Embodiments provide a tunable damping unit coupled to a moveable element. An actuator configured to drive the moveable element provides a primary load path, while the tunable damping unit provides a secondary load path that slows uncontrolled motion of the moveable element in the event of failure of the primary load path. The tunable damping unit can be tuned to a lower damping mode during normal operation to reduce extra loads on the actuator. The tunable damping unit can be quickly tuned to a higher damping mode in case of actuator failure.
B64U 40/10 - Dispositions mécaniques embarquées pour régler les surfaces de commande ou les rotorsDispositions mécaniques embarquées pour régler en vol la configuration de base pour régler les surfaces de commande ou les rotors
F16F 15/02 - Suppression des vibrations dans les systèmes non rotatifs, p. ex. dans des systèmes alternatifsSuppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif
F16F 15/03 - Suppression des vibrations dans les systèmes non rotatifs, p. ex. dans des systèmes alternatifsSuppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens électromagnétiques
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 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64U 10/20 - Aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
2.
BATTERY PACK WITH VENTING AND LOAD-BEARING CAPABILITIES
A battery pack including an enclosure, a plurality of rows of battery modules, where each battery module may include a plurality of battery cells, and a venting system positioned between a first row of battery modules and a second row of battery modules. The venting system is fluidly coupled to the first row and may define a first vent volume from each battery module of the first row to exterior of the battery pack, the venting system is fluidly coupled to the second row and may define a second vent volume from each battery module of the second row of battery modules to exterior of the battery pack, the first vent volume is fluidly isolated from the second vent volume; the venting system is coupled to a surface of the enclosure, and the venting system provides support to, and increases a rigidity of, the battery pack.
A battery module assembly may include a module chassis. The module chassis may include a first end plate, a second end plate, and a plurality of panels arranged in parallel to one another. First ends of the plurality of panels may be connected to the first end plate. Second ends of the plurality of panels may be connected to the second end plate. The module chassis may be adapted to hold a plurality of battery cells between the first end plate, the second end plate, and the plurality of panels. The battery module assembly may include an electronic component (e.g., DC/DC converter) abutted against the module chassis. The module chassis may be adapted to dissipate heat generated by the electronic component through the plurality of battery cells.
A thermal runaway (TR) propagation mitigation system includes a plurality of battery modules, and an onboard recirculation system coupled to the plurality of battery modules. The onboard recirculation system includes a primary valve for transitioning the onboard recirculation system between a closed loop configuration and an open loop configuration, a cooling fluid container storing cooling fluid provided to the TR propagation mitigation system when the onboard recirculation system is in the closed loop configuration, and a pump for flowing the cooling fluid through the TR propagation mitigation system when the onboard recirculation system is in the closed loop configuration. A method of cooling a plurality of battery modules includes transitioning a primary valve between an open configuration and a closed configuration, distributing cooling fluid through a common fluid line to the plurality of battery modules in a battery pack when the primary valve is in the closed configuration.
H01M 10/613 - Refroidissement ou maintien du froid
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
A battery module may include a circuit board including an electrical measurement circuitry configured to measure electrical characteristics of a battery electrically coupled to the circuit board, a plurality of busbars electrically coupled to the circuit board, and a plurality of battery cells electrically coupled to the circuit board through the plurality of busbars. A first battery cell of the plurality of battery cells may include a first terminal electrically coupled to a first busbar of the plurality of busbars and a second terminal electrically coupled to a second busbar of the plurality of busbars.
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 50/507 - Interconnecteurs pour connecter les bornes des batteries adjacentesInterconnecteurs pour connecter les cellules en dehors d'un boîtier de batterie comprenant un arrangement de plusieurs barres omnibus réunies dans une structure de conteneur, p. ex. modules de barres omnibus
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
A module chassis assembly may be adapted to hold battery cells between a first end plate, a second end plate, and a plurality of panels. The first end plate may be formed to include a first plurality of channels adapted to allow fluid to pass therethrough. The second end plate may be formed to include a second plurality of channels adapted to allow fluid to pass therethrough. Each panel may be formed to include a plurality of channels adapted to allow fluid to pass therethrough. The plurality of panels may be arranged in parallel to one another. First ends of the plurality of panels may be connected to the first end plate, and second ends of the plurality of panels may be connected to the second end plate so that the plurality of channels are fluidically connected to the first plurality of channels and the second plurality of channels.
