A network is described. The network is a peer-to-peer network of nodes. The nodes maintain a distributed ledger. The distributed ledger includes a list of transactions. The list of transactions includes various transactions for maintaining a decentralized root store between the nodes. The decentralized root store includes a list of certificate authorities which are trusted by the nodes in the network. The root certificates may be retrieved from the distributed ledger, validated, and then used to access the certificate authorities.
H04L 29/06 - Commande de la communication; Traitement de la communication caractérisés par un protocole
H04L 9/30 - Clé publique, c. à d. l'algorithme de chiffrement étant impossible à inverser par ordinateur et les clés de chiffrement des utilisateurs n'exigeant pas le secret
A method is disclosed herein. The method includes receiving, by a processor, an ejection command for ejecting an ejection seat from an aircraft; determining, by the processor, an airspeed and an altitude of the ejection seat; responsive to the altitude of the ejection seat indicating a second mode of operation, determining, by the processor, whether the airspeed of the ejection seat is at or above a first threshold and below a second threshold; and responsive to the airspeed of the ejection seat being at or above the first threshold and below the second threshold: sending, by the processor, a command to deploy a drogue parachute; and, responsive to a first predetermined time period expiring, sending, by the processor, a command to deploy a main parachute and sever the drogue parachute based on a variable drogue severance delay.
An optical device includes an electrochromic layer including a single electrochromic region and electronic drivers. The optical device includes a controller for controlling the electronic drivers to change the light transmission of the electrochromic region by applying different voltages to electrodes contacting the electrochromic region. The optical device includes a light intensity sensor for detecting light intensity of regions of a two-dimensional scene, the regions of the scene corresponding to regions of the electrochromic region. The electronic drivers are caused by the controller to apply different voltages to the electrodes to set the light transmission of the regions of the electrochromic region based on detected light intensity of the regions of the scene.
An anti-fuse apparatus for enabling or disabling features associated with one or more integrated circuits (IC) set into a substrate includes a layer of low melting point dielectric material deposited above and/or between two conductive pads set into the substrate and not otherwise electrically coupled. A layer of a low melting point conductive alloy is deposited above the dielectric layer, and a layer of an energetic material deposited above the conductive alloy layer. The energetic material is connected to an ignition circuit for triggering a thermal reaction within the energetic material, removing the dielectric layer and melting the conductive alloy to electrically bridge the conductive pads, enabling or disabling features associated with the ICs (or providing tamper-proof identification strapping) without otherwise fracturing or damaging the underlying substrate or ICs set thereinto.
H01L 23/525 - Dispositions pour conduire le courant électrique à l'intérieur du dispositif pendant son fonctionnement, d'un composant à un autre comprenant des interconnexions externes formées d'une structure multicouche de couches conductrices et isolantes inséparables du corps semi-conducteur sur lequel elles ont été déposées avec des interconnexions modifiables
5.
SYSTEM AND METHOD FOR EFFICIENT DIRECTIONAL DISCOVERY OF COMMUNICATIONS TERMINALS VIA BEAM INTERLEAVING
A node of a multi-node network includes a communications interface incorporating one or more paired antenna elements wherein a transmitter (Tx) element and receiver (Rx) element are oriented in opposing directions. The node discovers and/or links to other nodes of the network by orienting each paired antenna element to transmit to other nodes in one direction and receive in the opposing direction (e.g., through a transmit and receive region, the transmit region opposite the receive region). At subsequent time intervals (e.g., alternating with the first time interval or set thereof), the Tx antenna elements transmit in directions through the initial receive region, each transmit direction interleaved between two prior receive directions, while the Rx antenna elements simultaneously attempt to receive in opposing directions through the initial transmit region, each receive direction interleaved between two prior transmit directions.
G01S 3/40 - Systèmes pour déterminer une direction ou une déviation par rapport à une direction prédéterminée utilisant le réglage d'une orientation réelle ou effective d'une caractéristique de directivité d'une antenne ou d'un système d'antenne afin d'obtenir une valeur désirée du signal venu de cette antenne ou système d'antenne, p.ex. donner un signal max réglant l'orientation d'une caractéristique de directivité unique afin de produire un signal maximal ou minimal, p.ex. cadre rotatif ou système goniométrique équivalent
G01S 3/04 - Radiogoniomètres pour déterminer la direction d'où proviennent des ondes infrasonores, sonores, ultrasonores ou électromagnétiques ou des émissions de particules sans caractéristiques de direction utilisant des ondes radio - Détails
The mixer-first topology of receivers do not include low-noise amplifiers (LNA) preceding the mixer. The Mixer-First topology of radio receivers utilizes a direct-conversion quadrature mixer to down convert an RF signal to baseband, where a Hilbert Transform filter is used for sideband selection. When a switching mixer is used, the mixer-first receiver is capable of extremely high dynamic range and linearity. The downfall of the mixer-first topology is poor out-of-band signal rejection. A mixer-first receiver is described which achieves third-harmonic rejection without bandpass filtering proceeding the mixer.
A system for providing maneuvering behaviors to a vehicle is disclosed. The system may include one or more controllers communicatively coupled to one or more vehicles. The one or more controllers may include one or more processors configured to execute one or more program instructions causing the one or more processors to: initiate one or more maneuver primitives in response to decision engine selection; receive a plurality of input parameters for the one or more maneuver primitives, the plurality of input parameters including one or more initialization definition input parameters, one or more goal definition input parameters, one or more navigation state input parameters, one or more design input parameters, and one or more vehicle performance envelope input parameters; and generate one or more control signals at one or more predetermined intervals of time to maneuver the one or more vehicles based on the decision engine selection.
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. pilote automatique
A pitot tube restraint system is disclosed herein. The pitot tube restrain system includes an outer shaft, a pitot tube coupled to a first end of the outer shaft and extending outward from the outer shaft, a torsion spring disposed around the outer shaft, a stop pad coupled to the first end of the outer shaft, a base disposed adjacent the second end of the outer shaft, an inner shaft having disposed through the outer shaft, a first end of the inner shaft rotationally coupled to the stop pad and a second end of the inner shaft rotationally coupled to the base, a pawl disposed around the inner shaft and adjacent the second end of the outer shaft, the pawl configured to engage the second end of the outer shaft to prevent the pitot tube from rotating in a first direction, and a pawl spring disposed around the inner shaft.
A communication system applies impedance matching to an antenna specific to individual samples of a transmit signal. The system samples a signal and identifies the peak frequency content of each sample. Based on the peak frequency content, the system identifies an impedance match for a given antenna that provides the greatest energy transmission. The sampled portion of the signal is delayed to accommodate processing time to determine the impedance match and control settings. Control settings may be applied via discrete digital circuitry or continuous analog circuitry.
H01Q 5/335 - Dispositions permettant un fonctionnement sur différentes gammes d’ondes Éléments rayonnants individuels ou couplés, chaque élément étant alimenté d’une façon non précisée utilisant des circuits ou des composants dont la réponse dépend de la fréquence, p.ex. des circuits bouchon ou des condensateurs au point d’alimentation, p.ex. aux fins d’adaptation d’impédance
Disclosed are embodiments of antenna assemblies for integration with aircraft lighting systems. The antenna assemblies in some embodiments include a ground plane, a patch antenna positioned on the ground plane, and a radome covering the patch antenna. The patch antenna and radome are configured as an annular ring for positioning around a light fixture received through a center opening through each of the ground plane, patch antenna, and radome such that the antenna assembly can mount and connect to the aircraft utilizing the light fixture aperture without the need for a separate antenna aperture.
An integrated circuit may include two processing cores. Each processing core may include: a core controller operable to execute instructions to perform processing tasks; a memory resource connected to the core controller; and a hardware accelerator module connected to the core controller. The integrated circuit may further include: a shared bus connected to the respective hardware accelerator modules of the two processing cores; and a shared memory resource connected to the shared bus; where the only communication path between the two processing cores is via the hardware accelerator modules and the shared bus.
A method for managing software application tasks being performed in a multi-core processing system, the system comprising: a management core configured to manage the allocation of processing tasks in the system; a plurality of processing cores configured to execute instructions for performing processing tasks; at least one shared resource, wherein the at least one shared resource is connected to each of the processing cores; a contention assessment module configured to monitor the amount of contention in the system; and a processing suspension module configured to cause the suspension of processing on at least one of the processing cores; wherein the method comprises: determining a criticality level of each task to be performed; allocating each task to a respective processing core of the plurality of processing cores based on the determined criticality level; assigning a contention threshold to at least one processing core of the plurality of processing cores; monitoring the amount of contention caused by the at least one processing core that has been assigned a contention threshold; and if the amount of contention caused by the at least one processing core that has been assigned a contention threshold reaches the assigned contention threshold, suspending processing on that processing core.
