A sensor includes a mount arranged along a sensor axis, an airfoil body fixed to the mount and having a first face and second face extending along the sensor axis, a heater element, and a temperature probe. The heater element and the temperature probe are positioned within the airfoil body and extend axially along the airfoil body. The airfoil body defines within its interior a pressure channel having an inlet segment extending between the heater element and the first face of the airfoil body to prevent ice formation and/or melt ice entrained within air traversing the pressure channel. Gas turbine engines, methods of removing ice or preventing ice formation, and methods of making sensors are also described.
F01D 25/02 - De-icing means for engines having icing phenomena
F01D 21/12 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to temperature
G01K 13/02 - Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
An aerodynamic friction energy deicing system can include a heat energy device configured to be operatively connected to an aircraft structure and to convert heat energy due to aerodynamic friction on the aircraft structure into another form or to store heat energy due to aerodynamic friction on the aircraft structure. The converted or stored energy can be used for any suitable purpose, e.g., for use in ice prevention and/or deicing and/or powering one or more aircraft systems.
F28D 20/02 - Heat storage plants or apparatus in general; Regenerative heat-exchange apparatus not covered by groups or using latent heat
B64D 15/02 - De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
B64D 27/02 - Aircraft characterised by the type or position of power plant
3.
VARIABLE SHAPE SENSING ELEMENT OF A MAGNETOSTRICTIVE OSCILLATING ICE DETECTOR SENSOR FOR IMPROVED ICE COLLECTION EFFICIENCY USING ADDITIVE MANUFACTURING
A probe head of a magnetostrictive oscillator includes a base and a plurality of hollow protrusions extending from the base. Each protrusion of the plurality of hollow protrusions includes a first end and a second end opposite the first end. The second end is connected to the base. Each protrusion also includes an inner side and an outer side opposite the inner side.
G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object - Details
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
4.
VARIABLE SHAPE SENSING ELEMENT OF A MAGNETOSTRICTIVE OSCILLATING ICE DETECTOR SENSOR FOR IMPROVED ICE COLLECTION EFFICIENCY USING ADDITIVE MANUFACTURING
A probe head of a magnetostrictiye oscillator includes a base and a plurality of hollow protrusions extending from the base. Each protrusion of the plurality of hollow protrusions includes a first end and a second end opposite the first end. The second end is connected to the base. Each protrusion also includes an inner side and an outer side opposite the inner side.
A system includes a body, a sensor, a pressurized fluid source, and a blockage detection module. The body defines a cavity open to an ambient environment at a port. The sensor communicates with the cavity to produce a signal representative of a fluid pressure within the cavity. The blockage detection module includes a pressure regulator and a valve disposed along a conduit fluidly connecting the pressurized fluid source to the cavity. The blockage detection module includes a processor and memory encoded with instructions of a blockage detection method.
G01P 21/00 - Testing or calibrating of apparatus or devices covered by the other groups of this subclass
G01P 5/16 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes
A system includes a body, a sensor, a pressurized fluid source, and a blockage detection module. The body defines a cavity open to an ambient environment at a port. The sensor communicates with the cavity to produce a signal representative of a fluid pressure within the cavity. The blockage detection module includes a pressure regulator and a valve disposed along a conduit fluidly connecting the pressurized fluid source to the cavity. The blockage detection module includes a processor and memory encoded with instructions of a blockage detection method.
A method is disclosed for additive manufacturing a three-dimensional object layer-by-layer including depositing a layer of material on a bed surface or a previously deposited layer of the object to form the object layer-by-layer; providing energy to the material after each layer is deposited with the energy being provided by an energy source that forms an energized beam directed at the material; altering a property of a gas surrounding the material and through which the energized beam extends to alter a property of the object constructed from the material; melting the material with the energized beam to form a melted pool of liquefied material; and allowing the material to solidify to bond the material to a previous layer of material of the object.
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
8.
REVERSIBLE MOTOR CONFIGURED WITH MOTION STOPS FOR AIRCRAFT WINDSHIELD WIPER SYSTEM
Disclosed is an aircraft windshield wiper system, having: a wiper arm; a reversible motor that drives the wiper arm, the motor including: a stator; a rotor configured to rotate relative to the stator; a forward shaft segment that is driven by the rotor and being rotationally connected to the wiper arm; an aft shaft segment that is driven by the rotor, the aft shaft segment including a forward end and an aft end; a ball nut that translates along the aft shaft segment from rotation of the aft shaft segment; a forward stop at a forward end of the aft shaft segment, configured to stop forward translational motion of the ball nut along the aft shaft segment; and an aft stop at an aft end of the aft shaft segment, configured to stop aft translational motion of the ball nut along the aft shaft segment.
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
B60S 1/18 - Means for transmitting drive mechanically
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
9.
TEMPERATURE-BASED SUPPRESSION OF SPURIOUS ICE SIGNALS
An ice protection system for an aircraft includes an ice detector disposed in an external aircraft surface, a temperature sensor, and a controller. The ice detector includes an ice sensor. The controller includes an icing threshold module which receives a temperature measurement from the temperature sensor, receives an ice accretion signal from the ice sensor, compares the temperature measurement to an icing threshold temperature, and determines whether the temperature measurement is above the icing threshold temperature. The controller suppresses an icing conditions alert if the temperature measurement exceeds the icing threshold temperature.
An ice protection system for an aircraft includes an ice detector disposed in an external aircraft surface, a temperature sensor, and a controller. The ice detector includes an ice sensor. The controller includes an icing threshold module which receives a temperature measurement from the temperature sensor, receives an ice accretion signal from the ice sensor, compares the temperature measurement to an icing threshold temperature, and determines whether the temperature measurement is above the icing threshold temperature. The controller suppresses an icing conditions alert if the temperature measurement exceeds the icing threshold temperature.
In some applications, aircraft air data probes are heated to prevent rain, ice, or other moisture from attaching to the air data probe, ensuring proper functionality of the air data probe. But the elevated temperatures can have negative effects on the electronic components positioned within the air data probe. Therefore, thermal isolating features are added to a housing to thermally isolate the heated parts of the air data probe from the electronic components within the air data probe, which are required to stay relatively cool for proper functioning.
12.
AIR DATA PROBE ELECTRONICS HOUSING WITH RETENTION FEATURES
In some applications, aircraft air data probes are heated to prevent rain, ice, or other moisture from attaching to the air data probe. The body of the air data probe and the components positioned within the body of the air data probe can be constructed from differing materials, resulting in differing coefficient of thermal expansions for each component. Retention features are added to a housing to prevent an epoxy potting from expanding outside its intended region and preventing damage to the electronic components within the housing.
In some applications, aircraft air data probes are heated to prevent rain, ice, or other moisture from attaching to the air data probe, ensuring proper functionality of the air data probe. But the elevated temperatures can have negative effects on the electronic components positioned within the air data probe. Therefore, thermal isolating features are added to a housing to thermally isolate the heated parts of the air data probe from the electronic components within the air data probe, which are required to stay relatively cool for proper functioning.
In some applications, aircraft air data probes are heated to prevent rain, ice, or other moisture from attaching to the air data probe. The body of the air data probe and the components positioned within the body of the air data probe can be constructed from differing materials, resulting in differing coefficient of thermal expansions for each component. Retention features are added to a housing to prevent an epoxy potting from expanding outside its intended region and preventing damage to the electronic components within the housing.
15.
