Systems and methods for facilitating aerial vehicle services are provided. A service entity system can obtain multi-modal transportation services data indicative of a plurality of anticipated aerial transportation service. The service entity system can obtain vehicle attributes associated vehicle(s) of an aerial vehicle provider and determine an expected performance of the vehicle(s) based on the vehicle attributes and the anticipated aerial transportation services. The service entity system can generate an aerial vehicle service request that requests access to the vehicle(s) for providing aerial transportation services for the service entity based on the expected performance of the vehicle(s). A vehicle provider system can obtain a number of different aerial vehicle service requests from a number of different service entities. The vehicle provider system can select portions of the different aerial vehicle service requests to accept and provide access to vehicle(s) of the vehicle provider based on the selected portions.
Systems and methods for transferring aircraft within a landing area of an aerial transport are provided. A system includes a plurality of robotic devices configured to move aircraft within the landing area. The system obtains facility data to dynamically determine accessible and prohibited areas of the landing area. The system determines a robotic device to transfer an aircraft based on map data representing the prohibited/accessible areas of the landing area and robotic data representing attributes of each robotic device. The system determines a number of routes for the selected robotic device to transfer the aircraft within the landing area while avoiding prohibited areas of the landing area. The system generates command instructions for the selected robotic device and provides the command instructions to the selected robotic device to travel in accordance with the number of routes.
Example aspects of the present disclosure provide for an example method. The example method can include accessing a first request for providing transportation along a first multi-leg transportation journey and a second request for providing transportation along a second multi-leg transportation journey. The example method can include querying a vehicle slot register to access data descriptive of unallocated vehicle slots for providing transportation services. The example method can include computing, using a request arbitration model, a first allocation for servicing the first request and a second allocation for servicing the second request. The example method can include updating the vehicle slot register based on the first allocation and the second allocation. The example method can include outputting a first response for the first request indicating the first allocation. The example method can include outputting a second response for the second request indicating the second allocation.
An electric motor comprises a rotor and a stator. The rotor includes a housing having an inner surface and an outer surface, a first end, and a second end. Permanent magnets are located along the inner surface of the rotor housing. At least one groove is defined in the first end of the rotor housing. A sealing member includes at least one protrusion located in the at least one groove. A honeycomb panel may be located in a recess defined in the outer surface of the rotor housing. The electric motor may form part of a propulsions system for an aircraft, used to drive a rotor assembly including rotor blades.
Examples relate to a battery management system with an enhanced equivalent circuit model (ECM) for electric vehicles, including electric vertical takeoff and landing (eVTOL) aircraft. The system includes a memory to store an equivalent circuit model (ECM) configured to dynamically adjust a series resistance component in real-time based on operational data from a lithium-ion battery. This adjustment models lithium depletion effects under high discharge conditions. At least one processor is configured to continuously refine parameters of the ECM by analyzing discrepancies between predicted and actual battery performance, where the adjustments are based on real-time changes in state of charge, temperature, and current.
G01R 31/367 - Logiciels à cet effet, p. ex. pour le test des batteries en utilisant une modélisation ou des tables de correspondance
B64D 31/16 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01R 31/00 - Dispositions pour tester les propriétés électriquesDispositions pour la localisation des pannes électriquesDispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
G01R 31/382 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p. ex. état de charge
A power over Ethernet (POE) switch provides integrated power and data transmission tailored for aircraft systems. The POE switch accepts high voltage input from batteries and utilizes DC-DC converters to generate low voltage for switch electronics. This power is combined with Ethernet data signals and delivered over Ethernet cabling to connected devices. To manage substantial heat generation, the switch employs thermally isolated zones with dedicated heatsinks and forced airflow paths for each hot section. Noise isolation techniques including filters and transformers prevent electrical noise from degrading network signals. Independent cooling paths and noise mitigation enable reliable operation despite the challenging thermal and electrical environment. The integrated networking, power distribution, thermal management, and noise isolation reduce cabling needs. The tailored POE switch design provides robust power and data transmission for aviation components without adding significant weight or complexity.
Example methods calibrate battery models in electric aircraft using closed-loop feedback. Test points gaps are received. The aircraft connects to ground support equipment (GSE) and is immobilized. Certain battery packs are selected for testing. Propellers are ramped to create power draws per a test plan while monitoring voltage, current, and temperature telemetry. Selective battery packs are activated to focus loads. Telemetry data is processed and stored. Rest periods allow battery temperature stabilization between test points. Additional packs are tested if needed. Battery models are updated by analyzing telemetry data. Overall, the method maintains customized, accurate battery models using lab testing and in-situ calibration with the GSE. Frequent and ongoing recalibration via closed-loop feedback replaces assumptions with observed data for high-fidelity state-of-health predictions throughout the battery lifetime.
B60L 58/18 - 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 de plusieurs modules de batterie
G01R 31/00 - Dispositions pour tester les propriétés électriquesDispositions pour la localisation des pannes électriquesDispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
G01R 31/367 - Logiciels à cet effet, p. ex. pour le test des batteries en utilisant une modélisation ou des tables de correspondance
G01R 31/3842 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p. ex. état de charge combinant des mesures de tension et de courant
G06F 30/15 - Conception de véhicules, d’aéronefs ou d’embarcations
8.
Aerial Vehicle With Differential Control Mechanisms
Various examples are directed to an aerial vehicle comprising a fuselage, a first wing member, and a second wing member. The fuselage may have a nose end and a tail end. The first wing member may extend from the fuselage and comprise a first drive motor coupled to the first rotor. The second wing member may also extend from the fuselage substantially opposite the first wing member and may comprise a second drive motor coupled to a second rotor. A first motor may be coupled to rotate the first wing member and the first rotor about a first axis substantially perpendicular to a fuselage axis extending from the nose end to the tail end. A second motor may be coupled to rotate the second wing member and the second rotor about a second axis substantially perpendicular to the fuselage axis. A controller circuit may be configured to differentially actuate the first motor and the second motor.
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
An extension linkage for a wing flap can include at least one arm that includes two elements connected by a joint. The linkage can include an actuation mechanism, additional arms and/or each arm can include more than two elements, tie rods and/or cross pieces connecting two or more arms, and any other suitable components. The linkage functions to translate and rotate a body attached to one end of the arm relative to a primary structure attached to a second end of the arm. The linkage resides entirely within a space defined by the upper skin and the lower skin of the wing rearward of the mounting when in a retracted configuration.
09 - Appareils et instruments scientifiques et électriques
Produits et services
Downloadable software in the nature of a mobile application for accessing, reserving, and booking commercial flights for transporting one or more people on vertical take-off and landing vehicles (VTOL)s and electronic vertical take-off and landing vehicles (eVTOLs); Downloadable software in the nature of a mobile application for matching pilots to commercial flights booked by passengers on vertical take-off and landing vehicles (VTOL)s and electronic vertical take-off and landing vehicles (eVTOLs)
09 - Appareils et instruments scientifiques et électriques
Produits et services
Downloadable software in the nature of a mobile application for accessing, reserving, and booking commercial flights for transporting one or more people on vertical take-off and landing vehicles (VTOL)s and electronic vertical take-off and landing vehicles (eVTOLs); Downloadable software in the nature of a mobile application for matching pilots to commercial flights booked by passengers on vertical take-off and landing vehicles (VTOL)s and electronic vertical take-off and landing vehicles (eVTOLs)
09 - Appareils et instruments scientifiques et électriques
Produits et services
Downloadable software in the nature of a mobile application for accessing, reserving, and booking commercial flights for transporting one or more people on vertical take-off and landing vehicles (VTOL)s and electronic vertical take-off and landing vehicles (eVTOLs); Downloadable software in the nature of a mobile application for matching pilots to commercial flights booked by passengers on vertical take-off and landing vehicles (VTOL)s and electronic vertical take-off and landing vehicles (eVTOLs)
A multi-segment oblique flying wing aircraft which has three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high speed flight configuration, or may be adapted for take-off and cruise at a constant angle. In an extreme flight case, the central wing segment may rotate to a local sweep of ninety degrees.
The present disclosure provides systems and methods for real-time planning and fulfillment of multi-modal transportation services in a multi-modal ride sharing network. In particular, aspects of the present disclosure are directed to a computing system that creates an end-to-end multi-modal itinerary responsive to a user request for transportation service between an origin and a destination. The multi-modal itinerary can include two or more transportation legs that include travel via two or more different transportation modalities such as, as examples, via a car and via an aircraft.
Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft may be noisy. To accommodate this, the aircraft may utilize onboard sensors, offboard sensing, network, and predictive temporal data for noise signature mitigation. By building a composite understanding of real data offboard the aircraft, the aircraft can make adjustments to the way it is flying and verify this against a predicted noise signature (via computational methods) to reduce environmental impact. This might be realized via a change in translative speed, propeller speed, or choices in propulsor usage (e.g., a quiet propulsor vs. a high thrust, noisier propulsor). These noise mitigation actions may also be decided at the network level rather than the vehicle level to balance concerns across a city and relieve computing constraints on the aircraft.
An aircraft including an airframe and a plurality of propulsion assemblies coupled to the airframe, wherein each propulsion assembly includes an electric motor, a propeller coupled to the electric motor, and a tilt mechanism that connects the propulsion assembly to the airframe and transforms the propulsion assembly between a forward configuration and a hover configuration; wherein the plurality of propulsion assemblies is transformable between a forward arrangement and a hover arrangement, wherein each of the plurality of propulsion assemblies is in the forward configuration in the forward arrangement, wherein each of the plurality of propulsion assemblies is in the hover configuration in the hover arrangement, wherein the spacing between at least two of the propellers of the plurality of propulsion assemblies changes between the forward arrangement and the hover arrangement.
Examples relate to a charge handle for an electric aircraft. The charge handle can include a housing and a core slidably accommodated within the housing. A coolant flow path can be within the core, and a plurality of pressure sensors can be located within the core to detect pressure within the coolant flow path. A communication interface can transmit pressure data from the pressure sensors, enabling control of coolant flow based on the transmitted data. The plurality of pressure sensors can include at least two sensors. The coolant flow path can include a coolant in chamber and a coolant out chamber, with a first pressure sensor detecting pressure in the coolant in chamber and a second pressure sensor detecting pressure in the coolant out chamber.
B60L 53/16 - Connecteurs, p. ex. fiches ou prises, spécialement adaptés pour recharger des véhicules électriques
B60L 53/66 - Transfert de données entre les stations de charge et le véhicule
B60L 58/26 - 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 pour la commande de la température des batteries par refroidissement
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
18.
ISOLATED BATTERY PACK CHARGING SYSTEM WITH CONTROLLER
Examples relate to a charging system for an electric vehicle with multiple isolated battery packs. The system can include a charge handle with isolated power channels, each connecting to a respective battery pack. A controller can independently control each power channel according to a charging profile for each battery pack. The system can enable simultaneous charging of the battery packs and dynamically adjust charging parameters based on feedback from the vehicle.
B60L 53/16 - Connecteurs, p. ex. fiches ou prises, spécialement adaptés pour recharger des véhicules électriques
B60L 53/66 - Transfert de données entre les stations de charge et le véhicule
B60L 58/26 - 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 pour la commande de la température des batteries par refroidissement
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
19.
Rotor deployment mechanism for vertical take-off and landing aircraft
A deployment mechanism for use on an aerial vehicle adapted for vertical takeoff and landing using deployable thrust producing elements for takeoff and landing. The deployment mechanism may use linear actuation of a linkage assembly to deploy thrust producing rotor assemblies from a vertical thrust hove configuration to a horizontal thrust forward flight configuration. The aerial vehicle may include left side rotor assemblies and right side rotor assemblies which may be deployed by deployment mechanisms.
B64C 27/28 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
B64C 27/30 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec moyens permettant de réduire la traînée du rotor en période de non fonctionnement
B64C 39/06 - Aéronefs non prévus ailleurs à ailes en forme de disque ou d'anneau
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
A request for transport services that identifies a rider, an origin, and a destination is received from a client device. Eligibility of the request to be serviced by a vertical take-off and landing (VTOL) aircraft is determined based on the origin and the destination. A transportation system determines a first and a second hub for a leg of the transport request serviced by the VTOL aircraft and calculates a set of candidate routes from the first hub to the second hub. A provisioned route is selected from among the set of candidate routes based on network and environmental parameters and objectives including pre-determined acceptable noise levels, weather, and the presence and planned routes of other VTOL aircrafts along each of the candidate routes.
A system for use with a fuel cell stack supplied by a tank of hydrogen includes a combustor coupled to the fuel cell exhaust line to receive and combust residual hydrogen gas in the exhaust, a turbine coupled to the combustor to receive combusted exhaust from the combustor; and a mechanical device coupled to the turbine to extract work from rotation of the turbine. The combustor may further be coupled to receive and combust hydrogen in fuel cell circulation-loop purge gas, and the combustor may further combust hydrogen received from the fuel tank via a fuel tank purge line or on demand. Supplementary oxygen may be supplied to the combustor based on an oxygen level detected by the oxygen sensor in the combustor exhaust line.
H01M 8/0662 - Traitement des réactifs gazeux ou des résidus gazeux, p. ex. nettoyage
H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
H01M 8/0606 - Combinaison d’éléments à combustible avec des moyens de production de réactifs ou pour le traitement de résidus avec des moyens de production des réactifs gazeux
22.
THERMAL MANAGEMENT SYSTEM AND METHOD FOR AIRCRAFT FUEL CELLS
A fuel cell thermal management system and method for aerodynamic vehicles (such as aircraft) having propulsion systems powered by hydrogen fuel cells. The system and method reduce the overall amount of energy required to operate a propulsion system, which in turn reduces cooling requirements and improves efficiency. A cabin air reuse system uses cabin exhaust air as input air for the fuel cell. Because the cabin exhaust air is compressed, this saves the work involved in compressing air for input to the fuel cell.
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
B64D 13/02 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant pressurisé
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
23.
VTOL AIRCRAFT WITH DUAL PROPELLERS AND DIRECTIONAL CLUTCH
An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The deployment mechanisms deploy the rotor forward and up as they deploy from a forward flight configuration to a vertical thrust configuration. A single motor may drive two co-axial propellers, with a first propeller driven when the motor spins in a first direction, and a second propeller driven when the motor spins in a second direction.
A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.
A rotor assembly deployment mechanism configured to deploy a rotor assembly of a vertical take-off and landing aircraft from a horizontal, forward thrust, position to a vertical, hover, position. The rotor assembly deployment mechanism is configured to deploy an electric motor and propeller together. The deployment mechanism provides significant stiffness and strength with the use of torsion box constructions. The deployment mechanism may utilize bar linkages wherein the primary linkage pivot is of a large diameter relative to the span of the pivot in order to provide significant stiffness. The deployment mechanism may utilize rotary actuators to drive the deployment and stowing of the rotor assembly.
B64C 27/28 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 27/30 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec moyens permettant de réduire la traînée du rotor en période de non fonctionnement
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
26.
Method For Flying VTOL Aircraft With Forward Canted Rotors
A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight. The rotors are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have airfoils which may provide structural support for the rotors as well as providing lift during forward flight.
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 27/22 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion
B64C 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
B64C 27/82 - GiravionsRotors propres aux giravions caractérisés par l'existence d'un rotor auxiliaire ou d'un dispositif à jet fluide pour contrebalancer le couple du rotor de sustentation ou faire varier la direction du giravion
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64C 39/06 - Aéronefs non prévus ailleurs à ailes en forme de disque ou d'anneau
27.
Compact Blade Pitch Mechanism And Aircraft Using Same
A propeller blade pitch control mechanism configured to adjust and control the blade pitch of the blades of a multi-blade propeller simultaneously. The pitch control mechanism may have a pitch plate which is raised or lowered along a liner path along an axial direction using a linear drive, which may be a power screw. The pitch plate is coupled to the blade roots with kinematic links which transfer the linear axial motion of the pitch plate along the propeller spin axis into rotary motion of the propeller blade roots, thereby controlling the pitch of the propeller blades. The propeller pitch control mechanism may include springs or gas springs adapted to place the propeller blades in a low drag position in the event of failure of the blade pitch control mechanism.
Systems and methods of providing improved solutions for aviation transport networks, particularly for electric vertical takeoff and landing (eVTOL) aircraft, are provided. For example, a method for generating a network of skylanes for eVTOL aircraft travel in a particular geographic area includes accessing airspace data (e.g., aircraft track data and/or restricted zone data) defining an available portion of the particular geographic area for the eVTOL aircraft travel. The airspace data is used to compute skylane route data for a particular skylane defined by a plurality of waypoints in three-dimensional space between a first vertiport location and a second vertiport location for the eVTOL aircraft in the particular geographic area. The skylane route data can be added to a network of available skylanes and selected for deployment of a particular eVTOL aircraft.
