A method and aircraft power distribution system includes a power distribution bus supplying power along an electrical line, a primary communication module including a primary transceiver and a primary controller, and a plurality of secondary communication modules including a secondary transceiver communicatively coupled to the primary transceiver and a secondary controller communicatively coupled to the secondary transceiver.
H02J 3/38 - Arrangements for parallelly feeding a single network by two or more generators, converters or transformers
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 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 network; Circuit 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
2.
ACCURATE AND FAST POWER MODULE PROPERTIES ASSESSMENT
Systems and methods for accurate and fast measurement of junction temperature for power modules are provided. Such systems and methods include a one or more power transistors that each have a respective die surface over which is positioned and electrically coupled to a conductive overlay. A temperature sensor is physically bonded to a top surface of the conductive overlay to provide a direct temperature measurement for the one or more power transistors.
H01L 23/34 - Arrangements for cooling, heating, ventilating or temperature compensation
G01K 1/143 - Supports; Fastening devices; Arrangements for mounting thermometers in particular locations for measuring surface temperatures
G01K 7/02 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using thermoelectric elements, e.g. thermocouples
G01K 7/16 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using resistive elements
G01R 19/165 - Indicating that current or voltage is either above or below a predetermined value or within or outside a predetermined range of values
H01L 23/00 - SEMICONDUCTOR DEVICES NOT COVERED BY CLASS - Details of semiconductor or other solid state devices
H01L 23/538 - Arrangements for conducting electric current within the device in operation from one component to another the interconnection structure between a plurality of semiconductor chips being formed on, or in, insulating substrates
H01L 25/07 - Assemblies consisting of a plurality of individual semiconductor or other solid state devices all the devices being of a type provided for in the same subgroup of groups , or in a single subclass of , , e.g. assemblies of rectifier diodes the devices not having separate containers the devices being of a type provided for in group
H02H 7/12 - 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 norm for rectifiers for static converters or rectifiers
3.
ENERGY ACCUMULATOR APPARATUS AND ASSOCIATED METHODS
An energy accumulator module (EAM) is coupleable electrically in parallel between a power source and an electrical load via a first transmission line and a second transmission line, to receive a DC voltage from the power source. The EAM includes a power converter having inductor coupled at a first end to the first transmission line, and at a second end to a node, a switching stage including a buck leg and a boost leg, and a capacitor coupled electrically in series between the boost leg and the second transmission line. A controller module is configured to control the switching stage to operate in one of a charge mode to charge the capacitor, and a discharge mode to provide a current to the first transmission line.
H02M 3/158 - Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators including plural semiconductor devices as final control devices for a single load
H02M 1/00 - APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF - Details of apparatus for conversion
The disclosure relates to an apparatus for connecting an electronic component to a conductor. A housing includes at least one slot and defines at least one component chamber for carrying the electronic component. A liquid coolant can pass through the housing. A pair of conductive members extends from the housing through the at least one slot and can be releasably inserted into a channel defined in a support assembly. The support assembly facilitates an electrical connection between the conductive members and corresponding conductive contact members connected to a respective power supply or electrical load. The support assembly can provide an inward sealing force to a seal on the housing circumscribing the pair of conductive members.
H01R 33/88 - Coupling devices specially adapted for supporting apparatus and having one part acting as a holder providing support and electrical connection via a counterpart which is structurally associated with the apparatus, e.g. lamp holders; Separate parts thereof adapted for simultaneous co-operation with two or more identical counterparts
H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating
H01R 31/06 - Intermediate parts for linking two coupling parts, e.g. adapter
A method of transmitting a set of conforming data frames within an avionics system. The avionics system including a Flight Management System (FMS) and an avionics device. The method including generating, via the avionics device, at least one specialized message, transmitting, via the avionics device, the at least on specialized message, generating, via the avionics device, the set of conforming data frames, and transmitting, via the avionics device, at least a subset of the set of conforming data frames. The method comprising receiving, via the FMS, at least one transmission including at least one of the specialized header frame or the set of conforming data frames from the avionics device.
A rotor assembly for an electric machine includes a first end and a second end, the second end distal from the first end in an axial direction, a first radial wall extending between the first end and the second end and defining an inner cavity, and a second radial wall extending between the first end and the second end, the second radial wall radially-overlying the first radial wall and defining an outer cavity between the first radial wall and the second radial wall.
H02K 1/32 - Rotating parts of the magnetic circuit with channels or ducts for flow of cooling medium
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/04 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for rectification
A passive cooling system for aircraft electronics includes an electronics chassis having a chassis exterior and defining a chassis interior; a heat spreader having a body located in the chassis interior; a heatsink located in the chassis interior; a cold plate operably coupled to the electronic chassis and thermally coupled to the heatsink; a first plurality of heat pipes thermally coupled with the cold plate; and a second plurality of heat pipes thermally coupling the heatsink with the heat spreader.
A system and method for generating a time-sensitive network schedule for a desired TSN includes defining a network topology of the desired TSN including at least a set of end nodes communicative connected by way of a set of switching nodes, defining a set of device parameters for each of the set of end nodes and each of the set of switching nodes of the desired TSN, determining, by a TSN scheduler, a TSN schedule for the desired TSN based on the defined network topology and the defined set of device parameters for each of the set of end nodes and each of the set of switching nodes, and generating a per-device configuration for each of the set of end nodes and each of the set of switching nodes of the desired TSN, based on the determined TSN schedule.
A modular power overlay architecture includes at least two sets of power overlay tiles arranged to provide for or meet a desired power overlay architecture demand. The power overlay assembly can include a base having seats to receive the power overlay tiles. The power overlay tiles can include power switching components arranged relative to a conductive surface commonly arranged relative to each of the at least two sets of power overlay tiles.
A rotor assembly comprising rotatable element having a set of first permanent magnets and a set of second permanent magnets alternately circumferentially spaced about the rotatable element. The first permanent magnets are evenly spaced from each other, the second permanent magnets are evenly spaced from each other, and each second permanent magnet is disposed between and unevenly spaced from a respective pair of immediately adjacent first permanent magnets.
A modular POL component can be arranged to define a half-bridge converter topology, and can be coupled with other modular POL power components to define a full-bridge or 3-phase AC converter topology based on a desired power output. The assembled POL components can be mounted on a common electrically insulative substrate to define a POL power conversion device to provide the desired power output.
H01L 23/538 - Arrangements for conducting electric current within the device in operation from one component to another the interconnection structure between a plurality of semiconductor chips being formed on, or in, insulating substrates
H01L 25/18 - Assemblies consisting of a plurality of individual semiconductor or other solid state devices the devices being of types provided for in two or more different subgroups of the same main group of groups , or in a single subclass of ,
H05K 1/18 - Printed circuits structurally associated with non-printed electric components
H01L 23/485 - Arrangements for conducting electric current to or from the solid state body in operation, e.g. leads or terminal arrangements consisting of lead-in layers inseparably applied to the semiconductor body consisting of layered constructions comprising conductive layers and insulating layers, e.g. planar contacts
H01L 23/14 - Mountings, e.g. non-detachable insulating substrates characterised by the material or its electrical properties
H02M 7/5387 - Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters in a bridge configuration
12.
