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.
A module for containment of thermal runaway is disclosed. The module includes a plurality of stacked cells connected via cell interconnects and an enclosure formed from titanium configured to receive the plurality of stacked cells. The module further includes a plurality of channels formed from aluminum and configured to circulate a liquid to provide cooling to the plurality of stacked cells. The plurality of channels are located between the plurality of stacked cells and an interior surface of the enclosure. The module further includes a first adhesive located between a first side of the plurality of channels and the interior surface of the enclosure, the first adhesive configured to secure the interior surface of the enclosure to a surface of the plurality of channels, and thermal interface material located between the plurality of channels and the plurality of stacked cells.
H01M 10/651 - Means for temperature control structurally associated with the cells characterised by parameters specified by a numeric value or mathematical formula, e.g. ratios, sizes or concentrations
H01M 10/653 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
H01M 10/6557 - Solid parts with flow channel passages or pipes for heat exchange arranged between the cells
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.
F16F 15/02 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system
4.
MODULE ENCLOSURE FOR THERMAL RUNAWAY CONTAINMENT WITH MINIMAL MASS AND MANUFACTURING EASE
A module for containment of thermal runaway is disclosed. The module includes a plurality of stacked cells connected via cell interconnects and an enclosure formed from titanium configured to receive the plurality of stacked cells. The module further includes a plurality of channels formed from aluminum and configured to circulate a liquid to provide cooling to the plurality of stacked cells. The plurality of channels are located between the plurality of stacked cells and an interior surface of the enclosure. The module further includes a first adhesive located between a first side of the plurality of channels and the interior surface of the enclosure, the first adhesive configured to secure the interior surface of the enclosure to a surface of the plurality of channels, and thermal interface material located between the plurality of channels and the plurality of stacked cells.
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.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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 - On-board mechanical arrangements for adjusting control surfaces or rotorsOn-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
F16F 15/02 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system
F16F 15/03 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system using electromagnetic means
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B64U 10/20 - Vertical take-off and landing [VTOL] aircraft
9.
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.
B60L 58/26 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries for controlling the temperature of batteries by cooling
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 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H01M 50/507 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing comprising an arrangement of two or more busbars within a container structure, e.g. busbar modules
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from 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.
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.
H01M 50/233 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by physical properties of casings or racks, e.g. dimensions
H01M 50/358 - External gas exhaust passages located on the battery cover or case
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.
H01M 50/242 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by physical properties of casings or racks, e.g. dimensions adapted for protecting batteries against vibrations, collision impact or swelling
16.
HEATSINK FOR THERMAL MANAGEMENT OF BATTERY MODULE ELECTRONICS
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.
H01M 10/667 - Heat-exchange relationships between the cells and other systems, e.g. central heating systems or fuel cells the system being an electronic component, e.g. a CPU, an inverter or a capacitor
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 10/653 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
H01M 10/6556 - Solid parts with flow channel passages or pipes for heat exchange
H01M 50/258 - Modular batteriesCasings provided with means for assembling
H01M 50/287 - Fixing of circuit boards to lids or covers
17.
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.
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.
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 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H01M 50/204 - Racks, modules or packs for multiple batteries or multiple cells
H01M 50/507 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing comprising an arrangement of two or more busbars within a container structure, e.g. busbar modules
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 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing characterised by the shape of the interconnectors
H01M 50/533 - Electrode connections inside a battery casing characterised by the shape of the leads or tabs
H01M 50/00 - Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
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 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing characterised by the shape of the interconnectors
H01M 50/211 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for pouch cells
H01M 50/242 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by physical properties of casings or racks, e.g. dimensions adapted for protecting batteries against vibrations, collision impact or swelling
H01M 50/516 - Methods for interconnecting adjacent batteries or cells by welding, soldering or brazing
22.
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 - External gas exhaust passages located on the battery cover or case
H01M 50/367 - Internal gas exhaust passages forming part of the battery cover or caseDouble cover vent systems
F16K 17/16 - Safety valvesEqualising valves opening on surplus pressure on one sideSafety valvesEqualising valves closing on insufficient pressure on one side with fracturing member with fracturing diaphragm
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.
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.
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.
H02K 21/14 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures
Embodiments provide scissoring mechanisms for a vertical lift fan of an electric aircraft (e.g., a vertical take-off-landing eVTOL aircraft) where the blades of the vertical lift fan can be opened at almost zero speed. Exemplary scissoring mechanisms have position locking features that keep the collapsed blades in the low drag orientation once closed (e.g., in the stowed position). As a result, the scissoring mechanisms do not cause large impulses during opening and closing that cause large stresses and noise. In addition, the scissoring mechanisms provide an opportunity to check that the fans are opened properly prior to spinning them to the full operating speed. The scissoring mechanisms may not require an extra actuator, and rely on the propulsion motor.