Systems and methods of providing improved solutions for aviation transport networks, particularly for electric vertical takeoff and landing (eVTOL) aircraft, are provided. For example, a method for generating a network of skylanes for eVTOL aircraft travel in a particular geographic area includes accessing airspace data (e.g., aircraft track data and/or restricted zone data) defining an available portion of the particular geographic area for the eVTOL aircraft travel. The airspace data is used to compute skylane route data for a particular skylane defined by a plurality of waypoints in three-dimensional space between a first vertiport location and a second vertiport location for the eVTOL aircraft in the particular geographic area. The skylane route data can be added to a network of available skylanes and selected for deployment of a particular eVTOL aircraft.
A method of assigning an electric vertical takeoff and landing (eVTOL) aircraft to a skylane includes accessing: (i) a trip request for aerial transport at a particular travel time from an origin location to a destination location within a particular geographic area; and (ii) skylane network data indicative of a plurality of skylanes for eVTOL aircraft travel in the particular geographic area. A subset of the plurality of skylanes are computed as candidate skylanes for servicing the trip request. The candidate skylanes are determined based on a route assessment configured to evaluate an operating constraint associated with respective skylanes relative to parameter data for the particular geographic area at the particular travel time. A selected skylane is computed from the candidate skylanes for servicing the trip request, and a trip assignment is generated for deployment of an eVTOL aircraft from the origin location into the selected skylane.
A solid motor coil with conductive pathways as part of a unitary construction. The conductive pathways are separated by resistive insulating layers. The conductive pathways may vary in their location within the cross-section of the motor coil, which may significantly reduce eddy current losses. The solid motor coil may result in a higher packing factor than previous designs. The solid motor coil may reduce the eddy current loss per conductor, with commensurate reduction in peak temperature rise. An electric motor with solid motor coils provides improved heat conduction and improved efficiency, allowing for a smaller motor package at higher power levels.
H02K 3/26 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p. ex. avec des conducteurs en barre constitués par des conducteurs imprimés
H02K 3/28 - Schémas d'enroulements ou de connexions entre enroulements
H02K 15/04 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques d'enroulements avant leur montage dans les machines
A vertiport system dynamically updates configuration of a vertiport based on predicted usage of the vertiport during a given time frame. The vertiport system predicts vertiport usage using flight data and estimated passenger demands and determines a desired number of parking pads and a desired number of final approach and takeoff (FATO) pads for the vertiport during the time frame. Based on the desired number of parking pads and the desired number of FATO pads for the vertiport, the vertiport system determines an updated configuration of the vertiport. According to the updated configuration, the vertiport system updates the configuration of the vertiport for at least a portion of the time frame.
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 robust control method for an oblique flying wing aircraft includes computing an angular velocity error between a reference angular velocity and an actual angular velocity and computing a moment command with an angular velocity controller based at least in part on the angular velocity error. The angular velocity controller decouples two or more of a yaw rate axis, a pitch rate axis, and a roll rate axis of the asymmetric aircraft for the moment command.
An aerial vehicle configured with air intake in an otherwise higher drag location. In some aspects, the aerial vehicle is a vertical take-off and landing aircraft. The aircraft may intake the air to provide air to a hydrogen fuel cell system within the aircraft. The aircraft may have electric motor driven rotor assemblies which provide thrust for both vertical take-off and landing and forward flight operations. The electric motor driven rotor assemblies may be powered by electric power from the fuel cell system. The air intake may be on the forward portion of a nacelle placed in what would be a high drag location, such as at the junction of the wings and the fuselage, or the junction of the vertical stabilizers and the fuselage, for example.
A request for transport services that identifies a rider, an origin, and a destination is received from a client device. Eligibility of the request to be serviced by a vertical take-off and landing (VTOL) aircraft is determined based on the origin and the destination. The client device is sent an itinerary for servicing the transport request including a leg serviced by the VTOL aircraft. Confirmation is received that the rider has boarded the VTOL aircraft and determination made as to whether the VTOL aircraft should wait for additional riders. Instruction are sent to the VTOL aircraft to take-off if one or more conditions are met.
G05D 1/695 - Commande coordonnée de la position ou du cap de plusieurs véhicules pour maintenir la position des véhicules les uns par rapport aux autres, p. ex. pour les voyages en convoi ou les vols en formation
G06Q 10/0631 - Planification, affectation, distribution ou ordonnancement de ressources d’entreprises ou d’organisations
G06Q 50/40 - Procédés d’affaires s’appliquant à l’industrie du transport
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
36.
TILT ROTOR VERTICAL TAKE-OFF AND LANDING AERIAL VEHICLE
An aerial vehicle includes a fuselage supporting a pair of wings, with each of wings having a pair of booms attached thereto. A tilt rotor is positioned at each of the forward ends of each of the booms, to provide the aerial vehicle with at least four tilt rotors. A fixed rotor is positioned at and secured to the aft (or trailing) ends of each of the booms, to provide the aerial vehicle with at least four fixed rotors.
In one aspect, a system for charging an aircraft can include a robotic charging device, and a computing system configured to obtain data associated with a transportation itinerary and energy parameter(s) of the aircraft. The data associated with the transportation itinerary can be indicative of an aircraft landing facility at which the aircraft is to be located. The computing system can determine (e.g., select) a robotic charging device from among a plurality of robotic charging devices for charging the aircraft based on the transportation itinerary data and energy parameter(s) of the aircraft; determine charging parameter(s) for the robotic charging device based on the transportation itinerary data; and communicate command instruction(s) for the robotic charging device to charge the aircraft according to the charging parameter(s). The robotic charging device can be configured to automatically connect with a charging area of the aircraft for charging a battery onboard the aircraft.
B60L 53/16 - Connecteurs, p. ex. fiches ou prises, spécialement adaptés pour recharger des véhicules électriques
B60L 53/35 - Moyens pour l’ajustement automatique ou assisté de la position relative des dispositifs de charge et des véhicules
B60L 53/62 - Surveillance et commande des stations de charge en réponse à des paramètres de charge, p. ex. courant, tension ou charge électrique
B60L 53/65 - Surveillance et commande des stations de charge impliquant l'identification des véhicules ou de leurs types de batteries
B60L 53/66 - Transfert de données entre les stations de charge et le véhicule
B60L 58/12 - 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 de l'état de charge [SoC]
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]
38.
SIDESTRIPE IDENTIFICATION, ESTIMATION AND CHARACTERIZATION FOR ARBITRARY RUNWAYS
Various embodiments of an apparatus, methods, systems and computer program products described herein are directed to an Identification Engine. The Identification Engine identifies a portrayal in image data of at least one side stripe of an aircraft runway at a geographical location. The Identification Engine applies a three-dimensional (3D) map of the geographic location to the portrayal of the at least one side strip in the image data. Based on applying the 3D map, the Identification Engine determines a current position of an aircraft in the 3D map with respect to the aircraft runway at the geographical location.
G06T 7/246 - Analyse du mouvement utilisant des procédés basés sur les caractéristiques, p. ex. le suivi des coins ou des segments
G06V 10/774 - Génération d'ensembles de motifs de formationTraitement des caractéristiques d’images ou de vidéos dans les espaces de caractéristiquesDispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant l’intégration et la réduction de données, p. ex. analyse en composantes principales [PCA] ou analyse en composantes indépendantes [ ICA] ou cartes auto-organisatrices [SOM]Séparation aveugle de source méthodes de Bootstrap, p. ex. "bagging” ou “boosting”
G06V 20/17 - Scènes terrestres transmises par des avions ou des drones
A vertical takeoff and landing aircraft includes a starboard wing, a port wing, first and second tilt rotors coupled to the port and starboard wings respectively, and first and second batteries. A pair of control surfaces are arranged on a first side of the mid-sagittal plane of the aircraft, the pair comprising a first and a second control surface. A first flight actuator is electrically connected to the first battery and a second flight actuator is electrically connected to the second battery. The first and second flight actuators are mechanically connected to the first and second control surfaces respectively.
An oblique flying wing aircraft with internal ducting and airflow. The aircraft may have propulsion units within the wing body. The propulsion units may be off-axis internal to the wing to utilize locations with larger internal space available. In some aspects, the multi-segment oblique flying wing aircraft may have three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high-speed flight configuration, or may be adapted for take-off and cruise at a constant angle.
An aircraft includes a fuselage that includes a nose portion, a cabin portion, an underwing portion, and an aft portion. The nose portion includes sensors that generate sensor data. The cabin portion is aft of the nose portion and includes a passenger cabin. The underwing portion is aft of the cabin portion and includes a wing attachment region and a battery bay. The aft portion is aft of the underwing portion. A wing assembly including motor mounts and control surfaces is attached to the wing attachment region such that the underwing portion of the fuselage is located under the wing assembly. A tail assembly is attached to the aft portion. The electric motors are attached to motor mounts such that the propellers are in a pusher configuration facing rearward. An autonomous control system controls the electric motors and control surfaces based on the sensor data.
