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.
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.
5.
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.
6.
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.
G01R 33/18 - Mesure des propriétés de magnétostriction
B33Y 80/00 - Produits obtenus par fabrication additive
B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p.ex. par frittage ou fusion laser sélectif
B06B 1/08 - Procédés ou appareils pour produire des vibrations mécaniques de fréquence infrasonore, sonore ou ultrasonore utilisant l'énergie électrique fonctionnant par magnétostriction
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 43/00 - Aménagements ou adaptations des instruments
G01N 25/04 - Recherche ou analyse des matériaux par l'utilisation de moyens thermiques en recherchant le frittage du point de ramollissement
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.
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
B64C 7/00 - Structures ou carénages non prévus ailleurs
B64D 43/00 - Aménagements ou adaptations des instruments
F15D 1/10 - Action sur l'écoulement des fluides autour de corps formés d'un matériau solide
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 1/00 - Mesure des forces ou des contraintes, en général
G01L 1/18 - Mesure des forces ou des contraintes, en général en utilisant des propriétés des matériaux piézo-résistants, c. à d. des matériaux dont la résistance ohmique varie suivant les modifications de la grandeur ou de la direction de la force appliquée au matériau
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 - Procédés ou appareils spécialement adaptés pour transmettre des vibrations mécaniques de fréquence infrasonore, sonore ou ultrasonore impliquant une focalisation ou une réflexion
B64D 43/00 - Aménagements ou adaptations des instruments
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.
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.
13.
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.
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.
17.
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 - Dispositifs ou dispositions pour la commande de l'intensité, de la couleur, de la phase, de la polarisation ou de la direction de la lumière arrivant d'une source lumineuse indépendante, p.ex. commutation, ouverture de porte ou modulation; Optique non linéaire pour la commande de l'intensité, de la phase, de la polarisation ou de la couleur
G05D 25/02 - Commande de la lumière, p.ex. intensité, couleur ou phase caractérisée par l'utilisation de moyens électriques
19.
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.
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.
23.
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 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.
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.
H01R 13/502 - Socles; Boîtiers composés de différentes pièces
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
G01D 11/00 - MESURE NON SPÉCIALEMENT ADAPTÉE À UNE VARIABLE PARTICULIÈRE; DISPOSITIONS NON COUVERTES PAR UNE SEULE DES AUTRES SOUS-CLASSES POUR MESURER PLUSIEURS VARIABLES; APPAREILS COMPTEURS À TARIFS; DISPOSITIONS POUR LE TRANSFERT OU LA TRANSDUCTION DE MESURE NON SPÉCIALEMENT ADAPTÉES À UNE VARIABLE PARTICULIÈRE; MESURES OU TESTS NON PRÉVUS AILLEURS - Parties constitutives des dispositions pour la mesure qui ne sont pas spécialement adaptées à une variable particulière
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.
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 - Dispositions pour tester les propriétés électriques; Dispositions pour la localisation des pannes électriques; Dispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
G01D 18/00 - Test ou étalonnage des appareils ou des dispositions prévus dans les groupes
H05B 3/10 - Eléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur
28.
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.
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.
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 - Mesure de la pression permanente ou quasi permanente d’un fluide ou d’un matériau solide fluent par des éléments mécaniques ou hydrauliques sensibles à la pression sous forme de jauges, élastiquement déformables du type à diaphragme élastique
G01L 23/00 - Dispositifs ou appareils pour la mesure ou l'indication ou l'enregistrement des changements, rapides, tels que des oscillations, de la pression des vapeurs, des gaz ou des liquides; Indicateurs pour déterminer le travail ou l'énergie des moteurs à vapeur, à combustion interne ou à autres pressions de fluides à partir de la condition du fluide moteur
32.
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.
A microelectromechanical system (MEMS) strain gauge pressure sensor includes a top wafer stack having a top surface and a first cavity that is configured to receive a first fluid at a first pressure, a backing wafer having a bottom surface opposite the top surface of the top wafer stack; a diaphragm wafer positioned between the top wafer stack and the backing wafer and having a second cavity that is configured to receive a second fluid at a second pressure, and a pedestal connected laterally to the top wafer stack, the backing wafer, and the diaphragm wafer. The diaphragm wafer includes a diaphragm extending between the first cavity and the second cavity, and a resistor positioned on the diaphragm. The MEMS strain gauge pressure sensor has a central axis such that the MEMS strain gauge pressure sensor has mechanical symmetries about the central axis .
G01L 13/02 - Dispositifs ou appareils pour la mesure des différences entre plusieurs valeurs de la pression des fluides en utilisant des organes ou des pistons élastiquement déformables comme éléments sensibles
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.
A temperature sensor assembly for measuring a gas temperature in a gas flow stream includes a first substrate having a first surface configured to be connected to a thermally conductive structure in a gas path, a first temperature sensor mounted to the first substrate a first distance from the first surface, and a second temperature sensor mounted to the first substrate a second distance from the first surface. The second distance is less than the first distance. The first and second temperature sensors are arranged along a temperature gradient.
G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p.ex. à la pression
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
G01K 7/16 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments résistifs
G01K 7/42 - Circuits pour la compensation de l’inertie thermique; Circuits pour prévoir la valeur stationnaire de la température
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 support member coupled to a blade element through a clip and a fastener extending through the blade element. The support member can be made from a composite material and the clip and fastener allow for attachment of the blade element to the support member without piercing the support member.
A methodology includes circulating a temperature-controlled and flow-rate- controlled medium through a container at a controlled flow rate and submerging a thermistor with the medium. With the themiistor submerged, a power output of the thermistor is detennined and compared to a power criterion, after which classification of the thermistor occurs based on a comparison of the power output to the power criterion. The methodology can include submerging a reference thermistor within the medium and determining a reference power output of the reference thermistor with the reference thermistor submerged within the medium, the power criterion determined based on the reference power output.