A system-on-chip comprises a first core having a first processor architecture and a second core having a different second processor architecture. A shared bus is communicatively coupled to the cores. A shared memory is communicatively coupled to the shared bus, for storing shared data accessible by cores. A hardware comparison module is configured to compare first data, determined by one or more operations of the first core, and second data, determined by one or more operations of the second core, to detect an inconsistency between the first data and the second data, and to signal when an inconsistency is detected. A first comparison-data bus is communicatively coupled to the first core and to the comparison module, and arranged to provide the first data to the hardware comparison module. A second comparison-data bus is communicatively coupled to the second core and to the comparison module, and arranged to provide the second data to the comparison module. The first and second comparison-data buses are isolated from each other and from the shared bus.
A direct dry film (DDF) lamination method includes providing a chamber including a bladder, positioning a frame in the chamber, positioning a compound curve substrate in an interior space within the frame, and suspending, by the frame, an optically clear adhesive (OCA) sheet over the compound curve substrate. In embodiments, a top liner of the OCA sheet is scored or cut to introduce weakness imparting flexibility in the sheet corresponding to the curvature of the compound curve substrate. The method continues with evacuating the chamber, deploying the bladder, retracting the bladder, and venting the chamber. Additional steps prepare the product for further boding with a flexible film or rigid part having a matched curvature profile.
B32B 37/12 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par l'usage d'adhésifs
B32B 1/00 - Produits stratifiés ayant essentiellement une forme générale autre que plane
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 37/10 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par la technique de pressage, p.ex. faisant usage de l'action directe du vide ou d'un fluide sous pression
B32B 38/00 - Opérations auxiliaires liées aux procédés de stratification
15.
AESA-BASED SYNTHETIC NULLING FOR ENHANCED RADAR GROUND CLUTTER SUPPRESSION
A radar system uses multiple nulls to improve detection capabilities. Multiple radar pulses are transmitted and or received, each with a different null pattern. The returns from each pulse are averaged together to form a null window that is less noisy and potentially wider than a single null pattern. This approach can improve the signal-to-noise ratio and make it easier to detect objects of interest. The system may generate individual pulses from an AESA divided into several subarrays. Each subarray produces a pulse with a null in a different location in the radiation pattern centered about a location of interest. The contemporaneous return signals are averaged together.
G01S 7/28 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe - Détails des systèmes à impulsions
G01S 7/02 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe
G01S 7/292 - Récepteurs avec extraction de signaux d'échos recherchés
16.
MICRO-SMALL FORM FACTOR (USFF) STARING RECEIVER AS A PASSIVE SENSOR
A small-scale receiver design architecture is disclosed. The receiver architecture may include an amplifier, reconfigurable filters, a downconverter assembly, a processor, and one or more risers. The one or more risers may include ball grid array (BGA) interconnects configured for electrical coupling between the front-end assembly, the downconverter assembly, and the processor. The one or more risers may be configured to provide electromagnetically shielding to the front-end assembly, the downconverter assembly, and the processor. The one or more risers may be configured to thermally couple to the front-end assembly, the downconverter assembly, and the processor. The receiver architecture may include a sequential stacking of the one or more risers, the front-end assembly, the downconverter assembly, and the processor.
A combiner includes an active breakaway mechanism. The breakaway mechanism includes a biasing element to positively direct the breakaway mechanism to a safe state, and a release element. In the event of a crash, the release element disengages, and the biasing element pushes the combiner into a safe orientation. A processor and detection element may detect a crash event and actuate the release element. The biasing element may be hydraulic, a spring, a linear actuator, or the like. The release element may include a solenoid, electromagnet, spring, compressed gas, expanding gas, or the like.
A method of determining a set of landing sites for an aircraft includes retrieving a first map of the reachable area (300) surrounding the aircraft, converting data relating to a plurality of no-go zones into a second map (302), filtering the plurality of no-go zones from the first map using the second map to create a third map of potential landing sites (310), and identifying one or more feasible landing sites (312) from the third map based on one or more landing requirements of the aircraft.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
An in-flight entertainment (IFE) system may include a structural panel supporting one or more aircraft seat components. The one or more aircraft seat components may include a primary IFE display and a secondary IFE display. Both the primary IFE display and the secondary IFE display may be coupled to a portion of the structural panel facing the passenger. The primary display may receive and display a plurality of in-flight related content from at least one IFE source, while the secondary display may receive and display a plurality of media content associated with a personal electronic device (PED) of the passenger. The IFE system may also include at least one controller which is in communication with at least one of the primary IFE display, the secondary IFE display, and the PED. The controller may selectively display content received from at least one of the IFE source or the PED.
A method approximates outlines of weather cells within the weather radar data using geometric shapes. The weather cells are filtered and clustered into clusters. The edges of the clusters are detected through an edge detection algorithm. Geometric shapes are fit to the edges of the clusters. The geometric shapes require significantly less bandwidth when transmitting over a communication channel, as compared to the weather radar data. The method saves the radar data with very few parameters and thus reduces the required memory for storage and required throughput for exchange.
G01S 13/95 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour la météorologie
G01S 7/00 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , ,
21.
AEROSPACE ANTENNA AND NETWORK SYSTEM FOR SIMULTANEOUSLY DELIVERING INTERNET TO AIRCRAFT AND REPORTING AIR QUALITY INDEX PARAMETERS
A system collects air samples at altitude and shares data among aircraft in a network. The system includes an antenna with an antenna housing; the housing defines air inlets and outlets. While in flight, air samples are collected through the inlets, processed via sensors, and allowed to flow through to the outlet. Air quality data, including, but not limited to, contrail humidity, gas content, and particle density and size, may be transmitted to other aircraft in a network via the antenna. Air quality measurements are geolocated and correlated from different platforms at different altitudes. A data model or machine learning artificial intelligence may utilize the geolocated air quality data to make certain predictions.
A fuel quantity indicator system (FQIS) for an aircraft or other vehicle includes memory/data storage and a fuel quantity processing unit (FQPU). A neural network trained via machine learning and running on the FQPU receives fuel quantity (FQ) inputs from fuel tank sensors, e.g., tank density, fuel volume, water presence within the tank, at or near a given measurement time. The neural network additionally receives fuel flow (FF) inputs from flow sensors at the measurement time, indicating fuel flow to engines and auxiliary power units (APU) of the vehicle. Based on the FQ inputs and the FF inputs, the neural network calculates an estimated fuel quantity (EFQ) remaining, e.g., across all fuel tanks at or near a particular measurement time.
A system and method for monitoring and verification of digital gyroscopic sensors determines a primary angular velocity vector via a primary digital gyroscopic sensor triad and two or more backup angular velocity vectors via backup analog gyroscopic sensor triads. Based on additional aiding parameters, the aircraft attitude and heading reference system (AHRS) determines a primary attitude solution based on the primary angular velocity vector and one or more backup attitude solutions based on the backup angular velocity vectors. If no other faults are present with respect to the primary and backup gyroscopic sensor triads (e.g., the primary and backup triads are otherwise consistent in their measurements), and the primary attitude solution sufficiently deviates from the backup attitude solutions, the AHRS detects a solution fault in the primary gyroscopic sensor triad.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01C 19/00 - Gyroscopes; Dispositifs sensibles à la rotation utilisant des masses vibrantes; Dispositifs sensibles à la rotation sans masse en mouvement; Mesure de la vitesse angulaire en utilisant les effets gyroscopiques
24.
ADAPTIVE SCHEDULER FOR LOAD BALANCING OF UNPREDICTABLE, TIME-SENSITIVE REQUESTS FOR A SHARED RESOURCE
A resource allocation system receives user requests for system resources over time. The system records factors such as number of resource requests, total usage time, etc., and preempts earlier requests in favor of later requests based on those factors. The resource allocation system tracks metrics in real-time and establishes dynamic preemption thresholds based on usage over time. Preemption thresholds may be specific to individual users.