B64U 20/30 - Caractéristiques de construction de véhicules aériens sans pilote pour la sécurité, p. ex. avec des composants frangibles
B64U 101/61 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de passagersVéhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes au transport de passagers
42.
Oblique Flying Wing Aircraft With Internal Ducting And Internal Propulsion
An oblique flying wing aircraft with internal ducting and airflow. The aircraft may have propulsion units within the wing body. The propulsion units may be off-axis internal to the wing to utilize locations with larger internal space available. In some aspects, the multi-segment oblique flying wing aircraft may have three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high-speed flight configuration, or may be adapted for take-off and cruise at a constant angle.
Example embodiments are directed to generating an optimized network of flight paths and an operations volume around each of these flight paths. A network system creates a source network of paths, whereby the source network comprises a set of possible paths between two locations. The network system assigns a cost for traversing each edge of each path of the source network and aggregates the cost for traversing each edge of each path to obtain a cost for each path of the source network. Based on the cost for each path, the network system identifies a path having the lowest cost, whereby the path having the lowest cost is the optimized route between the two locations. The network system then generates an operations volume for the optimized route. The operations volume represents airspace surrounding the optimized route. The operations volume is transmitted to a further system for use.
An aircraft propulsion system with an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
B64C 1/38 - Constructions adaptées pour réduire les effets de l'échauffement aérodynamique ou d'un échauffement externe d'autre nature
B64C 21/08 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires réglables
B64C 23/00 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs
A slanted heat exchange system and method for use in aerodynamic vehicle and for transferring heat between a coolant and a fluid. In some examples, the aerodynamic vehicle is an aircraft, and the fluid is air. The slanted heat exchange system and method include a slanted heat exchanger that is slanted relative to a channel direction just before the slanted heat exchanger. The slanted heat exchanger has an increased frontal surface area while still preserving a relatively compact cross-sectional area when viewed from the front. An array of inlet turning vanes both diffuse and slow down the fluid while also turning the fluid to enter the slanted heat exchanger approximately perpendicular to the slanted heat exchanger. This mitigates turning losses and reduces any pressure drop across the heat exchanger. In some examples, an array of outlet turning vanes turns and accelerates the fluid exiting the slanted heat exchanger.
F28D 1/02 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes pour une seule des sources de potentiel calorifique, les deux sources étant en contact chacune avec un côté de la paroi de la canalisation, dans lesquels l'autre source de potentiel calorifique est une grande masse de fluide, p. ex. radiateurs domestiques ou de moteur de voiture avec des canalisations d'échange de chaleur immergées dans la masse du fluide
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The aerial vehicle may be powered with electric motors.
B64C 27/30 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec moyens permettant de réduire la traînée du rotor en période de non fonctionnement
B64C 11/10 - Montage des pales dans le cas de pales non réglables rigides
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The aerial vehicle may have rear mounted rotors adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may be powered with electric motors.
B64C 27/30 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec moyens permettant de réduire la traînée du rotor en période de non fonctionnement
B64C 11/10 - Montage des pales dans le cas de pales non réglables rigides
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
48.
TRAFFIC PATTERN CONTROL OF UAVS AND AUTOMATED DOWNWIND EXTENSIONS
Systems and methods for the modification of an aircraft landing pattern through a graphical user interface. The graphical user interface provides buttons associated with flight maneuvers that, when selected, trigger an autopilot of the aircraft to perform the corresponding maneuver. The maneuvers may include a loitering maneuver such as a 360 degree maneuver, a downwind extension maneuver and a turn to base maneuver.
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
Disclosed are methods and systems for predicting time varying loudness in a geographic region. Training data, including noise information, weather information, and traffic information is collected from a plurality of sensors located in a plurality of geographic regions. The information is collected during multiple time periods. The noise information includes time varying loudness. Static features of the geographic regions are also defined and included in the training data. The static and time varying dynamic features train a model. The model is used predict time varying loudness within a different region and at a time later than times the training data is collected. The predicted loudness levels are utilized, in some aspects, to determine a route for an aircraft.
A fuel cell system includes a hydrogen expansion system comprising an aeolipile, and a heat exchanger for receiving and expanding hydrogen received from a supply of hydrogen, for provision to the aeolipile. A generator coupled to the aeolipile may generate electrical power from operation of the aeolipile. The hydrogen leaving the aeolipile may be returned to the heat exchanger to transfer heat to the hydrogen received from the supply of hydrogen.
F01K 25/08 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières
H01M 8/04014 - Échange de chaleur par des fluides gazeuxÉchange de chaleur par combustion des réactifs
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
51.
MANAGING COOLING AIRFLOW USING VARIABLE-GEOMETRY OPENINGS
A variable-geometry cooling airflow management system and method for managing the cooling of a fuel cell on an aerodynamic vehicle (such as an aircraft). The cooling management is achieved by providing a conduit having a fan, radiator, and variable-geometry openings (such as variable-geometry inlet and variable-geometry outlet) at the conduit ends. Heat from the fuel cell is transferred to a coolant, which then flows through the radiator in the conduit. Cooling airflow passes over the radiator to provide fuel cell cooling. The amount of cooling airflow over the radiator is adjusted by varying the size of the variable-geometry inlet, the variable-geometry outlet, or both. Adjustments are made based on the operational parameters of the aircraft such as airspeed and flight configuration. A fan also may be located in the conduit, a speed of which is varied by the control system based on the operational parameters of the aircraft.
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
B60L 58/33 - 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 piles à combustible pour la commande de la température des piles à combustible, p. ex. en commandant la charge électrique par refroidissement
B64C 3/38 - Réglage des ailes complètes ou de certaines parties de ces ailes
B64D 27/31 - Aéronefs caractérisés par des groupes moteurs électriques à l'intérieur des ailes ou fixés à celles-ci
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
H01M 8/04007 - Dispositions auxiliaires, p. ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur
H01M 8/04029 - Échange de chaleur par des liquides
An aircraft (100) includes a fuel cell system (300) including a fuel cell (212) powered by hydrogen received from a supply of hydrogen, and a propulsion unit including a conduit through which a flow of air is propelled. A first heat exchanger (322) transfers heat from the fuel cell to a coolant fluid located in a coolant loop, and a second heat exchanger (406) is located in the conduit for heating the air passing through the conduit by transferring heat to the air from the coolant fluid via the second heat exchanger. This configuration serves to cool the fuel cell while increasing the efficiency of the propulsion unit.
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
A fuel cell system includes a fuel cell for receiving hydrogen from a supply of hydrogen. The system comprises a heat exchanger for transferring heat to the hydrogen from a coolant fluid located in a cooling loop. The cooling loop comprises a number of cooling cores located in a conduit that supplies air to the fuel cell. A compressor compresses air cooled by the cooling cores to provide compressed air to the fuel call. The cooling cores may be de-iced by a coolant fluid that has been warmed by operation of the fuel cell. Fuel cell system efficiency can be increased by cooling the air to be supplied to the fuel cell before or after compressing it.
An aircraft includes a fuel cell system including a fuel cell powered by hydrogen received from a supply of hydrogen, and a propulsion unit including a conduit through which a flow of air is propelled. A first heat exchanger transfers heat from the fuel cell to a coolant fluid located in a coolant loop, and a second heat exchanger is located in the conduit for heating the air passing through the conduit by transferring heat to the air from the coolant fluid via the second heat exchanger. This configuration serves to cool the fuel cell while increasing the efficiency of the propulsion unit.
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
A fuel cell system includes a fuel cell for receiving hydrogen from a supply of hydrogen. The system comprises a heat exchanger for transferring heat to the hydrogen from a coolant fluid located in a cooling loop. The cooling loop comprises a number of cooling cores located in a conduit that supplies air to the fuel cell. A compressor compresses air cooled by the cooling cores to provide compressed air to the fuel call. The cooling cores may be de-iced by a coolant fluid that has been warmed by operation of the fuel cell. Fuel cell system efficiency can be increased by cooling the air to be supplied to the fuel cell before or after compressing it.