G01R 31/00 - Dispositions pour tester les propriétés électriques; Dispositions pour la localisation des pannes électriques; Dispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
Apparatus and associated methods relate to optically determining rotation frequency of a rotatable member using a Fabry-Perot cavity formed between a mirror and a movable reflective mirror. A cavity dimension between the mirror and a movable reflective mirror changes in response to movement of the movable reflective mirror. The movable reflective mirror is bonded to a magneto-strictive material having a thickness dimension that changes in response to changes in a magnetic field. A magnet generates the magnetic field, which changes in response to rotation of the rotatable member.
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 is configured to clean water, dirt, and other debris from the windshield of the aircraft. The output shaft is configured to rotate and cause the wiper arm with the coupled wiper blade to sweep across and clean the windshield. A sensor and a trigger are coupled to an actuator to ensure accurate sweep angle and parking position of the wiper arm and wiper blade.
An algorithm and method for automatically generating test vectors for an LRU by deriving test vectors at the LRU boundary that, when simulated on the LRU, reproduce input and output of given test cases at the boundary of the individual requirements, and for knowing whether there are test cases that cannot be realised, i.e. test vectors cannot be derived at the LRU boundary to reproduce them at the boundary of individual requirements.
A water intrusion mitigation device for use in enclosures housing electric components and equipment that are sensitive to humidity includes a thermoelectric cooler and a water electrolyzer. The thermoelectric cooler has two sides: a first side that is configured to be heated with the application of an electric current and a second side that is configured to cooled with the application of an electric current. The water electrolyzer is a proton exchange membrane that is in thermal communication with the second side of the thermoelectric cooler.
Apparatus and associated methods relate to sensing a physical parameter and verifying correct operation of a system used to sense the physical parameter. A sensing device includes four resistive elements configured in a Wheatstone bridge configuration is configured to sense the physical parameter. A biasing network selectively provides first and second biasing conditions to the sensing device. First and second output electrical signals are generated by the sensing device in response to the first and second biasing conditions, respectively, selectively provided to the sensing device. The first and second output electrical signals are each indicative of the parameter value of the physical parameter, but not necessarily equal to one another. A verification module verifies correct operation of the system based on a consistency determination of first and second output electrical signals.
G01D 18/00 - Test ou étalonnage des appareils ou des dispositions prévus dans les groupes
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64D 43/00 - Aménagements ou adaptations des instruments
G01L 13/00 - Dispositifs ou appareils pour la mesure des différences entre plusieurs valeurs de la pression des fluides
G01B 7/16 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer les déformations dans un solide, p.ex. au moyen d'une jauge de contrainte à résistance
G01D 5/16 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier la résistance
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.
A hybrid heater system for an aircraft air data sensor includes a voltage source and a first hybrid heater set. The first hybrid heater set includes a carbon nanotube (CNT) heater, a first positive temperature coefficient (PTC) heater disposed in parallel with the CNT heater to form a parallel formation, and a second PTC heater disposed in series between the voltage source and the parallel formation.
G01D 11/00 - MESURE NON SPÉCIALEMENT ADAPTÉE À UNE VARIABLE PARTICULIÈRE; DISPOSITIONS NON COUVERTES PAR UNE SEULE DES AUTRES SOUS-CLASSES POUR MESURER PLUSIEURS VARIABLES; APPAREILS COMPTEURS À TARIFS; DISPOSITIONS POUR LE TRANSFERT OU LA TRANSDUCTION DE MESURE NON SPÉCIALEMENT ADAPTÉES À UNE VARIABLE PARTICULIÈRE; MESURES OU TESTS NON PRÉVUS AILLEURS - Parties constitutives des dispositions pour la mesure qui ne sont pas spécialement adaptées à une variable particulière
B82Y 30/00 - Nanotechnologie pour matériaux ou science des surfaces, p.ex. nanocomposites
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
G01P 5/165 - Agencement ou structure des tubes de Pitot
H05B 3/02 - Chauffage par résistance ohmique - Détails
H05B 3/12 - Eléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur caractérisés par la composition ou la nature du matériau conducteur
47.
ACOUSTIC AIR DATA SYSTEM WITH RADIALLY PAIRED RECEIVERS
An acoustic air data system includes first and second acoustic transmitters, an array of acoustic receivers, and control circuitry. The array is positioned to receive first and second acoustic signals. The control circuitry determines time difference of arrival (TDOA) of the first and second acoustic signals. The control circuitry determines, for each of a first and second set of acoustic receiver pairs, a signal velocity of the first and second acoustic signals, respectively, based on a distance between an inner acoustic receiver and an outer acoustic receiver and a corresponding TDOA for each pair of acoustic receivers. The control circuitry estimates one or more of wind angle, speed of sound, Mach number, and true airspeed of the airflow about the exterior of the vehicle based on parameters of a best fit circle.
G01P 5/24 - Mesure de la vitesse des fluides, p.ex. d'un courant atmosphérique; Mesure de la vitesse de corps, p.ex. navires, aéronefs, par rapport à des fluides en mesurant l'influence directe du courant de fluide sur les propriétés d'une onde acoustique de détection
G01P 13/00 - Indication ou enregistrement de l'existence ou de l'absence d'un mouvement; Indication ou enregistrement de la direction d'un mouvement
A system for determining parameters of a cloud atmosphere within a wind tunnel. The system includes: a light projector configured to project a pulse of light energy into a projection field of view; at least one light detector having a detection field of view that forms a range-limited intersection with the projection field of view, the range- limited intersection having a maximum sampling range so as to exclude wall structures of the wind tunnel, wherein the at least one light detector is configured to detect a backscattered portion of the projected pulse of light energy backscattered from within the range-limited intersection; and a cloud parameter calculator configured to determine parameters of the cloud atmosphere based on the backscattered portions detected.
A probe includes a probe head, a probe tip extending from the probe head and haying a sensor in fluidic communication with a first fluid stream, a pressure channel extending into the probe tip through the sensor face with a pressure sensor that senses pressure in the pressure channel, and a temperature channel extending into the probe tip through the sensor face. The temperature channel is parallel to and fluidly separate from the pressure channel and includes a temperature sensor that senses temperature in the temperature channel. The temperature channel directs fluid flow from a temperature orifice on the sensor face to at least one exit port distal from the sensor face, thereby discharging fluid flow into a second fluid stream.