Systems and methods of the present disclosure provide a service loop for a pouch cell tab by bending the service loop into the cord length at the cell-level. Embodiments of the present disclosure reduces the risk of cell damage or open circuit welds. Both failure modes have the potential to open circuit a battery mid-operation or trigger a thermal runaway. According to various embodiments, the service loop is integral to the pouch such that no additional parts are used to form the pouch cell.
H01M 50/503 - Interconnecteurs pour connecter les bornes des batteries adjacentesInterconnecteurs pour connecter les cellules en dehors d'un boîtier de batterie caractérisées par la forme des interconnecteurs
H01M 50/533 - Connexions d’électrodes dans un boîtier de batterie caractérisées par la forme des conducteurs ou des languettes
H01M 50/00 - Détails de construction ou procédés de fabrication des parties non actives des cellules électrochimiques autres que les piles à combustible, p. ex. piles hybrides
8.
ONE-WAY PRESSURE RATED BURST DISK DEVICE FOR THERMAL RUNAWAY GAS VENTING
Embodiments described herein provide for thermal runaway gas venting. A device includes a one-way pressure-rated burst disk component. The one-way pressure-rated burst disk component includes a retaining ring having an internal structure, a seal, and a disk disposed between the retaining ring and the seal such that the internal structure of the retaining ring is adjacent a first surface of the disk. The retaining ring secures the disk against a panel. The internal structure of the retaining ring opposes a force applied at a second surface of the disk from an opposite side of the panel. A battery pack includes a plurality of battery modules and a venting structure between a first row of battery modules and a second row of battery modules. Each battery module includes a plurality of battery cells and a one-way pressure-rated burst disk device.
H01M 50/358 - Passages externes d’évacuation des gaz sur le couvercle ou sur le boîtier de batterie
H01M 50/367 - Passages internes d’évacuation des gaz dans le couvercle ou le boîtier de la batterieSystèmes d’évent à double couvercle
F16K 17/16 - Soupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage ouvrant sur excès de pression d'un côtéSoupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté avec élément de rupture l'élément étant un diaphragme de rupture
Several techniques are provided for improved air traffic control communications that reduce the cognitive burden on a supervisor and improve supervisor comprehension and performance. Broadcasted audio messages (which can include voice communications) can be automatically filtered based on a targeted aircraft, audio transmissions can be transcribed into text for presentation to a supervisor in an understandable visual format, and/or a set of multiple audio messages can be queued and time-shifted to prevent overlap.
Methods, systems, and non-transitory, machine-readable media may facilitate air/ground voice links for remotely supervised aircraft and air traffic control communications. A three-dimensional (3D) geometry of a radio frequency (RF) service volume may be determined. Position information indicating a current position for each aircraft of a plurality of aircraft may be received. Based on the 3D geometry of the RF service volume and the position information, a subset of the plurality of aircraft may be determined to be within the RF service volume. One aircraft may be selected as an airborne repeater within the RF service volume. Routing of voice communications between one or more ground supervisor terminals and an ATC system for the subset of aircraft may be consolidated. The consolidating may include deactivating any air/ground voice link associated with aircraft of the subset of aircraft other than the one aircraft selected as the airborne repeater.
Techniques for outputting landing area conditions to aircraft using standardized message protocols are provided. In an example method, a computing device accesses a configuration for generating messages using a predetermined message format for a first air traffic management device located at a first landing area. The computing device updates the configuration with information about a condition at the first landing area using the predetermined message format. The computing device outputs, using the first air traffic management device, a message based on the configuration, including transmitting the message to a second air traffic management device associated with an aircraft within a predetermined distance of the first landing area.