A multicopter with angled rotors includes a fuselage and a plurality of rotors. At least some of the rotors are disposed on opposite sides of the fuselage and each is oriented at a corresponding angle to a substantially horizontal plane of the aircraft, the angle being of a magnitude such that a plane of rotation of the rotor does not intersect at least a critical portion of the fuselage.
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.
A power distribution circuit for an electrically powered aircraft includes a plurality of batteries and a plurality of electric propulsion systems. A plurality of isolated 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 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B64D 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
H02P 4/00 - Arrangements specially adapted for regulating or controlling the speed or torque of electric motors that can be connected to two or more different electric power supplies
30.
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.
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
B60L 58/00 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
B60L 58/18 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries of two or more battery modules
B60W 10/26 - Conjoint control of vehicle sub-units of different type or different function including control of energy storage means for electrical energy, e.g. batteries or capacitors
B64D 31/16 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants
B64D 35/026 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants the electric power plant being integral with the propeller or rotor
B64U 50/19 - Propulsion using electrically powered motors
H02K 19/10 - Synchronous motors for multi-phase current
H02M 7/42 - Conversion of DC power input into AC power output without possibility of reversal
H02P 27/06 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using DC to AC converters or inverters
31.
INDEPENDENT SLIDING MODE OBSERVERS FOR FAULT TOLERANT OPERATION OF MULTI-PHASE MACHINES
Embodiments provide a method for propulsion system control. The method includes receiving a first set of electrical parameters associated with a first set of windings of a plurality of windings of the three-phase motor, the first set of electrical parameters separated from a second set of electrical parameters associated with a second set of windings by a phase shift. The method further include determining a first set of control parameters for controlling a first amount of power delivered to the first set of windings. The method further includes determining an angle of a rotor. The method further includes adding the phase shift to the first set of electrical parameters to generate an updated first set of electrical parameters. The method further includes determining a second set of control parameters for controlling a second amount of power delivered to the second set of windings.
H02P 6/18 - Circuit arrangements for detecting position without separate position detecting elements
B60L 50/40 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by capacitors
B60L 50/51 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells characterised by AC-motors
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
H02P 27/08 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using DC to AC converters or inverters with pulse width modulation
32.
DISTRIBUTED LOW VOLTAGE POWER GENERATION ARCHITECTURE FOR BATTERY ELECTRIFIED AIRCRAFT
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.
A rotor system design can reduce blade-wake interaction by staggering the vertical mounting position of the rotor blades on a hub. By staggering the vertical position, as the hub turns, the turbulent air impingement on subsequent rotor blades can be reduced. By reducing the turbulence on subsequent rotor blades the drag and noise is reduced. In rotor systems with an even number of blades, opposing rotor blade pairs can be mounted at the same vertical distance which can be different from other opposing rotor blade pairs. In rotor systems with an odd number of rotor blades, the rotor blades can be mounted at a fixed or variable vertical distances from the preceding blade so each rotor blade travels in a different tip path plane. Other techniques for reducing the wake vortices impingement can include mounting opposing blades at a dihedral/anhedral angle with respect to subsequent rotor blades.
Embodiments provide a landing and approach navigation system. The navigation system can use a radar system onboard an aircraft to transmit radio energy. A rotating reflector at a landing area can reflect the radio energy back to the radar system with an amplitude-modulation that is due to the rotation. With synchronized timing between the reflector and the radar system, and known rotation characteristics of the reflector, the radar system can use the reflected radio energy to calculate the bearing of the aircraft relative to the reflector and landing area.
G01S 13/87 - Combinations of radar systems, e.g. primary radar and secondary radar
G01S 13/91 - Radar or analogous systems, specially adapted for specific applications for traffic control
H01Q 3/08 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying two co-ordinates of the orientation
35.
VTOL Aircraft Fan Tilting Mechanisms and Arrangements
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 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B64D 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
H02P 4/00 - Arrangements specially adapted for regulating or controlling the speed or torque of electric motors that can be connected to two or more different electric power supplies
36.
POWER DISTRIBUTION CIRCUITS FOR ELECTRICALLY POWERED AIRCRAFT
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.
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B64D 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
An electrically powered vehicle may include 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 may each be coupled in parallel to the DC bus. A plurality of motors may each be coupled to a respective inverter circuit of the plurality of inverter circuits. In various embodiments, the electrically powered vehicle may further include a plurality of switches, each switch coupled in series between a respective battery of the plurality of batteries.
B60L 58/19 - Switching between serial connection and parallel connection of battery modules
B60W 10/26 - Conjoint control of vehicle sub-units of different type or different function including control of energy storage means for electrical energy, e.g. batteries or capacitors
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
B64D 31/16 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64U 50/19 - Propulsion using electrically powered motors
G01R 19/165 - Indicating that current or voltage is either above or below a predetermined value or within or outside a predetermined range of values
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H02J 1/12 - Parallel operation of dc generators with converters, e.g. with mercury-arc rectifier
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H02M 3/04 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters
H02P 27/06 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using DC to AC converters or inverters
Embodiments of the invention are directed to systems and methods for reducing drag on an aircraft. The aircraft can include at least one propulsion system with rotor blades configured to reduce aerodynamic drag when the propulsion system is deactivated. To reduce the amount of drag, the rotor blades can be locked into an aerodynamic position, and prevented from passively spinning. Additionally, the rotor blades can be configured to have angular positions that reduce drag. For example, the rotor blades as a group may be configured to generally point toward and/or away from an airflow current.
