A blockage detection system for detecting aircraft probe blockages includes a processor, a communication device, and computer-readable memory. The computer-readable memory encoded with instructions that, when executed by the processor, cause the system to execute a blockage detection algorithm. The processor receives a static pressure and an impact pressure from one or more aircraft probes. The processor converts the static pressure and the impact pressure to a correlating variable, via the blockage detection algorithm. The processor evaluates the correlating variable, via the blockage detection algorithm, to determine if a value of the correlating variable exceeds a threshold indicative of a blockage. The processor outputs a blockage indicator, to a receiving system in response to the correlating variable exceeding the first threshold indicative of a blockage. The processor is further able to determine if the blockage has cleared by reference to an external comparative pressure measurement.
A method for identifying objects and determining their trajectories includes analyzing an image frame to identify an object, creating a bounding box around the object, filtering event data based on the position of the bounding box, and analyzing the filtered event data to determine a trajectory of the object. A system for identifying objects and determining trajectories of the objects.
G06V 10/764 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant la classification, p. ex. des objets vidéo
An air data reasoner system for evaluating aircraft sensor data obtained from aircraft sensors performs the following steps to generate organized outputs of aircraft sensor data. The system receives aircraft parameter values for various aircraft parameters from the plurality of aircraft sensors. The system selects applicable performance models for the aircraft parameter values from the repository of performance models. The system executes the applicable performance models to generate accuracy values corresponding to each of the aircraft parameter values. The system determines the most accurate parameter values and corresponding source aircraft sensor. The system compiles a list of available redundant source aircraft sensors. The system generates a threshold table with operating thresholds for each parameter. The system outputs the most accurate parameter values, the corresponding source aircraft sensors, the list of available redundant source aircraft sensors, and the threshold table to consuming systems.
Apparatus and associated methods relate to mode matching a plurality of optical beams to a corresponding plurality of optical power amplifiers. The mode-matched plurality of beams is generated by mode matching a single laser beam and then splitting the mode-matched beam into the plurality of beam-split portions. Each of the plurality of beam-split portions is then guided to a corresponding one of a plurality of optical power amplifiers that amplifies the beam-split portion guided thereto. Optical path lengths between the mode-matching optics and the plurality of optical power amplifiers are created to be substantially equal to one another thereby enabling optical mode matching of the mode-matched optical beam to each of the plurality of optical power amplifiers.
G01N 21/25 - CouleurPropriétés spectrales, c.-à-d. comparaison de l'effet du matériau sur la lumière pour plusieurs longueurs d'ondes ou plusieurs bandes de longueurs d'ondes différentes
G01N 21/39 - CouleurPropriétés spectrales, c.-à-d. comparaison de l'effet du matériau sur la lumière pour plusieurs longueurs d'ondes ou plusieurs bandes de longueurs d'ondes différentes en recherchant l'effet relatif du matériau pour les longueurs d'ondes caractéristiques d'éléments ou de molécules spécifiques, p. ex. spectrométrie d'absorption atomique en utilisant des lasers à longueur d'onde réglable
G01N 21/53 - Dispersion, c.-à-d. réflexion diffuse dans un corps ou dans un fluide dans un courant de fluide, p. ex. dans la fumée
H01S 3/00 - Lasers, c.-à-d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet
H01S 3/10 - Commande de l'intensité, de la fréquence, de la phase, de la polarisation ou de la direction du rayonnement, p. ex. commutation, ouverture de porte, modulation ou démodulation
H01S 3/23 - Agencement de plusieurs lasers non prévu dans les groupes , p. ex. agencement en série de deux milieux actifs séparés
A bulkhead for an air data probe includes an upstream end, a downstream end, and an upstream portion extending from the upstream end. The upstream portion includes an exterior surface, a first plurality of walls extending radially outward from the exterior surface of the upstream portion, a first pad extending radially outward from the exterior surface of the upstream portion, and a first plurality of channels formed between one or more of the first plurality of walls and the first pad. The first plurality of channels are configured to receive a wire heater.
A windshield wiper system includes an arm hub connected to a drive shaft, a curved cantilever beam connected to the arm hub, and an elastomeric wiper blade element. The curved cantilever beam has a cross-sectional shape. The elastomeric wiper blade element includes a mounting channel shaped to engage with the cross-sectional shape of the curved cantilever beam such that the elastomeric wiper blade element can be installed on the curved cantilever beam.
An automatic aircraft lighting control system can include a control module. The control module can be configured to receive imaging data from one or more cameras operatively associated with the aircraft and automatically control external aircraft lights based on the imaging data.
B60Q 1/34 - Agencement des dispositifs de signalisation optique ou d'éclairage, leur montage, leur support ou les circuits à cet effet les dispositifs ayant principalement pour objet d'indiquer le contour du véhicule ou de certaines de ses parties, ou pour engendrer des signaux au bénéfice d'autres véhicules pour indiquer un changement de direction
B60Q 1/46 - Agencement des dispositifs de signalisation optique ou d'éclairage, leur montage, leur support ou les circuits à cet effet les dispositifs ayant principalement pour objet d'indiquer le contour du véhicule ou de certaines de ses parties, ou pour engendrer des signaux au bénéfice d'autres véhicules pour engendrer des signaux à éclats durant la marche, autres que pour signaler le changement de direction, p. ex. appels de phares
B60Q 11/00 - Agencement des dispositifs témoin pour les dispositifs prévus dans les groupes
H05B 47/105 - Commande de la source lumineuse en réponse à des paramètres détectés
H05B 47/165 - Commande de la source lumineuse en suivant une séquence programmée pré-assignéeCommande logique [LC]
H05B 47/17 - Modes opérationnels, p. ex. passage du mode manuel au mode automatique ou interdiction d'opérations spécifiques
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 - Dispositifs comportant des éléments flexibles ou déformables, p. ex. comportant des membranes ou des lamelles élastiques
B81C 1/00 - Fabrication ou traitement de dispositifs ou de systèmes dans ou sur un substrat
G01L 1/14 - Mesure des forces ou des contraintes, en général en mesurant les variations de la capacité ou de l'inductance des éléments électriques, p. ex. en mesurant les variations de fréquence des oscillateurs électriques
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
H10N 30/30 - Dispositifs piézo-électriques ou électrostrictifs à entrée mécanique et sortie électrique, p. ex. fonctionnant comme générateurs ou comme capteurs
In accordance with at least one aspect of this disclosure, a method for seeding an optical beam includes, emitting an optical beam from an energy source towards an optical amplifier along an optical axis, and rotating one or more optical elements disposed with in the beam path of the optical beam between the energy source and the optical amplifier about the optical axis to a align the optical beam with a reference beam.