A system and method for removing modulated interference (e.g., FSK, MSK, CW) from an input signal demodulates the input signal into a tracking bitstream via a set of phase locked loop (PLL) filters, one PLL filter for each modulated interference component (e.g., signal) known or suspected to be interfering with the input signal. Each PLL filter estimates, based on an estimated modulation frequency and center frequency associated with its target modulated interference component, a peak magnitude, phase, and updated center frequency and, based on these parameters, approximates the target interference component. Each re-created modulated interference component is subtracted from the original input signal to produce an output signal from which the known or suspected modulated interference components have been substantially removed.
A wearable device includes neuromorphic event cameras. A processor receives data streams from the event cameras and makes application specific predictions/determinations. The event cameras may be outward facing to make determinations about the environment or a specific task, inward facing to monitor the state of the user, or both. The processor may be configured as a trained neural network to receive the data streams and produce output based on predefined sets of training data. Sensors other than event cameras may supply data to the processor and neural network, including other cameras via a feature recognition process.
A cabin management system is described. The cabin management system includes a housing. The housing is configured to receive one or more modules. The modules may be detached and reattached to the housing. The modules may be rearranged to achieve a desired layout of touchscreens, audio converter, and input/output ports. The modules may include a geometry which provides a flush-mounting between the housing and the modules. The flush-mounting may prevent a passenger from accessing the cavity defined by the housing. The audio converter includes a digital-to-analog converter and an audio jack. The digital-to-analog converter converts an uncompressed digital audio signal to an analog audio signal. The audio jack receives a stereo analog signal and outputs the stereo analog signal to an audio plug.
A computer system records eye tracking data and identifies movements in the eye tracking data to determine gaze and pupil dynamics. Eye tracking data is correlated with a current task and predetermined vigilance requirements. The system determines if the user is exhibiting an appropriate level of vigilance based on the task or is becoming fixated. When fixation is detected, the system may engage in remedial action. A task flow diagram represents the operator tasks. Interactions between the user and the instrumentation are used to estimate the probability distribution of the task the user is currently conducting. The system correlates eye tracking data and physiological data such as electroencephalogram (EEG) and functional near-infrared spectroscopy (fNIRs) to determine neuroactivity. Monitoring neuroactivity reduces the probability of a false positive for fixation.
A profile for a tool implementing a unified modeling language (UML) is described. The profile extends the UML to include decision management functionality. The profile includes stereotypes and customizations which generate question elements, decision elements, alternative elements, and the like. The association between the elements permits a design engineer to review previous decisions and the rationale behind the decisions. In particular, the one of alternative elements is associated with decision element by selected alternative relationship.
A runway overrun awareness and alerting system determines a breaking distance based on aircraft capabilities, and renders a graphical depiction of that breaking distance. The graphical depiction may be separately rendered on a head-up display and a primary flight display. The system may determine both a maximum deceleration breaking distance and a nominal deceleration breaking distance. The maximum deceleration breaking distance and nominal deceleration breaking distance may be separately rendered, and may be rendered to include a visual indicator if they exceed some safety threshold.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
B64D 43/00 - Aménagements ou adaptations des instruments
The system may include at least one a light emitter configured to emit light over a range of wavelengths onto an environment and at least one sensor assembly. The range of wavelengths emitted by the light emitter may be of wavelengths that are above or below wavelengths used by a night vision imaging system. The sensor assembly may include an image sensor and conversion layer. The image sensor may capture images of the environment illuminated by the light emitters and sense light in a given range of wavelengths. The conversion layer may receive the emitted light and convert the emitted light to converted light with a wavelength within the given range of wavelengths associated with the image sensor. The image sensor may be further configured to receive the converted light from the conversion layer, capture an image of the light emitter and output image data associated with the captured image.
G09G 5/00 - Dispositions ou circuits de commande de l'affichage communs à l'affichage utilisant des tubes à rayons cathodiques et à l'affichage utilisant d'autres moyens de visualisation
G02B 27/00 - Systèmes ou appareils optiques non prévus dans aucun des groupes ,
H04N 23/11 - Caméras ou modules de caméras comprenant des capteurs d'images électroniques; Leur commande pour générer des signaux d'image à partir de différentes longueurs d'onde pour générer des signaux d'image à partir de longueurs d'onde de lumière visible et infrarouge
H04N 23/55 - Pièces optiques spécialement adaptées aux capteurs d'images électroniques; Leur montage
32.
FREQUENCY SELECTION ALGORITHM FOR RESILIENT HF COMMUNICATION
Techniques for selecting frequencies of operation are described. HF signals may land at the receiver node with power levels dependent upon the transmit frequency. The frequency with the highest power level at the receiver node may be selected when the receiver node is not subject to interfering. The receiver node may be unable to receive a desired signal if an interfering signal has a signal level which is higher than the desired signal. The transmitter node may select a frequency which has a receiver signal level which is higher than the interfering signal for the selected frequency. The receiver node may then receive the transmit signal at the selected frequency even when subject to interfering from the interferer node.
A stack is described. The stack includes a rule engine. The rule engine is accessed via application programming interface (API) from any plug-in mission service. The rule engine includes rules and facts. The rules and facts are loaded separately from the API and from a cloudlet monitor. The rules and facts do not require source code updates to change. The stack is executable on processors of a node within a cloudlet. The cloudlet includes multiple of the nodes. The stack divides high-level tasks into low-level tasks which are individually executable by the nodes in the cloudlet.
Techniques for selecting frequencies of operation are described. HF signals may land at the receiver node with power levels dependent upon the transmit frequency. The frequency with the highest power level at the receiver node may be selected when the receiver node is not subject to interference. The receiver node may be unable to receive a desired signal if an interfering signal has a signal level which is higher than the desired signal. The interfering signals may have a signal level which is higher across all available frequencies. The transmitter node may determine a potential relay table with a communication link between the transmitter node and a relay node and a communication link between the relay node and the receiver node. The communication link may include link margins above the interfering signal, ensuring the links may be established. The nodes may then communicate even when subject to interference.
H04W 40/02 - Sélection d'itinéraire ou de voie de communication, p.ex. routage basé sur l'énergie disponible ou le chemin le plus court
H04W 72/0453 - Ressources du domaine fréquentiel, p.ex. porteuses dans des AMDF [FDMA]
H04W 72/541 - Critères d’affectation ou de planification des ressources sans fil sur la base de critères de qualité en utilisant le niveau d’interférence
35.
INTEGRATING INPUT AND OUTPUT CAPACITANCE WITH HIGH FREQUENCY SHUNT CAPACITANCE ON A SINGLE ADDITIVELY MANUFACTURED SUBSTRATE
A package is described. The package includes a die covered by a lid. The lid maintains a hermetic seal for the die. The package includes high frequency shunt capacitance in parallel with surface-mount capacitors. The high frequency shunt capacitance is formed by interdigital capacitors below the surface-mount capacitors. The interdigital capacitors, the surface-mount capacitors, and the die form a circuit which produces a stable output voltage. The output voltage may remain stable even when subject to noise due to energized particles in space. The package includes solder resist with openings for attaching the surface-mount capacitors to the interdigital capacitors. Advantageously, the interdigital capacitors may achieve high frequency shunt capacitance on the order of nano-farads as part of the frame geometry with minimal increase in package height.
H01L 25/16 - Ensembles consistant en une pluralité de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide les dispositifs étant de types couverts par plusieurs des groupes principaux , ou dans une seule sous-classe de , , p.ex. circuit hybrides
H01L 23/498 - Connexions électriques sur des substrats isolants
H01L 23/552 - Protection contre les radiations, p.ex. la lumière
A system, comprising: one or more imaging devices (202) configured to collect image data of a cockpit area of an aircraft; a pilot detection module (212) configured to determine a presence of one or more pilots in the cockpit area based on the image data; and a pilot posture module (214) configured to determine three-dimensional posture of the one or more pilots based on the image data.
G06V 20/52 - Activités de surveillance ou de suivi, p.ex. pour la reconnaissance d’objets suspects
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G06T 7/50 - Récupération de la profondeur ou de la forme
G06T 7/73 - Détermination de la position ou de l'orientation des objets ou des caméras utilisant des procédés basés sur les caractéristiques
G06V 10/82 - 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
G06V 40/10 - Corps d’êtres humains ou d’animaux, p.ex. occupants de véhicules automobiles ou piétons; Parties du corps, p.ex. mains
G06V 40/20 - Mouvements ou comportement, p.ex. reconnaissance des gestes
G08B 21/04 - Alarmes pour assurer la sécurité des personnes réagissant à la non-activité, p.ex. de personnes âgées
37.