H01M 8/04007 - Dispositions auxiliaires, p. ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur
H01M 8/04029 - Échange de chaleur par des liquides
H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
H01M 8/04223 - Dispositions auxiliaires, p. ex. pour la commande de la pression ou pour la circulation des fluides pendant le démarrage ou l’arrêtDépolarisation ou activation, p. ex. purgeMoyens pour court-circuiter les éléments à combustible défectueux
A fuel cell system includes a hydrogen expansion system comprising an aeolipile, and a heat exchanger for receiving and expanding hydrogen received from a supply of hydrogen, for provision to the aeolipile. A generator coupled to the aeolipile may generate electrical power from operation of the aeolipile. The hydrogen leaving the aeolipile may be returned to the heat exchanger to transfer heat to the hydrogen received from the supply of hydrogen.
Systems and methods for facilitating aerial vehicle services are provided. A service entity system can obtain multi-modal transportation services data indicative of a plurality of anticipated aerial transportation service. The service entity system can obtain vehicle attributes associated vehicle(s) of an aerial vehicle provider and determine an expected performance of the vehicle(s) based on the vehicle attributes and the anticipated aerial transportation services. The service entity system can generate an aerial vehicle service request that requests access to the vehicle(s) for providing aerial transportation services for the service entity based on the expected performance of the vehicle(s). A vehicle provider system can obtain a number of different aerial vehicle service requests from a number of different service entities. The vehicle provider system can select portions of the different aerial vehicle service requests to accept and provide access to vehicle(s) of the vehicle provider based on the selected portions.
A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight. The rotors are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have airfoils which may provide structural support for the rotors as well as providing lift during forward flight.
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 27/22 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion
B64C 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64C 39/06 - Aéronefs non prévus ailleurs à ailes en forme de disque ou d'anneau
B64C 27/82 - GiravionsRotors propres aux giravions caractérisés par l'existence d'un rotor auxiliaire ou d'un dispositif à jet fluide pour contrebalancer le couple du rotor de sustentation ou faire varier la direction du giravion
09 - Appareils et instruments scientifiques et électriques
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Downloadable software for procuring, engaging, booking, and coordinating air transportation services; downloadable software for managing financial transactions for air transportation services; downloadable software for matching passengers, pilots, aircraft, routes, and takeoff and landing infrastructure to provide air transportation services; downloadable software for managing aircraft availability, pilot availability, and takeoff and landing infrastructure availability for air transportation services; downloadable software for managing repair or maintenance of aircraft, air transportation equipment, ground support equipment, battery charging equipment, and aircraft cooling equipment; downloadable software for managing passenger experience for air transportation services; downloadable software for managing pilot operations for air transportation services, including managing preflight activities, flight routing clearance, post flight activities, and flight logging; downloadable software for managing battery charging for aircraft Providing temporary use of online non-downloadable software for procuring, engaging, booking, and coordinating air transportation services; providing temporary use of online non-downloadable software for managing financial transactions for air transportation services; providing temporary use of online non-downloadable software for matching passengers, pilots, aircraft, routes, and takeoff and landing infrastructure to provide air transportation services; providing temporary use of online non-downloadable software for managing aircraft availability, pilot availability, and takeoff and landing infrastructure availability for air transportation services; providing temporary use of online non-downloadable software for managing repair or maintenance of aircraft, air transportation equipment, ground support equipment, battery charging equipment, and aircraft cooling equipment; providing temporary use of online non-downloadable software for managing passenger experience for air transportation services; providing temporary use of online non-downloadable software for managing pilot operations for air transportation services, including managing preflight activities, flight routing clearance, post flight activities, and flight logging; providing temporary use of online non-downloadable software for managing battery charging for aircraft
An aerial vehicle includes a fuselage supporting a pair of wings, with each of wings having a pair of booms attached thereto. A tilt rotor is positioned at each of the forward ends of each of the booms, to provide the aerial vehicle with at least four tilt rotors. A fixed rotor is positioned at and secured to the aft (or trailing) ends of each of the booms, to provide the aerial vehicle with at least four fixed rotors.
A computing system for landing and storing vertical take-off and landing (VTOL) aircraft can be configured to receive aircraft data, passenger data, or environment data associated with a VTOL aircraft and determine a landing pad location within a landing facility based on the aircraft data, passenger data, and/or environment data. The landing facility can include a lower level and an upper level. The lower level can include a lower landing area and a lower storage area. The upper level can include an upper landing area. At least a portion of the upper level can be arranged over the lower storage area. The landing pad location can include a location within the lower landing area or the upper landing area of the landing facility. The computing system can communicate the landing pad location to an operator or a navigation system of the VTOL aircraft.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
E04H 6/44 - Bâtiments pour garer des voitures, du matériel roulant, des avions, des bateaux ou d’autres véhicules, p. ex. garages pour garer des avions
G05D 1/46 - Commande de la position ou du cap dans les trois dimensions
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 laminate material for an aircraft component is provided. The laminate material includes a first layer, a second layer and a rib disposed between the first and second layer. One or more connectors are configured to couple the ends of the rib to the first layer and the second layer. The connectors comprise a thermoplastic resin. Aircraft components are also provided.
B32B 3/18 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche interne formée d'éléments individuels
B32B 9/00 - Produits stratifiés composés essentiellement d'une substance particulière non couverte par les groupes
B32B 9/04 - Produits stratifiés composés essentiellement d'une substance particulière non couverte par les groupes comprenant une telle substance comme seul composant ou composant principal d'une couche adjacente à une autre couche d'une substance spécifique
B32B 27/18 - Produits stratifiés composés essentiellement de résine synthétique caractérisée par l'emploi d'additifs particuliers
B32B 27/28 - Produits stratifiés composés essentiellement de résine synthétique comprenant des copolymères de résines synthétiques non complètement couverts par les sous-groupes suivants
B64C 1/00 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
A hybrid power distribution system for an aircraft includes a first and second set of electrically-powered devices, such as inverters, motors and so forth. A first battery system is coupled to one or more of the first set of electrically-powered devices and a first fuel cell is coupled to one or more of the first set of electrically-powered devices. A second battery system is coupled to one or more of the second set of electrically-powered devices and a second fuel cell coupled to one or more of the second set of electrically- powered devices. The fuel cells and batteries together supply power to the electrically-powered devices as needed, while the fuel cells also keep the batteries charged.
B60L 58/21 - 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 de plusieurs modules de batterie ayant la même tension nominale
B60L 58/40 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la commande d'une combinaison de batteries et de piles à combustible
64.
Dynamic Tracking and Coordination of Multi-leg Transportation
Example aspects of the present disclosure relate to dynamic tracking and coordination of multi-leg transportation. The example method includes receiving a request for a transportation service. The method includes computing a multi-modal transportation itinerary for the user based on the request. The method includes accessing data associated with the multi-modal transportation service and data associated with a state of the user relative to the multi-modal transportation itinerary. The method includes computing a quality measurement of the multi-modal transportation service based on the data associated with the multi-modal transportation service and the data associated with the state of the user. And, the method includes initiating an adjustment action associated with the multi-modal transportation itinerary for the user based on the quality measurement.
Example aspects of the present disclosure relate to dynamic tracking and coordination of multi-leg transportation. The example method includes receiving a request for a transportation service. The method includes computing a multi-modal transportation itinerary for the user based on the request. The method includes accessing data associated with the multi-modal transportation service and data associated with a state of the user relative to the multi-modal transportation itinerary. The method includes computing a quality measurement of the multi-modal transportation service based on the data associated with the multi-modal transportation service and the data associated with the state of the user. And, the method includes initiating an adjustment action associated with the multi-modal transportation itinerary for the user based on the quality measurement.
A hydrogen circulation system for use with a fuel cell stack includes a supply line for receiving hydrogen gas from a supply of hydrogen, a fuel cell for receiving hydrogen gas from the supply line, an excess hydrogen line for receiving excess hydrogen from the fuel cell, and a turbocharger coupled to the excess hydrogen line and the supply line, to receive excess hydrogen from the excess hydrogen line, compress it, and return it to the supply line, the turbocharger being powered in use by hydrogen gas from the supply line.
