembly to develop a treating mist having a plurality of atomized droplets. The atomized droplets are suspended within any path of the core gas turbine engine from the annular inlet to an axial position downstream of a compressor of the core gas turbine engine. A portion of the treating mist is impacted or precipitated onto the component so as to wet the component, and a portion of the deposits on the component is dissolved by the treating mist.
A system and method preserves raw vibration data for a physical event involving a transport vehicle such as a helicopter, plane, boat, car, or truck. The event may involve unexpected mechanical stresses on the vehicle. The system and method preserves raw vibration data for parts of the transport vehicle, such as from multiple points along the drive train. The preserved raw vibration data includes data from time prior to the physical event. In an embodiment, the system and method continuously detects vibration data, and stores the most recent vibration data in a circular memory buffer. The buffer is continually updated with the most current vibration data. When an event is automatically detected or manually triggered, the most recently saved vibration data is transferred from the buffer to permanent storage, along with vibration data obtained subsequent to the event. This allows for a more thorough post-event analysis.
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
B64F 5/60 - Testing or inspecting aircraft components or systems
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
A network switch includes a first port configured for communication with a first electric device and a second port configured for communication with a second electric device in a deterministic network. The network switch includes one or more processors configured to receive at the first port a communication packet associated with the first electric device and the second electric device, determine if the communication packet satisfies a plurality of protocol constraints, and in response to the communication packet satisfying the plurality of protocol constraints, input one or more message characteristics from the communication packet into a model associated with a first industrial process. The model is configured to output a process behavioral classification based on the one or more message characteristics. The one or more processors receive a process behavioral classification for the communication packet, and selectively generate a control action for the ICS based on the process behavioral classification.
H04L 47/2441 - Traffic characterised by specific attributes, e.g. priority or QoS relying on flow classification, e.g. using integrated services [IntServ]
H04L 43/04 - Processing captured monitoring data, e.g. for logfile generation
H04L 67/12 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
H04L 45/00 - Routing or path finding of packets in data switching networks
A method for updating a flight plan by an avionics device includes receiving a first flight plan comprising a first set of flight parameters having at least one fuel-related first flight parameter, receiving a second flight plan for a subsequent second flight, the second flight plan based on a fuel remaining in the aircraft without refueling subsequent to the first flight, and receiving an update to the first flight plan. The method further includes, determining, with the avionics device, a set of first updated flight parameters comprising at least one fuel-related first updated flight parameter, determining, whether the fuel-related first updated flight parameter will satisfy predetermined criteria of the second flight plan, and when the fuel-related first updated flight parameter will not satisfy the predetermined criteria, displaying a first notification onboard the aircraft, and receiving a selection of a refueling locations.
A method for validating, with a first computing device onboard an aircraft, a flight plan having a set of first flight parameters comprising respective first values, loaded onto the first computing device of an aircraft includes receiving from a second source, by the first computing device, data comprising a set of second flight parameters having respective second values corresponding to the set of first flight parameters. The method includes comparing the first values of the set of first flight parameters to the second values of the corresponding set of second flight parameters by the first computing device, determining, whether an implausible condition exists. When an implausible condition is determined, the method includes automatically displaying a first notification on a display device in the aircraft, requesting a modification to the set of first flight parameters, and receiving a modification to the loaded flight plan based on the notification.
An extension tool has a proximal end and a distal end and comprises a plurality of sequentially arranged links moveable relative to one another and a support member defining the distal end and including a first wheel disposed at the distal end and a second wheel spaced apart from the first wheel. Additionally, or alternatively, an extension tool may comprise a plurality of windows defined in the plurality of sequentially arranged links. The windows are defined periodically along the plurality of sequentially arranged links such that a periodicity of the widows corresponds to a periodicity of a plurality of features of the component.
B25J 19/00 - Accessories fitted to manipulators, e.g. for monitoring, for viewingSafety devices combined with or specially adapted for use in connection with manipulators
Extension tools and methods of inserting extension tools within components are provided. For example, an extension tool has a proximal end and a distal end and comprises a plurality of sequentially arranged links moveable relative to one another and a support member defining the distal end and including a first wheel disposed at the distal end and a second wheel spaced apart from the first wheel. Additionally, or alternatively, an extension tool may comprise a plurality of windows defined in the plurality of sequentially arranged links. The windows are defined periodically along the plurality of sequentially arranged links such that a periodicity of the windows corresponds to a periodicity of a plurality of features of the component.