Embodiments provide a method for land hazard communication. The method includes transmitting a first message to a landing site computing system based at least in part on determining that a pilotless aircraft is within a threshold range of a landing site, the first message comprising a first passcode. The method can further include determining whether a second message comprising a second passcode is received from the landing site computing system in response to the first message, the second passcode corresponding to the first passcode. The method can further include determining a subset of maneuvers for landing condition from a set of maneuvers based at least in part on determining whether the second message comprising a second passcode is received from the landing site computing system. The method can further include causing the pilotless aircraft to perform the subset of maneuvers for the landing condition.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
G08G 5/54 - Aides à la navigation ou au guidage pour l’approche ou l’atterrissage
G08G 5/265 - Transmission d’informations relatives au trafic entre les aéronefs et les stations au sol pour la gestion des autorisations du contrôle du trafic aérien [ATC]
G08G 5/57 - Aides à la navigation ou au guidage pour les aéronefs sans pilote
Embodiments of the invention are directed to a linear actuator with a spherical joint. The spherical joint can provide a capacity for rotational adjustments between the linear actuator and an external structure to which the linear actuator is coupled by the spherical joint. The spherical joint can prevent external forces from entering the linear actuator and/or prevent misalignment between components of the linear actuator when external structures move or shift. The spherical joint can be configured so that it is parallel to a translating component of the linear actuator. For example, an axis of a hollow channel within the spherical joint can be parallel to and/or coincident with an axis of the translating component. The translating component may pass through the hollow channel of the spherical joint when actuated.
B64C 13/30 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des mécanismes à câbles, chaînes ou tiges
B64C 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
B64D 27/40 - Aménagements pour le montage de groupes moteurs sur aéronefs
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]
System, methods, and machine-readable media may facilitate control of an aircraft. An actuator may be controlled based on the following. A first control signal may be output, with a first command module, to control the actuator. The first command module may include a first electronic configuration. Commands generated by the first command module and/or system response signals may be monitored with a monitor module. The monitor module may include a third electronic configuration that is different from the first electronic configuration. A second control signal may be output, with a second command module, to control the actuator when the first command module is deactivated or malfunctioning. The second command module may include a second electronic configuration that is different from the first electronic configuration and the third electronic configuration. The actuator may be controlled using the second control signal when the first command module is deactivated or malfunctioning.
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
B64C 13/42 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide comportant des dispositifs de doublement de la commande ou de mise en position de secours
G05B 9/03 - Dispositions de sécurité électriques avec une boucle à canal multiple, c.-à-d. systèmes de commande redondants
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
A power distribution circuit for an electrically powered aircraft includes a plurality of batteries and a plurality of electric propulsion systems. A plurality of power distribution circuits each couple a battery of the plurality of batteries to two or more electric propulsion systems. The plurality of electric propulsion systems are positioned on the aircraft to apply balanced forces to the aircraft such that in the event of a failure, the aircraft remains stable and only experiences a loss in altitude or speed.
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]
B60L 50/60 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible utilisant de l'énergie fournie par des batteries
B64D 31/00 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs
16.
BATTERY CELL WITH THERMALLY CONDUCTIVE SIDE WALLS, BATTERY MODULE ASSEMBLY, AND TOOLING ASSEMBLY
Battery cells with a thermally conductive side wall, methods and tooling for forming the battery cells, and battery modules including the battery cells employ a thermally conductive adhesive to form the thermally conductive side wall. A battery cell includes an energy storing portion, a thermally conductive shell the encloses the energy storing portion, and a thermally conductive adhesive layer. The thermally conductive shell includes a base membrane and a cover membrane. The thermally conductive shell includes a perimeter portion including a perimeter portion of the cover membrane attached to a perimeter portion of the base membrane. A folded portion of the perimeter portion of the thermally conductive shell is bonded to a side surface of the thermally conductive shell via the thermally conductive adhesive to form a thermally conductive side wall of the battery cell.
H01M 10/653 - Moyens de commande de la température associés de façon structurelle avec les éléments caractérisés par des matériaux électriquement isolants ou thermiquement conducteurs
H01M 10/659 - Moyens de commande de la température associés de façon structurelle avec les éléments par stockage de la chaleur ou chaleur tampon, p. ex. capacité calorifique, changements ou transitions de phase liquide-solide
17.