A method includes emitting scanned reference laser light from a first tunable laser into a first atomic vapor filter to output filtered scanned reference laser light and receiving the filtered reference laser light with a first detector. The method includes emitting scanned outgoing signal laser light from a second tunable laser into an atmospheric space, receiving a return of the scanned signal laser light from Doppler shifted scattering from the atmospheric space into a second atomic vapor filter to output Doppler shifted filtered scanned signal laser light, and receiving the Doppler shifted filtered scanned signal laser laser light with a second detector. Each tunable laser wavelength scan is controlled independently using information from the wavelength scan received at the associated detector to maintain the center of the wavelength scan received at the detector as the bottom of an atomic absorption well. Velocity is determined using the Doppler shift of the light collected from atmospheric space as measured by the wavelength difference between the center wavelength of the scanned reference laser and the center wavelength of the scanned outgoing signal laser light which is transmitted into the atmosphere.
G01S 17/95 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la météorologie
G01P 5/26 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure 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 optique de détection
G01P 13/02 - Indication de la direction uniquement, p. ex. par une girouette
G01S 7/481 - Caractéristiques de structure, p. ex. agencements d'éléments optiques
G01S 17/58 - Systèmes de détermination de la vitesse ou de la trajectoireSystèmes de détermination du sens d'un mouvement
Apparatus and associated methods relate to laser communication between an aircraft and an airport ground station. The system includes one or more data collection devices/sensors configured to collect aircraft data. The system further includes an embedded system including a storage device, a data buffer, and a first laser link transceiver. The storage device stores the aircraft data from the one or more data collection devices/sensors. The data buffer receives the aircraft data from the storage device. The first laser link transceiver is mounted on the aircraft and connected to the data buffer to receive the aircraft data from the data buffer. The system further includes a second laser link transceiver mounted on the airport ground station and configured to optically connect directly to the first laser link transceiver and receive the aircraft data therefrom.
A windshield wiper system for an aircraft includes a wiper drive shaft with a first end and a second end opposite the first end. The second end includes a first threaded section between the first end and the second end, a second threaded section extending axially along the wiper drive shaft between the first threaded section and the second end relative to a center axis of the wiper drive shaft, and a spline section axially between the first threaded section and the second threaded section. Further included is a first nut to thread to the first threaded section, a second nut to thread to the second threaded section, and a wiper arm assembly including an adjustment sleeve configured to interlock with the spline section, a wiper arm with a first end configured to enclose the adjustment sleeve, and a second end of the wiper arm attached to a wiper blade.
An airborne object detection system can include one or more imaging devices configured to be disposed on an aircraft and to produce imaging data of one or more portions of an environment surrounding the aircraft, and an object detection system operatively connected to the one or more imaging devices to receive the imaging data. The object detection system can be configured to determine whether there are one or more collision risk objects in the imaging data that will or are likely to collide with the aircraft based on the imaging data. The object detection system can be configured to determine a collision location on the aircraft that the one or more collision risk objects will or are likely to collide with.
G06V 20/58 - Reconnaissance d’objets en mouvement ou d’obstacles, p. ex. véhicules ou piétonsReconnaissance des objets de la circulation, p. ex. signalisation routière, feux de signalisation ou routes
An aircraft sensor includes a housing, a strut connected to and extending from a top of the housing, and a probe extending from the strut. The strut includes a flange extending radially outward from a bottom portion of the strut and a body extending from a top of the flange. The strut also includes a bore extending into the strut body and having a closed end positioned in the body. The strut also includes a vent shaft fluidly connected to the bore and including an outlet.
A wiper apparatus includes a wiper axis interface configured for mounting a wiper assembly to a wiper drive. A lower wiper arm extends from the wiper axis interface to a wiper mount that is configured to connect the lower arm to an upper arm. A first end of the lower wiper arm proximate the wiper axis interface has a first airfoil profile and wall thickness. A second end of the lower wiper arm proximate the wiper mount has a second airfoil profile and wall thickness. An intermediate portion of the lower wiper arm extending between the first and second ends has a transitioning airfoil profile and thickness that transitions from the first airfoil profile and wall thickness to the second airfoil profile and wall thickness.
A system includes an optical ice detection (OID) sub-system optically coupled to light collection optics. A water vapor differential absorption LIDAR (WV-DIAL) sub-system is optically coupled to the OID laser source or light collection optics. The OID sub-system and the WV-DIAL sub-system share at least a portion of an optical path of the light source or through the light collection optics. The OID sub-system, the WV-DIAL sub-system, and the illumination and light collection optics can all be aboard an aircraft. A method includes using a set of illumination and light collection optics aboard an aircraft to obtain data indicative of optical ice detection (OID) and water vapor differential absorption LIDAR (WV-DIAL), e.g. to detect contrail forming conditions for the aircraft and/or predict persistence of contrails from the aircraft.