SYSTEM AND METHOD FOR AUTO-GENERATION OF TEST SCRIPTS
Provided is a system communicatively coupled to a network including a plurality of aviation assets. The system includes a processor; a memory including instructions which when executed by the processor cause the processor to perform operations including detecting a change in a state of the network, the change being characterized by comparing a previous state of the network with a current state of the network, and the change being associated with one or more assets of the plurality of assets. The operations also include fetching configuration data and test data from a plurality of sources, the fetching being responsive to detecting the change; generating, based on the change, the configuration data, the test data, one or more verification scripts; and executing a specified test utilizing the one or more verification scripts, the specified test being configured to analyze one or more assets of the plurality of aviation assets.
A method of cooling rotor winding end turns extending from a rotor core includes coupling a collar to a rotatable shaft of the rotor core. The collar has a first wall confronting the rotor core, a second wall spaced from and opposing the first wall, a third wall between the first and second walls defining a set of apertures therethrough, a first cavity cooperatively defined by the first, second and third walls, having a first opening opposing the third wall, a fourth wall circumscribing the third wall, a second cavity cooperatively defined by the second, third and fourth walls, the second cavity defining a second opening opposing the second wall. The first and second cavities are in fluid communication, and the rotor winding end turns are receivable into the second cavity. The method includes directing a coolant into the first cavity, and delivering the coolant to the second cavity.
A method and apparatus for forming a rotor for an electric machine includes serially adding layers of material to form a rotor body having a radially-extending post configured to receive a set of electrically-conductive windings, and also having a radially-extending winding end turn support formed contiguously from the rotor body.
H02K 15/09 - Forming windings by laying conductors into or around core parts by laying conductors into slotted rotors
H02K 15/02 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
A method to provide flexible access to an internal data of an regulated system, the method comprising receiving, by a data access component of the regulated system, a loadable configuration file defining a set of triggering events and a set of memory, determining the occurrence of a single triggering event, accessing at least a subset of memory that contain the internal data of the avionics system to retrieve data associated with the one or more memory of the set of memory, and outputting the retrieved data to a receiving component.
A semiconductor device cell includes a drift region having a first conductivity type, a well region having a second conductivity type disposed adjacent to the drift region, the well region defining a set of well region segments. A source region having the first conductivity type is disposed adjacent to the well region and surrounded by the well region. A channel region having the second conductivity type, and defining a set of channel region segments a periphery of the channel region segment being surrounded by the well region. The well region, source region, and channel region cooperatively define a first axial length extending across the surface.
H01L 29/06 - Semiconductor bodies characterised by the shapes, relative sizes, or dispositions of the semiconductor regions
H01L 29/16 - Semiconductor bodies characterised by the materials of which they are formed including, apart from doping materials or other impurities, only elements of Group IV of the Periodic System in uncombined form
H01L 29/10 - Semiconductor bodies characterised by the shapes, relative sizes, or dispositions of the semiconductor regions with semiconductor regions connected to an electrode not carrying current to be rectified, amplified, or switched and such electrode being part of a semiconductor device which comprises three or more electrodes
A semiconductor device cell includes a drift region having a first conductivity type, a well region having a second conductivity type disposed adjacent to the drift region, the well region defining a set of well region segments. A source region having the first conductivity type is disposed adjacent to the well region and surrounded by the well region. A channel region having the second conductivity type, and defining a set of channel region segments, a periphery of the channel region segment being surrounded by the well region. The well region, source region, and channel region cooperatively define a first axial length extending across the surface.
An avionics data network includes a network switch core configured for a time-sensitive networking (TSN) schema, a first and second set of networking end nodes communicatively coupled with the network switch core. The first set of networking end nodes includes a first subset of networking end nodes configured for a TSN schema and second subset of networking end nodes configured for a legacy Ethernet schema. The network switch core is configured to receive, from the first set of networking end nodes, a set of data frames, determine the respective schema of the set of data frames, forward the set of data frames to a predetermined queue on an egress port based on the determined respective schema, and transmit set of data frames to an end node having a corresponding schema.
A portable, hand-held computer functions as an intermediary between a database server and individual aircraft when the aircraft cannot be connected to the database server. By virtue of being portable and being locally linked (over time) to different aircraft, the intermediary computing device can provide the data upload validation and auditing for accurate billing of database usage for a flight database provided from the server. This ensures that each aircraft which receives an uploaded database is entitled to receive the upload based on a paid license. As a result, billing by the database vendor is based on usage. Licensing and data authentication is mediated by the intermediary computing device.
G06F 16/27 - Replication, distribution or synchronisation of data between databases or within a distributed database system; Distributed database system architectures therefor
An avionics system can provide data to a first receiving component associated with a proprietary first protocol and a second receiving component associated with a non-proprietary second protocol. A configuration tool generates a first configuration file comprising instructions for a data access component to provide a first data output to the first receiving component, and a second data output to the second receiving component. The configuration tool can generate a second configuration file including instructions to convert the second data output. The data access component can receive a definition database defining the first protocol to convert the data according to the non-proprietary second protocol. The data access component can provide the requested data to the first and second receiving components in accordance with the non-proprietary second protocol. The second receiving component is configured convert the data received based on the second configuration file.
Provided is a method and a configurable status console for an aircraft verification and integration system (VAIS) of an aircraft network of an aircraft implemented within a computer system having one or more processors, the configurable status console via a processor performs an on-going scanning operation of the aircraft network and a simulation network in communication with the aircraft network, retrieves data that includes performance data, VAIS parameters and messaging data in real-time from the aircraft network and the simulation network, to determine the health of the aircraft, and analyzes the data and configures the status of the aircraft or components or simulation thereof and generates a configured status for the aircraft or components or simulation thereof to be displayed at the configurable status console.
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
G07C 5/00 - Registering or indicating the working of vehicles
B64F 5/60 - Testing or inspecting aircraft components or systems
A combustion engine including a combustion chamber, a first bleed air supply, a second bleed air supply, a thermal bus and a turbomachine. The first bleed air supply being fluidly coupled to a first fluid from a portion of the combustion engine upstream of the combustion chamber. The second bleed air supply being fluidly coupled to a second fluid portion of the combustion engine downstream of the combustion chamber. The turbomachine having a compressor and a turbine. The compressor being fluidly coupled to the first bleed air supply. The turbine being fluidly coupled to the second bleed air supply.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
B64D 29/00 - Power-plant nacelles, fairings, or cowlings
A rotor assembly for an electric machine is disclosed. The rotor core has a cylindrical body defining an outwardly facing peripheral surface comprising a slotted portion including a set of slots defined by a set of rotor teeth projecting outwardly from the peripheral surface. Each rotor tooth comprises a respective first distal tip and a respective first radial length extending radially from a center point of the rotor core to the first distal tip. The peripheral surface further comprises a non-slotted portion defining a respective second radial length, extending radially from the center point of the rotor core to the outwardly facing peripheral surface. The first radial length is less than the second radial length.