ADDITIVE MATERIAL INTEGRATED HEATER DEPOSITED OR EMBEDDED WITHIN MAGNETOSTRICTIVE OSCILLATING ICE DETECTOR SENSOR
A probe head of a magnetostrictive oscillator includes a probe head body which includes a hollow cylindrical portion with a first end, a second end, a radially inner side, and a radially outer side. The probe head body further includes a hemispherical portion connected to the first end of the hollow cylindrical portion. The probe head further includes a heater element within the radially outer side of the hollow cylindrical portion and an electrically insulative layer around the heater element. The heater element and the electrically insulative layer are integral with the probe head body.
A strut of a magnetostrictive oscillator includes a strut body which includes an airfoil with a first end, a second end, a leading edge, a trailing edge, a first side, and a second side. The strut further includes a heater element within the first side and second side, wherein the heater element connects from the first side to the second side. The strut further includes an electrically insulative layer between the heater element and the strut body. The heater element and the electrically insulative layer are integral with the strut body.
G01B 7/06 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring length, width, or thickness for measuring thickness
H05B 3/06 - Heater elements structurally combined with coupling elements or with holders
G01D 5/14 - Mechanical means for transferring the output of a sensing member; Means 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 converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage
B64D 15/20 - Means for detecting icing or initiating de-icing
B33Y 80/00 - Products made by additive manufacturing
A probe head of a magnetostrictive oscillator includes a probe head body which includes a hollow cylindrical portion with a first end, a second end, a radially inner side, and a radially outer side. The probe head body further includes a hemispherical portion connected to the first end of the hollow cylindrical portion. The probe head further includes a heater element within the radially outer side of the hollow cylindrical portion and an electrically insulative layer around the heater element. The heater element and the electrically insulative layer are integral with the probe head body.
B33Y 80/00 - Products made by additive manufacturing
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B06B 1/08 - Processes or apparatus for generating mechanical vibrations of infrasonic, sonic or ultrasonic frequency making use of electrical energy operating with magnetostriction
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B64D 43/00 - Arrangements or adaptations of instruments
G01N 25/04 - Investigating or analysing materials by the use of thermal means by investigating sintering of softening point
A strut of a magnetostrictive oscillator includes a strut body which includes an airfoil with a first end, a second end, a leading edge, a trailing edge, a first side, and a second side. The strut further includes a heater element within the first side and second side, wherein the heater element connects from the first side to the second side. The strut further includes an electrically insulative layer between the heater element and the strut body. The heater element and the electrically insulative layer are integral with the strut body.
In one embodiment, a cover for an aircraft sensor includes a leading edge, the leading edge extending along a longitudinal axis. A first side panel extending from the leading edge in a positive x direction transverse to the longitudinal axis and a second side panel extending from the leading edge in the positive x direction. A first trailing edge on the first side panel, the first trailing edge opposite the leading edge. A second trailing edge on the second side panel, the second trailing edge opposite the leading edge. A first plurality of ridges on an outer surface of the first side panel.
In one embodiment, a cover for an aircraft sensor includes a leading edge, the leading edge extending along a longitudinal axis. A first side panel extending from the leading edge in a positive x direction transverse to the longitudinal axis and a second side panel extending from the leading edge in the positive x direction. A first trailing edge on the first side panel, the first trailing edge opposite the leading edge. A second trailing edge on the second side panel, the second trailing edge opposite the leading edge. A first plurality of ridges on an outer surface of the first side panel.
A windshield wiper system (WWS) is provided and includes a wiper blade assembly drivable along a first sweep angle, an internal wiper trigger disposed to move with the wiper blade assembly, a measurement system configured to monitor a position of the internal wiper trigger from which a corresponding position of the wiper blade assembly relative to the first sweep angle is measurable and to output a sweep angle feedback signal corresponding to monitoring results and a controller. The controller is receptive of the sweep angle feedback signal.
A stress-sensitive device includes a substrate having a first surface with a cavity defined therein and a three-dimensional deformable material extending along the first surface and into the cavity. The three-dimensional deformable material has an electrical characteristic responsive to deformation. A method of forming a three-dimensional stress-sensitive device includes providing a substrate having a first surface and a second surface opposite the first surface, forming a cavity in the substrate, wherein the cavity is open to the first surface, depositing a sacrificial layer in the cavity, depositing a deformable material on the sacrificial layer, and removing at least a portion of the sacrificial layer to form an interstitial space between the deformable material and the substrate in the cavity.
B81B 3/00 - Devices comprising flexible or deformable elements, e.g. comprising elastic tongues or membranes
G01L 1/14 - Measuring force or stress, in general by measuring variations in capacitance or inductance of electrical elements, e.g. by measuring variations of frequency of electrical oscillators
H01L 41/113 - Piezo-electric or electrostrictive elements with mechanical input and electrical output
B81C 1/00 - Manufacture or treatment of devices or systems in or on a substrate
G01L 1/18 - Measuring force or stress, in general using properties of piezo-resistive materials, i.e. materials of which the ohmic resistance varies according to changes in magnitude or direction of force applied to the material
A stress-sensitive device includes a substrate having a first surface with a cavity defined therein and a three-dimensional deformable material extending along the first surface and into the cavity. The three-dimensional deformable material has an electrical characteristic responsive to deformation. A method of forming a three-dimensional stress- sensitive device includes providing a substrate having a first surface and a second surface opposite the first surface, forming a cavity in the substrate, wherein the cavity is open to the first surface, depositing a sacrificial layer in the cavity, depositing a deformable material on the sacrificial layer, and removing at least a portion of the sacrificial layer to form an interstitial space between the deformable material and the substrate in the cavity.
G01L 1/18 - Measuring force or stress, in general using properties of piezo-resistive materials, i.e. materials of which the ohmic resistance varies according to changes in magnitude or direction of force applied to the material
Provided are embodiments for a direct drive wiper system. The system includes a motor that is operably coupled to a wiper system to drive one or more wiper arms of the wiper system, and a gearbox, wherein an input to the gearbox is coupled to the motor and an output of the gearbox is coupled to the wiper assembly, wherein the gearbox is configured to convert an input from the motor to an output to drive the wiper system. The system also includes a brake and stopper mechanism that is coupled to the gearbox and the wiper system. Also provided are embodiments for a method for operating the direct drive wiper system.
A wireless communication device includes a metallic chassis, a slot extending through a sidewall of the metallic chassis, and a slot antenna secured to an inner surface of the metallic chassis and adjacent the slot. The slot antenna is integrated into the metallic chassis, giving the appearance and function of an internal antenna used with wireless communication devices having non-metallic chassis.
A method for monitoring a vehicle-borne probe includes receiving, by a first edge device in communication with the probe, sensed data related to a characteristic of a heating element of the probe, analyzing, by a first application of the first edge device, the sensed data to generate a first data output, receiving, by a coordinator in communication with the first edge device, the first data output, and incorporating the first data output into a data package, receiving, by a cloud infrastructure in communication with the coordinator, the data package via a data gateway, and analyzing, by one of the cloud infrastructure and a ground station, the data package to estimate a remaining useful life and a failure of the probe.
G01P 21/00 - Testing or calibrating of apparatus or devices covered by the other groups of this subclass
G01P 5/16 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes
G01P 13/02 - Indicating direction only, e.g. by weather vane
G01K 13/02 - Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
27.
DYNAMIC AIR DATA PROBE PROGNOSTICS HEALTH MONITORING EDGE DEVICE
An edge device for use in a system for monitoring a vehicle-borne probe includes a first communication interface configured to receive sensed data related to a characteristic of a heating element of a first probe, a core application module configured to host a plurality of core applications, a dynamic application module configured to host a plurality of dynamic applications, and a processing unit configured to implement the plurality of core applications on the sensed data. The plurality of core applications includes a coarse data processing application configured to monitor and analyze the sensed data to generate a first data output.