Systems, computer-implemented methods and/or computer program products that facilitate measuring weight and balance and optimizing center of gravity are provided. In one embodiment, a system 100 utilizes a processor 106 that executes computer implemented components stored in a memory 104. A compression component 108 calculates compression of landing gear struts based on height above ground of an aircraft. A gravity component 110 determines center of gravity based on differential compression of the landing gear struts. An optimization component 112 automatically optimizes the center of gravity to a rear limit of a center of gravity margin.
B64C 17/02 - Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus
B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
B64D 31/06 - Initiating means actuated automatically
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
F02C 9/50 - Control of fuel supply conjointly with another control of the plant with control of working fluid flow
G01G 19/07 - Weighing apparatus or methods adapted for special purposes not provided for in groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
G01M 1/12 - Static balancingDetermining position of centre of gravity
A method of controlling an aircraft includes tracking, using at least one sensor, one of an input by a pilot or a biometric parameter of a first pilot during flight of the aircraft. The method also includes determining a lack of attention by the pilot or a depth of sleep of the pilot based on the biometric parameter.
A tool for inserting into a cavity is provided. The tool includes a plurality of segments moveably coupled to one another, each segment moveable relative to an adjacent segment between a bent position and a coupled position, the plurality of segments including a first segment, the first segment including: a core formed of a first material; and a shell formed of a second material and comprising or defining a guide feature, a drive feature, a line guide, or a combination thereof; wherein the first material defines a greater stiffness than the second material.
A method of assessing an operator emotional state and sending an alert based on the emotional state. The method includes tracking during a time period, using at least one sensor, one of an image sensor data, voice data or a biometric parameter of an operator. Determining, using a controller that is operatively connected to at least one sensor, a probability of a likely emotional state from a list of emotional states of an operator based on one of the image sensor data, voice data or the biometric parameter. Comparing, using a processor, the probability of one of the likely emotional states of the operator with a baseline emotional state of the operator. Sending, using the controller, an alert if most likely emotional state deviates from the baseline emotional state by a predetermined threshold.
G06K 9/00 - Methods or arrangements for reading or recognising printed or written characters or for recognising patterns, e.g. fingerprints
G06V 40/20 - Movements or behaviour, e.g. gesture recognition
A61B 5/18 - Devices for psychotechnicsTesting reaction times for vehicle drivers
G10L 25/63 - Speech or voice analysis techniques not restricted to a single one of groups specially adapted for particular use for comparison or discrimination for estimating an emotional state
An insertion tool for performing an operation on equipment, the insertion tool including: a plurality of segments, each segment of the plurality of segments including a body comprising: a first hinge; and a second hinge, the first hinge of a first segment being coupled to the second hinge of a second segment adjacent to the first segment through an interface, wherein the interface comprises a powder gap, a multi-modal interface, a compliance feature, a displace-to-lock configuration, an interference fit, or any combination thereof, wherein the insertion tool is configured to be selectively rigidizable using a strength member interfacing with the plurality of segments.
A cable tensioning system including: a body defining a balance point; a cable receiving area having gripping elements configured to grip and bias a cable relative to the cable tensioning system; and a sensor configured to sense changes to a balance of the body about the balance point, wherein the cable tensioning system is configured to maintain the cable within a preset range of tensions
An insertion tool for performing an operation on equipment, the insertion tool including: a plurality of segments, each segment of the plurality of segments including a body including: a first hinge; a second hinge, the first and second hinge members pivotally coupling adjacent segments of the plurality of segments together; and a cavity extending along the body of the segment, the cavity exiting the body at a plurality of exit locations, wherein at least one of the plurality of exit locations is disposed adjacent to the first hinge; and a selectively rigidizable strength member disposed within the cavity.