H01M 8/04089 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux
H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
F01D 1/32 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec transformation pression-vitesse exclusivement dans le rotor, p. ex. le rotor tournant sous l'action de jets issus de celui-ci
F02B 37/04 - Moteurs avec entraînement des pompes par les gaz d'échappement et par d'autres moyens, p. ex. avec une pompe entraînée par les gaz d'échappement et une seconde pompe entraînée mécaniquement
F02B 37/10 - Moteurs avec entraînement des pompes par les gaz d'échappement et par d'autres moyens, p. ex. avec une pompe entraînée par les gaz d'échappement et une seconde pompe entraînée mécaniquement une pompe au moins étant entraînée d'une façon alternée soit par les gaz d'échappement soit par un autre moyen
F03B 3/08 - "Machines" ou machines motrices du type "à réaction"Parties constitutives ou détails particuliers les concernant avec transformation de la vitesse en pression exclusivement dans les rotors
F01D 1/00 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur
H01M 8/04119 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux avec apport simultané ou évacuation simultanée d’électrolyteHumidification ou déshumidification
A hybrid power distribution system for an aircraft includes a first and second set of electrically-powered devices, such as inverters, motors and so forth. A first battery system is coupled to one or more of the first set of electrically-powered devices and a first fuel cell is coupled to one or more of the first set of electrically-powered devices. A second battery system is coupled to one or more of the second set of electrically-powered devices and a second fuel cell coupled to one or more of the second set of electrically-powered devices. The fuel cells and batteries together supply power to the electrically-powered devices as needed, while the fuel cells also keep the batteries charged.
B64D 31/00 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs
B60L 53/00 - Procédés de chargement de batteries spécialement adaptées aux véhicules électriquesStations de charge ou équipements de charge embarqués pour ces batteriesÉchange d'éléments d’emmagasinage d'énergie dans les véhicules électriques
B60L 58/40 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la commande d'une combinaison de batteries et de piles à combustible
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
A hydrogen circulation system for use with a fuel cell stack includes a supply line for receiving hydrogen gas from a supply of hydrogen, a fuel cell for receiving hydrogen gas from the supply line, an excess hydrogen line for receiving excess hydrogen from the fuel cell, and a turbocharger coupled to the excess hydrogen line and the supply line, to receive excess hydrogen from the excess hydrogen line, compress it, and return it to the supply line, the turbocharger being powered in use by hydrogen gas from the supply line.
H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
H01M 8/04089 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux
69.
Systems and Methods for Radar-Based Aircraft Maneuver Actions
Systems and methods for radar-based aircraft maneuver actions are provided. An example computer-implemented method includes transmitting, using one or more transmitters onboard an aircraft, one or more radio signals. Reflected radio data corresponding to one or more radio signals reflected from a plurality of radio detection and ranging (“radar”) reflectors placed at a plurality of locations associated with an aerial facility can be received using one or more radio receivers onboard the aircraft. A location for the aircraft can be computed based on the radio data and the plurality of locations associated with the aerial facility at which the radar reflectors are placed. A maneuver action for the aircraft can be initiated at a particular landing pad of the aerial facility based on the location.
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
G01S 13/75 - Systèmes utilisant la reradiation d'ondes radio, p. ex. du type radar secondaireSystèmes analogues utilisant des transpondeurs alimentés par les ondes reçues, p. ex. utilisant des transpondeurs passifs
G01S 13/91 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour la commande du trafic
A vertical take-off and landing aircraft and method which uses fixed rotors for both VTOL and forward flight operations. The rotors are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the wing. The wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight, or may have a single center wing. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 3/32 - Voilures spécialement adaptées pour le montage des groupes propulseurs
B64C 27/22 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64C 39/06 - Aéronefs non prévus ailleurs à ailes en forme de disque ou d'anneau
B64C 27/82 - GiravionsRotors propres aux giravions caractérisés par l'existence d'un rotor auxiliaire ou d'un dispositif à jet fluide pour contrebalancer le couple du rotor de sustentation ou faire varier la direction du giravion
Aerial vehicles are assigned to routes within a transportation network based on a state of charge, state of power, and/or state of health for the aerial vehicle. Such aspects can be modeled based on one or more statistical models and/or machine-learned models, among other examples. As another example, an energy budget is used to ensure that the state of charge, state of power, and/or state of health of the aerial vehicle during and/or after traveling the route remains within the energy budget. A payload is assigned to a route and an associated aerial vehicle, thereby generating an itinerary. In examples, the itinerary is validated by the aerial vehicle to ensure that the aerial vehicle is capable of traveling the route with the payload. In examples where the aerial vehicle rejects the itinerary, the itinerary is assigned to another aerial vehicle and a new itinerary is identified for the aerial vehicle.
B64D 43/00 - Aménagements ou adaptations des instruments
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
G06Q 10/047 - Optimisation des itinéraires ou des chemins, p. ex. problème du voyageur de commerce
G06Q 10/0631 - Planification, affectation, distribution ou ordonnancement de ressources d’entreprises ou d’organisations
A charge handle, according to some examples, for electrically charging an electric vehicle comprises a housing and a movable core with fluid, electrical, and data connectors that engage with a charge port on the vehicle. A drive mechanism moves the core between disengaged and engaged positions relative to the housing to extend or retract the connectors. A latching mechanism secures the housing to the vehicle when engaged and releases the handle when disengaged. The fluid connectors provide cooling fluid circulation, the electrical connectors deliver charging current, and the data connector enables communication. The sequenced engagement and disengagement of the connectors by the drive mechanism ensures safe connection under load. The latching mechanism allows self-contained engagement forces without pushing on vehicle body components. The charge handle provides a safe, reliable physical interface between electric vehicle charge ports and external charging equipment by managing high-power electrical, fluid, and data connections.
B60L 53/16 - Connecteurs, p. ex. fiches ou prises, spécialement adaptés pour recharger des véhicules électriques
B60L 53/66 - Transfert de données entre les stations de charge et le véhicule
B60L 58/26 - 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 pour la commande de la température des batteries par refroidissement
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
A charge handle, according to some examples, for electrically charging an electric vehicle comprises a housing and a movable core with fluid, electrical, and data connectors that engage with a charge port on the vehicle. A drive mechanism moves the core between disengaged and engaged positions relative to the housing to extend or retract the connectors. A latching mechanism secures the housing to the vehicle when engaged and releases the handle when disengaged. The fluid connectors provide cooling fluid circulation, the electrical connectors deliver charging current, and the data connector enables communication. The sequenced engagement and disengagement of the connectors by the drive mechanism ensures safe connection under load. The latching mechanism allows self-contained engagement forces without pushing on vehicle body components. The charge handle provides a safe, reliable physical interface between electric vehicle charge ports and external charging equipment by managing high-power electrical, fluid, and data connections.
B60L 53/16 - Connecteurs, p. ex. fiches ou prises, spécialement adaptés pour recharger des véhicules électriques
B60L 53/18 - Câbles spécialement adaptés pour recharger des véhicules électriques
H01R 13/631 - Moyens additionnels pour faciliter l'engagement ou la séparation des pièces de couplage, p. ex. moyens pour aligner ou guider, leviers, pression de gaz pour l'engagement uniquement
A network system provides delivery of items using unmanned aerial vehicles (UAV) or drones. The network system uses an infrastructure of nodes that include landing pads to dock drones, as well as interfaces to provide and receive items from docked drones. Nodes may be stationary (e.g., fixed at a building rooftop or public transit station) or mobile (e.g., mounted to a vehicle). The network system may determine a route for delivery of an item, where a drone transports the item for at least a portion of the route. For example, the route may include multiple waypoints associated with nodes between which drones travel. For other portions of the route, the network system may request a provider to transport the item using a ground-based vehicle.
Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft may be noisy. To accommodate this, the aircraft may utilize onboard sensors, offboard sensing, network, and predictive temporal data for noise signature mitigation. By building a composite understanding of real data offboard the aircraft, the aircraft can make adjustments to the way it is flying and verify this against a predicted noise signature (via computational methods) to reduce environmental impact. This might be realized via a change in translative speed, propeller speed, or choices in propulsor usage (e.g., a quiet propulsor vs. a high thrust, noisier propulsor). These noise mitigation actions may also be decided at the network level rather than the vehicle level to balance concerns across a city and relieve computing constraints on the aircraft.
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
G01C 21/20 - Instruments pour effectuer des calculs de navigation
G01C 21/34 - Recherche d'itinéraireGuidage en matière d'itinéraire
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G06Q 10/047 - Optimisation des itinéraires ou des chemins, p. ex. problème du voyageur de commerce
G06Q 10/0631 - Planification, affectation, distribution ou ordonnancement de ressources d’entreprises ou d’organisations
76.
Vehicle cabin thermal management system and method
The system can include an on-board thermal management subsystem. The system 100 can optionally include an off-board (extravehicular) infrastructure subsystem. The on-board thermal management subsystem can include: a battery pack, one or more fluid loops, and an air manifold. The system 100 can additionally or alternatively include any other suitable components.