G01L 19/00 - MESURE DES FORCES, DES CONTRAINTES, DES COUPLES, DU TRAVAIL, DE LA PUISSANCE MÉCANIQUE, DU RENDEMENT MÉCANIQUE OU DE LA PRESSION DES FLUIDES - Détails ou accessoires des appareils pour la mesure de la pression permanente ou quasi permanente d'un milieu fluent dans la mesure où ces détails ou accessoires ne sont pas particuliers à des types particuliers de manomètres
G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p.ex. à la pression
G01K 13/02 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler
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.
ABSTRACT A probe head for an air data probe includes a ceramic body and a heater embedded within the ceramic body. 19 Date Recue/Date Received 2020-11-05
AB STRACT A static plate heating arrangement includes a faceplate including a port extending from an exterior surface of the faceplate to an interior surface of the faceplate, a fixed resistance heater in thermal communication with the interior surface and surrounding the port, and a self- regulating heater in thermal communication with the interior surface and surrounding the fixed resistance heater. The fixed resistance heater and the self-regulating heater are electrically connected in series. 14 Date Recue/Date Received 2020-12-04
G01D 11/00 - MESURE NON SPÉCIALEMENT ADAPTÉE À UNE VARIABLE PARTICULIÈRE; DISPOSITIONS NON COUVERTES PAR UNE SEULE DES AUTRES SOUS-CLASSES POUR MESURER PLUSIEURS VARIABLES; APPAREILS COMPTEURS À TARIFS; DISPOSITIONS POUR LE TRANSFERT OU LA TRANSDUCTION DE MESURE NON SPÉCIALEMENT ADAPTÉES À UNE VARIABLE PARTICULIÈRE; MESURES OU TESTS NON PRÉVUS AILLEURS - Parties constitutives des dispositions pour la mesure qui ne sont pas spécialement adaptées à une variable particulière
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
H05B 1/02 - Dispositions de commutation automatique spécialement adaptées aux appareils de chauffage
H05B 3/22 - Eléments chauffants ayant une surface s'étendant essentiellement dans deux dimensions, p.ex. plaques chauffantes non flexibles
RUGGEDIZED TWO-AXIS OPTICAL BEAM STEERING DEVICE ABSTRACT An optical beam steering device is disclosed which includes an optical component for interacting with an optical beam, a gimbal supporting the optical component, a roll cage supporting the gimbal, and a mount that houses and rotatably supports the roll cage. The roll cage and the mount include adjustment features allowing for both linear and angular adjustments of the gimbal and the roll cage. 17 CA 3062690 2019-11-25
G02B 26/08 - Dispositifs ou dispositions optiques pour la commande de la lumière utilisant des éléments optiques mobiles ou déformables pour commander la direction de la lumière
G02B 7/00 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques
54.
ACOUSTIC DETECTION OF CHARACTERISTICS OF AN AIRSTREAM MOVING OVER AN AIRFOIL SURFACE
ACOUSTIC DETECTION OF CHARACTERISTICS OF AN AIRSTREAM MOVING OVER AN AIRFOIL SURFACE ABSTRACT Apparatus and associated methods relate to detecting turbulence of an airstream over an airfoil surface of an aircraft using a sequence of acoustic transducers attached to the airfoil surface of the aircraft along a path. Each of the sequence of acoustic transducers is configured to detect acoustic waves indicative of airstream condition proximate the acoustic transducer. A processor is configured to determine, for each of the sequence of acoustic transducers, a level of turbulence of the airstream proximate the acoustic transducer. 1 8 Date Recue/Date Received 2020-10-19
G01P 5/24 - Mesure de la vitesse des fluides, p.ex. d'un courant atmosphérique; Mesure de la vitesse de corps, p.ex. navires, aéronefs, par rapport à des fluides en mesurant l'influence directe du courant de fluide sur les propriétés d'une onde acoustique de détection
B64D 43/02 - Aménagements ou adaptations des instruments pour indiquer la vitesse des aéronefs ou les conditions de décrochage
55.
DETERMINING ALTITUDE OF AN AIRCRAFT DURING FLIGHT BASED ON VORTEX SHEDDING
DETER1VHNING ALTITUDE OF AN AIRCRAFT DURING FLIGHT BASED ON VORTEX SHEDDING ABSTRACT Apparatus and associated methods relate to determining altitude of an aircraft during flight based on properties of vortex shedding. A vortex-shedding projection is projected into the airstream adjacent to the exterior surface of the aircraft so as to cause vortex-shedding turbulence of the airstream. One or more downstream sound-pressure detectors, which are attached to the exterior surface of the aircraft downstream from the vortex- shedding projection, detect(s) a vortex-shedding frequency f of the vortex-shedding turbulence caused by the vortex- shedding projection. A processor determines the altitude of the aircraft based, at least in part, on the vortex-shedding frequency f of the vortex-shedding turbulence as detected by the one or more downstream sound-pressure detectors. Date Recue/Date Received 2020-09-10
G01C 5/00 - Mesure des hauteurs; Mesure des distances transversales par rapport à la ligne de visée; Nivellement entre des points séparés; Niveaux à lunette
G01P 5/24 - Mesure de la vitesse des fluides, p.ex. d'un courant atmosphérique; Mesure de la vitesse de corps, p.ex. navires, aéronefs, par rapport à des fluides en mesurant l'influence directe du courant de fluide sur les propriétés d'une onde acoustique de détection
ABSTRACT A system includes a lens mount defining an inner bore that includes inward facing threads for engaging a lens component, with a lens opening at one end of the lens mount. The lens mount includes outward facing threads for engaging a camera housing. A first seal ring is included inside the inner bore for sealing against the lens component. A second seal ring is included on an outside of the lens mount for sealing against the camera housing. 11 Date Recue/Date Received 2020-11-11
G02B 7/02 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques pour lentilles
G03B 17/08 - Corps d'appareils ou boîtiers étanches à l'eau
G03B 17/14 - Corps d'appareils avec moyens pour supporter des objectifs, des lentilles additionnelles, des filtres, des masques ou des tourelles de façon interchangeable
AB STRACT An air data probe includes a faceplate, a body connected to the faceplate, and a heating system comprising a coil, the coil being connected to the faceplate. The coil generates an electromagnetic field that couples with the body to heat the body. 21 Date Recue/Date Received 2020-11-02
G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
G01C 9/00 - Mesure de l'inclinaison, p.ex. par clinomètres, par niveaux
G01P 5/165 - Agencement ou structure des tubes de Pitot
A method and system of synchronizing a local clock with a master clock using a serial communication bus includes receiving by a serial data interface receiver a master time signal corresponding to a master clock, generating by a frequency tuning loop a time error signal corresponding to a difference between the master time signal and a local time signal, generating by the frequency tuning loop an actual frequency signal based on a base frequency and the time error signal, producing by the frequency tuning loop a command frequency error based on the actual frequency signal and the local time signal, and producing by the local clock an updated local time signal based on the command frequency error.