G01W 1/06 - Instruments pour indiquer des conditions atmosphériques par mesure de plusieurs variables, p. ex. humidité, pression, température, nébulosité ou vitesse du vent donnant l'indication des conditions météorologiques par combinaison des variables mesurées
G01S 17/86 - Combinaisons de systèmes lidar avec des systèmes autres que lidar, radar ou sonar, p. ex. avec des goniomètres
G01S 17/95 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la météorologie
An air-data probe component includes an additively manufactured inner member. The inner member includes integrally formed, monolithic structures including a mandrel bulkhead defining a plurality of pneumatic chambers therein in fluid communication with an outer surface of the mandrel bulkhead through respective pressure ports, and a plurality of pneumatic tubes extending aft of the mandrel bulkhead along a probe axis, each in fluid communication with a respective one of the plurality of pneumatic chambers. An outer cover tip can be engaged about the mandrel bulkhead with a plurality of bores therethrough for fluid communication of outside air pressure into the plurality of pneumatic tubes through the outer cover tip. A forward surface of the outer cover tip can be flush, conformal, and continuous with an aerodynamic outer surface of an aircraft.
In accordance with at least one aspect of this disclosure, a system can include, a housing assembly and an element assembly having a dual-material component therein, the element assembly joined within the housing assembly via a weld joint at a weld interface between the dual material component and the housing assembly.
A method includes converting audio to text, converting the text to a taxi path, and using a look-up table (LUT) to check for obstructions in the taxi path. The method includes issuing a warning if there are one or more obstructions in the taxi path based on the LUT or else refraining from issuing a warning if there are not one or more obstructions in the taxi path based on the LUT. Converting audio to text can include using a machine learning model. Before converting the audio to text, the method can include checking communications between a pilot and air traffic control (ATC) for keywords relevant to taxiing. Converting audio to text can be performed upon detecting the keywords in the audio. The audio can include words spoken by ATC to the pilot and/or words spoken by the pilot to ATC.
Apparatus and associated methods relate to improving measurement of metrics determined by laser air-data systems subject to unwanted background light. Such measurements are improved by estimating and excising the unwanted background light from the total light received by an optical receiver which receives a Doppler-shifted reflected portion of a projected beam of light backscattered by aerosols and air molecules of an atmosphere. The background light is estimated using a background-light rejection filter that separates the light received by the optical receiver into a beam sampling portion and a complementary non-beam portion. The beam sampling portion has band-pass wavelengths that include the Doppler-shifted reflected portion and a portion of the unwanted background light. The complementary non-beam portion includes background light of wavelengths outside of the band-pass wavelengths of the beam sampling portion. The non-beam sampling portion is used to estimate the unwanted background light included in the beam sampling portion.
Apparatus and associated methods relate to improving measurement of metrics determined by laser air-data systems subject to unwanted background light. Such measurements are improved by estimating and excising the unwanted background light from the total light received by an optical receiver which receives a Doppler-shifted reflected portion of a projected beam of light backscattered by aerosols and air molecules of an atmosphere. The background light is estimated using a background-light rejection filter that receives the light received by the optical receiver after it has been filtered by a vapor cell filter and separates the light received by the optical receiver into a beam sampling portion and a complementary non-beam portion. The non-beam sampling portion is used to estimate the background light portion within the beam sampling portion, which also contains the Doppler-shifted reflected portion of the projected beam used for calculating the metrics of air data.
Apparatus and associated methods relate to measuring metrics of a contrail produced by an aircraft engine. To measure such metrics, a beam of light is projected into a projection volume that intersects an exhaust path of the aircraft engine. Light from a reception volume that intersects the exhaust path of the aircraft engine is received. An intersection volume is formed by an intersection of the reception volume and the projection volume. The light received includes a reflected portion of the projected beam backscattered by the atmosphere from within the intersection volume. The reflected portion of light received is used to determine whether a contrail is forming within the intersection volume. An alert is generated in response to determination that a control is forming within the intersection volume.
Apparatus and associated methods relate to improving measurement of metrics of air data of an atmosphere outside an aircraft. Such measurements are improved by estimating a daylight portion of light received by an optical receiver configured to receive a reflected portion of the projected beam backscattered by the atmosphere. Estimation of the daylight portion is performed using a daylight filter. The daylight filter receives the light received by the optical receiver after it has been filtered by a vapor cell filter and separates the light, as filtered, into a beam sampling portion and a complementary non-sampling portion. The non-beam sampling portion includes wavelengths immediately adjacent to the beam sampling portion. The non-beam sampling portion is used to estimate the daylight portion within the beam sampling portion, which also contains the reflected portion of the projected beam used for calculating the metrics of air data.
G01S 17/95 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la météorologie
G01P 5/26 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure 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 optique de détection
G01S 7/481 - Caractéristiques de structure, p. ex. agencements d'éléments optiques
G01S 17/58 - Systèmes de détermination de la vitesse ou de la trajectoireSystèmes de détermination du sens d'un mouvement
In accordance with at least one aspect of this disclosure, a system includes a wiper drive shaft configured to drive a wiper arm between a start position and an end sweep position. The wiper drive shaft includes external threads defined therein and at a distal end thereof. An axial length of the external threads along the wiper drive shaft defines the start position and the end sweep position, and a total desired sweep angle between the start position and end sweep position. The wiper drive shaft includes and a first hard stop groove and a second hard stop groove, each defined at a respective first axial offset and a second axial offset from the external threads to define a first hard stop position and second hard stop position.