DAMPING UNIT AS A SECONDARY LOAD PATH FOR A MOVABLE ELEMENT WITH ACTUATOR
Embodiments provide a damping unit coupled to a moveable element. An actuator configured to drive the moveable element provides a primary load path, while the damping unit provides a secondary load path that slows uncontrolled motion of the moveable element in the event of failure of the primary load path. To test the working condition of the damping unit, a load on the actuator can be measured when the actuator drives the moveable element. If the load is greater than a predetermined threshold, it can be determined that the damping unit is providing a damping force against the actuator, and therefore the damping unit is operational.
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 27/51 - Amortissement des mouvements des pales
B64U 40/10 - Dispositions mécaniques embarquées pour régler les surfaces de commande ou les rotorsDispositions mécaniques embarquées pour régler en vol la configuration de base pour régler les surfaces de commande ou les rotors
B64U 10/20 - Aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
18.
SYSTEM AND METHODS FOR IMPROVED SITUATIONAL AWARENESS IN AVIATION
Methods and systems for providing status of other aircraft in a vicinity of an operator controlled aircraft. A method of providing status of other aircraft in a vicinity of an operator controlled aircraft include displaying an operator controlled aircraft icon on a display to represent positioning of the operator controlled aircraft. Radio transmissions from the other aircraft are processed to generate corresponding text. The text is processed to determine at least one of an identifier of the other aircraft, a position of the other aircraft, or an intent of the other aircraft. An aircraft icon representing the other aircraft indicative of at least one of the position of the other aircraft, the identifier of the other aircraft, or the intent of the other aircraft is displayed on a display.
Embodiments provide techniques for illustrating and manipulating flight parameters communicated to an aircraft. More specifically, techniques disclosed herein provide a graphical user interface (GUI) that enables the adjustment of flight parameters via a translucent or transparent compass rose icon overlaid on a flight map, to intuitively select, transmit, and execute commands at an aircraft. For example, a controller may adjust one or more flight parameters, such as speed, heading, and/or altitude of an aircraft, such as an autonomous aircraft, by dragging an arrow icon around a compass rose icon displayed in connection with the aircraft on the GUI.
B64C 13/00 - Systèmes de commande ou systèmes de transmission pour actionner les gouvernes, les volets hypersustentateurs, les aérofreins ou les destructeurs de portance (spoilers)
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p. ex. pour l’aviationDispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p. ex. la distance, la vitesse ou l’accélération
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
G06F 3/01 - Dispositions d'entrée ou dispositions d'entrée et de sortie combinées pour l'interaction entre l'utilisateur et le calculateur
G06F 3/02 - Dispositions d'entrée utilisant des interrupteurs actionnés manuellement, p. ex. des claviers ou des cadrans
G06F 3/04847 - Techniques d’interaction pour la commande des valeurs des paramètres, p. ex. interaction avec des règles ou des cadrans
G01C 21/00 - NavigationInstruments de navigation non prévus dans les groupes
A power distribution control approach employs power distribution buses that are controllably energized and de-energized to control which aerial vehicle systems received power based on the applicable operational mode. A method of controlling power distribution in an electrically powered vertical takeoff and landing aircraft includes receiving an operational mode indication that identifies an operational mode. The operational mode is one of predetermined operational modes for the aircraft. Power distribution buses of the aircraft are controlled, based on the operational mode indication, to control each of the power distribution buses to be energized or de-energized.
H02J 9/00 - Circuits pour alimentation de puissance de secours ou de réserve, p. ex. pour éclairage de secours
H02J 9/04 - Circuits pour alimentation de puissance de secours ou de réserve, p. ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve
B64C 27/68 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales utilisant l'énergie électrique, p. ex. avec un amplificateur de puissance électrique
B60L 50/15 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant la puissance de propulsion fournie par des générateurs entraînés par le moteur, p. ex. des générateurs entraînés par des moteurs à combustion avec alimentation supplémentaire en énergie électrique
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
Embodiments provide mechanisms for coupling rotor blade pitch to propulsion system tilt angle in an aircraft, and more specifically in electric aircrafts. A system may include a tiltable propulsion system configured to move between a first tilt angle and a second tilt angle, wherein the tiltable propulsion system includes a plurality of rotor blades each configured to move between a first pitch position and a second pitch position; a tilting mechanism coupled to the tiltable propulsion system and configured to move the tiltable propulsion system between the first tilt angle and the second tilt angle; a pitching mechanism coupled to one or more of the plurality of rotor blades and configured to move one or more of the plurality of rotor blades between the first pitch position and the second pitch position; and an actuator configured to operate both the tilting mechanism and the pitching mechanism simultaneously.