Apparatus and associated methods relate to creating corrected images of a scene for a terminal-imaging seeker using an electrically-controllable coded- aperture mask pattern embodied in a programmable spatial light modulator. The coded-aperture mask pattern includes a plurality of pinhole-like apertures, each of which is configured to perform pinhole-like lensing of the scene. The plurality of pinhole-like apertures form a multiplex of overlapping images on a focal plane array aligned with the optical axis. An image processor reconstructs, based on a configuration of the plurality of pinhole-like apertures and the multiplex of overlapping images, a single image of the scene.
G02B 26/02 - Dispositifs ou dispositions optiques pour la commande de la lumière utilisant des éléments optiques mobiles ou déformables pour commander l'intensité de la lumière
G02F 1/133 - Dispositions relatives à la structure; Excitation de cellules à cristaux liquides; Dispositions relatives aux circuits
A micro-fuse assembly includes a substrate, a number of thin-film micro-fuses on the substrate, and a topping wafer configured to sealingly engage to at least one of the substrate or the thin-film micro-fuses to define a cavity therebetween. The cavity is configured to encapsulate the thin-film micro-fuses within an inert environment sealed within the cavity. A method of encapsulating a micro-fuse assembly within an inert environment using a topping wafer is also disclosed.
An optical system includes an illumination source. A lens is optically coupled to the illumination source for projecting a line image. The lens conforms to a curved profile, and the lens is a Fresnel lens. A method of projecting a line image includes generating illumination from an illumination source. The method includes focusing the illumination through a lens to form a line image, wherein the lens is as described above.
G01S 7/481 - Caractéristiques de structure, p.ex. agencements d'éléments optiques
G02B 3/08 - Lentilles simples ou composées à surfaces non sphériques à surfaces discontinues, p.ex. lentille de Fresnel
G02B 27/18 - Systèmes ou appareils optiques non prévus dans aucun des groupes , pour projection optique, p.ex. combinaison de miroir, de condensateur et d'objectif
62.
MONITORING AND EXTENDING HEATER LIFE THROUGH POWER SUPPLY POLARITY SWITCHING
A method and system for monitoring a heating arrangement includes applying a first polarity voltage to a heater of the heating arrangement, detecting a first polarity heating leakage current, applying a second polarity voltage to the heating arrangement, detecting a second polarity heating leakage current, and determining health of the heating arrangement via the first polarity heating leakage current and the second polarity heating leakage current.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01R 31/52 - Test pour déceler la présence de courts-circuits, de fuites de courant ou de défauts à la terre
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
G01D 18/00 - Test ou étalonnage des appareils ou des dispositions prévus dans les groupes
H05B 3/18 - Eléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur le conducteur étant enrobé dans un matériau isolant
A method includes forming an image of a scene on a sensor through a coded aperture, wherein the coded aperture and sensor are optically coupled within an imaging platform to form a superpositioned, physically encoded image of the scene on the sensor. The method includes generating raw image data from the sensor representative of the superpositioned, physically encoded image of the scene, and transmitting the raw image data to a platform remote from the imaging platform so the raw data is encrypted during transmission. The method can include using the platform remote from the imaging platform to deconvolve the superpositioned, physically encoded image into a decoded image.
Apparatus and associated methods relate to determining an effective size, quantity, shape, and type of water particles in a cloud atmosphere based on differences in amplitudes of optical signals backscattered at different backscattering angles. Off-axis backscattering - backscattering at angles other than 180 degrees - is affected by the effective size, quantity, shape, and type of water droplets. Detected amplitudes of optical signals that are backscattered at different angles are used to indicate the effective size, quantity, shape, and type of water particles in the cloud atmosphere. In some embodiments, optical emitters and detectors are configured to measure amplitudes of optical signals backscattered at backscattering angles of both on-axis - 180 degrees - and off-axis varieties.
Disclosed is an apparatus for arc welding, comprising: a torch body comprising a power supply line and a gas supply line; two or more metal segments movable relative to one another being sized and shaped to surround a seam between two elongated objects to be welded together, the two or more metal segments being in electrical communication with the power supply line; and a gas jacket attached to each of the metal segments.
G01D 11/00 - MESURE NON SPÉCIALEMENT ADAPTÉE À UNE VARIABLE PARTICULIÈRE; DISPOSITIONS NON COUVERTES PAR UNE SEULE DES AUTRES SOUS-CLASSES POUR MESURER PLUSIEURS VARIABLES; APPAREILS COMPTEURS À TARIFS; DISPOSITIONS POUR LE TRANSFERT OU LA TRANSDUCTION DE MESURE NON SPÉCIALEMENT ADAPTÉES À UNE VARIABLE PARTICULIÈRE; MESURES OU TESTS NON PRÉVUS AILLEURS - Parties constitutives des dispositions pour la mesure qui ne sont pas spécialement adaptées à une variable particulière
G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
G01C 9/00 - Mesure de l'inclinaison, p.ex. par clinomètres, par niveaux
H05B 3/20 - Eléments chauffants ayant une surface s'étendant essentiellement dans deux dimensions, p.ex. plaques chauffantes
B32B 7/025 - Propriétés électriques ou magnétiques
67.