A windshield wiper system for an aircraft includes a wiper arm and a wiper shaft with a first end connected to a base of the wiper arm. An electric motor is coupled to the wiper shaft to rotationally drive the wiper shaft. The windshield wiper system also includes a brake system. The brake system includes an electromagnet comprising an energized mode and a de-energized mode. The brake system also includes an anti-rotation assembly with a first element and a second element. The first element is connected directly to the wiper shaft. The second element is rotationally stationary relative the wiper shaft and the first element. The second element is configured to interlock with the first element to prevent rotation of the first element and the wiper shaft when both the electromagnet is in the de-energized mode and the wiper arm is in a park position.
A windshield wash system includes a pump with an inlet and an outlet, and a fluid reservoir fluidically connected to the inlet of the pump. A fluid delivery line is fluidically connected to the outlet of the pump and at least one nozzle is fluidically connected to the fluid delivery line. An electronic control unit is in controlling communication with the pump. A pressure sensor is in the fluid delivery line and is in communication with the electronic control unit.
A wiper apparatus includes a wiper arm extending from a first wiper arm end to second wiper arm end. The wiper arm has an airfoil profile. The wiper arm includes a core having a lattice structure with shell extending around the lattice structure. A composite layer is formed around the core. The composite layer conforms to an outer surface of the shell. A method of making a wiper apparatus includes forming a core of a wiper arm with a lattice structure surrounded by a shell. The method includes depositing a layer of composite material on an outer surface of the shell.
In accordance with at least one aspect of this disclosure, an air data probe includes, an outer shell defining an airflow path from an inlet at a proximal end thereof to a distal end thereof and a heater configured to be installed within the outer shell an in the airflow path, the water dam comprising, one or more sensing elements at a distal end thereof. The system also includes, a water dam disposed on or in the heater winding and between a proximal end and distal end of the heater winding configured to impede a flow of water droplets and ice crystals to permit proper drain hole operation, prevent moisture buildup in rear areas of the probe and pressure lines, and prevent interaction of the flow of water and the one or more sensing elements. The water dam is configured to mechanically stabilize itself on or in the heater winding during installation of the heater winding and water dam into the outer shell.
An ice detection sensor apparatus includes a strut body extending along a longitudinal axis. The strut body includes an axially extending wall extending around the longitudinal axis to surround an interior space, and an axial-facing end wall connected to an axial end of the axially extending wall. The axial-facing end wall partially bounds the interior space. A magneto strictive oscillator sensing element extends from the interior space, through the axial-facing end wall. The sensing element is engaged to the axial-facing end wall for oscillation along the longitudinal axis relative to the axial-facing end wall. A permanent magnet (PMG) element is integral with, e.g., monolithic with, the strut body.
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.
In accordance with at least one aspect of this disclosure, a system includes a wiper arm configured to sweep along a sweep zone defined between a start position and an end sweep position, a wiper drive shaft operatively connected at a proximal end to the wiper arm to drive the wiper arm between the start position and the end sweep position, a tracer operatively connected to a distal end of the wiper drive shaft configured to mimic movement of the wiper arm, and one or more position indicators disposed proximate a distal end of the tracer corresponding to at least the start position and the end sweep position, where the distal end of the tracer configured interact with the one or more limiters during operation of the wiper arm.
An optical apparatus can be configured to cover an optical transceiver. At least a portion of the apparatus can be configured to move relative to the transceiver between a block state wherein the apparatus is configured to block transmission from a transmitter of the optical transceiver to a receiver of the optical transceiver as well as block emission from the transmitter to the atmosphere, and one or more transmit states wherein the apparatus is configured to allow at least partial transmission from the transmitter of the optical transceiver to a receiver of the optical transceiver while blocking emission from the transmitter to the atmosphere.
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
In accordance with at least one aspect of this disclosure, a system includes a wiper system having at least one wiper arm configured to wipe a windshield of a vehicle, a reservoir configured to hold washer fluid, and a fluid line fluidly connected between the reservoir and the wiper system configured to provide the jet of washer fluid from an outlet of the reservoir to the wiper arm for spraying onto the windshield. The reservoir includes, an interior volume having an outlet, and a piston configured to force the washer fluid through the outlet to produce a jet of washer fluid at the outlet.
A doppler lidar system includes an acousto-optic modulator. The acousto-optic modulator frequency shifts light to simulate a Doppler effect of a target without moving the target relative to a transceiver. A detector detects a frequency. One or more processors then calibrate the doppler lidar system based on the detected frequency. The acousto-optic modulator is then decoupled to return the doppler lidar system to a normal operating condition. The acousto-optic modulator is coupled in a transmit path or a receive path of the doppler lidar system.
G01P 21/02 - Essai ou étalonnage d'appareils ou de dispositifs couverts par les autres groupes de la présente sous-classe de tachymètres
G01P 5/26 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure 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 optique de détection
A method of ice protection includes performing anti-icing on a forward portion of an air data sensor for a first duration while maintaining de-icing on an aft portion of the air data probe in a deactivated state. The method includes activating de-icing on the aft portion of the air data probe for a second duration while also performing anti-icing on the forward portion of the air data sensor.
A method includes checking an optical detector with a field of view for degradation by: directing the optical detector to a surface of an object in the field of view, wherein the surface is positioned at a given distance from the optical detector, and wherein the surface has a known reflectance; detecting an optical return from the surface with the optical detector to generate a return signal; and determining whether the return signal is representative of a degraded signal. The method includes outputting an alert for maintenance action if the return signal is indicative of a degraded signal.
A cloud phase detection system can include a light receiver system configured to receive reflected light from a cloud, and a cloud phase module operatively connected to the light receiver system and configured to calculate a fourth Stokes parameter and a multiple scattering ratio (MSR) parameter based on the reflected light. The cloud phase module can be configured to determine a phase of a cloud based on a relationship between the fourth Stokes parameter and the MSR parameter.