Power distribution systems, battery packs, and batteries employ battery modules that are connected in series to generate a high-voltage output and in parallel to generate a low-voltage output. A battery includes battery modules and a direct current to direct current converter. The battery modules are electrically connected in series to generate a first battery high-voltage output. The battery modules are electrically connected in parallel to generate a battery modules low-voltage output. The direct current to direct current converter generates a battery low-voltage output from the battery modules low-voltage output.
Embodiments provide an animated graphical user interface for simultaneously monitoring multiple autonomous aircraft. More specifically, techniques disclosed herein provide a GUI that allows for one-to-many supervision where a remote supervisor (e.g., human or artificial intelligence) may continuously monitor and/or interact with a plurality of autonomous aircraft. For example, the autonomous aircraft may include one or more autonomous electric vertical takeoff landing (eVTOL) aircraft. Embodiments provide command input system and techniques that reduce human error by assigning an input mechanism and a command input menu to a unique flight parameter.
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
B64U 101/00 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques
24.
REMOTE SUPERVISION OF MULTIPLE AUTONOMOUS AIRCRAFT
Embodiments provide a flight supervision platform including a server computer and an animated graphical user interface for simultaneously monitoring multiple autonomous aircraft. More specifically, techniques disclosed herein provide a flight supervision platform that allows for one-to-many supervision where a remote supervisor (e.g., human or artificial intelligence) may continuously monitor and/or interact with a plurality of autonomous aircraft. For example, the autonomous aircraft may include one or more autonomous electric vertical takeoff landing (eVTOL) aircraft. The flight supervision platform may display information and receive input via the GUI and transmit commands based on the received input to the autonomous 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
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
G05G 9/047 - Mécanismes de commande manuelle équipés d'un seul organe de commande travaillant avec plusieurs organes commandés, p. ex. en sélection ou simultanément l'organe de commande étant manœuvré de différentes manières indépendantes, chacune de ces manœuvres individuelles entraînant un seul organe commandé dans lesquels la manœuvre de l'organe de commande peut être effectuée de plusieurs manières simultanément l'organe de commande étant manœuvré à la main autour d'axes orthogonaux, p. ex. manches à balai
Electric motors and related methods employ a stator assembly as part of a housing assembly that reacts output shaft loads to a mounting base. An electric motor includes an output shaft, a rotor coupled to the output shaft, a first housing, a first bearing assembly coupled to the first housing, a second housing, a second bearing assembly coupled to the second housing, and a stator assembly. The stator assembly includes a structural stator core member and stator coils. The structural stator core member extends circumferentially around the output shaft. The second housing is coupled to the first housing by the stator core.
F03D 3/04 - Mécanismes moteurs à vent avec axe de rotation sensiblement perpendiculaire au flux d'air pénétrant dans le rotor comportant des moyens fixes de guidage du vent, p. ex. par aubages ou canaux directeurs
H02K 1/22 - Parties tournantes du circuit magnétique
F03D 7/02 - Commande des mécanismes moteurs à vent les mécanismes moteurs à vent ayant l'axe de rotation sensiblement parallèle au flux d'air pénétrant dans le rotor
H02K 9/22 - Dispositions de refroidissement ou de ventilation par un matériau solide conducteur de la chaleur s'encastrant dans, ou mis en contact avec, le stator ou le rotor, p. ex. des ponts de chaleur
Embodiments provide a VTOL aircraft including a plurality of tilting propeller assemblies each coupled to a support structure and configured to transition between a vertical flight and a forward flight position. Each tilting propeller assembly comprising a propeller and a movable fairing provided downstream of the propeller. The movable fairing is configured to extend along an axis of rotation of the propeller. When the tilting propeller assembly transitions between the vertical and forward flight position, the movable fairing is configured to swivel to extend parallel to the direction of resultant airflow over the tilting propeller assembly into a minimum drag orientation. The movable fairing is damped enough to prevent any oscillations from the propeller wake shedding, and at the same time, keep the propeller aligned in a minimum-drag orientation with the resultant flow.