ADDITIVE MANUFACTURING SYSTEM INCLUDING AN OPTICAL ISOLATOR
An additive manufacturing apparatus including an energy source configured for transmitting a laser, a build plate configured to have a powder configured to be heated by the laser for additive manufacturing, at least one mirror positioned between the energy source and the build plate, the at least one mirror configured to direct the laser from the energy source to the build plate, and an optical isolator configured to reduce energy bounce back into the energy source.
A sensor assembly includes a housing defining a potting chamber and arranged along a sensor axis, a mounting flange extending about the sensor axis the axially offset along the sensor axis from the housing, and one or more intermediate flange. The one or more intermediate flange is arranged between the housing and the mounting flange along the sensor axis, the one or more intermediate flange coupling the mounting flange to the housing. The one or more intermediate flange is spaced apart from mounting flange to limit thermal communication between the mounting flange and the housing. Gas turbine engines and methods of cooling sensor assemblies are also described.
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p.ex. à la pression
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
69.
SENSORS ASSEMBLIES AND METHODS OF MAKING SENSOR ASSEMBLIES
A sensor assembly includes a mounting portion arranged to support a sensing device, a thermal shunt portion extending from the mounting portion, and a housing portion. The housing portion extends from the thermal shunt portion and is arranged on a side of the thermal shunt portion opposite the mounting portion to limit temperature of a sensor connector fixed to the housing portion of the sensor assembly. Gas turbine engines having sensor assemblies and methods of making sensor assemblies are also described.
G01D 11/00 - MESURE NON SPÉCIALEMENT ADAPTÉE À UNE VARIABLE PARTICULIÈRE; DISPOSITIONS NON COUVERTES PAR UNE SEULE DES AUTRES SOUS-CLASSES POUR MESURER PLUSIEURS VARIABLES; APPAREILS COMPTEURS À TARIFS; DISPOSITIONS POUR LE TRANSFERT OU LA TRANSDUCTION DE MESURE NON SPÉCIALEMENT ADAPTÉES À UNE VARIABLE PARTICULIÈRE; MESURES OU TESTS NON PRÉVUS AILLEURS - Parties constitutives des dispositions pour la mesure qui ne sont pas spécialement adaptées à une variable particulière
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
70.
DYNAMIC SWEEP ANGLE MEASUREMENT FOR FAULT MONITORING OF WINDSHIELD WIPER SYSTEMS
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.
An air data probe with a corrosion protection coating system includes a body with an external and an internal surface and a uniform, pinhole-free first protection layer applied by atomic layer deposition (ALD) to reduce corrosion of the body, including corrosion initiated by sulfur and nitrogen compounds. The air data probe further includes a second protection layer, covering the first protection layer over the external surfaces of the body to protect the air data probe from foreign object impact damage.
C23C 16/22 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c. à d. procédés de dépôt chimique en phase vapeur (CVD) caractérisé par le dépôt de matériaux inorganiques, autres que des matériaux métalliques
C23C 28/04 - Revêtements uniquement de matériaux inorganiques non métalliques
C23F 15/00 - Autres méthodes pour prévenir la corrosion, l'entartrage ou les incrustations
A method of characterizing an aerosol, the method comprising illuminating aerosol particles located within a measurement volume with a first electromagnetic radiation pulse emitted from a first source and receiving one or more electromagnetic radiation returns that have been scattered by the aerosol particles illuminated by the first electromagnetic radiation pulse at one or more sensors, illuminating the aerosol particles within the measurement volume with a second electromagnetic radiation pulse emitted from a second source and receiving a one or more electromagnetic radiation returns scattered by the aerosol particles illuminated by the second electromagnetic radiation pulse at the one or more sensors, determine at least one of intensity based on the one or more electromagnetic radiation returns, and determine an aerosol parameter based on an algorithm and the at least one intensity.
G01S 13/88 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques
G01N 15/00 - Recherche de caractéristiques de particules; Recherche de la perméabilité, du volume des pores ou de l'aire superficielle effective de matériaux poreux
G01N 15/02 - Recherche de la dimension ou de la distribution des dimensions des particules
G01N 15/06 - Recherche de la concentration des suspensions de particules
73.
THERMALLY-MATCHED PIEZORESISTIVE ELEMENTS IN BRIDGES
A micromechanical pressure sensor for measuring a pressure differential includes a diaphragm having an inner region and two edge regions, one opposite the other with respect to the inner region. Two or more piezoresistive resistance devices are on the diaphragm, at least one in each of the inner and edge region, and are configured to be electrically connected in a bridge circuit. The micromechanical pressure sensor is configured so that an operating temperature of the one or more piezoresistive resistance devices in the inner region is substantially the same as an operating temperature of the one or more piezoresistive resistance devices in at least one of the edge regions throughout a full operating range such that an error of the micromechanical pressure sensor output resulting from self-heating is less than if the micromechanical pressure sensor were not configured to maintain the operating temperatures substantially the same.
G01L 9/06 - Mesure de la pression permanente, ou quasi permanente d’un fluide ou d’un matériau solide fluent par des éléments électriques ou magnétiques sensibles à la pression; Transmission ou indication par des moyens électriques ou magnétiques du déplacement des éléments mécaniques sensibles à la pression, utilisés pour mesurer la pression permanente ou quasi permanente d’un fluide ou d’un matériau solide fluent en faisant usage des variations de la résistance ohmique, p.ex. de potentiomètre de dispositifs piézo-résistants
A distributed air data module system includes several air data systems and a control module communicatively connected to each air data system via a data channel. Each of the air data systems includes a sensor that is configured to sense an air data parameter and to provide a sensor output signal that is indicative of the sensed air data parameter, and a sensor analog-to-digital converter that produces a digital air data parameter signal that is representative of the sensor output signal. Each air data system has an associated air data system address code. The control module is configured to generate a selected air data system address code corresponding to a selected air data systems, receive the digital air data parameter signal associated with the selected air data system via the data channel, and transmit the digital air data parameter signal via an aircraft data bus.