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé l'air étant réchauffé ou refroidi
B60L 1/00 - Fourniture de l'énergie électrique à l'équipement auxiliaire des véhicules à traction électrique
B60L 1/08 - Méthodes ou dispositifs pour commande et régulation
B60L 3/00 - Dispositifs électriques de sécurité sur véhicules propulsés électriquementContrôle des paramètres de fonctionnement, p. ex. de la vitesse, de la décélération ou de la consommation d’énergie
B60L 58/26 - 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 pour la commande de la température des batteries par refroidissement
B60L 58/27 - 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 pour la commande de la température des batteries par chauffage
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
H01M 10/48 - Accumulateurs combinés à des dispositions pour mesurer, tester ou indiquer l'état des éléments, p. ex. le niveau ou la densité de l'électrolyte
H01M 10/613 - Refroidissement ou maintien du froid
H01M 10/617 - Types de commande de la température pour réaliser l'uniformité ou une répartition désirée de la température
H01M 10/637 - Systèmes de commande caractérisés par l’emploi de dispositifs sensibles à la température, p. ex. dispositifs NTC, PTC ou bimétalSystèmes de commande caractérisés par la commande du courant interne circulant à travers la batterie, p. ex. par commutation
H01M 10/6555 - Barres ou plaques disposées entre les éléments
H01M 10/658 - Moyens de commande de la température associés de façon structurelle avec les éléments par isolation ou protection thermique
H01M 10/663 - Relations d'échange de chaleur entre les éléments et d'autres systèmes, p. ex. chauffage central ou piles à combustibles le système étant un climatiseur ou un moteur
H01M 50/249 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports spécialement adaptés aux aéronefs ou aux véhicules, p. ex. aux automobiles ou aux trains
Systems and methods for battery-based aircraft performance are provided. An example computer-implemented method includes accessing, by a computing system, flight plan data for a first flight. Based on the flight plan data, the computing system can compute a first expected power demand on the aircraft's battery system for the first flight. The computing system can access initial battery state data of the aircraft. The computing system can compute, using a battery model, a first capability output based the first expected power demand and the initial battery state. The first capability output can be indicative of a range/ToF of the aircraft for the first flight. The computing system can determine an ability of the aircraft to perform the first flight based on the first capability output and generate an itinerary accordingly. The computing system can transmit, over a network, instructions associated with implementing the itinerary for performance by the aircraft.
Example aspects of the present disclosure relate to battery-based flight planning for electric vehicles. The example method includes accessing a performance reserve requirement associated with aerial operations within an airspace and battery conditions for one or more batteries onboard an electric aircraft. The method includes computing a reserve state of charge for the electric aircraft to complete a future flight within the airspace based on the performance reserve requirements and the battery conditions. The method includes computing one or more battery charging parameters for the electric aircraft to complete the future flight based on the reserve state of charge. The method includes confirming an electric aircraft's ability to perform the future flight, adjusting a preflight activity, or adjusting the future flight based on the battery charging parameters.
Systems and methods for battery-based aircraft performance are provided. An example computer-implemented method includes accessing, by a computing system, flight plan data for a first flight. Based on the flight plan data, the computing system can compute a first expected power demand on the aircraft's battery system for the first flight. The computing system can access initial battery state data of the aircraft. The computing system can compute, using a battery model, a first capability output based the first expected power demand and the initial battery state. The first capability output can be indicative of a range/ToF of the aircraft for the first flight. The computing system can determine an ability of the aircraft to perform the first flight based on the first capability output and generate an itinerary accordingly. The computing system can transmit, over a network, instructions associated with implementing the itinerary for performance by the aircraft.
Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft can be sensitive to uneven weight distributions, e.g., the payload of an aircraft is primarily loaded in the front, back, left, or right. When the aircraft is loaded unevenly, the center of mass of the aircraft may shift substantially enough to negatively impact performance of the aircraft. Thus, in turn, there is an opportunity that the VTOL may be loaded unevenly if seating, luggage placement, and/or positions of internal components are not coordinated. Among other advantages, dynamically assigning the payloads and adjusting components of the VTOL aircraft can increase VTOL safety by ensuring the VTOL aircraft is loaded evenly and meets all weight requirements; can increase transportation efficiency by increasing rider throughput; and can increase the availability of the VTOL services to all potential riders.
A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.
A laminate material for an aircraft component is provided. The laminate material includes a first layer, a second layer and a rib disposed between the first and second layer. One or more connectors are configured to couple the ends of the rib to the first layer and the second layer. The connectors comprise a thermoplastic resin. Aircraft components are also provided.
B32B 3/30 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche continue dont le périmètre de la section droite a une allure particulièreProduits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche comportant des cavités ou des vides internes caractérisés par une couche comportant des retraits ou des saillies, p. ex. des gorges, des nervures
F16B 5/00 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles
F16B 11/00 - Assemblage d'éléments structuraux ou parties de machines par collage ou en les pressant l'un contre l'autre, p. ex. soudage sous pression à froid
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 3/26 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche continue dont le périmètre de la section droite a une allure particulièreProduits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche comportant des cavités ou des vides internes
B32B 7/05 - Liaison entre couches les couches n’étant pas liées sur toute la surface, p. ex. liaison discontinue ou par motifs particuliers
B29C 65/48 - Assemblage d'éléments préformésAppareils à cet effet en utilisant des adhésifs
A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.
B64C 11/48 - Ensembles de plusieurs hélices coaxiales
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
B64D 35/06 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission entraîne plusieurs hélices ou rotors les hélices ou rotors tournant en sens inverse
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
84.
MULTI-ELEMENT LIFTING SYSTEM WITH INTEGRATED PROPULSION AND AIRCRAFT USING SAME
A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 3/32 - Voilures spécialement adaptées pour le montage des groupes propulseurs
B64C 23/00 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
A solid motor coil with conductive pathways as part of a unitary construction. The conductive pathways are separated by resistive insulating layers. The conductive pathways may vary in their location within the cross-section of the motor coil, which may significantly reduce eddy current losses. The solid motor coil may result in a higher packing factor than previous designs. The solid motor coil may reduce the eddy current loss per conductor, with commensurate reduction in peak temperature rise. An electric motor with solid motor coils provides improved heat conduction and improved efficiency, allowing for a smaller motor package at higher power levels.
H02K 3/52 - Fixation des enroulements de pôles saillants ou de leurs connexions
B33Y 80/00 - Produits obtenus par fabrication additive
H02K 3/04 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p. ex. avec des conducteurs en barre
H02K 3/14 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p. ex. avec des conducteurs en barre disposés dans des encoches avec des conducteurs transposés, p. ex. des conducteurs torsadés
G01D 5/20 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p. ex. une armature mobile
86.
High efficiency hydrogen fueled high altitude thermodynamic fuel cell system and aircraft using same
A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.
H01M 8/04 - Dispositions auxiliaires, p. ex. pour la commande de la pression ou pour la circulation des fluides
B60L 58/33 - 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 piles à combustible pour la commande de la température des piles à combustible, p. ex. en commandant la charge électrique par refroidissement
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
H01M 8/04014 - Échange de chaleur par des fluides gazeuxÉchange de chaleur par combustion des réactifs
H01M 8/04029 - Échange de chaleur par des liquides
H01M 8/04119 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux avec apport simultané ou évacuation simultanée d’électrolyteHumidification ou déshumidification
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
A method for controlling an aircraft includes accessing input data indicative of at least airspeed of the aircraft and determining trim values based at least in part on the input data. The trim values includes an angle of attack trim value for the aircraft. The method also includes accessing data indicative of the trim values by a flight controller and controlling, using the flight controller, operation of the aircraft based at least in part on the trim values.
An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The deployment mechanisms deploy the rotor forward and up as they deploy from a forward flight configuration to a vertical thrust configuration.
A vertiport system dynamically updates configuration of a vertiport based on predicted usage of the vertiport during a given time frame. The vertiport system predicts vertiport usage using flight data and estimated passenger demands and determines a desired number of parking pads and a desired number of final approach and takeoff (FATO) pads for the vertiport during the time frame. Based on the desired number of parking pads and the desired number of FATO pads for the vertiport, the vertiport system determines an updated configuration of the vertiport. According to the updated configuration, the vertiport system updates the configuration of the vertiport for at least a portion of the time frame.
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
90.
Multi-modal transportation service planning and fulfillment
The present disclosure provides systems and methods for real-time planning and fulfillment of multi-modal transportation services in a multi-modal ride sharing network. In particular, aspects of the present disclosure are directed to a computing system that creates an end-to-end multi-modal itinerary responsive to a user request for transportation service between an origin and a destination. The multi-modal itinerary can include two or more transportation legs that include travel via two or more different transportation modalities such as, as examples, via a car and via an aircraft.