A cable tensioning system including: a body defining a balance point; a cable receiving area having gripping elements configured to grip and bias a cable relative to the cable tensioning system; and a sensor configured to sense changes to a balance of the body about the balance point, wherein the cable tensioning system is configured to maintain the cable within a preset range of tensions.
B65H 59/28 - Co-operating surfaces mounted for relative movement and arranged to deflect material from straight path the surfaces being urged towards each other
B65H 59/38 - Adjusting or controlling tension in filamentary material, e.g. for preventing snarlingApplications of tension indicators by regulating speed of driving mechanism of unwinding, paying-out, forwarding, winding, or depositing devices, e.g. automatically in response to variations in tension
B65H 59/34 - Surfaces movable automatically to compensate for variation in tension
An insertion tool for performing an operation on equipment, the insertion tool including: a plurality of segments, each segment of the plurality of segments including a body including: a first hinge; a second hinge, the first and second hinge members pivotally coupling adjacent segments of the plurality of segments together; and a cavity extending along the body of the segment, the cavity exiting the body at a plurality of exit locations, wherein at least one of the plurality of exit locations is disposed adjacent to the first hinge; and a selectively rigidizable strength member disposed within the cavity.
B25B 33/00 - Hand tools not covered by any other group in this subclass
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
78.
INSERTION TOOL WITH RIGIDIZED AND NON-RIGIDIZED CONFIGURATIONS
An insertion tool for performing an operation on equipment, the insertion tool including: a plurality of segments, each segment of the plurality of segments including a body comprising: a first hinge; and a second hinge, the first hinge of a first segment being coupled to the second hinge of a second segment adjacent to the first segment through an interface, wherein the interface comprises a powder gap, a multi-modal interface, a compliance feature, a displace-to-lock configuration, an interference fit, or any combination thereof, wherein the insertion tool is configured to be selectively rigidizable using a strength member interfacing with the plurality of segments.
B25B 33/00 - Hand tools not covered by any other group in this subclass
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
A tool system for inserting into a cavity, the tool system including a first continuum having a flexible body defining a connection interface; and a second continuum having a flexible body defining a connection interface; and an engagement mechanism configured to couple the connection interfaces of the first and second continua together to form the tool.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
G01N 21/88 - Investigating the presence of flaws, defects or contamination
G01N 21/954 - Inspecting the inner surface of hollow bodies, e.g. bores
A tool system for inserting into a cavity, the tool system including a first continuum having a flexible body defining a connection interface; and a second continuum having a flexible body defining a connection interface; and an engagement mechanism configured to couple the connection interfaces of the first and second continua together to form the tool.
B64F 5/60 - Testing or inspecting aircraft components or systems
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
G01N 21/954 - Inspecting the inner surface of hollow bodies, e.g. bores
81.
System and method for operating a power distribution system
A method and power distribution system for operating in a low power consumption mode includes a primary power distribution node defining a primary distribution switch having an output and operable in a first conducting mode and a second non-conducting mode, and wherein operating in the second non-conducting mode includes a leakage current through the power distribution switch, at least one enabled electrical load downstream of the primary power distribution node, the at least one enabled electrical load connectable to the primary power distribution node by way of the primary distribution switch, and a primary power distribution node power source configured to supply power to the output of the primary distribution switch when the primary distribution switch is operating in the second non-conducting mode.
B64D 41/00 - Power installations for auxiliary purposes
H02J 3/14 - Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load by switching loads on to, or off from, network, e.g. progressively balanced loading
H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
Systems and methods of servicing equipment including determining, by one or more computing devices, a workscope associated with the equipment; and at least partially-autonomously servicing the equipment in response to the determined workscope.
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
A method of kitting a robotic assembly for servicing aviation equipment including determining a current workscope associated with the equipment; determining at least one of parts and tooling associated with the current workscope; equipping the robotic assembly with at least some of the determined parts, tooling, or both; and the robotic assembly at least partially autonomously servicing the equipment using the equipped parts, tooling, or both.
A method of servicing equipment, the method comprising: recording information associated with servicing of the equipment in view of a workscope at a first location; sending the recorded information to a node; receiving service input from a third party located at a second location different from the first location, the third party having prepared the service input in response to the recorded information on the node; and performing the service using the received service input.