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 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
27.
COMPACT VERTIPORT WITH EFFICIENT SPACE UTILIZATION
Embodiments provide a compact vertiport system. The vertiport system may be efficient and compact by combining, into one space and time period, multiple activities that typically take place in different spaces and different times. For example, when an aircraft is being moved from a landing zone to a takeoff zone, the aircraft may also be charged simultaneously. Also, passenger exchange may take place while the aircraft is being moved. As a result, compact vertiport systems may fit into smaller spaces (e.g., tops of buildings, or smaller plots of land).
An electrically powered propulsion system for an aircraft includes batteries, electric propulsion assemblies, and power distribution circuits. Each battery is coupled with two or more of the electric propulsion assemblies via a respective one of the power distribution circuits. The electric propulsion assemblies are positioned on the aircraft and operable to apply balanced forces to the aircraft such that in the event of a failure, the aircraft is not subjected to large changes in roll, pitch, and/or yaw.
Disclosed is an electric aircraft, which includes a fuselage and at least one wing coupled to the fuselage. The electric aircraft includes a plurality of tilting fans coupled to the at least one wing, the plurality of tilting fans being configured to move between a vertical lift position and a forward flight position. The electric aircraft includes a plurality of tilting mechanisms coupled with at least one tilting fan. The electric aircraft includes a first actuator coupled to a first subset of the plurality of tilting mechanisms. The first subset of tilting mechanisms are identified among the plurality of tilting mechanisms according to a coupling scheme. The first actuator tilts a first group of tilting fans coupled to the first subset of the plurality of tilting mechanisms simultaneously.
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
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 27/22 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion
B64C 3/32 - Voilures spécialement adaptées pour le montage des groupes propulseurs
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 19/00 - Dispositifs de commande des aéronefs non prévus ailleurs
Embodiments provide battery cells and/or battery submodules including a phase change material (PCM) for absorbing excess heat that may be released within the battery cell and/or battery submodule. The PCM may be provided in form of a layer within the battery cell in addition to a thermal insulation layer. Alternatively, the PCM layer may replace the thermal insulation layer. The PCM may be provided on one or more sides of the battery submodule within a container that contains the battery submodule. The PCM may be a solid PCM provided in form of a layer and/or one or more strips. The PCM may also include a liquid PCM that is provided in the container containing the battery submodule.
H01M 10/659 - Moyens de commande de la température associés de façon structurelle avec les éléments par stockage de la chaleur ou chaleur tampon, p. ex. capacité calorifique, changements ou transitions de phase liquide-solide
H01M 10/613 - Refroidissement ou maintien du froid
H01M 10/6569 - Fluides qui subissent un changement ou une transition de phase liquide-gaz, p. ex. évaporation ou condensation
H01M 10/6552 - Tubes fermés transférant la chaleur par conductivité thermique ou par transition de phase, p. ex. tubes caloporteurs
Embodiments provide an electric aircraft with a plurality of lift fan assemblies that are configured to provide vertical lift, and one or more pusher propellers that are configured to provide forward thrust. The lift fan assemblies may be coupled to the wings of the aircraft via one or more support structures, and the wings may be coupled to an upper region of the fuselage. The pusher propeller(s) may be coupled to a tailing end of the fuselage. The lift fan assemblies and the pusher propeller(s) may provide thrust and movement in directions that are orthogonal to one another. A control system coupled to the aircraft may control the lift fan assemblies and the one or more pusher propellers to activate, increase in power, and decrease in power. The lift fan assemblies and the one or more pusher propellers may be operated separately, and may be active at different times.