G01P 5/16 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes
G01P 5/08 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring variation of an electric variable directly affected by the flow, e.g. by using dynamo-electric effect
G05B 19/04 - Programme control other than numerical control, i.e. in sequence controllers or logic controllers
G01R 31/00 - Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
28.
DYNAMIC MULTI-STAGE AIR DATA PROBE PROGNOSTICS HEALTH MONITORING MANAGEMENT
A system for monitoring a vehicle-borne probe includes a first edge device in communication with the probe and configured to sense data related to a characteristic of a heating element of the probe, a coordinator in communication with the first edge device and configured to receive a first data output from the first edge device and to incorporate the first data output into a data package, a cloud infrastructure in communication with the coordinator via a data gateway and configured to analyze the data package to estimate a remaining useful life and predict a failure of the probe, and a ground station in communication with the cloud infrastructure and configured to refine remaining useful life estimation and failure prediction techniques of the system.
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
29.
DYNAMIC AIR DATA PROBE PROGNOSTICS HEALTH MONITORING COORDINATOR
A coordinator for use in a system for monitoring a vehicle-borne probe includes a first communication interface configured to exchange data with at least one edge device of a plurality of edge devices, a second communication interface configured to exchanged data with a cloud infrastructure and at least one vehicle system, and a processing unit. The processing unit is configured to analyze synthesized data comprising first data outputs from at least one edge device of the plurality of edge devices, second data outputs from at least one edge device of the plurality of edge devices, and data from the at least one vehicle system. The processing unit is further configured to implement a data processing application to analyze the synthesized data to generate a third data output, and incorporate the synthesized data and the third data output into a data package.
Apparatus and associated methods relate to sensing pressure and mitigating the error introduced by the thermoelectric effect. A pressure sensing device includes a pressure sensor, a temperature sensor, and an error correction device. The pressure sensor produces a voltage output proportional to a sensed pressure. The temperature sensor measures a first temperature at a first location and a second temperature at a second location to produce a temperature difference signal. The error correction device modifies the pressure output proportionally to the temperature difference signal to produce a temperature adjusted pressure output which compensates for error introduced from the temperature difference.
G01L 9/04 - Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means by making use of variations in ohmic resistance, e.g. of potentiometers of resistance strain gauges
A method and system for constraining navigational drift in a munition caused by Inertial Measurement Unit (IMU) bias error during flight of the munition in a constellation of a plurality of munitions in a Global Positioning System (GPS) denied attack. Each munition is provided with a datalink communication system to communicate with other munitions in the constellation and a navigation system having an IMU for guiding the munition in flight. An estimated position and covariance of the estimated position is determined for each munition via each munitions' navigation system. A range of each munition relative to at least one other munition in the munition constellation is determined via each munitions' datalink communication system. The estimated position and range to at least one other munition in the munition constellation is shared by each munition via each munitions' datalink communication system. Navigational drift for each munition is determined utilizing the estimated position of at least one other munition and the range to that at least one other munition in the munition constellation. And navigational drift in each munition is constrained by compensating for IMU bias error in each munition utilizing the determined navigational drift for each respective munition in the munition constellation.
A method including obtaining at each of a plurality of nodes navigation data of the node, communicating at each node its navigation data to the other nodes via each node's datalink communication system, receiving at each node navigation data communicated from the other nodes, determining at each node distance range of the node relative to the other nodes for which navigation data was received, determining at each node a constellation of the nodes as a function of the navigation data of the node, the navigation data received from the other nodes, and the distance range of the node relative to the other nodes, accessing formation constraints to form the constellation at each node, calculating at each node first guidance commands to maneuver the node to adjust the constellation to be in compliance with the formation constraints; and navigating each node to execute a maneuver based on the first guidance commands.
A method and system for coordinating munitions in a salvo to form a constellation in a Global Positioning System (GPS) denied attack of a plurality of targets. Each munition is provided with a datalink communication system to communicate with other munitions and a navigation system for guiding the munition in flight. An estimated position of each munition is determined relative to the other munitions in the salvo via each munitions' datalink communication system. Two-Way Timing and Ranging (TRTW) techniques are utilized to determine positioning of each munition relative to one another. A distance range of each munition relative to the other munitions in the salvo is determined via each munitions' datalink communication system. A constellation formation of the plurality of munitions in the salvo is determined based upon the determined relative position and distance range of each munition relative to one another. A target seeker basket coordinate respectively for each munition in the constellation formation is determined relative to an array of targets. Each munition in the constellation is then navigated in flight to its respective target seeker basket coordinate via its navigation system, wherein navigating to a respective target seeker basket includes coordinating a flight path of each munition in the constellation relative to one another to its respective determined target seeker basket. And coordinating the flight path of each munition includes determining an Estimated Time of Arrival (ETA) for each munition relative to its determined target seeker basket.
A method for collaboration of a plurality of nodes includes determining at each node SLAM data for the node, the SLAM data including estimated position of features and/or targets observed and processed by the node using SLAM algorithms and covariance associated with the estimated positions, communicating at each node the node's SLAM data to the other nodes via each nodes' datalink communication system, receiving at each node SLAM data communicated from the other nodes via each node's datalink communication system, combining at each node the node's SLAM data and the SLAM data received from the other nodes based on features or targets included in SLAM data from the other nodes, refining at each node estimated positions of features and/or targets based on results of the combining, and navigating each node to a target at the target destination as a function of at least one of the refined estimated positions.
A method can include vapor depositing a corrosion resistant coating to internal and external surfaces of a metallic air data probe. For example, vapor depositing can include using atomic layer deposition (ALD). The method can include placing the metallic air data probe in a vacuum chamber and evacuating the vacuum chamber before using vapor deposition. The corrosion resistant coating can be or include a ceramic coating. In certain embodiments, vapor depositing can include applying a first precursor, then applying a second precursor to the first precursor to form the ceramic coating.
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
C23C 16/30 - Deposition of compounds, mixtures or solid solutions, e.g. borides, carbides, nitrides
C23C 16/44 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating
G01P 13/02 - Indicating direction only, e.g. by weather vane
A wave generator for an ultrasonic air data system can be configured to collect data derived from a flow of air in a downstream direction. The wave generator can include an ultrasonic wave source configured to output ultrasonic waves from a first end and a wave shaper connected to the first end of the ultrasonic wave source. The wave shaper can be configured to focus the ultrasonic waves into an area downstream from the ultrasonic wave source bounded by a first plane parallel to the downstream direction and a second plane orthogonal to the first plane.
G01P 5/24 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring the direct influence of the streaming fluid on the properties of a detecting acoustical wave
B64D 43/00 - Arrangements or adaptations of instruments
A wave generator for an ultrasonic air data system can be configured to collect data derived from a flow of air in a downstream direction. The wave generator can include an ultrasonic wave source configured to output ultrasonic waves from a first end and a wave shaper connected to the first end of the ultrasonic wave source. The wave shaper can be configured to focus the ultrasonic waves into an area downstream from the ultrasonic wave source bounded by a first plane parallel to the downstream direction and a second plane orthogonal to the first plane.
B06B 3/04 - Processes or apparatus specially adapted for transmitting mechanical vibrations of infrasonic, sonic or ultrasonic frequency involving focusing or reflecting
B64D 43/00 - Arrangements or adaptations of instruments
A flow angle sensor includes a sensing element, a background component connected to and movable with the sensing element, the background component having a marker, a lens adjacent the disk, an image sensor axially aligned with the lens, a light source positioned to illuminate the disk, and an image processing system connected to the image sensor. The image processing system provides an angle of attack output based on a location of the marker sensed by the image sensor.