LANGUAGE MODELS FOR AUTOMATIC MICROBENCHMARK GENERATION
Disclosed is a method of training a language model to generate “microbenchmarks” in which the training data is specifically associated with certain microarchitecture characteristics that the “microbenchmarks” are designed for testing. Also disclosed are language models that have been trained in this manner, and the corresponding use thereof to generate “microbenchmarks”.
An autonomous agent of a team of autonomous agents (e.g., semi- or fully autonomous vehicles) includes a self-simulator incorporating a faster than real time (FTRT) processing environment for online simulation of each agent of the team. Based on the current mission status and one or more action sets determining the behaviors of the autonomous agents, the behaviors of each agent of the team are projected forward within the FTRT environment to determine mission status metrics relevant to the effectiveness of a particular action set towards optimal completion of mission objectives currently assigned to the team. Based on the mission status metrics, the self-simulator can select and provide an action set for optimized completion of mission objectives. For example, the self-simulator can recommend switching to a different preloaded action set or, in some cases, construct an optimized action set selected from multiple preloaded action sets tested in the FTRT environment.
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. pilote automatique
A preselect value is sent to a primary flight display for confirmation from both pilots (i.e., from the captain and the first officer). The preselect value removes single point failure when updating the barometric altimeter pressure setting in the barometric altimeter from an uplink message from air traffic control. The preselect value is loaded with the barometric altimeter pressure setting from the uplink message. The pilots each swap the preselect value with the active barometric altimeter pressure setting on the primary flight displays. The new active barometric altimeter pressure setting is then pushed to the barometric altimeters both active barometric altimeter pressure settings match.
B64D 43/00 - Aménagements ou adaptations des instruments
G01C 5/00 - Mesure des hauteurs; Mesure des distances transversales par rapport à la ligne de visée; Nivellement entre des points séparés; Niveaux à lunette
A system for detecting threats at an area is disclosed. The system may include a controller including one or more processors configured to execute a set of program instructions stored in a memory. The set of program instructions may be configured to cause the one or more processors to receive safe historical data of an area configured to be representative of a lack of threats, receive new data of the area from one or more nodes, compare the new data and the safe historical data to identify a difference between the new data and the safe historical data, and update a database based on the difference.
A system and method for transporting passengers via uncrewed aircraft systems (UAS) receives passenger requests for transport between origin and destination points. Based on the request a transport plan is generated for each passenger, identifying the passenger, assigning a UAS and including a flight plan (which includes flight instructions and a communications plan for the UAS control system). Based on the transport plan one or more encoded flight plan datasets are generated. Each encoded dataset is downloadable to and displayable by the passenger's portable computing device, and scannable and decodable by reader devices at the origin and destination ports and aboard the UAS. Scanning an encoded dataset both grants the passenger access to the origin port and UAS and confirms the passenger's presence. Further, each assigned UAS downloads from the decoded flight plan data the necessary configuration data to fulfill its portion/s of the flight plan.
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. pilote automatique
42.
GROUND AIR TRAFFIC MONITORING UNDER LOW VISIBILITY CONDITIONS USING AUGMENTED REALITY (USING HEAD-MOUNTED DISPLAY)
An augmented reality system in an air traffic control tower receives data from multiple airfield sensors and from local aircraft and correlates the data in space and time. Features of the airfield are rendered visually in an augmented reality headset during low visibility conditions. The augmented reality system renders visualizations of aircraft and may render data from the aircraft to coincide with the visualizations. The augmented reality system may receive data from systems within the air traffic control tower, commonly rendered on displays in the air traffic control tower and rendered such data within the augmented reality display.
An on aircraft computer system records and analyzes biometric data to identify indicia of impaired performance, such as pilot fatigue, attention tunneling, or cognitive overload. Such impairment is identified by alterations in pilot gaze or eye movement, head movement, facial parameters, eye lid position, heart rate, breathing, or brain wave patterns. Appropriate corrective action is applied based on the type of impaired performance identified, including altering a level of automation, contacting a ground dispatcher or ground pilot, or contacting a co-pilot or other crew member. Biometric data is continuously logged and correlated with data from other avionics systems to refine formulas relating biometric data to states of alertness and crew rest procedures.
An aircraft-based system and method for automated reporting and logging of aircraft maintenance events receives flight deck effects (FDEs) with correlated maintenance messages indicating maintenance statuses (e.g., faults and/or failures) and/or Air Transport Association (ATA) classifications for each reporting aircraft system, subsystem or component. The logging system generates event messages based on each received FDE, predicting additional information based on the correlated maintenance message such as recommended maintenance actions, replacement parts or components, and/or Minimum Equipment List (MEL) actions associated with a component fault or failure. Event messages are automatically transmitted via datalink to ground-based maintenance and dispatch. Further, event messages are automatically logged to an aircraft maintenance log.
A method is disclosed herein. The method includes determining, by a processor, a first time value in response to a switch being actuated a first time by a first striker, determining, by the processor, a second time value in response to the switch being actuated a second time by a second striker, the second striker disposed a first distance from the first striker and the second time value being after the first time value, calculating, by the processor, a change in time between the first time value and the second time value, and adjusting, by the processor, a timing sequence based on the change in time.
A radar system including an AESA illuminates a target with a first pulse for a desired beam pointing angle (azimuth and elevation). The AESA then illuminates the target with a second pulse for the desired pointing angle, the second pulse defining a radiation pattern with a main beam in phase with the first pulse, but side lobes that are out of phase. The radar system receives return signals and combines the return signals to null the side lobes by the principle of superposition. The radar processing unit is time synced such that the pulse-pair is interpreted as a single ultra-low level side lobe return radiation pattern.
G01S 7/28 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe - Détails des systèmes à impulsions
A system may include a processor configured to: (a) obtain parameters; (b) based on the parameters, update flight-state data associated with an aircraft; (c) obtain a trained machine learning (ML) model; (d) based at least on the updated flight-state data and the trained ML model, infer a direction from a current cell for a reroute; (e) based on the inferred direction and the updated flight-state data, set the current cell and identify neighboring cells; (f) calculate an optimal next cell by using a shortest path finding (SPF) algorithm to select the optimal next cell from the neighboring cells; (g) iteratively repeat steps (d) through (f) such that the current cell is set as the optimal next cell until a goal state is reached; (h) construct a re-route using optimal cells iteratively calculated in step (f); and (i) output the re-route.
A system may include an auto brake valve installed in an aircraft, an auto brake selector (ABS) switch communicatively coupled to the auto brake valve, and a runway overrun awareness and alerting system (ROAAS) communicatively coupled to the auto brake valve. The ABS switch may be configured to have a manual ABS switch setting to control the auto brake valve. The ROAAS may include at least one processor configured to: obtain ROAAS output data, the ROAAS output data including at least one of selected runway, runway distance remaining, runway stopping point, or runway condition; obtain a trained artificial intelligence (AI) and/or machine learning (ML) model; based at least on the ROAAS output data and the trained AI and/or ML model, infer an ABS brake setting; and set the auto brake valve in accordance with the ABS brake setting.
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/174 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage caractérisées par l'utilisation de logiques particulières de commande, p.ex. de la logique floue
B60T 8/32 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p.ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p.ex. accélération ou décélération
A method is disclosed herein. The method includes receiving, by a processor, a first acceleration data from an accelerometer, calculating, by the processor, a change in velocity based on the first acceleration data, the change in velocity being calculated over a first period of time, and adjusting, by the processor, a timing sequence based on the change in velocity.
G01P 15/16 - Mesure de l'accélération; Mesure de la décélération; Mesure des chocs, c. à d. d'une variation brusque de l'accélération en calculant la dérivée par rapport au temps d'un signal de vitesse mesuré
B64D 11/06 - Aménagements ou adaptations des sièges
A system and related method for multiple-sensitivity optical phase modulation splits an optical carrier generated by a photonic source into at least two copies and directs the copies (e.g., via optical circulators or polarization rotators) to an electro-optical (EO) phase modulator such that the phase modulator phase-modulates each optical copy according to a received radio frequency (RF) signal of interest based on characteristics distinct to each optical copy (e.g., optical path direction, signal polarization) that provide for phase modulation of each optical copy at a different sensitivity voltage. The variably modified optical copies are directed to a photonic processor for further signal processing in the optical domain.