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 5/08 - Surfaces stabilisatrices montées sur ou supportées par les ailes
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 27/28 - 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
Battery management systems and methods can provide real-time automated monitoring of various aspects of battery health and operation. Some battery management systems can use an equivalent cell circuit model to predict a range for the expected behavior of a battery cell under actual operating conditions in real-time. The prediction can be compared to the actual behavior of the cell to determine whether an anomaly exists. Some battery management systems can maintain an estimate of battery state-of-health parameters such as charge capacity and internal resistance and can update these estimates in real time while the battery is being discharged and/or charged. Anomalous variations in a monitored parameter can trigger a real-time fault notification.
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
H02J 7/02 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries pour la charge des batteries par réseaux à courant alternatif au moyen de convertisseurs
H02J 7/04 - Régulation du courant ou de la tension de charge
H02J 5/00 - Circuits pour le transfert d'énergie électrique entre réseaux à courant alternatif et réseaux à courant continu
H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
33.
POWER DISTRIBUTION CIRCUITS FOR VEHICLES WITH ENERGY REGENERATION
An electrically powered vehicle comprises a DC bus and a plurality of batteries, each coupled in parallel to the DC bus. At least one switch is coupled in series between at least one battery of the plurality of batteries and the DC bus and a plurality of inverter circuits are each coupled in parallel to the DC bus. A plurality of motors are each coupled to a respective inverter circuit of the plurality of inverter circuits. In various embodiments the electrically powered vehicle further comprises a plurality of switches, each switch coupled in series between a respective battery of the plurality of batteries.
B60K 6/48 - Agencement ou montage de plusieurs moteurs primaires différents pour une propulsion réciproque ou commune, p. ex. systèmes de propulsion hybrides comportant des moteurs électriques et des moteurs à combustion interne les moteurs primaires étant constitués de moteurs électriques et de moteurs à combustion interne, p. ex. des VEH caractérisés par l'architecture du véhicule électrique hybride du type parallèle
B60K 6/20 - Agencement ou montage de plusieurs moteurs primaires différents pour une propulsion réciproque ou commune, p. ex. systèmes de propulsion hybrides comportant des moteurs électriques et des moteurs à combustion interne les moteurs primaires étant constitués de moteurs électriques et de moteurs à combustion interne, p. ex. des VEH
B60K 6/22 - Agencement ou montage de plusieurs moteurs primaires différents pour une propulsion réciproque ou commune, p. ex. systèmes de propulsion hybrides comportant des moteurs électriques et des moteurs à combustion interne les moteurs primaires étant constitués de moteurs électriques et de moteurs à combustion interne, p. ex. des VEH caractérisés par des appareils, des organes ou des moyens spécialement adaptés aux VEH
B60K 6/28 - Agencement ou montage de plusieurs moteurs primaires différents pour une propulsion réciproque ou commune, p. ex. systèmes de propulsion hybrides comportant des moteurs électriques et des moteurs à combustion interne les moteurs primaires étant constitués de moteurs électriques et de moteurs à combustion interne, p. ex. des VEH caractérisés par des appareils, des organes ou des moyens spécialement adaptés aux VEH caractérisés par les moyens d'accumulation d'énergie électrique, p. ex. les batteries ou les condensateurs
B60K 6/42 - Agencement ou montage de plusieurs moteurs primaires différents pour une propulsion réciproque ou commune, p. ex. systèmes de propulsion hybrides comportant des moteurs électriques et des moteurs à combustion interne les moteurs primaires étant constitués de moteurs électriques et de moteurs à combustion interne, p. ex. des VEH caractérisés par l'architecture du véhicule électrique hybride
Embodiments provide an aircraft with one or more tilting fan assemblies that are configured to tilt between a forward flight position and a vertical lift position. The aircraft may also include a plurality of lift fan assemblies for vertical movement. The tilting fan assemblies may be coupled to the fuselage or wings of the aircraft via one or more tilting mechanisms. A control system coupled to the aircraft may control the one or more tilting mechanisms to move the tilting fan assemblies between the forward flight position and the vertical lift position. The tilting fan assemblies may be coupled to one or more support structures that are coupled the fuselage or wings of the aircraft.
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 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 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
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
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
brevets