A rotor assembly comprises a rotor core comprising a first end and an opposing second end, and an outwardly facing peripheral surface having a set of rotor teeth projecting outwardly therefrom to define a set of rotor slots therebetween. Each rotor tooth can comprise a first rotor tooth wall, an opposing second rotor tooth wall, and a distal tip between the first rotor tooth wall and second rotor tooth wall. Each respective rotor slot can be defined by a respective first rotor tooth wall of a first rotor tooth, and a respective second rotor tooth wall of a second rotor tooth, and includes a first rotor core conduit extending axially along a length of the first rotor tooth. The first rotor core conduit can comprise a first rotor core conduit inlet at the rotor core first end and a first rotor core conduit inlet at the rotor core second end, the rotor core conduit defining a first taper that is narrower at first rotor core conduit inlet than the first rotor core conduit outlet.
A rotor assembly includes a rotor core having a rotatable shaft and defining at least one rotor post, a winding wound around the post that defines an end turn, and a coil support assembly including a coil support disc rotatably coupled to the rotatable shaft and comprising a radially inner portion and a radially outer portion coupled via a set of spokes. The radially outer portion overlies an end turn and defines a set of channels therethrough sized and disposed to receive a flow of fluid from the set of rotor windings.
A method of cooling a set of rotor winding end turns of a rotor assembly can include directing a fluid coolant flow to a coil support assembly, delivering the fluid coolant flow, by a first coolant distribution ring of the coil support assembly, radially outward toward rotor winding end turns; and delivering the fluid coolant flow, by a coil support disc of the coil support assembly, axially outward toward the rotor winding end turns. The method can further include expelling fluid coolant flow by a second coolant distribution ring radially outward toward a set of stator windings, and expelling, by the coil support disc, the fluid coolant flow axially outward toward the rotor core.
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
27.
SEMICONDUCTOR DEVICE PACKAGE AND METHOD OF FORMING
A semiconductor device package comprises a semiconductor switching device having a body, including a first side, and an opposing second side coupled to a substrate. A gate terminal is defined on the semiconductor switching device body first side, the gate terminal having a first side, and an opposing second side facing the semiconductor switching device body. A first gate resistor is disposed on the gate terminal first side, and coupled electrically in series with the gate terminal.
A power overlay (POL) module includes a semiconductor device having a body, including a first side and an opposing second side. A first contact pad defined on the semiconductor device first side and a dielectric layer, having a first side and an opposing second side defining a set of first apertures therethrough, is disposed facing the semiconductor device first side. The POL module, includes a metal interconnect layer, having a first side and an opposing second side, the metal interconnect layer second side is disposed on the dielectric layer first side) and extends through the set of first apertures to define a set of vias electrically coupled to the first contact pad. An enclosure defining an interior portion is coupled to the metal interconnect layer first side, and a phase change material (PCM) is disposed in the enclosure interior portion.
A semiconductor device package comprises a semiconductor switching device having a body, including a first side, and an opposing second side coupled to a substrate. A gate terminal is defined on the semiconductor switching device body first side, the gate terminal having a first side, and an opposing second side facing the semiconductor switching device body. A first gate resistor is disposed on the gate terminal first side, and coupled electrically in series with the gate terminal.
H01L 21/02 - Manufacture or treatment of semiconductor devices or of parts thereof
H01L 21/18 - Manufacture or treatment of semiconductor devices or of parts thereof the devices having at least one potential-jump barrier or surface barrier, e.g. PN junction, depletion layer, carrier concentration layer the devices having semiconductor bodies comprising elements of group IV of the Periodic System or AIIIBV compounds with or without impurities, e.g. doping materials
H01L 29/00 - SEMICONDUCTOR DEVICES NOT COVERED BY CLASS - Details of semiconductor bodies or of electrodes thereof
H01L 29/161 - Semiconductor bodies characterised by the materials of which they are formed including, apart from doping materials or other impurities, only elements of Group IV of the Periodic System in uncombined form including two or more of the elements provided for in group
30.
SYSTEMS AND METHODS FOR FLEXIBLE WRITING OF INTERNAL DATA OF REGULATED SYSTEM
An environment and non-transitory computer readable medium that provide runtime write access to a regulated system. A method of providing runtime write access to a regulated system comprising receiving an unauthorized input parameter, and generating a runtime instruction communication. The runtime instruction communication can be modified by an unauthorized function.
A method of automatic configuration of a communications interface of an unknown data network, the method comprising connecting an Electronic Flight Bag (EFB) to the unknown data network, attempting to open communication ports, in response to attempting to open communication ports, receiving data from the unknown data network, determining, by a controller module, if the selected communications interface can interpret the received data, and operating the communications interface of the EFB in accordance with the selected communications interface.
H04L 41/08 - Configuration management of networks or network elements
B64D 43/00 - Arrangements or adaptations of instruments
G06F 3/0482 - Interaction with lists of selectable items, e.g. menus
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
Systems and methods of planning and scheduling resources of an airline include using machine learning models to generate custom behavioral characteristics for a plurality of operational components of the airline based on operations data. The custom behavioral characteristics are used to define inputs and outcomes in simulations of the operational components of the airline. The simulation outputs performance indicators and a feedback loop captures previously ignored interactions between the operational components of the airline based on the performance indicators and custom behavioral characteristics of inputs and outcomes corresponding to the plurality of operational components of the airline.
The disclosure relates to an apparatus and method for liquid cooling of an electronic component. A housing includes an insertion slot and defines at least one component chamber for carrying the electronic component. A fluid inlet and fluid outlet are provided on the housing. A liquid coolant circuit passes through the housing at least from the inlet to the outlet.
H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating
H01L 23/473 - Arrangements for cooling, heating, ventilating or temperature compensation involving the transfer of heat by flowing fluids by flowing liquids
Systems and methods for airspace management. One embodiment of an aerial vehicle, includes a first sensor for detecting a lateral field of view of the aerial vehicle and a vehicle computing device. The vehicle computing device may include a memory component and a processor. The memory component may store logic that, when executed by the processor, causes the aerial vehicle to calculate a detection boundary for the aerial vehicle to maintain a well clear requirement, wherein the detection boundary is based on instantaneous trajectory, planned future trajectory, and a capability of the aerial vehicle and utilize the capability of the aerial vehicle and data from the first sensor to maintain the vehicle within detection boundary. In some embodiments the logic may cause the vehicle to provide an instruction to maintain the aerial vehicle within the detection boundary.
A system for read-access of a regulated system, the system comprising a specialized data store, at least one memory, and a flexible reader. The specialized data store able to receive at least a portion of a set of procedures that define a respective set of systematic data and executable operations. The at least one memory including at least one set of data related to the set of procedures.
G06F 11/36 - Preventing errors by testing or debugging of software
G06F 12/14 - Protection against unauthorised use of memory
G06F 21/62 - Protecting access to data via a platform, e.g. using keys or access control rules
G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
An electrical filter circuit is disclosed. The circuit includes a first input line and a second input line. A first transmission line is coupled electrically in series at a first node with a first output line, and an inductor is coupled electrically in series between the first input line and the first transmission line. The filter also includes a second transmission line having a first impedance coupled to the first node. The second input line is coupled electrically in series at a second node with a second output line. A third transmission line is coupled to the second node, and a capacitor is coupled electrically in series between the second transmission line and the third transmission line. The first output line has a second impedance that is greater than the first impedance.