A How angle sensor includes a sensing element, a background component connected to and movable with the sensing element, the background component having a marker, a lens adjacent the disk, an image sensor axially aligned with the lens, a light source positioned to illuminate the disk, and an image processing system connected to the image sensor. The image processing system provides an angle of attack output based on a location of the marker sensed by the image sensor.
40.
Heating prognostics system for ice protection system
A method of monitoring an ice protection system of a rotorcraft or an aircraft includes applying heat to rotating blades of the rotorcraft or the aircraft according to a heater duty cycle and determining an anticipated ice shed time for ice to shed from the rotating blades. Torque of the rotating blades is sensed, and an actual ice shed time for ice to shed from the rotating blades is determined based on the sensed torque. A status of the ice protection system is determined based on the anticipated ice shed time and the actual ice shed time, and the status of the ice protection system is output for consumption by a consuming system.
A corrosion-resistant air data probe includes a hollow tube having at least one opening, an inner surface of the hollow tube defining an interior cavity, a heating element, and a continuous layer of a braze material. The heating element is disposed adjacent to the inner surface, within the interior cavity. The continuous layer of the braze material completely covers the heating element and covers at least a portion of the inner surface.
A pressure sensor includes a Wheatstone bridge circuit including a first resistor, a second resistor, a third resistor, and a fourth resistor having matching output characteristics. The pressure sensor further includes a first trim resistor in series with the Wheatstone bridge circuit, wherein the first trim resistor has output characteristics matching the output characteristics of the first resistor, the second resistor, the third resistor, and the fourth resistor of the Wheatstone bridge. The pressure sensor additionally includes a second trim resistor in parallel or a parallel loop with the Wheatstone bridge circuit, wherein the second trim resistor has output characteristics matching the output characteristics of the first resistor, the second resistor, the third resistor, and the fourth resistor of the Wheatstone bridge.
G01L 9/06 - Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means by making use of variations in ohmic resistance, e.g. of potentiometers of piezo-resistive devices
G01L 19/06 - Means for preventing overload or deleterious influence of the measured medium on the measuring device or vice versa
G01R 27/08 - Measuring resistance by measuring both voltage and current
43.
SYSTEM AND METHOD OF WIPER ELECTRIC DRIVE CONTROL USING FOUR QUADRANT OPERATION
A windshield wiper system includes a three-phase motor, the three-phase inverter, a brake circuit, and a controller. The controller transmits commutation signals to the three-phase inverter to drive the motor according to an inboard-to-outboard speed profile and to drive the motor according to an outboard-to-inboard speed profile. The controller activates the brake circuit based on the inboard-to outboard speed profile, or the outboard-to-inboard speed profile, and a direct current bus voltage.
H02P 21/22 - Current control, e.g. using a current control loop
H02P 27/12 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using dc to ac converters or inverters with pulse width modulation pulsing by guiding the flux vector, current vector or voltage vector on a circle or a closed curve, e.g. for direct torque control
A corrosion-resistant air data probe includes a hollow tube having at least one opening, an inner surface of the hollow tube defining an interior cavity, a heating element, and a continuous layer of a braze material. The heating element is disposed adjacent to the inner surface, within the interior cavity. The continuous layer of the braze material completely covers the heating element and covers at least a portion of the inner surface.
45.
SYSTEM AND METHOD OF WIPER ELECTRIC DRIVE CONTROL USING FOUR QUADRANT OPERATION
A windshield wiper system includes a three-phase motor, the three-phase inverter, a brake circuit, and a controller. The controller transmits commutation signals to the three-phase inverter to drive the motor according to an inboard-to-outboard speed profile and to drive the motor according to an outboard-to-inboard speed profile. The controller activates the brake circuit based on the inboard-to outboard speed profile, or the outboard-to-inboard speed profile, and a direct current bus voltage.
A method of monitoring an ice protection system of a rotorcraft or an aircraft includes applying heat to rotating blades of the rotorcraft or the aircraft according to a heater duty cycle and determining an anticipated ice shed time for ice to shed from the rotating blades. Torque of the rotating blades is sensed, and an actual ice shed time for ice to shed from the rotating blades is determined based on the sensed torque. A status of the ice protection system is determined based on the anticipated ice shed time and the actual ice shed time, and the status of the ice protection system is output for consumption by a consuming system.
A pressure sensor includes a Wheatstone bridge circuit including a tirst resistor, a second resistor, a third resistor, and a fourth resistor haying matching output characteristics. The pressure sensor further includes a first trim resistor in series with the Wheatstone bridge circuit, wherein the first trim resistor has output characteristics matching the output characteristics of the first resistor, the second resistor, the third resistor, and the fourth resistor of the Wheatstone bridge. The pressure sensor additionally includes a second trim resistor in parallel or a parallel loop with the Wheatstone bridge circuit, wherein the second trim resistor has output characteristics matching the output characteristics of the first resistor, the second resistor, the third resistor, and the fourth resistor of the Wheatstone bridge.
Provided are embodiments including a system for performing health monitoring. The system includes a measurement device configured to measure pressure of an environment, a heating element of the heater section coupled to the measurement device, a first sensing element operably coupled to a first region of the measurement device, and a second sensing element operably coupled to a second region of the measurement device. The system also includes a programmable logic that is configured to generate a status signal or flag based at least in part on conditions of the first region or the second region of the measurement device, a processing system configured to control the heating element responsive to reaching a threshold temperature, and a display configured to display a status of the first region or second region of the measurement device based at least in part on the status signal or flag.
A method of operating an optical icing conditions sensor includes transmitting a first light beam with a first transmitter and a second light beam with a second transmitter, thereby illuminating two illumination volumes. A first receiver receives the first light beam. A second receiver receives the second light beam. A controller measures the intensity of light received by the first and second receivers. The controller compares the intensities to threshold values and determines if either intensity is greater than the threshold values. The controller determines a cloud is present if either intensity is greater than the threshold values. The controller calculates a ratio of the intensities if a cloud is present. The controller determines, using the ratio, whether the cloud contains liquid water droplets, ice crystals, or a mixture of liquid water droplets and ice crystals.
B64D 15/20 - Means for detecting icing or initiating de-icing
G01N 21/3577 - Investigating relative effect of material at wavelengths characteristic of specific elements or molecules, e.g. atomic absorption spectrometry using infrared light for analysing liquids, e.g. polluted water
An optical sensor for an aircraft includes two detectors, a light source, and a controller. The detectors are oriented along detector paths and have tilt angles and fields of view. The detectors are configured to detect light reflected from an illumination volume and to generate detector signals that correspond to intensities of detected light. The tilt angles are equal such that each detector is oriented in an opposite direction within a plane containing a light source path and the detector paths. The light source is oriented along the light source path and is configured to illuminate the illumination volume which overlaps with the fields of view within a predetermined distance range. The controller is configured to receive the detector signals, detect whether a cloud is present based upon the detector signals, determine a cloud phase, and calculate a density of the detected cloud.
G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
G06K 9/00 - Methods or arrangements for reading or recognising printed or written characters or for recognising patterns, e.g. fingerprints
G02B 30/25 - Optical systems or apparatus for producing three-dimensional [3D] effects, e.g. stereoscopic images by providing first and second parallax images to an observer’s left and right eyes of the stereoscopic type using polarisation techniques
A vision-based aircraft cabin light monitoring/control system is used to maintain the light intensity level within the aircraft cabin at a desired level. The system uses video cameras to continuously monitor the ambient light entering the passenger cabin windows, analyzes the video stream/feed to identify the light intensity level within the cabin, identifies the window whose state should be controlled, and generates commands to control the window through central cabin controllers. The system further compensates for light sources internal to the cabin and monitors the phase of flight to ensure compliance to specific light conditions within the aircraft cabin.