G01K 1/024 - Moyens d’indication ou d’enregistrement spécialement adaptés aux thermomètres pour l’indication à distance
G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
G01C 9/00 - Mesure de l'inclinaison, p.ex. par clinomètres, par niveaux
G01L 19/08 - Moyens pour l'indication ou l'enregistrement, p.ex. pour l'indication à distance
G08C 15/12 - Dispositions caractérisées par l'utilisation du multiplexage pour la transmission de plusieurs signaux par une voie commune successivement, c. à d. utilisant la division de temps les signaux étant représentés par des caractéristiques d'impulsion dans la voie de transmission
75.
A METHOD FOR POST-FLIGHT DIAGNOSIS OF AIRCRAFT LANDING PROCESS
A method for an automated aircraft landing analysis including: receiving one or more aircraft landing performance parameters for one or more landing phases; determining a landing performance deviation for each of the one or more landing phases in response to the one or more aircraft landing performance parameters; identifying at least one of a system fault, a failure, and a pilot error that could have led to the landing performance deviations for each of the one or more landing phases; developing a fault tree for the landing performance deviations for each of the one or more landing phases; identifying measurable parameters, calculable parameters, inferable parameters, or observable parameters within the fault tree; converting the fault tree into a high level reasoning model using a standard inference methodology; performing a root cause analysis; identifying a root cause of the landing performance deviation; and displaying the root cause of landing performance deviation.
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
An air data sensor can include an acoustic transmitter configured to output an acoustic signal into an airflow and a plurality of acoustic transducers configured to receive the acoustic signal output by the acoustic transducer. The air data sensor can also include a light source configured to output a light beam into the airflow, and a light receiver configured to receive scattered light from the light beam. The light source and the light receiver can be bistatic such that a measurement zone is formed away from the air data sensor.
G01D 5/62 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens spécifiés dans plusieurs des groupes , , , et utilisant des moyens à base de radiation d'ondes ou de particules non couverts par le groupe
B64D 43/00 - Aménagements ou adaptations des instruments
G01D 5/58 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens spécifiés dans plusieurs des groupes , , , et utilisant des moyens optiques, c. à d. utilisant de la lumière infrarouge, visible ou ultraviolette
77.
PIEZOELECTRIC MEMS DEVICE WITH CANTILEVER STRUCTURES
A MEMS device includes a first layer, a second layer connected to the first layer, a first mooring portion, a second mooring portion, and a MEMS device body. The MEMS device body is connected to the first mooring portion and the second mooring portion. The MEMS device body further includes a first cantilever attached to the first mooring portion, a second cantilever attached to the second mooring portion, and a spring. The spring is in operable communication with the first cantilever and the second cantilever.
An air date probe includes a base portion, a strut portion extending from the base portion, and a tube assembly secured to an extending from the strut portion. One or more of the tube assembly or the strut portion includes a sleeve member having a sleeve outer surface positioned at a sleeve frustum angle relative to a sleeve member axis. A thin film heater is positioned at the sleeve outer surface, and the tin film heater and the sleeve member are positioned in a housing member. The housing member has a housing inner surface having a housing frustum angle such that the thin film heater is retained by compression between the housing member inner surface and the sleeve member outer surface.
A method including providing power to an aircraft probe anti-ice system, monitoring an actual power demand of the aircraft probe anti-ice system, monitoring an air data parameter and atmospheric conditions surrounding an aircraft and calculating an expected power demand of the aircraft probe anti-ice system based on the air data parameters and the atmospheric conditions, comparing the actual power demand of the aircraft probe anti-ice system to the expected power demand, and performing a corrective action if the actual power demand and the expected power demand are different by more than an acceptable amount.
Provided are embodiments for performing encryption and decryption in accordance with one or more embodiments. The embodiments include generating a random key address, obtaining a pre-stored key using the random key address, and re-arranging portions of the pre-stored key using the random key address. Embodiments also include selecting a dynamic logic operation based on the random key address, receiving data for encryption, and combining portions of the received data for encryption with the re-arranged portions of the pre-stored key using the dynamic logic operation to produce encrypted data. Embodiments include re-arranging portions of the encrypted data based on the random key address and combining the re-arranged portions of the encrypted data with the random key address into an encrypted data packet for transmission. Also provided are embodiments for a transmitter and receiver for performing the encryption and decryption.
A windshield wiper system (WWS) is provided and includes a wiper blade, a motor assembly and a control system. The wiper blade includes a tip. The motor assembly is configured to drive the wiper blade in a sweep pattern across a windshield. The control system is configured to control the driving of the wiper blade by the motor assembly in accordance with positions of the tip of the wiper blade.
Systems and methods for sensing an analog signal through digital input/output (I/O) pins are provided. Aspects include an analog to digital (ADC) circuit configured to generate a digital signal based on observations of the analog signal obtained from an analog circuit, where the ADC circuit includes a difference amplifier, a comparator, a divideby2 counter and two AND gates. Aspects also include a controller including a pin configured to receive the digital signal. The controller is configured to count pulses within the digital signal and determine values corresponding to the analog signal based on the counted pulses.
An adjustable moment counterweight assembly for an angle of attack sensor includes a fixed counterweight configured to fixedly attach to a shaft of the angle of attach sensor, the shaft being rotatable about an axis; an adjustable counterweight configured to move in a radial direction relative to the fixed counterweight via rotation of a threaded member; and a first fastener in operable communication with the fixed counterweight and the adjustable counterweight such that the first fastener can fixedly attach the adjustable counterweight to the fixed counterweight.
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 having an opening, a vane assembly extending through the opening of the faceplate, a vane shaft connected to the vane assembly and extending within the housing, the vane shaft having a bore extending through the vane shaft, a bearing surrounding the vane shaft, a vane shaft seal surrounding the vane shaft adjacent the bearing, and a first vent hole extending from an interior surface of the vane shaft to an exterior surface of the vane shaft between the bearing and a first end of the vane shaft seal, the first vent hole being in fluid communication with the bore of the vane shaft.