An aircraft includes at least one source collecting a set of navigational parameters of the aircraft, the at least one source obtaining flight data for the aircraft and including at least one of a global positioning system, an inertial reference system, or a sensor. The aircraft further includes a flight control computer communicatively coupled to the source and including a first processor and a first memory having a machine-readable medium, as well as a flight management system communicatively coupled to the flight control computer.
F16K 31/06 - Operating means; Releasing devices magnetic using a magnet
F02N 9/04 - Starting of engines by supplying auxiliary pressure fluid to their working chambers the pressure fluid being generated otherwise, e.g. by compressing air
F16K 1/12 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with streamlined valve member around which the fluid flows when the valve is opened
F16K 15/02 - Check valves with guided rigid valve members
F16K 15/18 - Check valves with actuating mechanism; Combined check valves and actuated valves
F16K 31/08 - Operating means; Releasing devices magnetic using a magnet using a permanent magnet
38.
WET AND DRY CAVITY GENERATOR SYSTEMS AND METHODS OF MANUFACTURING THE SAME
A method for manufacturing a main rotor for a generator is provided. The method includes printing at least part of a rotor shaft by a three-dimensional printing process. The step of printing at least part of the rotor shaft includes printing a plurality of closed outlets and a plurality of open outlets. A rotor core is printed by the three-dimensional printing process. The step of printing the rotor core includes printing a plurality of liquid coolant conduits that extend through the rotor core and fluidly connecting the plurality of liquid coolant conduits to the plurality of closed openings.
H02K 15/02 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
H02K 19/22 - Synchronous generators having windings each turn of which co-operates alternately with poles of opposite polarity, e.g. heteropolar generators
H02K 19/38 - Structural association of synchronous generators with exciting machines
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
39.
EVAPORATIVE THERMAL MANAGEMENT SYSTEMS AND METHODS
Devices and methods are provided herein useful to thermal management. In some embodiments, a thermal management device includes a housing with a fixed amount of working fluid disposed therein. The substrate is in thermal communication with the thermal management device such that evaporation of the working fluid controls the temperature of the substrate. Evaporated working fluid exits the housing through one or more vents. The housing further includes a plurality of supports that increase the surface area to volume ratio of the housing. The high surface area to volume ratio of the housing increases the rate of heat transfer and also minimizes or otherwise reduces the size and weight of the thermal management device. The supports may further serve to mechanically support the substrate, enabling the housing to act as a combined thermal and mechanical device.
An apparatus may receive first data, in a first data format, from one or more unmanned aircraft system service suppliers comprising first positions of one or more unmanned aircraft systems, receive second data, in a second data format, from one or more communications systems comprising second positions of one or more manned aircraft, transmit third data, in a third data format, comprising the first positions of the one or more unmanned aircraft systems and the second positions of the one or more manned aircraft, receive a first control signal comprising a control command associated with one or more of the unmanned aircraft systems or one or more of the manned aircraft, and transmit a second control signal comprising the control command to one or more of the unmanned aircraft system service suppliers or to one or more of the communications systems.
A proximity sensor comprises a reference inductor, a first set of sensor inductors, a first set of comparators, each comparator of the first set of comparators corresponding to one of the sensor inductors of the first set of sensor inductors, and an alternating current voltage source to output a sinusoidal voltage to the reference inductor and each of the sensor inductors. Each comparator of the first set of comparators receives a voltage across the reference inductor as a reference voltage and each comparator of the first set of comparators receives a voltage across a corresponding sensor inductor as an input voltage.
G01V 3/10 - Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination or deviation operating with magnetic or electric fields produced or modified by objects or geological structures or by detecting devices using induction coils
H03K 5/24 - Circuits having more than one input and one output for comparing pulses or pulse trains with each other according to input signal characteristics, e.g. slope, integral the characteristic being amplitude
A method may include detecting, during a flight of an aircraft system, a conflict with a planned route of the aircraft system, determining one or more alternate routes for the aircraft system to avoid the conflict, wherein each of the one or more alternate routes avoid secondary conflicts with active flight operations, transmitting first data to cause first visual information indicating the conflict and second visual information indicating the one or more alternate routes to be displayed to a user, receiving second data indicating one of the one or more alternate routes being selected by the user, and updating the planned route of the aircraft system to include the alternate route selected by the user.
Systems and methods for providing surveillance services for an unmanned vehicle are described herein. One embodiment of a method includes receiving surveilled data from a surveillance monitor regarding the unmanned aerial vehicle and at least one other aircraft, receiving trajectory data from at least one trajectory data source, and comparing the surveilled data with the trajectory data to determine whether the unmanned aerial vehicle is on path to collide with a third party aerial vehicle. In some embodiments, in response to determining that the unmanned aerial vehicle is on path to collide with the third party aerial vehicle, the method includes determining an alternate route for the unmanned aerial vehicle; and communicating at least a portion of the alternate route to the unmanned aerial vehicle.
Systems and methods for trajectory planning for an unmanned aerial vehicle. A mission specification for fulfillment by an unmanned aerial vehicle is received. The mission specification identifies a waypoint, an optimization criterion, and information identifying the unmanned aerial vehicle. It is determined whether candidate flight trajectories are available. Maneuvers from a motions library that defines available maneuvers are modeled to identify candidate flight trajectories to the waypoint which satisfy a restriction condition and do not conflict with a flight plan for another aerial vehicle. If candidate flight trajectories are available, desired flight trajectories are selected. A mission approval is submitted to a receiving party.
Systems and methods provide a services architecture. An air mobility platform locally stores a native application at. The air mobility platform receives a first request for a first service and data identifying the first user as a priority user type or a non-priority user type. A second request for a second service and data related to the second user identifies the user type is received. The air mobility platform calculates a priority for the first request. If the priority for the first request exceeds the priority for the second request, a third party application is accessed for the first request. The air mobility platform submits the data related to the first request from the third party application to at least one of the first unmanned aerial vehicle or the first user.
H04L 67/125 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks involving control of end-device applications over a network
A method to validate a flight plan for an aircraft includes receiving aviation data, determining a flight plan based on the aviation data; determining a set of flight parameters for the flight plan, receiving terrain data, and performing a safety validation of the flight plan, wherein the safety validation comprises: comparing the set of flight parameters with the terrain data; and determining, based on the comparison, whether the flight plan satisfies predetermined flight criteria, and in the event of a determination that the flight plan does not satisfy the predetermined flight criteria, displaying a first notification indicative of the determination.
A flight recorder system of an aircraft includes a resource controller module (RCM) communicatively coupled, via a switch fabric, to a set of flight recorder system modules (FRM). Each FRM comprises a respective control module, a respective local memory, and a respective set of input and output (I/O) ports communicatively coupled to the switch fabric. The RCM is configured to detect a respective FRM coupled to the switch fabric, and based on the detection, configure an operation of the FRM, and wherein the respective local memory of the FRM is readable by the RCM, and shareable with the other FRMs via the switch fabric.
A method includes receiving a flight plan of an aircraft comprising one or more contingency routes, determining a plurality of possible trajectories of the aircraft based on the flight plan and the one or more contingency routes, identifying navigation data associated with one or more locations along each of the possible trajectories, and transmitting the navigation data to the aircraft.