The aircraft can include: an airframe, a tilt mechanism, a payload housing, and can optionally include an impact attenuator, a set of ground support members (e.g., struts), a set of power sources, and a set of control elements. The airframe can include: a set of rotors and a set of support members. By utilizing a larger rotor blade area (and/or larger rotor disc area) and adjusting the blade pitch and RPM, the rotors can augment the lift generated by the aerodynamic profile of the aircraft in the forward flight mode in addition to providing forward thrust. Variants generating lift with the rotors can reduce or eliminate additional control surfaces (e.g., wing flaps, ailerons, ruddervators, elevators, rudder, etc.) on the aircraft since the thrust and motor torque is controllable (thereby indirectly controlling lift) at each rotor, thereby enabling pitch, yaw, and/or roll control during forward flight.
A method for determining airspeed of an aircraft that includes determining a rotor model relating a power coefficient of a propeller of the aircraft to an axial inflow velocity through the propeller as a function of a set of rotor operating parameters; determining the set of rotor operating parameters by sampling an electronic control signal associated with an electric motor actuating the propeller; computing the axial inflow velocity through the propeller based on the set of rotor operating parameters using the rotor model; and determining the airspeed based on the axial inflow velocity.
A method and system for modeling aerodynamic interactions in complex eVTOL configurations for realtime flight simulations and hardware testing which includes decomposing the aircraft into aerodynamic subcomponents, wherein the interactions between these components are handled by flow simulations of the surrounding fluid, which may be Euler flow CFD simulations. A computer generated simulation can be used to analyze the fluid flow and pressures, the forces delivered by an aircraft into the fluid and the forces onto the aircraft from the fluid, to determine the position and attitude of the aircraft, and other aspects. The system may be used as a flight simulator for pilot training in a realtime environment. The system may be used to support component testing using an interface to those components, such as flight electronics and actuators, to test the components in high fidelity simulations of actual flight demands on those components. The system may also be used to support design analysis in non-realtime to run numerous simulations on different designs and to provide comparative output.
G09B 9/24 - Simulateurs pour l'enseignement ou l'entraînement pour l'enseignement de la conduite des véhicules ou autres moyens de transport pour l'enseignement du pilotage des aéronefs, p. ex. bancs d'entraînement au pilotage sans visibilité comprenant l'affichage ou l'enregistrement de la trajectoire de vol simulée
G06F 30/28 - Optimisation, vérification ou simulation de l’objet conçu utilisant la dynamique des fluides, p. ex. les équations de Navier-Stokes ou la dynamique des fluides numérique [DFN]
Embodiments relate to dynamic stroking seats for vertical take-off and landing (VTOL) aircraft. Seat ballast tanks are attached to aircraft seats. The seats are sprung by a fixed or variable load energy absorption system. The weight of a user is determined and assigned to a corresponding seat of the user. Based on the weight of the user, the fluid level in the ballast tank is monitored and adjusted to achieve a target weight range.
F16F 7/08 - Amortisseurs de vibrationsAmortisseurs de chocs avec surfaces de friction à déplacement rectiligne l'une le long de l'autre
B60N 2/42 - Sièges spécialement adaptés aux véhiculesAgencement ou montage des sièges dans les véhicules à des fins particulières ou pour des véhicules particuliers le siège étant construit pour protéger son occupant des effets des forces d'accélération anormales, p. ex. sièges anticollision ou sièges de sécurité
F16F 7/112 - Amortisseurs de vibrationsAmortisseurs de chocs utilisant un effet d'inertie l'élément d'inertie étant monté de manière élastique sur des ressorts à fluide
B60N 2/00 - Sièges spécialement adaptés aux véhiculesAgencement ou montage des sièges dans les véhicules
B64D 11/06 - Aménagements ou adaptations des sièges
95.
Systems and Methods for Generating Flight Plans Used by a Ride Sharing Network
The present disclosure provides systems and methods for systems and methods for generating potential flight plans to be used by a ride sharing network, including dynamic and/or automated changes to flight plans that have been engaged with passengers based on real-time information. In particular, the systems and methods of the present disclosure can operate to generate a fleet-level set of potential flight plans which comply with one or more constraints for a fleet of aircraft. The potential flight plans can be exposed into and used by a ride sharing network to provide transportation to users.
A battery interconnection system incorporating a temperature control mechanism having a first battery cell and a second battery cell is provided. The first battery cell has an electrically positive tab and an electrically negative tab. The second battery cell has an electrically positive tab and a electrically negative tab. The electrically positive tab of the first battery cell couples with the electrically positive tab of the second battery cell. Moreover, the electrically negative tab of the first battery cell couples with the electrically negative tab of the second battery cell. The first battery cell includes a cathode electrically coupled with the electrically positive tab of the first battery cell and the second battery cell includes a cathode electrically coupled with the electrically positive tab of the second battery cell. The first battery cell also has an anode electrically coupled with the a electrically negative tab of the first battery cell and the second battery cell has an anode electrically coupled with the electrically negative tab of the second battery cell.
H01M 10/613 - Refroidissement ou maintien du froid
H01M 10/647 - Éléments prismatiques ou plans, p. ex. éléments de type poche
H01M 10/654 - Moyens de commande de la température associés de façon structurelle avec les éléments situés à l'intérieur du boîtier des éléments, p. ex. mandrins, électrodes ou électrolytes
H01M 50/112 - Monoblocs comprenant des compartiments multiples
H01M 50/124 - Boîtiers primairesFourreaux ou enveloppes caractérisés par le matériau ayant une structure en couches
H01M 50/186 - Éléments de scellement caractérisés par la position des éléments de scellement
H01M 50/211 - Bâtis, modules ou blocs de multiples batteries ou de multiples cellules caractérisés par leur forme adaptés aux cellules en forme de poche
A battery interconnection system incorporating a temperature control mechanism having a first battery cell and a second battery cell is provided. The first battery cell has an electrically positive tab and an electrically negative tab. The second battery cell has an electrically positive tab and a electrically negative tab. The electrically positive tab of the first battery cell couples with the electrically positive tab of the second battery cell. Moreover, the electrically negative tab of the first battery cell couples with the electrically negative tab of the second battery cell. The first battery cell includes a cathode electrically coupled with the electrically positive tab of the first battery cell and the second battery cell includes a cathode electrically coupled with the electrically positive tab of the second battery cell. The first battery cell also has an anode electrically coupled with the a electrically negative tab of the first battery cell and the second battery cell has an anode electrically coupled with the electrically negative tab of the second battery cell.
A method of determining the capability of a nonlinear aircraft power source includes accessing status values representing a current state of an energy storage system in an aircraft, accessing demand values related to expected power demands on the energy storage system, modeling an ongoing status of the energy storage system using the status values and the demand values to predict when one of the status values will reach a threshold value, and providing an output of a capability of the aircraft based on the status value reaching the threshold value.
A battery cell that includes a plurality of anodes and a plurality of cathodes is provided. The battery cell has a pouch laminate disposed over the plurality of anodes and the plurality of cathodes along with a temperature control mechanism centrally located within the pouch laminate. The temperature control mechanism is disposed between anodes of the plurality of anodes and cathodes of the plurality of cathodes such that the temperature control mechanism is centrally located within battery cell. The temperature control mechanism can regulate a temperature of the battery cell while also regulate an amount of pressure applied to the plurality of anodes and cathodes. The temperature control mechanism can include passageways through which heat transfer fluid can pass that be used to regulate the temperature and the pressure.
H01M 10/654 - Moyens de commande de la température associés de façon structurelle avec les éléments situés à l'intérieur du boîtier des éléments, p. ex. mandrins, électrodes ou électrolytes
H01M 10/647 - Éléments prismatiques ou plans, p. ex. éléments de type poche
H01M 10/0585 - Structure ou fabrication d'accumulateurs ayant uniquement des éléments de structure plats, c.-à-d. des électrodes positives plates, des électrodes négatives plates et des séparateurs plats
A vertical take-off and landing (VTOL) aircraft provides transportation to users of a network system. The network system may include multiple aircraft or other types of vehicles to provide multi-model transportation. An aircraft may include a fuselage, a truss coupled to the fuselage, and multiple distributed electric propellers coupled to the truss. The distributed electric propellers may be positioned on at least two different planes. The fuselage may include a cabin having one or more seats for the passengers arranged in a configuration that has a compact footprint, provides legroom, provides visibility to surroundings of the aircraft, or facilitates convenient ingress or egress of passengers. The aircraft may open a port cabin door and starboard cabin door for simultaneous ingress or egress of passengers.