A method of detecting damage to a gas turbine engine, the method including observing a thermal response of the engine during a thermal transition occurring when the engine transitions between an elevated temperature and a lesser temperature; determining potential damage to the gas turbine engine based on the observed thermal response of the gas turbine engine; and generating an action in response to the determined potential damage to the gas turbine engine.
F01D 21/12 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to temperature
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
F01D 21/20 - Checking operation of shut-down devices
Systems and methods of servicing engines, an exemplary method of servicing an engine, the method including receiving, by one or more computing devices, information corresponding to one or more components of the engine; determining, by the one or more computing devices, a location of the one or more components of the engine with respect to a location of an augmented reality device; and presenting, in a current field of view display of the augmented reality device, at least a portion of the information corresponding to the one or more components of the engine, wherein the portion of the information includes a rendering of the one or more components, instructions regarding operations to be performed on the one or more components, directional arrows or contextual information associated with the one or more components, or any combination thereof.
G06V 20/20 - ScenesScene-specific elements in augmented reality scenes
G06V 40/20 - Movements or behaviour, e.g. gesture recognition
G08B 7/06 - Signalling systems according to more than one of groups Personal calling systems according to more than one of groups using electric transmission
G09B 5/06 - Electrically-operated educational appliances with both visual and audible presentation of the material to be studied
G09B 19/00 - Teaching not covered by other main groups of this subclass
A method of servicing aviation equipment including at least partially-autonomously inspecting components of the equipment using an environmental capture device, wherein at least partially-autonomous inspection includes: capturing information associated with the equipment using the environmental capture device; identifying the components of the equipment using one or more computing devices; determining, by the one or more computing devices, whether each identified component is properly positioned relative to the equipment using reference information; and for components not properly positioned relative to the equipment, determining if there is damage to the component or equipment.
G07C 5/00 - Registering or indicating the working of vehicles
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
A computer implemented method for servicing an engine including receiving information including an initial condition profile, CP1, of the engine; forming a workscope associated with a servicing operation of the engine in view of the initial condition profile, CP1; servicing the engine in view of the workscope; determining at least in part an updated condition profile, CP2, of the engine in view of information acquired during the service; and storing the updated condition profile, CP2, for use in a subsequent service operation.
B60S 5/00 - Servicing, maintaining, repairing, or refitting of vehicles
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
A robotic assembly for servicing equipment, the robotic assembly including an area configured to receive components associated with a workscope of the equipment; an environmental capture device configured to capture information associated with an environment in which the robotic assembly is disposed; and one or more computing devices configured to: locate the equipment in the environment; autonomously navigate the robotic assembly through the environment to the equipment; and autonomously adjust a position of the robotic assembly in response to the workscope.
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
Systems and methods of servicing engines including a method of servicing an engine, the method including navigating at least a portion of a robotic assembly to a location associated with the engine; applying, from the robotic assembly, a medium to one or more adjustable components of the engine while the engine is at an elevated temperature; waiting a duration of time; and with the robotic assembly, operating on the one or more adjustable components.
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
A robotic assembly configured to service an engine, wherein the robotic assembly includes an environmental capture device configured to provide information associated with an environment in which the engine is disposed to one or more computing devices, and wherein the one or more computing devices are configured to use the information to inspect the engine before and after repair operations associated with the service to check for repair equipment, or parts thereof, left in the engine after the repair.
B60S 5/00 - Servicing, maintaining, repairing, or refitting of vehicles
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
A method for updating, for an aircraft, a first flight plan having a first set of flight parameters, includes receiving, via an avionics device, a change to the first flight plan, determining a second set of flight parameters based on the change to the first flight plan, receiving, by the avionics device, at least one of terrain data and special use airspace (SUA) data. The method includes performing, with the avionics device, a safety validation of the second set of flight parameters, wherein the safety validation comprises: comparing the second set of flight parameters with the received at least one of terrain data and SUA data, and determining, based on the comparison, whether the second set of flight parameters presents a risk to safe flight.