G02F 1/01 - Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour
B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
A method of operating an optical icing conditions sensor includes transmitting, with a transmitter, a light beam and thereby illuminating an illumination volume. A receiver array receives light over a range of receiving angles. The receiver array is configured to receive light having the wavelength over a receiver array field of view which overlaps with the illumination volume. A controller measures an intensity of light received by the receiver array. The controller determines that a cloud is present if the intensity is greater than a threshold value. The controller calculates scattering profile data of the light received by the receiver array if a cloud is determined to be present, which includes an angle of a scattering intensity peak within the range of receiving angles and a breadth of the scattering intensity peak. The controller estimates a representative droplet size within the cloud using the scattering profile data.
An optical sensor tor an aircraft includes two detectors, a light source, and a controller. The detectors are oriented along detector paths and have tilt angles and fields of view. The detectors are configured to detect light reflected from an illumination volume and to generate detector signals that correspond to intensities of detected light. The tilt angles are equal such that each detector is oriented in an opposite direction within a plane containing a light source path and the detector paths. The light source is oriented along the light source path and is configured to illuminate the illumination volume which overlaps with the fields of view within a predetennined distance range. The controller is configured to receive the detector signals, detect whether a cloud is present based upon the detector signals, detennine a cloud phase, and calculate a density of the detected cloud.
54.
DETECTION OF AIRCRAFT ICING CONDITIONS AND DISCRIMINATION BETWEEN LIQUID DROPLETS AND ICE CRYSTALS
A method of operating an optical icing conditions sensor includes transmitting a first light beam with a first transmitter and a second light beam with a second transmitter, thereby illuminating two illumination volumes. A first receiver receives the first light beam. A second receiver receives the second light beam. A controller measures the intensity of light received by the first and second receivers. The controller compares the intensities to threshold values and determines if either intensity is greater than the threshold values. The controller determines a cloud is present if either intensity is greater than the threshold values. The controller calculates a ratio of the intensities if a cloud is present. The controller determines, using the ratio, whether the cloud contains liquid water droplets, ice crystals, or a mixture of liquid water droplets and ice crystals.
A vision-based aircraft cabin light monitoring/control system is used to maintain the light intensity level within the aircraft cabin at a desired level. The system uses video cameras to continuously monitor the ambient light entering the passenger cabin windows, analyzes the video stream/feed to identify the light intensity level within the cabin, identifies the window whose state should be controlled, and generates commands to control the window through central cabin controllers. The system further compensates for light sources internal to the cabin and monitors the phase of flight to ensure compliance to specific light conditions within the aircraft cabin.
G02F 1/01 - Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour
G05D 25/02 - Control of light, e.g. intensity, colour or phase characterised by the use of electric means
56.
DETECTION OF AIRCRAFT ICING CONDITIONS AND DETERMINATION OF LIQUID CLOUD DROPLET SIZE
A method of operating an optical icing conditions sensor includes transmitting, with a transmitter, a light beam and thereby illuminating an illumination volume. A receiver array receives light over a range of receiving angles. The receiver array is configured to receive light having the wavelength over a receiver array field of view which overlaps with the illumination volume. A controller measures an intensity of light received by the receiver array. The controller determines that a cloud is present if the intensity is greater than a threshold value. The controller calculates scattering profile data of the light received by the receiver array if a cloud is determined to be present, which includes an angle of a scattering intensity peak within the range of receiving angles and a breadth of the scattering intensity peak. The controller estimates a representative droplet size within the cloud using the scattering profile data.
An aircraft windshield wiper system includes a wiper blade with a composite support member and a blade element that interfaces with the windshield of the aircraft to clear the windshield of rain and other debris. The composite support member includes a wash tube integral with the composite support member, such that the wash tube receives windshield washing fluid from a fluid reservoir and dispenses the fluid onto the windshield of the aircraft. A plurality of clips can be used to couple the composite support member to the blade element.
An aircraft windshield wiper system includes a wiper blade with a composite support member and a blade element that interfaces with the windshield of the aircraft to clear the windshield of rain and other debris. The composite support member includes a wash tube integral with the composite support member, such that the wash tube receives windshield washing fluid from a fluid reservoir and dispenses the fluid onto the windshield of the aircraft. A plurality of clips can be used to couple the composite support member to the blade element.
An aircraft windshield wiper system includes a wiper blade with a composite support member and a blade element that interfaces with the windshield of the aircraft to clear the windshield of rain and other debris. The composite support member includes a wash tube integral with the composite support member, such that the wash tube receives windshield washing fluid from a fluid reservoir and dispenses the fluid onto the windshield of the aircraft. A plurality of clips can be used to couple the composite support member to the blade element.
An aircraft windshield wiper system includes a wiper blade with a composite support member and a blade element that interfaces with the windshield of the aircraft to clear the windshield of rain and other debris. The composite support member includes a wash tube integral with the composite support member, such that the wash tube receives windshield washing fluid from a fluid reservoir and dispenses the fluid onto the windshield of the aircraft. A plurality of clips can be used to couple the composite support member to the blade element.
A probe head of an air data probe includes a unitary body extending from a first end to a second end of the probe head and a rod heater. The body includes an inlet adjacent the first end of the probe head, an air passageway extending through the body from the inlet to the second end of the probe head, a water dam extending radially through the body such that the air passageway is redirected around the water dam, and a heater bore extending within the body. The rod heater is positioned within the heater bore.
G01F 1/688 - Structural arrangements; Mounting of elements, e.g. in relation to fluid flow using a particular type of heating, cooling or sensing element
62.
Air data probe with enhanced conduction integrated heater bore and features
A probe head of an air data probe includes a body extending from a first end to a second end of the probe head and a rod heater. The body includes an inlet adjacent the first end of the probe head, an air passageway extending through the body from the inlet to a second end of the probe head, a water dam extending radially through the body such that the air passageway is redirected around the water dam, a heater bore extending within the body, and an enhanced conduction area between heater bore and an exterior surface of the probe head. The inlet, the air passageway, the water dam, and the heater bore are all unitary to the body. The rod heater is positioned within the heater bore.
G01F 1/05 - Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects
G01F 1/688 - Structural arrangements; Mounting of elements, e.g. in relation to fluid flow using a particular type of heating, cooling or sensing element
An aircraft windshield wiper system includes a wiper arm, a wiper blade coupled to a first end of the wiper arm, and an output shaft coupled to a second end of the wiper arm. The wiper blade includes a fluid dispensing system including nozzles, a fluid control unit, fluid lines, fluid source, and a user interface. The wiper blade with the fluid dispensing system is configured to dispense a variety of fluids directly from the wiper blade onto the windshield of an aircraft.
B05B 1/00 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means
B05B 1/14 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means with strainers in or outside the outlet opening
B05B 7/24 - Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas with means, e.g. a container, for supplying liquid or other fluent material to a discharge device
B05B 9/03 - Spraying apparatus for discharge of liquid or other fluent material without essentially mixing with gas or vapour characterised by means for supplying liquid or other fluent material
B05B 12/14 - Arrangements for controlling delivery; Arrangements for controlling the spray area for supplying a selected one of a plurality of liquids or other fluent materials to a single spray outlet
B05B 13/04 - Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work the spray heads being moved during operation
B08B 1/00 - Cleaning by methods involving the use of tools, brushes, or analogous members
B08B 3/02 - Cleaning by the force of jets or sprays
B08B 5/02 - Cleaning by the force of jets, e.g. blowing-out cavities
B08B 13/00 - Accessories or details of general applicability for machines or apparatus for cleaning
F02C 6/06 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
B60S 1/08 - Wipers or the like, e.g. scrapers characterised by the drive electrically driven
64.