A motion planning system and method receives requests for routing a set of dissimilar aircraft through a defined airspace. Each aircraft has a starting and destination position relative to the airspace. A start state is based on the earliest start, and a goal state on the destination. The system connects start and goal states via a sequence of next states by projecting each state incrementally forward in time. Candidate next states include all possible next paths to a next position of each aircraft combined with next paths and positions of its neighbors, with unsafe next states culled from the set. Remaining next states are prioritized on the basis of aggregate system cost for all next paths and an estimated system cost to achieve the goal state, and an optimal next state is added to the sequence. When the goal state is achieved, optimal flight plans are generated for each aircraft.
A system and method for monitoring blood oxygen levels via an eye tracking camera includes a computer system with a processor configured to identify capillaries in the image stream of a pilot's eye. Changes in capillary size over time is directly correlated to blood flow levels. The processor may monitor capillary color. Changes in capillary color is directly correlated to blood oxygen levels. The processor may take remedial action when the pilot's blood oxygen level drops below a threshold. Such remedial action may include alerting the pilot, automatically alerting ground control crew, applying increasing levels of flight automation, etc.
A61B 5/1455 - Mesure des caractéristiques du sang in vivo, p.ex. de la concentration des gaz dans le sang, de la valeur du pH du sang en utilisant des capteurs optiques, p.ex. des oxymètres à photométrie spectrale
A61B 3/113 - Appareils pour l'examen optique des yeux; Appareils pour l'examen clinique des yeux du type à mesure objective, c. à d. instruments pour l'examen des yeux indépendamment des perceptions ou des réactions du patient pour déterminer ou enregistrer le mouvement de l'œil
A61B 3/14 - Dispositions spécialement adaptées à la photographie de l'œil
A61B 5/00 - Mesure servant à établir un diagnostic ; Identification des individus
A shock load attenuation device is provided. The shock load attenuation device includes a crushable material; a first compartment in the crushable material surrounding a first line; and a second compartment in the crushable material surrounding a second line. In response to the first line being acted upon by a first force and the second line being acted upon by a second force, a first loop in the first line is configured to slide along the second line and a first loop in the second line is configured to slide along the first line, crushing the crushable material.
B64D 17/36 - Suspension de la charge incorporant des dispositifs de frottement ou de raccordement frangibles pour réduire le choc à l'ouverture de la coupole
F16F 7/12 - Amortisseurs de vibrations; Amortisseurs de chocs utilisant une déformation plastique de ses organes
F16F 7/14 - Amortisseurs de vibrations; Amortisseurs de chocs du type support de câble, c. à d. des câbles formant des boucles en prise par friction
A microprocessor is described. The microprocessor includes a software-based monitor for detecting TLB corruptions. The TLB corruptions contribute to undetected erroneous upset rate of the microprocessor. The software monitor detects errors in the TLB. The software-based monitor detects TLB corruptions in microprocessors where hardware protection mechanisms are not available. The software monitor mitigates single event effects due to atmospheric particles and improves the safety of high integrity computing products.
G06F 12/1027 - Traduction d'adresses utilisant des moyens de traduction d’adresse associatifs ou pseudo-associatifs, p.ex. un répertoire de pages actives [TLB]
G06F 12/1009 - Traduction d'adresses avec tables de pages, p.ex. structures de table de page
55.
AUDIO-VISUAL PILOT ACTIVITY RECOGNITION SYSTEM AND METHOD
An audio-visual pilot activity recognition system including one or more image collectors, one or more audio collectors, and a processor configured to collect at least one image signal from the one or more image collectors, collect at least one audio signal from the one of more audio collectors, and determine a pilot activity based on the collected at least one image signal and the collected at least one audio signal.
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
G06T 7/50 - Récupération de la profondeur ou de la forme
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
G06T 17/00 - Modélisation tridimensionnelle [3D] pour infographie
A system may include a radio and a processor. The processor may be configured to: obtain information of a flight plan; obtain a command and control (C2) communication plan; and output instructions to operate the radio to connect with at least one given antenna of at least one given radio tower at a given time according to the C2 communication plan. The radio may be configured to connect with the at least one given antenna of the at least one given radio tower at the given time according to the C2 communication plan.
A system and method for controlling nationally protected data flows (e.g., wargame data, training data) through a shared network locally encrypts a protected portion of shared data (e.g., ACMI/weapons flyout data) flowing through a shared network infrastructure. The protected portion is pre-encrypted according to local encryption keys controlled by a local entity (e.g., a nation or multi-national coalition partners) but not shared with other infrastructure partners or participants. The partially encrypted dataset is then fully encrypted (according to host/infrastructure encryption keys accessible to all infrastructure participants) for travel through the security infrastructure via secure datalink. All network destinations having access to the infrastructure keys can decrypt and access the nonprotected portion, but only those network destinations (e.g., other aircraft or vehicles) affiliated with the local entity and/or having access to the local encryption keys may decrypt and access the protected data portion.
A system is described. The system connects an aircraft weather radar to a ground station. The ground station may include improved situational awareness regarding weather cells due to the connection to the aircraft weather radar. In particular, the situational awareness may be improved in areas not covered by ground weather radars. For example, the ground station may provide earlier rerouting to the aircraft around the weather cells. The aircraft may transmit data regarding the weather cells at an interval. The interval may be dynamically adjusted based on a number of factors to ensure adequate situational awareness while optimizing the resources of an air-to-ground communication link.
A system for graphical indication of a corridor is disclosed. The system may include a display and a processor. The processor may be configured to receive corridor position data of a corridor and aircraft position data indicative of a position of an aircraft. The processor may also be configured to determine a relative distance of the aircraft in relation to the corridor based on the corridor position data and the aircraft position data. The processor may further be configured to display a corridor graphic associated with the corridor based on the relative distance.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
60.
Wavelength division multiplexing (WDM) approach to phase lock distributed digital and RF electronics over fiber
A system and method for transmission and receipt of signals within a distributed system are disclosed. In the distributed system there may be a plurality of digital and radio frequency (RF) electronics. The plurality of digital electronics may be coupled to the plurality of radio frequency electronics with at least one fiber optic cable. The at least one fiber optic cable may support wavelength division multiplexing (WDM). Further, the digital electronics may combine a time-at-the-tone signal, a pulse per second signal, and a standard frequency reference signal via amplitude modulation to produce a single complex wave. The single complex wave and other signals may be simultaneously transmitted along the at least one fiber optic cable to the plurality of RF electronics via WDM.
A hierarchical modular arbitration architecture for a mobile platform guidance system is disclosed. In embodiments, the architecture comprises a hierarchy of arbitration layers, each arbitration layer narrower in scope than the layer above (e.g., mission objective arbitrators, route arbitrators, path arbitrators). Each arbitration layer includes one or more objective-based arbitrators in communication with one or more applications or modes. Each arbitrator receives control input (e.g., from the pilot, from aircraft sensors) and control signals from the level above, selecting a mode to make active based on decision agents within the arbitrator layer which control mode priorities and sequencing (e.g., some flight objectives may involve multiple arbitrators and their subject applications coordinating in sequence). Each arbitrator passes control signals associated with fulfilling the commands of the active mode to the level below and reports application and error information to the arbitrator level above and/or human/artificial pilot machine interfaces.
A system and method for detection of GNSS signal spoofing with high integrity error bounding determines a parity space formulation for coordinates of a GNSS-driven master position solution (e.g., fully absolute/GNSS or blended GNSS/IRS solution) and a corresponding coasted position solution (e.g., less frequently GNSS-updated), wherein a parity vector expresses consistency of the master coordinate with the coasted coordinate. Based on a desired level of missed detection, protection levels are determined for the parity space formulation, and integrity bounds on the master and coasted solutions calculated. The parity vector is compared with a detection threshold. If, for any solution component (e.g., direction, axis) of the master solution, the parity vector meets or exceeds the threshold, a spoofer is detected and a coasted solution is propagated with its coasted integrity bound. If no spoofer is detected, the master solution and its master integrity bound are propagated as output.
G01S 19/39 - Détermination d'une solution de navigation au moyen des signaux émis par un système de positionnement satellitaire à radiophares le système de positionnement satellitaire à radiophares transmettant des messages horodatés, p.ex. GPS [Système de positionnement global], GLONASS [Système mondial de satellites de navigation] ou GALILEO
G01S 19/49 - Détermination de position en combinant ou en commutant entre les solutions de position dérivées du système de positionnement par satellite à radiophares et les solutions de position dérivées d'un autre système l'autre système étant un système de position inertielle, p.ex. en hybridation lâche
63.