In accordance with at least one aspect of this disclosure, a system include, a wiper arm configured to sweep along a sweep zone defined between a start position and an end sweep position. A wiper drive shaft is operatively connected at a proximal end to the wiper arm to drive the wiper arm between the start position and the end sweep position. At least an angular encoder is operatively connected to a distal end of the wiper drive shaft configured to record an actual position of the wiper arm. A controller is operatively connected to the encoder to receive positon wiper arm position data therefrom.
A packaged pressure sensor assembly is disclosed that includes a pressure sensor including an upper substrate and a lower substrate bonded to one another by way of a first glass frit having a first bonding temperature, so as to define a hermetically sealed pressure sensing chamber therebetween, and a housing defining an internal cavity having a base with a support surface for supporting the pressure sensor, wherein the pressure sensor is bonded to the support surface of the base by a second glass frit having a second bonding temperature that is lower than the first bonding temperature.
G01L 9/00 - 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 pressionTransmission 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
A gas detection system includes a first optical fiber bundle connected to a first multi-pass cell for connecting the first multi-pass cell to a Raman spectrum analyzer. A second optical fiber bundle is connected to the first multi-pass cell for connecting the first multi-pass cell to a second multi-pass cell. The second optical fiber bundle can include a delay coil configured to provide temporal spacing between spectral returns from the first multi-pass cell and from the second multi-pass cell. The first and second multi-pass cells can be biconic multipass cells with a the first optical fiber bundle directed toward a first D-mirror, which is directed toward a T-mirror, which is directed toward a second D-mirror, which is directed toward the second optical fiber bundle. The D-mirrors can be on an opposite end of the first multi-pass cell from the T-mirror and the first and second optical fiber bundles.
G01M 3/04 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par détection de la présence du fluide à l'emplacement de la fuite
A detector includes a scoop portion. The scoop portion includes a top surface extending continuously from a forward tip to an aft end, a bottom surface opposite from the top surface, and a receiving portion therebetween. The bottom surface includes an aperture. The top surface includes a detent formed therein opposite from the aperture across the receiving portion. The detent is configured and adapted to receive at least a portion of a sensor. A method includes additively manufacturing a scoop portion and brazing a strut portion to the scoop portion. The scoop portion includes an upper surface, a lower surface, and a receiving portion therebetween.
G01K 7/18 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments résistifs l'élément étant une résistance linéaire, p. ex. un thermomètre à résistance de platine
B33Y 80/00 - Produits obtenus par fabrication additive
G01K 1/14 - SupportsDispositifs de fixationDispositions pour le montage de thermomètres en des endroits particuliers
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
42.
SYSTEMS AND METHODS FOR WAFER DIE ASSEMBLY BONDING
A wafer die assembly includes a first wafer having at least a central cavity defined therein. The wafer die assembly includes a second wafer mounted to the first wafer. At least one of the first or second wafers includes an etched pattern. The etched pattern including at least one peripheral cavity, and a raised area raised relative to the peripheral cavity. A method of assembling a wafer die assembly includes etching a central cavity into a first wafer and etching a pattern into at least one of the first wafer or a second wafer. The first wafer and/or the second wafer includes a raised area raised relative to the peripheral cavity or the central cavity. The method includes bonding the second wafer to the first wafer.
Apparatus and associate methods relate to desaturation protection of a metal-oxide-semiconductor field-effect transistor (MOSFET) or an insulated-gate bipolar transistor (IGBT). Desaturation protection circuitry provides desaturation protection to the MOSFET or IGBT as well protection of the desaturation protection circuitry, should such circuitry be connected to reverse power. The desaturation protection circuitry determines a desaturation condition based on a control voltage generated by a Zener-diode-resistor network conductively coupled between first and second conduction nodes of the MOSFET or IGBT. The Zener-diode-resistor network is coupled to first and second conduction nodes via a rectifying diode that is configured to protect the desaturation protection circuitry from reverse bias power. Negative feedback limits current through a signal isolation device that is conductively isolated from the output node, which indicates whether the desaturation condition has been determined.
H03K 17/082 - Modifications pour protéger le circuit de commutation contre la surintensité ou la surtension par réaction du circuit de sortie vers le circuit de commande
44.
System and method for a secure unidirectional network interface
A secure network interface system includes a secure domain interface, a processing system, a network function device, and a network interface. The processing system is configured to send and receive information within secure systems, transmit configuration data for the network interface, compile data from the secure systems into a plurality of data packets, and transmit the plurality of data packets to the network function device without being physically capable of receiving data packets from the network function device, thus providing a demonstration of security partitioning. The network function device receives the configuration data, configures the network interface using the configuration data, and provides discrete feedback to the processing system regarding a configuration status. The network interface sends the plurality of data packets to one or more external unsecure systems and to limits a communication protocol type received from one or more external unsecure systems.
A sensor includes an airfoil body, a heater element, and a temperature probe. The airfoil body defines a sensor axis and having a leading edge, a trailing edge, and an ice accretion feature. The heater element extends axially through the airfoil body between the leading edge and the trailing edge of the airfoil body. The temperature probe extends axially through the airfoil body between the heater element and the trailing edge of the airfoil body. The heater element is axially overlapped by the ice accretion feature to accrete ice chordwise forward of a tip surface aperture. Gas turbine engines, methods of making sensors, and methods of accreting ice on sensors are also described.