G06T 7/70 - Determining position or orientation of objects or cameras
G01S 19/48 - 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
G01S 19/05 - Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers providing aiding data
Systems and methods for flight mission planning are provided. One embodiment of a method includes defining a mission to be performed by a plurality of assets, where defining the mission includes defining an area for the mission and a target for the mission, determining, available assets for completing the mission, and determining a capability for the available assets. Some embodiments include defining operations to complete the mission, based on the capability of the available assets and assigning each of the operations to respective assets of the available assets to complete the mission, where assigning each of the operations incudes communicating customized instructions to each of the respective assets being utilized.
A method may include receiving a request for a first set of data to be gathered by an unmanned aircraft system. A first unmanned aircraft system may be identified that is capable of gathering the first data. A request may be transmitted to the first unmanned aircraft system to gather the first set of data. The first set of data gathered by the first unmanned aircraft system may be received.
A method for a time sensitive network (TSN) having a network topology is disclosed. The method includes determining a set of data flow permutations corresponding to the network topology, computing a respective full schedule corresponding to each data flow permutation of the set of data flow permutations, determining a respective time to compute the full schedule for each flow permutation of the set of data flow permutations, and computing a respective partial schedule for each data flow permutation of the set of data flow permutations. The method further includes selecting a data flow permutation of the set of data flow permutations based at least in part on the respective time to compute the full schedule for the selected flow permutation, and saving the selected data flow permutation to a memory.
H04L 49/253 - Routing or path finding in a switch fabric using establishment or release of connections between ports
H04L 47/2441 - Traffic characterised by specific attributes, e.g. priority or QoS relying on flow classification, e.g. using integrated services [IntServ]
H04L 49/351 - Switches specially adapted for specific applications for local area network [LAN], e.g. Ethernet switches
Systems and techniques to facilitate intelligent unmanned aerial vehicle traffic management via an infrastructure network are presented. In an example, a traffic management system can include a data collection component, a flight path component, and a communication component. The data collection component receives navigation data and parameter data associated with an unmanned aerial vehicle. The navigation data is associated with a starting point and destination for the unmanned aerial vehicle. The parameter data is indicative of information associated with the unmanned aerial vehicle. The flight path component generates flight path data for the unmanned aerial vehicle based on the navigation data, the parameter data and infrastructure network data received from an intelligent sensor node network. The communication component transmits the flight path data to the unmanned aerial vehicle.
An aircraft includes an environmental control system having a bleed air inlet, a gas turbine engine having at least one low pressure bleed air supply and at least one high pressure bleed air supply, and a turbo air cycle machine having a first turbine section, a second turbine section, a first compressor section, and second compressor section.
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
54.
Methods for managing communications involving a lockstep processing system
A method for managing communications involving a lockstep processing comprising at least a first processor and a second processor can include receiving, at a data synchronizer, a first signal from a first device. The method can also include receiving, at the data synchronizer, a second signal from a second device. In addition, the method can include determining, by the data synchronizer, whether the first signal is equal to the second signal. When the first signal is equal to the second signal, the method can include transmitting, by the data synchronizer, the first signal to the first processor and the second signal to the second processor. Specifically, in example embodiments, transmitting the first signal to the first processor can occur synchronously with transmitting the second signal to the second processor.
Methods and systems for generating a recovery scheduling solution in response to a scheduling disruption are disclosed. A method includes receiving a request to modify an original schedule operations solution based on disruptive events, computing a flight recovery solution to reschedule disrupted flights, generating a crew recovery solution using the flight recovery solution that includes covered and uncovered flights by assigning flight crews to rescheduled disrupted flights, iteratively generating recommendations to delay or cancel uncovered flights until a best recovery solution is obtained, the best recovery solution including a crew recovery solution with a least amount of uncovered flights, iteratively generating, by the processing device, subsequent flight and crew recovery solutions based on the recommendations, generating a passenger recovery solution based on the best recovery solution and re-assigning disrupted passengers to the rescheduled disrupted flights, and configuring the airline recovery scheduling solution.
Systems and methods of generating a recovery scheduling solution in response to a scheduling disruption are disclosed. A method includes receiving a request to modify an original schedule operations solution based on disruptive events associated with flights, wherein the disruptive events causes the disruption, computing a flight recovery solution based on rescheduling flights with a minimum number of breaks in original crew-pairings and a minimum number of breaks in original passenger connections for connecting flights in order to reschedule disrupted flights, generating a crew recovery solution using the flight recovery solution by assigning flight crews to rescheduled disrupted flights, generating a passenger recovery solution based on the crew recovery solution and reassigning disrupted passengers to the rescheduled disrupted flights, and configuring the airline recovery scheduling solution using flight, crew, and passenger recovery solutions in order to transmit the recovery scheduling solution to an operations control center.
G06Q 10/02 - Reservations, e.g. for tickets, services or events
G06Q 10/04 - Forecasting or optimisation specially adapted for administrative or management purposes, e.g. linear programming or "cutting stock problem"
57.
METHODS AND SYSTEMS FOR GENERATING CREW AND PASSENGER FRIENDLY OPERATIONS RECOVERY SOLUTIONS
Systems and methods of generating a recovery scheduling solution in response to a scheduling disruption are disclosed. A method includes receiving a request to modify an original schedule operations solution based on disruptive events associated with flights, wherein the disruptive events causes the disruption, computing a flight recovery solution based on rescheduling flights with a minimum number of breaks in original crew-pairings and a minimum number of breaks in original passenger connections for connecting flights in order to reschedule disrupted flights, generating a crew recovery solution using the flight recovery solution by assigning flight crews to rescheduled disrupted flights, generating a passenger recovery solution based on the crew recovery solution and re-assigning disrupted passengers to the rescheduled disrupted flights, and configuring the airline recovery scheduling solution using the flight, the crew, and the passenger recovery solutions in order to transmit the recovery scheduling solution to an operations control center.
Methods and systems for generating a recovery scheduling solution in response to a scheduling disruption are disclosed. A method includes receiving a request to modify an original schedule operations solution based on disruptive events, computing a flight recovery solution to reschedule disrupted flights, generating a crew recovery solution using the flight recovery solution that includes covered and uncovered flights by assigning flight crews to rescheduled disrupted flights, iteratively generating recommendations to delay or cancel uncovered flights until a best recovery solution is obtained, the best recovery solution including a crew recovery solution with a least amount of uncovered flights, iteratively generating, by the processing device, subsequent flight and crew recovery solutions based on the recommendations, generating a passenger recovery solution based on the best recovery solution and re-assigning disrupted passengers to the rescheduled disrupted flights, and configuring the airline recovery scheduling solution.
A rotor assembly comprising rotatable element defining a periphery, a first set of elements defining magnetic pole regions and a second set of elements defining interpolar regions that alternately placed about the periphery. The rotor assembly further comprising a containment band circumscribing the first set of elements and the second set of elements. The containment band defining a first set of material and a second set of material, with each overlying at least a portion of the first set of elements or the second set of elements.