METHOD FOR USING STATELESS SOFTWARE DATABASE DATA TO PERFORM DATA AND CONTROL COUPLING
A system for evaluating stateless software using read and write operations to storage is disclosed. The system may include a controller, which may include one or more processors configured to execute program instructions stored on a memory. The one or more processors may be configured to evaluate the stateless software, including modules of the stateless software. The stateless software may be configured to store data on a storage such that each request to the stateless software does not rely on a state of the stateless software from a previous request. The evaluating of the stateless software may include executing the stateless software based on a set of requests, recording a log of read operations and write operations to the storage during the executing of the stateless software, and determining a performance of the stateless software based on a parsing and evaluation of the read and write operations.
A synthesized non-Foster time-variant filter is disclosed for matching impedance. The synthesized non-Foster time-variant filter may include a negative-inductor circuit and a negative-capacitor circuit. The negative-inductor circuit and the negative-capacitor circuit may be configured to be dynamically controlled based on a known transmit signal. The negative-inductor circuit may be configured to synthesize a negative inductance of a range of inductances. The negative-capacitor circuit may include a plurality of capacitors coupled together in parallel. Each capacitor may include a first capacitor end and a second capacitor end. The negative-capacitor circuit may be configured to synthesize a negative capacitance of a range of capacitances. The negative-capacitor circuit may include a plurality of inductors coupled together in series. Each inductor may include a first inductor end and a second inductor end.
A method for e-AC flight dispatch is disclosed, in accordance with one or more embodiments of the present disclosure. The method may include receiving a set of training data. The method may include training a machine learning algorithm of an electric flight dispatch module based on the received set of training data. The method may include receiving one or more sets of real-time data, the one or more sets of real-time data including at least one of airport infrastructure data, airline information data, or battery management data. The method may include generating a set of output data for dispatching an electric aircraft using the trained machine learning algorithm of the electric flight dispatch module.
A system for displaying an indication of aerodynamically unstable proximate UAM traffic is disclosed. The system includes at least one display and at least one processor communicatively coupled to the at least one display. The at least one processor may be configured to receive air traffic data associated with at least one proximate aircraft. The air traffic data may include a proximate aircraft's rate of descent, rate of turn, or lateral speed. The at least one processor may be configured to determine that the proximate aircraft is aerodynamically unstable if the proximate aircraft's rate of descent, rate of turn, or lateral speed exceeds a maximum rate of descent, rate of turn, or lateral speed, respectively. The at least one processor may be further configured to generate and output a visual representation of aerodynamic instability to the at least one display.
A system utilizes two ground-based radios; each radio is equipped for two-way timing and ranging. An aerial vehicle receives radio signals from the two ground-based radios and triangulates its location with respect to those two ground-based radios. The aerial vehicle then executes a landing procedure at a landing site with respect to the triangulated location. The aerial vehicle includes a barometer, radar, or laser altimeter for vertical measurement. The aerial vehicle also includes an inertial measurement unit (IMU), air data system, and magnetometer. The ground-based radios may supply a ground level altitude measurement. The aerial vehicle may perform an acquisition orbit for improved accuracy. The acquisition orbit provides an expanded range of geometries with respect to the two ground-based radios.
A system for assessing safe fulfillment of a mission plan or flight plan by a pilot receives physiological pilot monitoring data sensed inflight while the pilot is executing a flight plan. The system correlates pilot monitoring data with specific flight operations performs a post-flight fatigue assessment of the pilot (e.g., a performance score with respect to the completed flight plan and/or an assessment of the current fatigue state of the pilot). The system adds the pilot's post-flight fatigue state assessment to an individualized pilot profile. On receiving a subsequent flight plan for fulfillment by the pilot, the system performs a pre-flight risk assessment based on all available information, e.g., a risk assessment with respect to the pilot's fulfillment of the flight plan as a whole and/or specific risk assessments corresponding to fulfillment of component flight operations of the flight plan.
An unmanned aerial vehicle (UAV) is described. The UAV includes functions such as geo-location-based approvals, targeted system updates and dynamic rule enforcements, authentical, internet protocol (IP) whitelisting, and application control. The functions are controlled from the firmware level. The functions may ensure a highly secure and controlled embedded system on the UAV in the event an application of the UAV is compromised by a third party. UEFI is used to provide a tamper proof way of enforcing permitted flights on authorized equipment.
G06F 9/44 - Dispositions pour exécuter des programmes spécifiques
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. pilote automatique
09 - Appareils et instruments scientifiques et électriques
Produits et services
Computer hardware, Computer hardware for displaying moving maps, Electronic display interface with recorded software for electronic video informational and entertainment display and generation units for the aviation industry, computer software recorded for displaying moving maps; Downloadable application for phone or tablet providing an interactive moving maps system
A system is described. The system predicts a landing runway for the aircraft. The landing runway is predicted using geometry and parameters which describe the position of the aircraft in space. The parameters include track alignment, vector alignment, vertical alignment, in-approach geometry, and in-flight plan. The parameters are combined to determine runway alignment scores for each runway. The runway alignment scores indicate how well the aircraft is aligned with the runways. The parameters are not equal in their contribution to the decision-making process and need to be weighted. The parameters are normalized, weighted, and summed to determine the runway alignment score.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
A receiver system is disclosed. The receiver system may include an omnidirectional receiver configured to receive an incoming signal, a directional receiver configured to receive the incoming signal, and an integrity controller. The integrity controller may be configured to determine an integrity of the incoming signal by synchronizing a clock of the omnidirectional receiver and a clock of the directional receiver, receiving an omnidirectional signal of the incoming signal, receiving a directional signal of the incoming signal, translating between a phase of the omnidirectional signal and a phase of the directional signal based on the synchronizing, ensuring a signal equivalency based on the translating, calculating an angle of arrival of the incoming signal based on carrier phase differences associated with the directional signal, and identifying the incoming signal as a trusted satellite signal based on a comparison of the angle of arrival with an expected angle of arrival.
A system for utilizing a boot prefetch module is disclosed, such as a hyperconverged system with centralized storage. The system may include a controller. The controller may include one or more processors configured to execute program instructions causing the one or more processors to perform a parallelized boot of a plurality of nodes. The performing of the parallelized boot may include retrieving node boot data associated with the respective node from centralized storage. The one or more boot prefetch modules may be configured to perform the retrieving of the node boot data prior to the respective node being booted. The one or more boot prefetch modules may be coordinated in retrieving the node boot data and be configured to perform decryption and/or signature verification.
G06F 21/57 - Certification ou préservation de plates-formes informatiques fiables, p.ex. démarrages ou arrêts sécurisés, suivis de version, contrôles de logiciel système, mises à jour sécurisées ou évaluation de vulnérabilité
H04L 9/32 - Dispositions pour les communications secrètes ou protégées; Protocoles réseaux de sécurité comprenant des moyens pour vérifier l'identité ou l'autorisation d'un utilisateur du système
74.
CONTROLLED RADIATION PATTERN ANTENNA FOR JAMMING/SPOOFING RESISTANT AIRBORNE GNSS SENSORS
A GNSS active antenna with improved performance in the presence of interfering signals is described. The GNSS active antenna meets the requirements of DO-301 for Airborne GNSS antennas when in normal operation. The GNSS active antenna also generates a low elevation null steered to any azimuth angle when in an environment with an interfering signal. The null has minimal performance impacts at higher elevation angles near zenith. The GNSS active antenna includes a right-hand circular polarized microstrip antenna with a concentric vertically polarized monopole antenna. The GNSS active antenna also meets the requirements of ARINC 743 antenna outline and mounting hole pattern.
A system and method for creating avionic databases is disclosed. The system may receive an avionic database of an area, surveyed coordinate points of the area, and new satellite imagery of the area. The system may georeference the new satellite imagery using the surveyed coordinate points as ground control points, generating georeferenced coordinate points of the new satellite imagery in different locations of the area. The system may create a second avionic database based on the georeferenced coordinate points.
A system and method are provided for selecting features from a digital chart, and entering corresponding flight plan amendments into a flight plan by direct transfer to an FMS. Based on the selection, the system may prompt the user for subsequent selections. Digital charts are generated in dynamically or in real-time according to a set of databases, including the databased used by the FMS. Elements within the databases are characterized so that the flight crew can select which elements are displayed. Features in the digital chart may be made selectable or unselectable based on a filtering process. The filtering process may be based on environmental variables, aircraft capabilities, safety tolerances, etc.