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
F01D 25/02 - Dispositifs de dégivrage pour machines motrices dans lesquelles se produisent des phénomènes de givrage
G01K 1/08 - Dispositifs de protection, p. ex. étuis
G01K 1/20 - Compensation des effets des variations de température autres que celles à mesurer, p. ex. variations de la température ambiante
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
B33Y 80/00 - Produits obtenus par fabrication additive
A biometric sensing system for an aircraft cockpit includes an infrared camera, infrared illuminators, and a CPU. The infrared camera is mounted in a flight deck display surface of the cockpit and has a field of view including an upper body region of a flight crew member when the flight crew member is seated in the cockpit. The infrared illuminators are mounted in the flight deck display surface and directed to illuminate the upper body region of the flight crew member when the flight crew member is seated in the cockpit. The CPU can communicate instructions to the infrared camera and infrared illuminators, receive image data captured by the infrared camera, and process the image data captured by the infrared camera in order to determine an alertness level of the flight crew member based on at least one biometric characteristic within the captured image data.
G06V 20/59 - Contexte ou environnement de l’image à l’intérieur d’un véhicule, p. ex. concernant l’occupation des sièges, l’état du conducteur ou les conditions de l’éclairage intérieur
A61B 5/00 - Mesure servant à établir un diagnostic Identification des individus
A61B 5/0205 - Évaluation simultanée de l'état cardio-vasculaire et de l'état d'autres parties du corps, p. ex. de l'état cardiaque et respiratoire
A61B 5/024 - Mesure du pouls ou des pulsations cardiaques
A61B 5/08 - Dispositifs de mesure pour examiner les organes respiratoires
A61B 5/18 - Dispositifs pour l'exécution des tests de capacité pour conducteurs de véhicules
G08B 7/06 - Systèmes de signalisation selon plus d'un des groupes Systèmes d'appel de personnes selon plus d'un des groupes utilisant une transmission électrique
H04N 23/23 - Caméras ou modules de caméras comprenant des capteurs d'images électroniquesLeur commande pour générer des signaux d'image uniquement à partir d'un rayonnement infrarouge à partir du rayonnement infrarouge thermique
A pressure sensor includes a header with a cavity, a pressure sensing element, an isolator, an isolator support, a damping gap, and oil. The pressure sensing element is in the cavity. The isolator has corrugations and is mounted to a top of the header. The isolator covers the cavity. The isolator support is in the cavity of the header above the pressure sensing element. The isolator support is corrugated. The corrugations of the isolator support align with the corrugations on the isolator. The damping gap is between the isolator support and the isolator. The damping gap has a constant width between the isolator support and the isolator. Oil fills the damping gap and the cavity in the header. The oil moves between the damping gap and the header cavity in response to external pressure changes moving the isolator.
A method of making an object includes partially additively manufacturing the object onto a removable platen using an additive manufacturing system, removing the platen with the object from a base of the additive manufacturing system, processing the object on the platen, inserting the platen with the object that has been processed into the additive manufacturing system or a different system, mating the platen with the object that has been processed to the base of the additive manufacturing system or a base of the different system using a registration feature, and manufacturing a layer onto the object that has been processed.
A positional lens locking assembly for focusing and maintaining focus of a camera lens assembly includes a lens tube, a camera housing, a sealing member, and a locking member. The lens tube has a head and a barrel. The head extends outward from the barrel and the barrel has a threaded portion. The camera housing has a first threaded bore configured to receive the threaded portion of the barrel. The sealing member is disposed between the head and the camera housing and is configured to be compressed between the head and the camera housing. The locking member is configured to retain the lens tube in a position.
H04N 23/52 - Éléments optimisant le fonctionnement du capteur d'images, p. ex. pour la protection contre les interférences électromagnétiques [EMI] ou la commande de la température par des éléments de transfert de chaleur ou de refroidissement
A method includes obtaining data from an event camera for each of a plurality of time instances. The data includes events corresponding to changes detected by a corresponding plurality of pixels of the event camera at each time instance. Temporally regularized optical flow velocities are determined at each time instance. Each of the pixels has a respective one of the optical flow velocities at each time instance. An optical flow of a feature of an object in a field of view of the event camera is determined based on a predetermined relationship between the temporally regularized optical flow velocities at a selected time instance and the temporally regularized optical flow velocities at a subsequent time instance. The feature of the object corresponds to one of the plurality of events at the selected time instance and one of the plurality of events at the subsequent time instance.
G06V 20/40 - ScènesÉléments spécifiques à la scène dans le contenu vidéo
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
G06T 7/269 - Analyse du mouvement utilisant des procédés basé sur le gradient
G06V 10/44 - Extraction de caractéristiques locales par analyse des parties du motif, p. ex. par détection d’arêtes, de contours, de boucles, d’angles, de barres ou d’intersectionsAnalyse de connectivité, p. ex. de composantes connectées
G06V 20/52 - Activités de surveillance ou de suivi, p. ex. pour la reconnaissance d’objets suspects
A pyrometer configured to sense thermal radiation within a volume (e.g., a turbomachine turbine or turbine engine) can include a photodiode configured to sense radiation at least within a desired infrared bandwidth and to output a photodiode signal, and an optical bandpass filter disposed in front of the photodiode to prevent radiation outside of the desired bandwidth from reaching the photodiode. The desired infrared bandwidth can be selected to be outside the absorption bands of one or more selected fluids such that the presence of one or more fluids (gasses) within the volume does not affect radiation that reaches the photodiode.
A system includes a first sensor positioned to sense presence of a contrail in a first volume, wherein the first volume at least partially overlaps an expected volume of a contrail proximate an aircraft. A second sensor is positioned to sense a background reference in a second volume, where the second volume does not overlap the expected volume of a contrail proximate an aircraft. A controller is operatively connected to the first and second sensors. The controller includes machine readable instructions configured to cause the controller to utilize data input from both the first and second volumes to determine if a contrail is present from the aircraft. A system includes machine readable instructions configured to cause the controller to predict persistence of contrails on an intended route through the volume of airspace and to determine an improved route and/or propulsion operation to reduce contrail formation and persistence relative to the intended route.