AIR DATA PROBE WITH ENHANCED CONDUCTION INTEGRATED HEATER BORE AND FEATURES
A probe head of an air data probe includes a body extending from a first end to a second end of the probe head and a rod heater. The body includes an inlet adjacent the first end of the probe head, an air passageway extending through the body from the inlet to a second end of the probe head, a water dam extending radially through the body such that the air passageway is redirected around the water dam, a heater bore extending within the body, and an enhanced conduction area between heater bore and an exterior surface of the probe head. The inlet, the air passageway, the water dam, and the heater bore are all unitary to the body. The rod heater is positioned within the heater bore.
65.
AIR DATA PROBE WITH INTEGRATED HEATER BORE AND FEATURES
A probe head of an air data probe includes a unitary body extending from a first end to a second end of the probe head and a rod heater. The body includes an inlet adjacent the first end of the probe head, an air passageway extending through the body from the inlet to the second end of the probe head, a water dam extending radially through the body such that the air passageway is redirected around the water dam, and a heater bore extending within the body. The rod heater is positioned within the heater bore.
A multi-fiber optical sensor system includes a light source configured to generate light energy, a transmitter fiber configured to receive the light energy from the light source and to project light energy out of a projecting end of the transmitter fiber over a transmitter fiber field of view, and a plurality of receiver fibers. Each of the plurality of receiver fibers has a receiving end aligned proximate and substantially parallel to the projecting end of the transmitter fiber and is configured to receive a received portion of the projected light energy reflected from a target within a receiver field of view. The multi-fiber optical sensor system also includes a lenslet array configured to shape the transmitter fiber field of view and give the transmitter field of view a finite cross-sectional area. The lenslet array has a plurality of lens corresponding to the transmitter fiber and each of the plurality of receiver fibers and is further configured to shape the receiver fiber field of view, tilt the center of the field of view with respect to the axis of the projected light energy for each of the plurality of receiver fibers and give the receiver fiber field of view for each of the plurality of receiver fibers a finite cross-sectional area. The multi-fiber optical sensor system also includes a detector configured to detect the portion of the projected light energy received by each of the plurality of receiver fibers. The receiver fiber field of view for each of the plurality of receiver fibers crosses the transmitter fiber field of view between a first crossing point at a distance Rmin from a lens axis and a last crossing point at a distance Rmax from the lens axis. There is a center crossing point Rmid at a point where a centerline of the receiver fiber field of view for each of the plurality of receiver fibers crosses a centerline of the transmitter fiber field of view. The range between Rmin and Rmax for each of the plurality of receiver fibers defines a detection zone such that each of the plurality of receiver fibers has a unique detection zone. Targets include a hard target and/or constituents of a cloud atmosphere.
A multi-fiber optical sensor system includes a light source configured to generate light energy, a transmitter fiber configured to receive the light energy from the light source and to project light energy out of a projecting end of the transmitter fiber over a transmitter fiber field of view, and a plurality of receiver fibers. Each of the plurality of receiver fibers has a receiving end aligned proximate and substantially parallel to the projecting end of the transmitter fiber and is configured to receive a received portion of the projected light energy reflected from a target within a receiver field of view. The multi-fiber optical sensor system also includes a lenslet array configured to shape the transmitter fiber field of view and give the transmitter field of view a finite cross-sectional area. The lenslet array has a plurality of lens corresponding to the transmitter fiber and each of the plurality of receiver fibers and is further configured to shape the receiver fiber field of view, tilt the center of the field of view with respect to the axis of the projected light energy for each of the plurality of receiver fibers and give the receiver fiber field of view for each of the plurality of receiver fibers a finite cross-sectional area. The multi-fiber optical sensor system also includes a detector configured to detect the portion of the projected light energy received by each of the plurality of receiver fibers. The receiver fiber field of view for each of the plurality of receiver fibers crosses the transmitter fiber field of view between a first crossing point at a distance Rmm from a lens axis and a last crossing point at a distance Rma,,, from the lens axis. There is a center crossing point Rmid at a point where a centerline of the receiver fiber field of view for each of the plurality of receiver fibers crosses a centerline of the transmitter fiber field of view. The range between R. and Rmax for each of the plurality of receiver fibers defines a detection zone such that each of the plurality of receiver fibers has a unique detection zone. Targets include a hard target and/or constituents of a cloud atmosphere.
An angle of attack sensor includes a housing having an open end and a closed end, a faceplate positioned on the open end of the housing, the faceplate comprising a periphery at an outer edge of the faceplate, a central opening, and an exterior surface extending from the periphery to the central opening, and a vane assembly extending through the central opening of the faceplate. The exterior surface of the faceplate has a sloped profile from the periphery to the central opening.
An angle of attack sensor includes a housing having an open end and a closed end. A faceplate is positioned on the open end of the housing. The faceplate comprises an integral bearing support cage that extends into the housing and is configured to accept a first bearing and a second bearing, a periphery at an outer edge of the faceplate, a central opening, and an exterior surface extending from the periphery to the central opening. A vane assembly extends through the central opening of the faceplate. A vane shaft extends into the housing and is connected to the vane assembly, and a rotational position sensor is connected to the vane shaft.
An angle of attack sensor includes a housing and a faceplate. A vane assembly extends through a central opening of the faceplate and includes a vane. The vane comprises a root, a tip, a leading edge, a trailing edge, a first lateral face, and a second lateral face. The first lateral face and the second lateral face are symmetric about a chord of the vane and each have a forward section with an outer surface profile that is nonlinear and geometrically convex from the leading edge to a transition point at a tangent to the widest point of the geometrically convex outer surface profile and each have an aft section with an outer surface profile that extends out to form a diverging wedge shape from the transition point to the trailing edge.
A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that an evacuation slide deployment path is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to identify a region within the captured image data that corresponds to the evacuation slide deployment path, determine whether the evacuation slide deployment path will generate a failed deployment outcome, and produce a warning associated with the evacuation slide deployment path in response to determining that the evacuation slide deployment path will generate the failed deployment outcome.
A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that an engine inlet of an engine of the aircraft is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to determine whether persons or foreign objects are present near the engine inlet, or detect damage or deformation of the engine inlet.
G06V 20/52 - Surveillance or monitoring of activities, e.g. for recognising suspicious objects
H04N 7/18 - Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
G06V 10/22 - Image preprocessing by selection of a specific region containing or referencing a pattern; Locating or processing of specific regions to guide the detection or recognition
G06V 40/10 - Human or animal bodies, e.g. vehicle occupants or pedestrians; Body parts, e.g. hands
G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks
G06T 7/246 - Analysis of motion using feature-based methods, e.g. the tracking of corners or segments
G06T 7/70 - Determining position or orientation of objects or cameras
G06V 10/75 - Image or video pattern matching; Proximity measures in feature spaces using context analysis; Selection of dictionaries
A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that a wheel of a main landing gear of the aircraft is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to monitor the landing gear.
G06T 7/246 - Analysis of motion using feature-based methods, e.g. the tracking of corners or segments
G06T 7/70 - Determining position or orientation of objects or cameras
G06T 7/73 - Determining position or orientation of objects or cameras using feature-based methods
G06V 10/22 - Image preprocessing by selection of a specific region containing or referencing a pattern; Locating or processing of specific regions to guide the detection or recognition
G06V 10/75 - Image or video pattern matching; Proximity measures in feature spaces using context analysis; Selection of dictionaries
G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks
A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that a leading edge of a wing of the aircraft is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to predict a likelihood of foreign object collision with the leading edge of the wing, or detect damage or deformation to the leading edge.