G06T 19/00 - Transformation de modèles ou d'images tridimensionnels [3D] pour infographie
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
77.
System including touchscreen display computing device having adjustable sensitivity and method therefor
A system includes a touchscreen display computing device including a touchscreen display and at least one processor. The touchscreen display may be communicatively coupled to the at least one processor. The touchscreen display computing device may be installed in a vehicle. The at least one processor may be configured to: receive vibration data from a vibration sensor installed onboard the vehicle; calculate, in real time, at least one slew setting associated with an adjustable sensitivity of the touchscreen display based at least on the vibration data; adjust, in real time, the adjustable sensitivity of the touchscreen display based at least on the at least one slew setting; receive, from a user in real time, a touch input from the touchscreen display using the adjusted adjustable sensitivity; and output an instruction based at least on the touch input.
G06F 3/041 - Numériseurs, p.ex. pour des écrans ou des pavés tactiles, caractérisés par les moyens de transduction
G01H 11/00 - Mesure des vibrations mécaniques ou des ondes ultrasonores, sonores ou infrasonores par détection des changements dans les propriétés électriques ou magnétiques
78.
METHOD AND MICROARCHITECTURE FOR ANOMALY DETECTION BASED ON HARDWARE PERFORMANCE MONITORS
A method for detecting anomalies in the nominal execution of tasks in a processor system includes executing a task on the processor system, monitoring, in real time via dedicated communication means, hardware performance monitors, HPMs, of at least one resource of the processor system resulting from the execution of the task on the processor system; classifying the task based on the monitored HPMs; comparing the classified task with an expected completion profile of the task; and if the classified task deviates from the expected completion profile, then identifying an anomaly in the nominal execution of the task.
A method for designing custom microarchitectures includes proposing an initial microarchitecture comprising at least two intellectual property, IP, components and at least one interference channel, ICh, based on final requirements of the microarchitecture. The method further includes prototyping the proposed microarchitecture; executing at least one μBenchmark on the prototyped microarchitecture; monitoring at least one Performance Monitoring Counter, PMC, resulting from the execution of the at least one μBenchmark to identify whether the prototyped microarchitecture satisfies timing and contention requirements of the microarchitecture. If all timing and contention requirements are met, the prototyped custom microarchitecture is accepted as the custom microarchitecture. If they are not met, a source of contention is identified by identifying bottlenecks in the at least one PMC during the execution of the at least one μBenchmark and the proposed microarchitecture is adapted to mitigate the contention scenario or modify a Hardware Performance Monitor unit.
G06F 30/331 - Vérification de la conception, p.ex. simulation fonctionnelle ou vérification du modèle par simulation avec accélération matérielle, p.ex. en utilisant les réseaux de portes programmables [FPGA] ou une émulation
80.
SYSTEM AND METHOD FOR PERFORMANCE PREDICTION OF ELECTRIC AIRCRAFT
A system and for performance prediction of an electric aircraft is disclosed. The system may include a controller including one or more processors configured to execute a set of program instructions stored in a memory. The set of program instructions may be configured to cause the one or more processors to receive aircraft data, route data, and environmental data. The aircraft data may include battery data of the battery of the electric aircraft. The system may also be configured to predict an available range based on the aircraft data and the environmental data.
B60L 58/16 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries en fonction du vieillissement de la batterie, p.ex. du nombre de cycles de charge ou de l'état de santé [SoH]
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G01R 31/374 - Dispositions pour le test, la mesure ou la surveillance de l’état électrique d’accumulateurs ou de batteries, p.ex. de la capacité ou de l’état de charge avec des moyens pour corriger la mesure en fonction de la température ou du vieillissement
G01R 31/3835 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p.ex. état de charge ne faisant intervenir que des mesures de tension
A system and method are provided for continuously monitoring manual flight inputs and updating a flight management system with those manual inputs. The flight management system recalculates and provides predictions based on the manual inputs. The flight management system may continuously monitor certain thresholds. The flight management system utilizes the crew entered speed schedule until a threshold is exceeded. When the flight management system is reengaged, it may utilize the manually entered speeds within the speed schedule for a current phase of the flight. The flight management system may analyze the manual input and corresponding predictions to determine if they are within or conform to certain predefined criteria before using them for automated flight.
A communications node for transmitting and receiving beyond line of sight (BLOS) communications through an evaporation duct (ED) environment proximate to a body of water (e.g., coastal, littoral) models environmental conditions (e.g., duct heights) based on current climate data for the ED environment. Based on the modelled ED conditions, the node generates signal propagation models for each of a set of possible transmitting frequencies (e.g., likely signal loss, transmission range). Based on the most current ED signal propagation model, the node selects the optimal transmission frequency for BLOS communications through the evaporation duct.
A system and method for tactical routing of directional communications identifies directional communications links from a transmitting (Tx) node to a receiving (Rx) node of a multi-node network. Within the network environment, the Tx node identifies deadzones, or areas wherein directional communications links between the Tx and Rx nodes may be constrained. The Tx node assigns each identified directional communications link a link cost; constrained links are assigned a higher cost than unconstrained links. Based on the assigned link costs (and other link cost information received from other network nodes), the Tx node constructs an optimal transmission route to the desired Rx node, the transmission route comprising a sequence one of more directional links selected to optimally fulfill mission objectives (e.g., minimal aggregate link cost).
A system and method for enhancing pilot situational awareness stores to an onboard navigational database hybrid approach procedure sets, e.g., approaches to a landing or other waypoint wherein a first portion of the approach is performed or executed according to a first approach procedure set (e.g., to a final approach fix (FAF) or other waypoint), and a second portion of the approach (e.g., once the FAF/waypoint is sequenced) is performed/executed according to a different approach procedure set, e.g., an RNP AR-to-LPV hybrid approach. Flight displays provide textual approach indicators, e.g., when the hybrid approach is loaded and arming of the first segment is upcoming, or when the first and second segments are respectively armed and activated (e.g., when the necessary conditions are satisfied). Hybrid approach indicators may alternatively or additionally be provided via flight mode annunciators (FMA) of the flight display.
A baggage handling system is described. The baggage handling system may include cameras. Video from the cameras may be automatically monitored. The video may be automatically monitored in real time across the entire journey of the baggage. The baggage handling system may provide an automated approach to identify theft of airport bags\luggage without manual effort required by humans. The bags may then be safely transported through an airport without theft or tampering. The automated surveillance and responding system may not depend on airport staff to monitor for baggage theft. The automated surveillance and responding system may detect multiple types of baggage theft/tampering.
G08B 13/196 - Déclenchement influencé par la chaleur, la lumière, ou les radiations de longueur d'onde plus courte; Déclenchement par introduction de sources de chaleur, de lumière, ou de radiations de longueur d'onde plus courte utilisant des systèmes détecteurs de radiations passifs utilisant des systèmes de balayage et de comparaison d'image utilisant des caméras de télévision
G06V 10/25 - Détermination d’une région d’intérêt [ROI] ou d’un volume d’intérêt [VOI]
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
G06V 20/40 - RECONNAISSANCE OU COMPRÉHENSION D’IMAGES OU DE VIDÉOS Éléments spécifiques à la scène dans le contenu vidéo
G06V 20/52 - Activités de surveillance ou de suivi, p.ex. pour la reconnaissance d’objets suspects
A cabin management control device is disclosed for automating cabin features (e.g., shades, lights) and/or a GUI based on flight data. The cabin management control device may include a computing device having a touchscreen. The computing device may be in communication with an aircraft network and cabin controller. The computing device may be configured to display a graphical user interface (GUI) configured to control cabin features. The computing device may be configured to: receive flight data; receive camera feed data; determine whether to display the camera feed data based on the flight data; and direct, based on the flight data, an automatic adjustment of the cabin features. The cabin features may include at least one of: a window level of one or more window shades; or a cabin lighting level of one or more lights.
A system and method for accessing data to meet disparate security, integrity, and latency requirements includes multiple databases instantiated in the system with different performance attributes. The system receives a data access request from a client application. The system determines one or more data access requirements associated with the data access request and identify a database or set of databases that conform to those requirements. The system then submits the data access request to the identified databases and returns the result to the client application. The system may determine a data integrity threshold for the data access request, and submit the data access request to two or more databases simultaneously.