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p. ex. à la température, à la pression, à la vitesse du rotor
G06V 20/56 - Contexte ou environnement de l’image à l’extérieur d’un véhicule à partir de capteurs embarqués
In accordance with at least one aspect of this disclosure, a method of detecting a fault in a plurality of optical detectors includes receiving a first return beam from a first optical detector interrogation beam to generate a first optical signal indicative of an atmospheric condition from a first location on board the aircraft and receiving a second return beam from a second optical detector interrogation beam to generate a second optical signal indicative of the atmospheric condition from a second location on board the aircraft. The method includes, comparing each of the first and second optical signals with a baseline value to determine whether there is a fault in at least one optical detector of the plurality of optical detectors.
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 - Dispositifs de dégivrage pour machines motrices dans lesquelles se produisent des phénomènes de givrage
F01D 21/12 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à la température
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
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p. ex. à la pression
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
F01D 25/10 - Chauffage, p. ex. réchauffage avant démarrage
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
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 - Appareils ou ensembles fonctionnels d'accumulation de chaleur en généralAppareils échangeurs de chaleur de régénération non couverts par les groupes ou utilisant la chaleur latente
B64D 15/02 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
56.
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.
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
G01N 29/22 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonoresVisualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet Détails
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 5/16 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant les différences de pression dans le fluide en utilisant des tubes de Pitot
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.
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.
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
B60S 1/08 - Essuie-glaces ou analogues, p. ex. grattoirs caractérisés par l'entraînement entraînés électriquement
B60S 1/16 - Moyens de transmission pour l'entraînement
B60S 1/18 - Moyens de transmission pour l'entraînement mécaniques
H02K 7/00 - Dispositions pour la mise en œuvre d'énergie mécanique associées structurellement aux machines dynamo-électriques, p. ex. association structurelle avec des moteurs mécaniques d'entraînement ou des machines dynamo-électriques auxiliaires
H02K 7/06 - Moyens de transformation d'un mouvement alternatif en un mouvement circulaire ou vice versa
H02K 7/08 - Association structurelle avec des paliers
H02K 7/116 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des engrenages
60.
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.
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.
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 15/20 - Dispositifs pour détecter le givrage ou amorcer la mise en action du dégivrage
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
62.
AIR DATA PROBE ELECTRONICS HOUSING WITH THERMAL ISOLATING FEATURES
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.
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 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer la longueur, la largeur ou l'épaisseur pour mesurer l'épaisseur
H05B 3/06 - Éléments chauffants combinés constructivement avec des éléments d'accouplement ou avec des supports
G01D 5/14 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens 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 déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension
B64D 15/20 - Dispositifs pour détecter le givrage ou amorcer la mise en action du dégivrage
B33Y 80/00 - Produits obtenus par fabrication additive
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.
G01N 1/14 - Dispositifs d'aspiration, p. ex. pompesDispositifs d'éjection
B81B 3/00 - Dispositifs comportant des éléments flexibles ou déformables, p. ex. comportant des membranes ou des lamelles élastiques
B81C 1/00 - Fabrication ou traitement de dispositifs ou de systèmes dans ou sur un substrat
G01L 1/14 - Mesure des forces ou des contraintes, en général en mesurant les variations de la capacité ou de l'inductance des éléments électriques, p. ex. en mesurant les variations de fréquence des oscillateurs électriques
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
H10N 30/30 - Dispositifs piézo-électriques ou électrostrictifs à entrée mécanique et sortie électrique, p. ex. fonctionnant comme générateurs ou comme capteurs
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 - Essai ou étalonnage d'appareils ou de dispositifs couverts par les autres groupes de la présente sous-classe
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
G01P 5/16 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant les différences de pression dans le fluide en utilisant des tubes de Pitot
G01P 13/02 - Indication de la direction uniquement, p. ex. par une girouette
71.
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 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant les différences de pression dans le fluide en utilisant des tubes de Pitot
G01P 5/08 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant la variation d'une variable électrique directement affectée par l'écoulement, p. ex. en utilisant un effet dynamo-électrique
G05B 19/04 - Commande à programme autre que la commande numérique, c.-à-d. dans des automatismes à séquence ou dans des automates à logique
G01R 31/00 - Dispositions pour tester les propriétés électriquesDispositions pour la localisation des pannes électriquesDispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
72.
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 - 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
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
73.
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 - 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 pressionTransmission 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 jauges de contrainte à résistance
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.
F41G 7/36 - Systèmes de commande de guidage pour missiles autopropulsés basés sur des données prédéterminées de la position de la cible utilisant des références inertielles
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 coordination of a plurality of munitions in a Global Positioning System (GPS) denied attack of a plurality of ground targets. A relative position of each munition is determined relative to the other munitions in the salvo and a distance range is determined of each munition relative to the other munitions in the salvo. A constellation formation is determined for the plurality of munitions in the salvo relative to a target seeker basket such that each munition in the constellation formation is navigated to its respective target seeker basket, whereby a change in navigation for each munition is caused when necessary such that each munition arrives at its determined seeker basket at an approximate same time.