A common-mode voltage cancellation (CMVC) circuit, is disclosed. The circuit includes a set of input lines arranged to receive a respective phase voltage, and a set of output lines arranged to provide a respective output phase voltage. The circuit further includes a set of coupled inductors, each having a respective primary winding and secondary winding coupled in signal communication at a respective upstream end to a respective input line to receive a respective phase voltage therefrom, each respective phase voltage having a common-mode voltage component. Each primary winding being coupled at a respective downstream end to ground, and each secondary winding being coupled in series between the respective input line and a respective output line. The circuit includes a set of capacitors, each capacitor being electrically coupled to a respective input line and in series with a respective primary winding of the set of coupled inductors.
H03H 7/06 - Frequency selective two-port networks including resistors
H03H 1/00 - Constructional details of impedance networks whose electrical mode of operation is not specified or applicable to more than one type of network
Various flight leg visualization techniques are enabled. For instance, a method comprises retrieving, by a flight management system from a navigation database, a route of an aircraft associated with the flight management system, determining, by the flight management system, leg terminations on the route, determining, by the flight management system, a leg termination of the leg terminations to display, and displaying, by the flight management system, the leg termination.
A system and method to assist aircraft pilots with rapid decision-making in cases where the pilot needs to make a flight diversion at low altitudes due to an emergency (for example, loss of thrust). Once an emergency need for diversion is detected, the system and method generates a list of alternative airports the plane can reach given: (i) the current conditions of the plane; (ii) a real-emergency time simulation of evolving conditions of the plane; (iii) the environment at potential landing sites; and (iv) the environment on the flight path to those sites. For airports potentially within reach, the system and method provides a confidence scores for successful landings for alternative simulated landing options. The simulations and confidence scores take into account aircraft position, altitude, speed, and possible further problems with the aircraft for the both the current flight path and for each simulated alternative.
B64D 45/08 - Landing aids; Safety measures to prevent collision with earth's surface optical
B64D 43/00 - Arrangements or adaptations of instruments
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
G05B 17/02 - Systems involving the use of models or simulators of said systems electric
A portable, hand-held computer functions as an intermediary between a database server and individual aircraft when the aircraft cannot be connected to the database server. By virtue of being portable and being locally linked (over time) to different aircraft, the intermediary computing device can provide the data upload validation and auditing for accurate billing of database usage for a flight database provided from the server. This ensures that each aircraft which receives an uploaded database is entitled to receive the upload based on a paid license. As a result, billing by the database vendor is based on usage. Licensing and data authentication is mediated by the intermediary computing device.
G06F 16/27 - Replication, distribution or synchronisation of data between databases or within a distributed database system; Distributed database system architectures therefor
A turbine engine that includes an engine core, a core casing surrounding the engine core, at least one cowl surrounding the core casing, a power converter located between the at least one cowl and the core casing, an electrical generator disposed within the engine core, at least one electrical strut having an outer wall defining an interior and extending radially between the engine core and the core casing; and at least one electrical conduit located within the interior and electrically coupling the generator to the power converter.
A processing system for an unmanned vehicle (UV) such as an unmanned aerial vehicle (UAV) is provided. The processing system comprises a first processing unit of an integrated circuit and a second processing unit of the integrated circuit. The processing system comprises a first operating system provisioned using the first processing unit. The first operating system is configured to execute a first vehicle control process. The processing system comprises a virtualization layer configured using at least the second processing unit, and a second operating system provisioned using the virtualization layer. The second operating system is configured to execute a second vehicle control process.
A method for scheduling a transmission of data flows in a network. The method includes identifying an unscheduled set of data flows to be scheduled for a respective transmission on a subset of the set of links defining a respective path, scheduling a respective transmission of a subset of data flows on the respective path, wherein the schedule defines a start time, a duration, and a cycle time of the transmission on each respective link in the path. The method includes determining a conflict between an unscheduled data flow and a scheduled data flow with respect to a link in the path, displaying the unscheduled data flow, the link, and the scheduled data flow with which the conflict occurs, and displaying, for each scheduled data flow, an image depicting each respective link of the path, and a data transmission schedule with respect to each respective link in the path.
A system and method for generating a time-sensitive network schedule for a desired TSN includes defining a network topology of the desired TSN including at least a set of end nodes communicative connected by way of a set of switching nodes, defining a set of device parameters for each of the set of end nodes and each of the set of switching nodes of the desired TSN, determining, by a TSN scheduler, a TSN schedule for the desired TSN based on the defined network topology and the defined set of device parameters for each of the set of end nodes and each of the set of switching nodes, and generating a per-device configuration for each of the set of end nodes and each of the set of switching nodes of the desired TSN, based on the determined TSN schedule.
A combustion engine including at least one combustion chamber, a first bleed air supply fluidly coupled to a portion of the combustion engine upstream the combustion chamber, a second bleed air supply fluidly coupled to a portion of the combustion engine downstream the combustion chamber, and a turbomachine comprising a first compressor, a second compressor, and a first turbine mounted to a common shaft, with the first and second compressors in serial flow arrangement. The turbomachine, further comprising an intercooler serially fluidly coupling a portion of the first compressor to a portion of the second compressor.
F02C 5/12 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
F02C 7/143 - Cooling of plants of fluids in the plant of working fluid before or between the compressor stages
69.
SYSTEMS AND METHODS FOR PROVIDING CONTINGENCY AUTOMATION TO EMERGENCY RESPONSE
Disclosed herein are embodiments for providing contingency automation to emergency response. One embodiment of a method includes determining a route for a vehicle to a primary destination, and determining a first upcoming area along the route that has been previously identified as an emergency response zone, where the emergency response zone may be used as a secondary destination in a contingency route for the vehicle in an emergency. In some embodiments, the method may include reserving airspace for the contingency route, determining that the emergency response zone is no longer useful, based on an updated position of the vehicle, and canceling the contingency route from reservation.
A combustion engine including at least one combustion chamber, a first bleed air supply fluidly coupled to a portion of the combustion engine upstream the combustion chamber, a second bleed air supply fluidly coupled to a portion of the combustion engine downstream the combustion chamber, a first thermal bus, and a turbomachine including a compressor, a rotary pump, and a first turbine, with the compressor and rotary pump in serial flow arrangement and the rotary pump being fluidly coupled to the first thermal bus.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
B64D 29/00 - Power-plant nacelles, fairings, or cowlings
A combustion engine including at least one combustion chamber, a first bleed air supply fluidly coupled to a portion of the combustion engine upstream the combustion chamber, a second bleed air supply fluidly coupled to a portion of the combustion engine downstream the combustion chamber, a first thermal bus, and a turbomachine including a compressor, a rotary pump, and a first turbine, with the compressor and rotary pump in serial flow arrangement and the rotary pump being fluidly coupled to the first thermal bus.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
B64D 29/00 - Power-plant nacelles, fairings, or cowlings
A machine-readable media including executable instructions, when executed by one or more processors of a flight management system in a following aircraft. The machine-readable media configured to provide instructions to a flight management system of a following aircraft operating according to a following aircraft planned path, in reference to a target aircraft operating according to a target aircraft planned path, receive information regarding the target aircraft, set a required time of arrival at an achieve-by-point, and engage a required time of arrival function to enable the following aircraft to reach the achieve-by-point by the required time of arrival.