Systems and methods for treating a component of an installed and assembled gas turbine engine are provided. Accordingly, the method includes operably coupling a delivery assembly to an annular inlet of a core gas turbine engine. A portion of treating fluid is atomized with the delivery assembly to develop a treating mist having a plurality of atomized droplets. The atomized droplets are suspended within any path of the core gas turbine engine from the annular inlet to an axial position downstream of a compressor of the core gas turbine engine. A portion of the treating mist is impacted or precipitated onto the component so as to wet the component, and a portion of the deposits on the component is dissolved by the treating mist.
A power distribution node, includes a power switch controllably operable to supply energy from an input to an output when the power switch is closed and to not supply energy from the input to the output when the power switch is open, a controller module, a supply power source connected with and energizing the controller module, and a control circuit configured to sense a power characteristic of the power distribution node.
B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
H02J 9/06 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over
B64D 41/00 - Power installations for auxiliary purposes
G06F 1/3206 - Monitoring of events, devices or parameters that trigger a change in power modality
H02H 1/00 - Details of emergency protective circuit arrangements
H02H 9/02 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess current
A power distribution panel with a backplane, an insulating panel covering the backplane, and at least one electronic component mounted to the insulating panel. A set of feet can be mounted to the insulating panel and configured to absorb stress applied to the insulating panel where the set of feet are located in the same plane as the backplane.
A contactor apparatus and method for operating the contactor apparatus can include a contactor assembly with a contactor coil operably coupled to a contactor switch. One or more sensors can be provided in the contactor assembly adapted to measure one or more aspects of the contactor assembly. Based upon the measured aspects, a controller can initiate operation of the contactor switch to effectively toggle the contactor switch at a zero-crossing point along an alternating current waveform.
H01H 47/18 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current for modifying the operation of the relay for introducing delay in the operation of the relay
H01H 47/00 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current
B64D 41/00 - Power installations for auxiliary purposes
H01H 47/26 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current for supplying energising current for relay coil having thermo-sensitive input
H01H 33/59 - Circuit arrangements not adapted to a particular application of the switch and not otherwise provided for, e.g. for ensuring operation of the switch at a predetermined point in the AC cycle
H01H 9/56 - Circuit arrangements not adapted to a particular application of the switching device and for which no provision exists elsewhere for ensuring operation of the switch at a predetermined point in the AC cycle
H02H 3/02 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection Details
A heat sink for a heat-generating component of an electronic device has a backbone panel with opposing upper and lower surfaces. Cooling elements extend away from the upper surface of the heat sink and terminate in upper ends that define a topological surface. Thermally conducting structures extend away from the lower surface of the heat sink and terminate in tips that define a surface that is complementary to the surface of the heat-generating component of the electronic device.
F28F 3/04 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
F28F 13/06 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
A system and method for compiling and monitoring a list of operational aircraft components to determine if a threshold is met. Utilizing the list and the threshold can provide for monitoring the network of aircraft components to monitor both health and security of the aircraft network and components thereof. The system can then indicate or alert when a threshold is met or exceeded. Such an alert can be on a display to a pilot, for example, or to a remote monitoring station.
H04L 41/06 - Management of faults, events, alarms or notifications
H04L 41/0681 - Configuration of triggering conditions
H04L 41/0686 - Additional information in the notification, e.g. enhancement of specific meta-data
H04L 41/0853 - Retrieval of network configurationTracking network configuration history by actively collecting configuration information or by backing up configuration information
H04L 43/067 - Generation of reports using time frame reporting
A method and circuit for determining and extinguishing electrical faults includes a power supply, and electrical load, a controller module, and electrical sensors, and when the controller module does not extinguish the electrical fault, another switch blows a fuse.
H02H 7/22 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for distribution gear, e.g. bus-bar systemsEmergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for switching devices
A method for updating a flight plan comprising, via an avionics device, at least a portion of a flight plan from an external source, authenticating or validating the update, generating a set of updated flight parameters, comparing the set of updated flight parameters with a current set of flight parameters, receiving a set of environmental conditions, performing a series of plausibility checks and automatically updating at least a portion of the flight plan or generating an indication.