An aircraft-based system for tracking and verifying control inputs from potentially incapacitated pilot stores to memory expected control input sets, e.g., control procedures for controlling an aircraft through segments of a flight plan. When pilot monitors indicate a state of potential incapacitation of a pilot (e.g., fatigue, unresponsiveness, hypoxia), the control input tracking system records any control inputs submitted via the flight deck controls by the incapacitated pilot, reviewing each recorded control input compared to expected control inputs (e.g., for the current flight segment). When a recorded control input sufficiently deviates from the corresponding expected control input (e.g., such that aircraft safety or mission criticality may be affected), the pilot and/or flight crew may receive feedback alerting to the deviant control input (e.g., which may be overridden or which may require confirmation prior to execution).
A system is disclosed for Doppler nulling configured for security. The system may include a receiver or transmitter node. The receiver or transmitter node may include a communications interface with an antenna element and a controller. The controller may include one or more processors and have information of own node velocity and own node orientation relative to a common reference frame. The receiver or transmitter node may be time synchronized to apply Doppler corrections to signals, the Doppler corrections associated with the receiver or transmitter node's own motions relative to the common reference frame, the Doppler corrections applied using Doppler null steering along Null directions based on a protocol. The protocol may include a protocol modulation, such as a modulation of the signals for security purposes.
G01S 5/00 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de position; Localisation par coordination de plusieurs déterminations de distance
G01S 13/58 - Systèmes de détermination de la vitesse ou de la trajectoire; Systèmes de détermination du sens d'un mouvement
A system and method for optimizing pre-departure sequencing instantiates independent agent processes for each aircraft. Each independent agent is trained via multi-agent reinforcement machine learning with an existing set of data to maximize that agent's individual reward within established bounds and while cooperating with each other agent. The interaction of the independent agents produces an optimized pre-departure sequence. The individual reward is defined with respect to a change between the current timestamp and the newly suggested timestamp. A lower delta results in a higher reward.
Whenever an avionics computer system receives a flight plan, the avionics computer system performs rules-based conformity checks with respect to a predefine set of rules/thresholds. The rules may be general aviation best practices (no rate of elevation change beyond some threshold, no single change in direction beyond some threshold, etc.) or specific to the aircraft (no violation of an operational ceiling, no violation of some defined fuel reserve, etc.). Violations of the rules and criteria are communicated to crew members via visual indicia of such violations, including the relative severity.
A computer-implemented method of training a software agent for protecting a computer system comprises receiving performance monitoring counter (PMC) data, comprising data from one or more hardware performance monitoring counters (PMCs) of the computer system, and receiving an output from an anomaly detector that is arranged to detect anomalies in the computer system. State data, comprising at least the PMC data, is provided to the software agent which selects a security policy from a set of security policies in dependence upon the state data, and applies the selected security policy to the computer system. A reward function is evaluated to determine a reward value which depends on at least the output of the anomaly detector. The reward value is used to train the software agent using reinforcement learning for selecting security policies from the set of security policies.
A system and method for controlling a scrolling function in a touchscreen display defines a touch sensitive region for the scrollbar. When the touch sensitive region receives a press-and-hold input, the system renders large directional inputs for the corresponding window/list selection window and enters a persistent state wherein the directional inputs supersede the scrolling function. The scrollbar input may be deactivated during the persistent state. The persistent state is exited when the user makes a selection outside the directional inputs. The system may define press-and-hold touch sensitive regions larger than the touch sensitive region for the scrollbar generally. The larger press-and-hold regions may be associated with, and extend beyond, a currently active window/dialog box.
G06F 3/04855 - Interaction avec des barres de défilement
G06F 3/0482 - Interaction avec des listes d’éléments sélectionnables, p.ex. des menus
G06F 3/0488 - Techniques d’interaction fondées sur les interfaces utilisateur graphiques [GUI] utilisant des caractéristiques spécifiques fournies par le périphérique d’entrée, p.ex. des fonctions commandées par la rotation d’une souris à deux capteurs, ou par la nature du périphérique d’entrée, p.ex. des gestes en fonction de la pression exer utilisant un écran tactile ou une tablette numérique, p.ex. entrée de commandes par des tracés gestuels
A system for detecting an alignment of a relay lens assembly and a combiner of a head-up display is disclosed. The system includes an illuminated reticle spatially coupled to the relay lens assembly, an optical sensor spatially coupled to the combiner, and a control module configured to receive an input from the optical sensor, determine a position of the combiner relative to the relay lens assembly based on the received input; and generate an output based on a determined position of the combiner relative to the relay lens assembly. In another system, the illuminated reticle is spatially coupled to the combiner, and the optical sensor is spatially coupled to the relay lens assembly. The system may also participate in a feedback loop with the head-up display to reduce jitter in the head-up display.
G01B 11/27 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour tester l'alignement des axes pour tester l'alignement des axes
G01B 11/14 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer la distance ou la marge entre des objets ou des ouvertures espacés
A method is disclosed herein. The method includes receiving, by a processor, an ejection command for ejecting an ejection seat from an aircraft; determining, by the processor, an equivalent airspeed and an equivalent altitude of the ejection seat; and, responsive to the airspeed and the altitude indicating a second mode of operation: sending, by the processor, a command to deploy a drogue parachute; determining, by the processor, a variable drogue severance delay; and responsive to the variable drogue severance delay expiring, sending, by the processor, a command to sever the drogue parachute and deploy a main parachute.
A ground station is used by an air traffic controller to provide support to an aircraft. In particular, the ground station may mirror or regenerate a weather radar overlay of a flight display of the aircraft. The air traffic controller and the flight crew may then both see the same real-time weather information with minimum delay and achieve a similar level of situation awareness. The weather radar overlay may be displayed on a display of the ground station. The ground station may receive weather data and ADS-B data or other forms of location data and intended flight path from the aircraft via an air-to-ground communication channel. The weather data may be used to regenerate the weather radar overlay. The ground station may also use the ADS-B data to generate a coverage map of the aircraft in a selected airspace.
G01S 7/00 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , ,
G01S 13/95 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour la météorologie
97.
Polarization maintaining parametric optical frequency comb generator
A system is described. The system includes HNLF for generating an optical frequency comb and a single mode fiber for reducing a pulse duration of comb. The system includes a FRM to reflect the light in back propagation through the HNLF and the single mode fiber. Perturbations in a state of polarization caused by the HNLF and the single mode fiber are cancelled between the forward propagation and the backward propagation. The optical frequency comb may then be polarization maintaining without an active component such as a polarization controller and a feedback circuit.
An apparatus for displaying an image, including: an input image node configured to provide at least a first and a second image modulated lights; and a holographic waveguide device configured to propagate the at least one of the first and second image modulated lights in at least a first direction. The holographic waveguide device includes: at least a first and second interspersed multiplicities of grating elements disposed in at least one layer, the first and second grating elements having respectively a first and a second prescriptions. The first and second multiplicity of grating elements are configured to deflect respectively the first and second image modulated lights out of the at least one layer into respectively a first and a second multiplicities of output rays forming respectively a first and second FOV tiles.
G02B 30/34 - Stéréoscopes fournissant une paire stéréoscopique d'images séparées correspondant à des vues déplacées parallèlement du même objet, p.ex. visionneuses de diapositives 3D
99.
SYSTEM AND METHOD FOR APPLICATION OF DOPPLER NULL SCANNING (DNS) TO POSITION NAVIGATION TIMING (PNT)
A system may include a receiver node. The receiver node may include a communications interface and a controller. The receiver node is time synchronized with a transmitter node to apply Doppler corrections to the receiver node's own motions relative to a common reference frame. The receiver node may be configured to: The receiver node may be configured to: based at least on the receiver node being time synchronized with the transmitter node to apply Doppler corrections and the common reference frame, use Doppler null scanning (DNS) to determine DNS derived information, the DNS derived information including a bearing and the receiver node's relative position relative to the transmitter node; and output a position, navigation, and timing (PNT) solution based at least on the DNS derived information.
G01S 5/00 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de position; Localisation par coordination de plusieurs déterminations de distance
G01S 13/58 - Systèmes de détermination de la vitesse ou de la trajectoire; Systèmes de détermination du sens d'un mouvement
A system and method for generating an enhanced set of NOTAMs. The system and method include converting one or more abbreviated terms of a NOTAM text of the NOTAM into one or more respective expanded terms. The system and method include applying a set of capitalization rules to the NOTAM text. The system and method include emphasizing a portion of each word of the NOTAM text based on one or more emphasizing rules, where words are terms with only letters. The system and method include directing at least a portion of the enhanced set of NOTAMs to be at least one of displayed via a display or physically printed by a printer.