A method for a time sensitive network (TSN) having a network topology is disclosed. The method includes determining a set of flow permutations corresponding to the network topology, computing a respective full schedule corresponding to each flow permutation of the set of flow permutations, determining a respective time to compute the full schedule for each flow permutation of the set of flow permutations, and computing a respective partial schedule for each data flow permutation of the set of flow permutations. The method further includes selecting a data flow permutation of the set of data flow permutations based at least in part on the respective time to compute the full schedule for the selected flow permutation, and saving the selected data flow permutation to a memory.
H04L 49/253 - Routing or path finding in a switch fabric using establishment or release of connections between ports
H04L 47/2441 - Traffic characterised by specific attributes, e.g. priority or QoS relying on flow classification, e.g. using integrated services [IntServ]
H04L 49/351 - Switches specially adapted for specific applications for local area network [LAN], e.g. Ethernet switches
74.
Method for resiliency in compute resources in avionics
A system and method for compiling and dynamically reconfiguring the management of functionalities carried among a set of multiple common compute nodes. During the inoperation of one node of the set of multiple common compute nodes, higher-criticality functionalities can be reassigned to other common nodes to ensure maintained operation of the higher-criticality functionalities.
Systems and methods for mapping trip trajectories include identifying one or more vehicle trips (e.g., aircraft flights). One or more trajectory configurations associated with at least a portion of each vehicle trip can be identified, and location data associated with the one or more vehicle trips can be requested. Trip trajectory data based at least in part from the location data associated with the one or more vehicle trips and the one or more trajectory configurations associated with at least a portion of each vehicle trip can be generated. The trip trajectory data can be provided for display on a map of a geographic area including one or more locations defined by the location data associated with the one or more vehicle trips.
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
G01C 21/20 - Instruments for performing navigational calculations
An apparatus and method for operating an avionics data network includes a network switch core configured for a time-sensitive networking (TSN) schema, a set of ARINC 664 (A664) and a set of TSN networking end nodes communicatively connected with the network switch core. The network switch core is configured to receive, from the first set of networking end nodes, a set of data frames, determine the respective schema of the set of data frames, police the set of data frames based on the determined respective schema using a set of predetermined rules, forward the set of data frames to a predetermined queue on an egress port of the network switch core based on the determined respective schema, and transmit set of data frames to an end node of the second set of networking end nodes having a corresponding schema.
Disclosed herein are embodiments for providing a trusted autonomy framework for unmanned aerial systems. One embodiment of a method includes receiving a request from an entity to participate in secure data sharing within the trusted autonomy framework for unmanned aerial systems, receiving a type of data that will be shared via the entity, and verifying an identity of the entity, a security infrastructure of the entity, and validating the data to be shared. In some embodiments, in response to verifying, accepting the entity into the trusted autonomy framework for unmanned aerial systems.
A valve assembly for use in a bleed air system or any other pneumatic, hydraulic, mechanical, magnetic, or electrical system that includes a valve assembly. The value assembly includes a valve housing, a valve member, a pressure regulator, and a position sensor assembly. The valve housing includes an inlet and outlet that is angled from the inlet. The valve member slides between a first position wherein the valve member is closed and abuts a seat within the valve housing and a second position wherein the valve member is in a position a distance away from the seat.
F16K 31/363 - Operating means; Releasing devices actuated by fluid in which fluid from the conduit is constantly supplied to the fluid motor the fluid acting on a piston
F16K 37/00 - Special means in or on valves or other cut-off apparatus for indicating or recording operation thereof, or for enabling an alarm to be given
F16K 27/02 - Construction of housings; Use of materials therefor of lift valves
A control system an unmanned vehicle includes a first processing unit configured to execute a primary autopilot process for controlling the unmanned vehicle. The control system further includes a programmable logic array in operative communication with the first processing unit. The control system also includes a state machine configured in the programmable logic array. The state machine is configured to enable control of the unmanned vehicle according to a backup autopilot process in response to an invalid output of the first processing unit.
Disclosed herein are embodiments for providing altitude reporting. Some embodiments may include receiving a query from a first vehicle regarding altitude data of the first vehicle, providing the altitude data to the first vehicle, and receiving, by the computing device, a computed altitude from the first vehicle. Some embodiments include calculating an altitude uncertainty parameter for the first vehicle, determining a true altitude from the altitude data and the altitude uncertainty parameter, and determining whether the true altitude is within a predetermined threshold of a second altitude of a second vehicle. Some embodiments may be configured for, in response to determining that the true altitude is within the predetermined threshold, notifying at least one of the following: the first vehicle or the second vehicle.
A method and system of operating a vehicle in a descent profile, the method comprising obtaining, at a controller module, a mathematical model of performance characteristics for an aircraft, generating an optimal guidance trajectory, and operating the aircraft in accordance with the optimal guidance trajectory prior to operating in a position-based guidance.
A valve assembly including a valve body with an inlet port and an outlet port, a flow passage and a valve element disposed within the flow passage, an actuator and a lockout mechanism configured to maintain the position of the valve assembly in an opened position or a closed position. The lockout mechanism can include at least one screw.
Disclosed herein are embodiments for providing conformance volume based airspace access. Some embodiments include receiving data related to a route from an origination location to a destination location, receiving data related to a vehicle that will traverse the route, and determining an airspace volume from the origination location to the destination location along the route, where the airspace volume is based on at least a portion of the route data and at least a portion of the vehicle data. Some embodiments calculate a cost of the airspace volume and provide the cost to a user.
A method of providing an indication identifying a flight as including or not including a flight path deviation, the method includes receiving flight data associated with a flight, the flight data comprising a plurality of coordinates indicating a location of an aircraft at a plurality of times during the flight. The method also includes classifying a plurality of time intervals of the flight by applying a convolutional neural network algorithm to subsets of the plurality coordinates to determine that the time interval includes or does not include at least one flight path deviation. The method also includes identifying the flight as including at least one flight path deviation if at least one of the time intervals is classified as including the at least one flight path deviation and providing an indication identifying the flight as including at least one flight path deviation to a second computing system in response to identifying the flight as including at least one flight path deviation.
An apparatus may receive first data, in a first data format, from one or more unmanned aircraft system service suppliers comprising first positions of one or more unmanned aircraft systems, receive second data, in a second data format, from one or more communications systems comprising second positions of one or more manned aircraft, transmit third data, in a third data format, comprising the first positions of the one or more unmanned aircraft systems and the second positions of the one or more manned aircraft, receive a first control signal comprising a control command associated with one or more of the unmanned aircraft systems or one or more of the manned aircraft, and transmit a second control signal comprising the control command to one or more of the unmanned aircraft system service suppliers or to one or more of the communications systems.
A method of operating an aircraft interface device may comprise receiving a request for a data dictionary from an electronic flight bag application and transmitting the data dictionary to the electronic flight bag application. The data dictionary may comprise a mapping between a plurality of parameters associated with an aircraft and a plurality of parameter identifiers. Values of the parameters may be retrieved by the aircraft interface device. The method may also include receiving a request for values of one or more of the parameters from the electronic flight bag, retrieving values of the parameters, and transmitting the values of the parameters to the electronic flight bag application.