A pressure and temperature probe of a gas turbine engine includes a base portion and an airfoil portion extending from the base portion to an end portion located at a distal end of the probe. The airfoil portion includes a leading edge located at an upstream end of the probe relative to a direction of airflow across the probe. A temperature sensor is located in a temperature sensor chamber located in the airfoil portion, and a temperature airflow hole in the end portion is configured to admit an airflow into the temperature sensor chamber around the temperature sensor. The temperature airflow hole is configured and positioned such that the airflow admitted via the temperature airflow hole has a turning angle of less than 90 degrees into the temperature sensor chamber.
G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p.ex. à la pression
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
A probe head of an air data probe includes an insert, a portion of a heater, an outer shell, a tip weld, and a braze. The insert includes a first end, a second end opposite the first end, and a body portion extending between the first end and the second end. The body portion includes a groove. The portion of the heater is positioned within the groove. The outer shell surrounds the insert and the portion of the heater. The outer shell includes a tip portion defining a first end of the outer shell and a body portion extending from the tip portion defining a second end of the outer shell. The tip weld is between the outer shell and the first end of the insert, and the braze is between the insert and the second end of the outer shell adjacent a second end of the insert. The portion of the heater is hermetically sealed between the insert and the outer shell.
G01D 11/00 - MESURE NON SPÉCIALEMENT ADAPTÉE À UNE VARIABLE PARTICULIÈRE; DISPOSITIONS NON COUVERTES PAR UNE SEULE DES AUTRES SOUS-CLASSES POUR MESURER PLUSIEURS VARIABLES; APPAREILS COMPTEURS À TARIFS; DISPOSITIONS POUR LE TRANSFERT OU LA TRANSDUCTION DE MESURE NON SPÉCIALEMENT ADAPTÉES À UNE VARIABLE PARTICULIÈRE; MESURES OU TESTS NON PRÉVUS AILLEURS - Parties constitutives des dispositions pour la mesure qui ne sont pas spécialement adaptées à une variable particulière
87.
HEALTH MONITORING OF AN ELECTRICAL HEATER OF AN AIR DATA PROBE
Apparatus and associated methods relate to determining health of an electrical heater of an air data probe based on a comparison between a calculated expected value and a measured value of an electrical property of the electrical heater. The expected value of the electrical property is calculated based in part on the electrical power provided to the electrical heater and further based in part on the aircraft flight parameters and/or environmental conditions. Such aircraft flight parameters and/or environmental conditions can include at least one of: electric power source status, airspeed, air pressure, altitude, air temperature, humidity, liquid water content, ice water content, droplet/particle size distribution, angle of attack, and angle of sideslip. These aircraft flight parameters and/or environmental conditions are received via an aircraft interface.
G01R 15/18 - Adaptations fournissant une isolation en tension ou en courant, p.ex. adaptations pour les réseaux à haute tension ou à courant fort utilisant des dispositifs inductifs, p.ex. des transformateurs
G01D 1/18 - Dispositions pour la mesure donnant des résultats autres que la valeur instantanée d'une variable, d'application générale avec dispositions pour signaler le dépassement d'une valeur prédéterminée d'un paramètre non spécifié
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.
A windshield wiper assembly includes a wiper blade, an output shaft, and a stop member. The output shaft is supported for rotation about a rotation axis and is fixed in rotation relative to the output shaft. The stop member is fixed in rotation relative to the output shaft and extends radially from the output shaft to limit rotation of the output shaft about the rotation axis, the stop member thereby limiting movement of the wiper blade beyond a predetermined sweep range of the wiper blade. Windshield wiper systems, aircraft with windshield wiper assemblies and systems, and methods of controlling sweep of wiper blades in windshield wiper assemblies and systems are also described.
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.
A system and method for monitoring the health of a heater connected to a power supply by a power cable that includes a first power lead conducting an inlet current having an inlet current direction, and a second power lead conducting an outlet current having an outlet current direction opposite to the inlet current direction. The power cable passes through a center region of a toroid core one or more times, and a secondary winding on the toroid core is configured to induce a secondary voltage indicative of a difference between the inlet current and the outlet current, which defines the leakage current. The system includes a prognostic processor that is configured to calculate a heater health indication based on the secondary voltage, which is indicative of the heater health.
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
G01D 18/00 - Test ou étalonnage des appareils ou des dispositions prévus dans les groupes
G01R 15/18 - Adaptations fournissant une isolation en tension ou en courant, p.ex. adaptations pour les réseaux à haute tension ou à courant fort utilisant des dispositifs inductifs, p.ex. des transformateurs
A micromechanical piezoresistive pressure sensor includes a diaphragm configured to mechanically deform in response to an applied load, a sensor substrate located on the diaphragm, and a number of piezoresistive resistance devices located on the sensor substrate. The piezoresistive resistance devices are arranged in a first planar array defining a grid pattern having two or more rows, each row being aligned in a first direction. The piezoresistive resistance devices are configured to be electrically connected in a number of bridge circuits, whereby the piezoresistive resistance devices in each row is electrically connected in an associated bridge circuit. A method of using the micromechanical piezoresistive pressure sensor is also disclosed.
G01L 9/06 - Mesure de la pression permanente, ou quasi permanente d’un fluide ou d’un matériau solide fluent par des éléments électriques ou magnétiques sensibles à la pression; Transmission ou indication par des moyens électriques ou magnétiques du déplacement des éléments mécaniques sensibles à la pression, utilisés pour mesurer la pression permanente ou quasi permanente d’un fluide ou d’un matériau solide fluent en faisant usage des variations de la résistance ohmique, p.ex. de potentiomètre de dispositifs piézo-résistants
G01L 13/02 - Dispositifs ou appareils pour la mesure des différences entre plusieurs valeurs de la pression des fluides en utilisant des organes ou des pistons élastiquement déformables comme éléments sensibles
G01L 27/00 - Test ou étalonnage des appareils pour la mesure de la pression des fluides
Disclosed is a thin-film micro-fuse assembly having: a substrate; an insulating layer disposed on the substrate, the insulating layer comprising silicon dioxide; a conductor disposed on the insulating layer, the conductor forming: an inlet terminal, an outlet terminal and a fuse element between the inlet terminal and the outlet terminal, the inlet terminal and the outlet terminal widthwise converging toward the fuse element, and the fuse element having a first thickness and a first width that is between 1 and 5 times the first thickness.