F41G 7/34 - Systèmes de commande de guidage pour missiles autopropulsés basés sur des données prédéterminées de la position de la cible
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
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 16/44 - 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 procédé de revêtement
C23C 16/455 - 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 procédé de revêtement caractérisé par le procédé utilisé pour introduire des gaz dans la chambre de réaction ou pour modifier les écoulements de gaz dans la chambre de réaction
G01P 13/02 - Indication de la direction uniquement, p. ex. par une girouette
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 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure 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 43/00 - Aménagements ou adaptations des 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 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 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 21/36 - Dispositions pour le freinage ou le ralentissementCommande dans quatre quadrants
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
H02P 21/18 - Estimation de la position ou de la vitesse
H02P 21/22 - Commande du courant, p. ex. en utilisant une boucle de commande
H02P 27/12 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par le type de tension d'alimentation utilisant une tension d’alimentation à fréquence variable, p. ex. tension d’alimentation d’onduleurs ou de convertisseurs utilisant des convertisseurs de courant continu en courant alternatif ou des onduleurs avec modulation de largeur d'impulsions appliquant des impulsions en guidant le vecteur-flux, le vecteur-courant, ou le vecteur-tension sur un cercle ou une courbe fermée, p. ex. pour commande directe du couple
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 - 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 pressionTransmission 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 19/06 - Moyens pour empêcher la surcharge ou l'influence délétère du milieu à mesurer sur le dispositif de mesure ou vice versa
G01R 27/08 - Mesure de la résistance par mesure à la fois de la tension et de l'intensité
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 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 modulationOptique non linéaire pour la commande de l'intensité, de la phase, de la polarisation ou de la couleur
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
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 - Dispositifs pour détecter le givrage ou amorcer la mise en action du dégivrage
G01N 21/3577 - CouleurPropriétés spectrales, c.-à-d. comparaison de l'effet du matériau sur la lumière pour plusieurs longueurs d'ondes ou plusieurs bandes de longueurs d'ondes différentes en recherchant l'effet relatif du matériau pour les longueurs d'ondes caractéristiques d'éléments ou de molécules spécifiques, p. ex. spectrométrie d'absorption atomique en utilisant la lumière infrarouge pour l'analyse de liquides, p. ex. l'eau polluée
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 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G02B 30/25 - Systèmes ou appareils optiques pour produire des effets tridimensionnels [3D], p. ex. des effets stéréoscopiques en fournissant des première et seconde images de parallaxe à chacun des yeux gauche et droit d’un observateur du type stéréoscopique utilisant des techniques de polarisation
G06V 20/17 - Scènes terrestres transmises par des avions ou des drones
90.
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 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 - Dispositions de structureMontage des éléments, p. ex. relativement à l'écoulement de fluide utilisant un élément de chauffage, de refroidissement ou de détection d'un type particulier
94.
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 - Mesure du débit volumétrique ou du débit massique d'un fluide ou d'un matériau solide fluent, dans laquelle le fluide passe à travers un compteur par un écoulement continu en utilisant des effets mécaniques
G01F 1/688 - Dispositions de structureMontage des éléments, p. ex. relativement à l'écoulement de fluide utilisant un élément de chauffage, de refroidissement ou de détection d'un type particulier
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.
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
B05B 1/00 - Buses, têtes de pulvérisation ou autres dispositifs de sortie, avec ou sans dispositifs auxiliaires tels que valves, moyens de chauffage
B05B 1/14 - Buses, têtes de pulvérisation ou autres dispositifs de sortie, avec ou sans dispositifs auxiliaires tels que valves, moyens de chauffage avec des orifices de sortie multiplesBuses, têtes de pulvérisation ou autres dispositifs de sortie, avec ou sans dispositifs auxiliaires tels que valves, moyens de chauffage avec des filtres placés dans ou à l'extérieur de l'orifice de sortie
B05B 7/24 - Appareillages de pulvérisation pour débiter des liquides ou d'autres matériaux fluides provenant de plusieurs sources, p. ex. un liquide et de l'air, une poudre et un gaz avec des moyens, p. ex. un récipient, pour alimenter en liquide ou autre matériau fluide un dispositif de décharge
B05B 9/03 - Appareillages de pulvérisation pour débiter des liquides ou d'autres matériaux fluides, n'impliquant pas de mélange avec des gaz ou des vapeurs caractérisés par les moyens d'alimentation en liquide ou en autre matériau fluide
B05B 12/14 - Aménagements de commande de la distributionAménagements de réglage de l’aire de pulvérisation pour fournir à un orifice de pulvérisation unique, un liquide ou un autre matériau fluide choisi parmi plusieurs
B05B 13/04 - Moyens pour supporter l'ouvrageDisposition ou assemblage des têtes de pulvérisationAdaptation ou disposition des moyens pour entraîner des pièces les têtes de pulvérisation étant déplacées au cours de l'opération
B08B 1/00 - Nettoyage par des procédés impliquant l'utilisation d'outils
B08B 3/02 - Nettoyage par la force de jets ou de pulvérisations
B08B 5/02 - Nettoyage par la force de jets, p. ex. le soufflage de cavités
B08B 13/00 - Accessoires ou parties constitutives, d'utilisation générale, des machines ou appareils de nettoyage
F02C 6/06 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p. ex. sans sortie de puissance mécanique délivrant des gaz comprimés
B60S 1/08 - Essuie-glaces ou analogues, p. ex. grattoirs caractérisés par l'entraînement entraînés électriquement
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.
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.
G06T 7/246 - Analyse du mouvement utilisant des procédés basés sur les caractéristiques, p. ex. le suivi des coins ou des segments
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
G06T 7/73 - Détermination de la position ou de l'orientation des objets ou des caméras utilisant des procédés basés sur les caractéristiques
G06V 10/22 - Prétraitement de l’image par la sélection d’une région spécifique contenant ou référençant une formeLocalisation ou traitement de régions spécifiques visant à guider la détection ou la reconnaissance
G06V 10/75 - Organisation de procédés de l’appariement, p. ex. comparaisons simultanées ou séquentielles des caractéristiques d’images ou de vidéosApproches-approximative-fine, p. ex. approches multi-échellesAppariement de motifs d’image ou de vidéoMesures de proximité dans les espaces de caractéristiques utilisant l’analyse de contexteSélection des dictionnaires
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