A system and method for flexible read-access of a set of procedures during runtime of a regulated system, the system comprising a set of procedures each defining a respective set of systematic data and an executable operation, a specialized data store configured to receive at least a subset of procedures, at least one memory including at least one set of data relating to the set of procedures, a receiving component communicatively coupled to the regulated system, and a flexible reader authorized for read-access to the specialized data store and the at least one memory.
G06F 11/36 - Preventing errors by testing or debugging of software
G06F 12/14 - Protection against unauthorised use of memory
G06F 21/62 - Protecting access to data via a platform, e.g. using keys or access control rules
G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
A method to provide flexible access to an internal data of an regulated system, the method comprising receiving, by a data access component of the regulated system, a loadable configuration file defining a set of triggering events and a set of memory, determining the occurrence of a single triggering event, accessing at least a subset of memory that contain the internal data of the avionics system to retrieve data associated with the one or more memory of the set of memory, and outputting the retrieved data to a receiving component.
A power overlay (POL) module includes a semiconductor device having a first side and an opposing second side, a dielectric sheet having a first side coupled to the semiconductor device second side, and an opposing second side, the dielectric sheet defining an aperture therethrough. The POL module also includes a first conductive layer disposed on the second side of the dielectric sheet and electrically coupled through the aperture to the semiconductor device second surface, a first conductive plate having a first side, and an opposing second side coupled to the first surface of the semiconductor device. The POL module further includes a first heat sink coupled the first side of the conductive plate and a first thermal interface layer disposed between the first conductive plate and the first heat sink.
An electric machine having an electrically insulative manifold is disclosed. In one example aspect, an electric machine includes a non-electrically conductive manifold. The manifold defines a chamber operable to receive a cooling fluid. The electric machine includes a prime winding in fluid communication with the chamber and one or more secondary windings in electrical communication with the prime winding and in fluid communication with the chamber. Further, the electric machine includes an electric machine terminal extending through the non-electrically conductive manifold and coupled with the prime winding. The electric machine terminal can provide or collect cooling fluid from the chamber of the manifold and can act as the electrical connection point for directing electrical power to or from the windings of the electric machine. The non-electrically conductive manifold electrically decouples the windings of the electric machine despite each winding receiving cooling fluid provided or collected at the manifold.
A method of performing fault isolation for an aircraft comprises identifying a fault that occurs during a flight of the aircraft; identifying a first set of parameters associated with the aircraft based on the identification of the fault; automatically determining values of the first set of parameters to obtain a first set of measured values; determining whether the first set of measured values are within acceptable ranges; and identifying a source of the fault based on the determination of whether the first set of measured values are within the acceptable ranges.
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
92.
Systems and methods for market based deconfliction for unmanned traffic management
A method of performing deconfliction comprises receiving a request to accept a first operational intent associated with a first unmanned aircraft system, determining whether a conflict exists between the first operational intent and one or more scheduled operational intents, and if a conflict exists between the first operational intent and a second operational intent associated with a second unmanned aircraft system, transmitting data associated with the conflict to a first operator of the first unmanned aircraft system and a second operator of the second unmanned aircraft system, and transmitting information to the first and second operator allowing them to negotiate a resolution of the conflict. If a conflict does not exist, the first operational intent may be accepted. Bids may also be received for a right to utilize a volume of airspace at a particular time and the right may be granted to a highest bidder.
A rotating rectifier associated with an electric machine is provided. In one example aspect, a rotating rectifier includes a diode. The diode can be one diode of a stage of diodes. The rotating rectifier can also include a connection lead, such an exciter connection lead. The connection lead has a diode contact segment in contact with the diode and a first spring segment and a second spring segment positioned on opposite sides of the diode contact segment. The first spring segment and the second spring segment can be positioned adjacent to the diode contact segment. The first spring segment and the second spring segment each have one or more spring laps. The spring laps can be non-planar spring laps, such as undulating spring laps.
A component includes a magnetic core having a body formed of a first material, defining a first opening and a second opening thereon. A duct formed of a second material extends at least partially through the body between the first opening and the second opening. The first opening and the second opening are in fluid communication by way of the duct.
B33Y 80/00 - Products made by additive manufacturing
H01F 27/245 - Magnetic cores made from sheets, e.g. grain-oriented
H01F 41/02 - Apparatus or processes specially adapted for manufacturing or assembling magnets, inductances or transformers; Apparatus or processes specially adapted for manufacturing materials characterised by their magnetic properties for manufacturing cores, coils or magnets
H05K 1/18 - Printed circuits structurally associated with non-printed electric components
H05K 3/34 - Assembling printed circuits with electric components, e.g. with resistor electrically connecting electric components or wires to printed circuits by soldering
An onboard system establishes a first-EFB connection between a first electronic flight bag (EFB) and an aircraft interface device (AID), and establishes a first-EFB session between the first EFB and a flight management computer (FMC) based on a session identifier for the first EFB. The first-EFB connection is associated with a first-EFB connection identifier for the first EFB, and the first-EFB session is established over the first-EFB connection in accordance with the first-EFB connection identifier. The onboard system establishes a second-EFB connection between a second EFB and the AID, and establishes a second-EFB session between the second EFB and the FMC based on a session identifier for the second EFB. The second-EFB connection is associated with a second-EFB connection identifier for the second EFB, and the second-EFB session is established over the second-EFB connection in accordance with the second-EFB connection identifier.
H04L 29/08 - Transmission control procedure, e.g. data link level control procedure
H04L 67/146 - Markers for unambiguous identification of a particular session, e.g. session cookie or URL-encoding
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
A method and apparatus for forming a rotor for an electric machine includes serially adding layers of material to form a rotor body having a radially-extending post configured to receive a set of electrically-conductive windings, and also having a radially-extending winding end turn support formed contiguously from the rotor body.
H02K 15/09 - Forming windings by laying conductors into or around core parts by laying conductors into slotted rotors
H02K 15/02 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
A method of making a component of an electric machine using an additive manufacturing process is disclosed. The method includes forming a first lamina of a conductive material, building a first layer of a second material on a first surface of the first lamina, treating the second material on the first surface of the first lamina to define a first insulative layer, and building on the first insulative layer a second lamina of a conductive material. The steps can be repeated iteratively until a desired thickness or number of layers is reached.
A system and a method for identifying errors within a modular framework of a system comprising of a flight management system and an error reporting system. The modular components and correlating code modulars of the modular framework can be executed collectively or independently. Each modular component can be designed to incorporate independent modular updates or modifications.
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
G06F 11/07 - Responding to the occurrence of a fault, e.g. fault tolerance
An enclosure for an electric machine includes a housing defining an axial bore having an opening at a first end of the bore. The housing comprises a first wall having a first inboard surface partially defining the bore, and a first outboard surface spaced from the first inboard surface, the first wall defining a first coolant channel disposed between the first inboard and first outboard surface. An end cap is fastenable to the housing to cover the opening.
G05D 1/10 - Simultaneous control of position or course in three dimensions
B64D 43/00 - Arrangements or adaptations of instruments
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