Provided are embodiments for a resistor array. The resistor array includes a plurality of resistor elements, where the plurality of resistor elements includes a redundancy region for a most significant bit of an expected value. The resistor array also includes one or more switches coupled to the plurality of resistor elements, and a first terminal and a second terminal coupled to the plurality of resistor elements. Also provided are embodiments for trimming the resistor array where the resistor array includes a redundancy region for a most significant bit for an expected value.
H03H 1/00 - RÉSEAUX D'IMPÉDANCES, p.ex. CIRCUITS RÉSONNANTS; RÉSONATEURS - Détails de réalisation des réseaux d'impédances dont le mode de fonctionnement électrique n'est pas spécifié ou est applicable à plus d'un type de réseau
Provided are embodiments including a system tor 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.
G01D 18/00 - Test ou étalonnage des appareils ou des dispositions prévus dans les groupes
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
G01P 21/00 - Essai ou étalonnage d'appareils ou de dispositifs couverts par les autres groupes de la présente sous-classe
G01K 7/01 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments semi-conducteurs à jonctions PN
96.
PROGNOSTIC MONITORING OF COMPLEMENTARY AIR DATA SYSTEM SENSORS
A aircraft health management system for identifying an anomalous signal from one or more air data systems (ADS) includes one or more of a frequency processor, configured to provide a spectral signal that is representative of a frequency content of the first ADS signal, a noise processor, configured to provide a noise signal that is representative of a noise level of the first ADS signal, and a rate processor, configured to provide a rate signal that is representative of a rate of change of the first ADS signal. The aircraft health management system also includes a comparator configured to provide a differential signal between the first ADS signal and the second ADS signal, and a prognostic processor configured to determine if the ADS signal is anomalous by comparing values representative of a flight condition signal, the differential signal, and the spectral, noise, and/or rate signals.
G01S 19/23 - Test, contrôle, correction ou étalonnage d'un élément récepteur
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64D 43/00 - Aménagements ou adaptations des instruments
G01C 25/00 - Fabrication, étalonnage, nettoyage ou réparation des instruments ou des dispositifs mentionnés dans les autres groupes de la présente sous-classe
A system includes a laser air data sensor and an acoustic air data sensor. The laser air data sensor is configured to emit directional light into airflow about an aircraft exterior and to generate first air data parameter outputs for the aircraft based on returns of the emitted directional light. The acoustic air data sensor is configured to emit acoustic signals into the airflow about the aircraft exterior, sense the acoustic signals, and generate second air data parameter outputs for the aircraft based on the sensed acoustic signals.
G01S 17/88 - Systèmes lidar, spécialement adaptés pour des applications spécifiques
G01S 17/86 - Combinaisons de systèmes lidar avec des systèmes autres que lidar, radar ou sonar, p.ex. avec des goniomètres
G01S 17/875 - Combinaisons de systèmes utilisant des ondes électromagnétiques autres que les ondes radio pour déterminer l'attitude
G01C 5/06 - Mesure des hauteurs; Mesure des distances transversales par rapport à la ligne de visée; Nivellement entre des points séparés; Niveaux à lunette en utilisant des moyens barométriques
G01S 17/87 - Combinaisons de systèmes utilisant des ondes électromagnétiques autres que les ondes radio
G01S 17/95 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la météorologie
98.
PRESSURE TRANSDUCER INCLUDING KOVAR INTEGRATED PACKAGES
A pressure sensor assembly is formed by: forming an inlet channel by brazing a transition portion to a pressure port with a high temperature brazing processes, wherein the transition portion and the pressure port are both hollow tubular members and are formed of different materials, the pressure port including a base and a projection extending therefrom; after the inlet channel is formed, joining a header and a sensor to the pressure port with a soldering process that is at a lower temperature than the high temperature brazing process, wherein the header is joined to the base of the pressure port and the sensor is joined to the projection of the pressure port and is in fluid communication with a fluid to be measured through the pressure port; and welding a cover to the header.
An ultrasonic air data system can include a pole having a length longer than a boundary layer thickness of a boundary layer flow such that at least a distal end of the pole is configured to extend outwardly from an aircraft surface to be at least partially outside of the boundary layer flow. The system can include a transmitter disposed on or in the pole at or near the distal end of the pole such that the transmitter is located at least partially outside of the boundary layer flow when in use, wherein the transmitter is configured to output a transmitter signal. The system can include one or more receivers disposed downstream of the pole as defined by the boundary layer flow and configured to receive the transmitter signal.
G01D 5/48 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens à base de radiation d'ondes ou de particules
G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
G01P 5/24 - Mesure de la vitesse des fluides, p.ex. d'un courant atmosphérique; Mesure de la vitesse de corps, p.ex. navires, aéronefs, par rapport à des fluides en mesurant l'influence directe du courant de fluide sur les propriétés d'une onde acoustique de détection
G01P 13/02 - Indication de la direction uniquement, p.ex. par une girouette
100.
ARRAY OF INDEPENDENTLY-CONTROLLABLE LASER DIODE BARS FOR SCANNING A LINEAR ILLUMINATION PATTERN
Apparatus and associated methods relate to an array of independently- controllable laser diode bars configured to scan a linearly-structured beam of light upon a scene. Each of the independently-controllable laser diode bars is distributed along a common axis. Each of the independently-controllable laser diode bars is configured to emit a beam of light in an emission direction orthogonal to the common axis. Each of the independently- controllable laser diode bars can be energized in a sequence, thereby scanning the scene in the direction of the common axis.
G02B 27/18 - Systèmes ou appareils optiques non prévus dans aucun des groupes , pour projection optique, p.ex. combinaison de miroir, de condensateur et d'objectif
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
brevets