G06V 20/52 - Surveillance or monitoring of activities, e.g. for recognising suspicious objects
H04N 7/18 - Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
G06V 10/22 - Image preprocessing by selection of a specific region containing or referencing a pattern; Locating or processing of specific regions to guide the detection or recognition
G06T 7/246 - Analysis of motion using feature-based methods, e.g. the tracking of corners or segments
A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that a jet bridge cabin is within the field of view of the camera when the aircraft is within a docking distance of the jet bridge cabin. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera by identifying physical characteristics of the jet bridge cabin, extracting, using the identified physical characteristics of the jet bridge cabin, alignment features corresponding to the physical characteristics of the jet bridge cabin that are indicative of alignment between the jet bridge cabin and the aircraft door, determining, based on the alignment features, whether the physical characteristics of the jet bridge cabin within the captured image data satisfy threshold alignment criteria to produce an alignment state, and outputting an indication of the alignment state.
A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that a ground surface is within the field of view of the camera during taxiing of the aircraft. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera for docking guidance by identifying, within the captured image data, a region on the ground surface corresponding to an alignment fiducial indicating a parking location for the aircraft, determining, based on the region of the captured image data corresponding to the alignment fiducial indicating the parking location, a relative location of the aircraft with respect to the alignment fiducial, and outputting an indication of the relative location of the aircraft to the alignment fiducial.
A connector includes a shell, an insert that fits within the shell, and a socket that extends within the insert. The socket includes a hood, a body within the hood, an annular tine extending from the body within the hood, an annular lip extending around the tine adjacent an end of the tine, and a cavity formed within the tine.
A connector includes a shell, an insert that fits within the shell, and a socket that extends within the insert. The socket includes a hood, a body within the hood, an annular tine extending from the body within the hood, an annular lip extending around the tine adjacent an end of the tine, and a cavity formed within the tine.
A contamination sensor for an optical sensor observation window includes a source, two prisms, a detector, and a controller. The source can emit a collimated light beam at an incident angle that is greater than a critical angle of an interface between a fluid and the window. The window has a refractive index greater than the refractive index of the fluid. The prisms can direct the collimated light beam within the window such that the collimated light beam reflects within a contamination detection zone of the window. The detector can receive the collimated light beam. The controller can communicate with the source and detector. The controller can calculate an emission/detection ratio defined by a difference between an amount of light emitted by the source and an amount of light that passes from the source to the detector by a total internal reflectance of the window.
Apparatus and associated methods relate to monitoring health of a system for sensing rotational frequency of a rotatable member. A plurality of magnetic speed probes, each of which is configured to sense the rotational frequency of the rotatable member, are arranged in transmissive proximity with one another. A transmitter-configured one of the plurality of magnetic speed probes includes a signal coupler that couples an electrical signal generated by a radio-frequency signal generator into the inductive coil of the transmitter-configured magnetic speed probe, thereby radiatively transmitting an electromagnetic signal. A speed-probe monitor electrically coupled to each of the plurality of magnetic speed probes determines, based on the coil current sensed by each of the plurality of magnetic speed probes in response to the electromagnetic signal radiatively transmitted, health of the system.
G01P 3/48 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
G01P 3/487 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by rotating magnets
A contamination sensor for an optical sensor observation window includes a source, two prisms, a detector, and a controller. The source can emit a collimated light beam at an incident angle that is greater than a critical angle of an interface between a fluid and the window. The window has a refractive index greater than the refractive index of the fluid. The prisms can direct the collimated light beam within the window such that the collimated light beam reflects within a contamination detection zone of the window. The detector can receive the collimated light beam. The controller can communicate with the source and detector. The controller can calculate an emission/detection ratio defined by a difference between an amount of light emitted by the source and an amount of light that passes from the source to the detector by a total internal reflectance of the window.
A configurable windshield wiper system for a variable sweep angle and/or variable sweep speed. The system includes a bidirectional motor, a gearbox, the gearbox having and input shaft operably coupled to the motor and an output shaft; the gear box configured to ratiometrically step down the number of turns at its output shaft relative to its input shaft; a wiper arm for sweeping a surface of a windshield, the wiper arm operably coupled to an output of the gearbox; and a controller in operable communication with the motor, the controller configured to execute an algorithm to control the position and speed of the motor to achieve a configured sweep angle and configured sweep speed for the wiper arm.
A sensor assembly for monitoring a heater system for an aircraft probe sensor includes a current sensor module with a current sensor core and a high electromagnetically permeable enclosure around the current sensor core. An input wire pathway extends through the current sensor core and is configured to receive a heater input wire. A return wire pathway extends through the current sensor core and is configured to receive a heater return wire. A high electromagnetically permeable tube extends through the current sensor core and is configured to extend around one of the input wire and the heater return wire.
POSITIVE TEMPERATURE COEFFICIENT RESISTOR HEATER ASSEMBLY HEALTH MONITORING ABSTRACT A system for determining a health status of a positive temperature coefficient resistor (PTCR) heater assembly includes a PTCR heater assembly and a health monitoring system. An input voltage is provided to the PTCR heater assembly to provide heating. The health monitoring system includes a first sensor configured to sense the input voltage at the PTCR heater assembly and a second sensor configured to sense a current through the PTCR heater assembly. The health monitoring system is configured to determine a baseline characteristic and an observed characteristic each relating to an inrush peak of the PTCR heater assembly and based on the input voltage and the current. The health monitoring system compares the observed characteristic to the baseline characteristic to assess a health status of the PTCR heater assembly and outputs the health status for PTCR heater assembly diagnostics and/or prognostics. Date Recue/Date Received 2022-04-20
G01R 31/00 - Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
B64F 5/60 - Testing or inspecting aircraft components or systems
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
G01D 18/00 - Testing or calibrating apparatus or arrangements provided for in groups
H05B 3/10 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor
87.
INFRARED INSPECTION SYSTEM FOR HEATERS COMPRISED OF POSITIVE TEMPERATURE COEFFICIENT RESISTORS
An apparatus and method for inspecting articles incorporating positive temperature coefficient resistors. The inspection apparatus includes a computing device, a power source, a housing, a support, and a thermal imager, each mounted within an interior volume of the housing. The inspection method includes receiving a first thermal image of the unpowered article mounted within the support and receiving a second thermal image of the powered article after an optimized time delay. The method further includes outputting a health indication of the positive temperature coefficient resistors based on a comparison of the first thermal image and the second thermal image.
A system for determining a health status of a positive temperature coefficient resistor (PTCR) heater assembly includes a PTCR heater assembly and a health monitoring system. An input voltage is provided to the PTCR heater assembly to provide heating. The health monitoring system includes a first sensor configured to sense the input voltage at the PTCR heater assembly and a second sensor configured to sense a current through the PTCR heater assembly. The health monitoring system is configured to determine a baseline characteristic and an observed characteristic each relating to an inrush peak of the PTCR heater assembly and based on the input voltage and the current. The health monitoring system compares the observed characteristic to the baseline characteristic to assess a health status of the PTCR heater assembly and outputs the health status for PTCR heater assembly diagnostics and/or prognostics.
An air data probe includes a probe head having an interior surface defining a cavity, a component positioned within the cavity of the probe head, a plurality of protrusions defining contact between the interior surface of the probe head and a peripheral surface of the component prior to brazing the component to the probe head, and a braze material located between the interior surface of the probe head and the peripheral surface of the component as a result of brazing the component to the probe head.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
G01P 5/16 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes
B23K 1/00 - Soldering, e.g. brazing, or unsoldering
90.
INFRARED INSPECTION SYSTEM FOR HEATERS COMPRISED OF POSITIVE TEMPERATURE COEFFICIENT RESISTORS
An apparatus and method for inspecting articles incorporating positive temperature coefficient resistors. The inspection apparatus includes a computing device, a power source, a housing, a support, and a thermal imager, each mounted within an interior volume of the housing. The inspection method includes receiving a first thermal image of the unpowered article mounted within the support and receiving a second thermal image of the powered article after an optimized time delay. The method further includes outputting a health indication of the positive temperature coefficient resistors based on a comparison of the first thermal image and the second thermal image.
Provided are embodiments for a system having an avionics system that is configured to dynamically communicate one or more configurable parameters of a wiper and wash system based at least in part on a selected mode, and an avionics bus that is configured to communicate dynamic parameters from the avionics system. The system also includes a wash system having a fluid reservoir and fluid level sensor, and a wiper system including a control unit (ECU) that is configured to operate the system based at least in part on the one or more configurable parameters, wherein the wiper system is coupled to the wash system and supplies the wash fluid to the wiper system. Also provided are embodiments of a method for performing dynamic control of the aircraft windscreen wiper and wash system configuration parameters.
An aircraft pressure measurement device includes a pressure sensor, a pressure measurement path, a valve, and a fluid port. The pressure measurement path extends between an aircraft skin and the pressure sensor, and the valve is positioned within the pressure measurement path between the aircraft skin and the pressure sensor. The valve is configured to regulate airflow through the pressure measurement path, and the fluid port is configured to allow a pressurized fluid into the pressure measurement path to clear the pressure measurement path of debris.
A differential MEMS pressure sensor includes a topping wafer with a top side and a bottom side, a diaphragm wafer having a top side connected to the bottom side of the topping wafer and a bottom side, and a backing wafer having a top side connected to the bottom side of the diaphragm wafer and a bottom side. The topping wafer includes a first cavity formed in the bottom side of the topping wafer. The diaphragm wafer includes a diaphragm, a second cavity formed in the bottom side of the diaphragm wafer underneath the diaphragm, an outer portion surrounding the diaphragm, and a trench formed in the top side of the diaphragm wafer and positioned in the outer portion surrounding the diaphragm.
G01L 13/02 - Devices or apparatus for measuring differences of two or more fluid pressure values using elastically-deformable members or pistons as sensing elements
G01L 9/00 - Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means
G01F 1/36 - Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects by measuring pressure or differential pressure the pressure or differential pressure being created by the use of flow constriction
G01L 27/00 - Testing or calibrating of apparatus for measuring fluid pressure
94.
Predicting failure and/or estimating remaining useful life of an air-data-probe heater
Apparatus and associated methods relate to predicting failure and/or estimating remaining useful life of an air-data-probe heater. Failure is predicted or useful life is estimated based on an electrical metric of the electrical operating power provided to a resistive heating element of the air-data-probe heater. The electrical metric of the air data probe heater is one or more of: i) phase relation between voltage across the resistive heating element and leakage current, which is conducted from the resistive heating element to a conductive sheath surrounding the resistive heating element; ii) a time-domain profile of leakage current through the heating element insulation during a full power cycle; and/or iii) high-frequency components of the electrical current conducted by the resistive heating element and/or the voltage across the resistive heating element.
A pressure sensor includes a housing, an isolator positioned at a first end of the housing, and a first cavity formed between the first end of the housing and the isolator. The pressure sensor further includes a second cavity formed in the housing and a channel with a first end fluidly connected to the first cavity and a second end fluidly coupled to the second cavity. A pressure sensor chip is positioned in the second cavity and includes a first diaphragm positioned at a top side of the pressure sensor chip laterally outwards from the second end of the channel to prevent a fluid from jetting onto the first diaphragm.
G01L 9/00 - Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means
G01L 19/00 - MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE - Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
G01L 19/06 - Means for preventing overload or deleterious influence of the measured medium on the measuring device or vice versa
96.
PREDICTING FAILURE AND/OR ESTIMATING REMAINING USEFUL LIFE OF AN AIR-DATA-PROBE HEATER
Apparatus and associated methods relate to predicting failure and/or estimating remaining useful life of an air-data-probe heater. Failure is predicted or useful life is estimated based on an electrical metric of the electrical operating power provided to a resistive heating element of the air-data-probe heater. The electrical metric of the air data probe heater is one or more of: i) phase relation between voltage across the resistive heating element and leakage current, which is conducted from the resistive heating element to a conductive sheath surrounding the resistive heating element; ii) a time-domain profile of leakage current through the heating element insulation during a full power cycle; and/or iii) high-frequency components of the electrical current conducted by the resistive heating element and/or the voltage across the resistive heating element.
Apparatus and associated methods relate to predicting failure and/or estimating remaining useful life of an air-data-probe heater. Failure is predicted or useful life is estimated based on an electrical metric of the electrical operating power provided to a resistive heating element of the air-data-probe heater. The electrical metric of the air data probe heater is one or more of: i) phase relation between voltage across the resistive heating element and leakage current, which is conducted from the resistive heating element to a conductive sheath surrounding the resistive heating element; ii) a time-domain profile of leakage current through the heating element insulation during a full power cycle; and/or iii) high-frequency components of the electrical current conducted by the resistive heating element and/or the voltage across the resistive heating element.
H05B 3/86 - Heating arrangements specially adapted for transparent or reflecting areas, e.g. for demisting or de-icing windows, mirrors or vehicle windshields the heating conductors being embedded in the transparent or reflecting material
G01R 31/52 - Testing for short-circuits, leakage current or ground faults
G01P 5/16 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes
98.
PREDICTING FAILURE AND/OR ESTIMATING REMAINING USEFUL LIFE OF AN AIR-DATA-PROBE HEATER
Apparatus and associated methods relate to predicting failure and/or estimating remaining useful life of an air-data-probe heater. Failure is predicted or useful life is estimated based on an electrical metric of the electrical operating power provided to a resistive heating element of the air-data-probe heater. The electrical metric of the air data probe heater is one or more of: i) phase relation between voltage across the resistive heating element and leakage current, which is conducted from the resistive heating element to a conductive sheath surrounding the resistive heating element; ii) a time-domain profile of leakage current through the heating element insulation during a full power cycle; and/or iii) high-frequency components of the electrical current conducted by the resistive heating element and/or the voltage across the resistive heating element.
A pressure sensor includes a housing, an isolator positioned at a first end of the housing, and a first cavity fomied between the first end of the housing and the isolator. The pressure sensor further includes a second cavity formed in the housing and a channel with a first end fluidly connected to the first cavity and a second end fluidly coupled to the second cavity. A pressure sensor chip is positioned in the second cavity and includes a first diaphragm positioned at a top side of the pressure sensor chip laterally outwards from the second end of the channel.
G01L 7/08 - Measuring the steady or quasi-steady pressure of a fluid or a fluent solid material by mechanical or fluid pressure-sensitive elements in the form of elastically-deformable gauges of the flexible-diaphragm type
G01L 23/00 - Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid
100.
PREDICTING FAILURE AND/OR ESTIMATING REMAINING USEFUL LIFE OF AN AIR-DATA-PROBE HEATER
Apparatus and associated methods relate to predicting failure and/or estimating remaining useful life of an air-data-probe heater. Failure is predicted or useful life is estimated based on an electrical metric of the electrical operating power provided to a resistive heating element of the air-data-probe heater. The electrical metric of the air data probe heater is one or more of: i) phase relation between voltage across the resistive heating element and leakage current, which is conducted from the resistive heating element to a conductive sheath surrounding the resistive heating element; ii) a time-domain profile of leakage current through the heating element insulation during a full power cycle; and/or iii) high-frequency components of the electrical current conducted by the resistive heating element and/or the voltage across the resistive heating element.