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.
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.
G06F 3/04817 - Interaction techniques based on graphical user interfaces [GUI] based on specific properties of the displayed interaction object or a metaphor-based environment, e.g. interaction with desktop elements like windows or icons, or assisted by a cursor's changing behaviour or appearance using icons
G06F 3/0484 - Interaction techniques based on graphical user interfaces [GUI] for the control of specific functions or operations, e.g. selecting or manipulating an object, an image or a displayed text element, setting a parameter value or selecting a range
Embodiments of the invention are directed to improving efficiency on an aircraft. The aircraft can include at least one propulsion system with one or more strakes attached to a spinner and positioned adjacent to the root portion of one or more corresponding rotor blades. The strakes can be configured to align with the rotor blades when the rotor blades are set to a cruising pitch position.
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.
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.
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.
Embodiments of the invention are directed to methods and systems for providing electric power with individualized charging parameters to each battery in a multi-battery system. Electric power from the single power source can be distributed in a controlled and unequal manner. Custom charging parameters can be designed for each battery. The custom charging parameters can be determined based on battery metrics gathered for that battery, and can be designed to optimize for a number of suitable priorities, such as recharging speed and battery health. As a result, each battery can be recharged according to individual needs.
B60L 58/18 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries of two or more battery modules
B60L 53/22 - Constructional details or arrangements of charging converters specially adapted for charging electric vehicles
B60L 53/62 - Monitoring or controlling charging stations in response to charging parameters, e.g. current, voltage or electrical charge
B60L 58/12 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to state of charge [SoC]
G01R 31/396 - Acquisition or processing of data for testing or for monitoring individual cells or groups of cells within a battery
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
47.
LAND HAZARD COMMUNICATION BETWEEN A LANDING SITE AND A PILOTLESS AIRCRAFT
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.
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.
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.
B60L 58/10 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
B60L 58/18 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries of two or more battery modules
B60L 58/22 - Balancing the charge of battery modules
For each cell in a plurality of cells from a same manufacturing run, a first and a second cell characteristic are received in order to obtain a plurality of cell characteristics. For each cell, a batch compatibility number that is associated with a number of compatible cells that that cell is compatible with is determined based at least in part on the plurality of cell characteristics. The plurality of cells is sorted according to the batch compatibility numbers to obtain a sorted list of cells. A plurality of compatible cells to include in a battery is selected from the plurality of cells, including by evaluating the plurality of cells according to the order of the sorted list of cells and beginning with the lowest batch compatibility number.
G01R 31/367 - Software therefor, e.g. for battery testing using modelling or look-up tables
G01R 31/396 - Acquisition or processing of data for testing or for monitoring individual cells or groups of cells within a battery
G06F 7/08 - Sorting, i.e. grouping record carriers in numerical or other ordered sequence according to the classification of at least some of the information they carry
H01M 6/50 - Methods or arrangements for servicing or maintenance, e.g. for maintaining operating temperature
H01M 10/04 - Construction or manufacture in general
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
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 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
B64C 27/52 - Tilting of rotor bodily relative to fuselage
B64D 27/40 - Arrangements for mounting power plants in aircraft
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 27/20 - Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
F16C 11/06 - Ball-jointsOther joints having more than one degree of angular freedom, i.e. universal joints
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 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
B64C 27/52 - Tilting of rotor bodily relative to fuselage
B64D 27/40 - Arrangements for mounting power plants in aircraft
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
Electrically powered vehicles with redundant power distribution circuits employ inverters and a multi-phase alternating current (AC) motor. An electrically powered vehicle includes batteries, inverters, interphase transformers, and a three-phase AC motor. Each of the inverters generates a three-phase AC input from power supplied by an associated one of the batteries. The interphase transformers generate drive phases for the AC motor from the three-phase AC inputs generated by the inverters.
B60L 58/19 - Switching between serial connection and parallel connection of battery modules
B60W 10/26 - Conjoint control of vehicle sub-units of different type or different function including control of energy storage means for electrical energy, e.g. batteries or capacitors
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
B64U 50/19 - Propulsion using electrically powered motors
G01R 19/165 - Indicating that current or voltage is either above or below a predetermined value or within or outside a predetermined range of values
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H02J 1/12 - Parallel operation of dc generators with converters, e.g. with mercury-arc rectifier
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H02M 3/04 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters
H02P 27/06 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using DC to AC converters or inverters
Embodiments provide a propeller ground stop mechanism configured to keep an unpowered propeller of an aircraft (e.g. when the aircraft is on the ground and not operating) static. The propeller is prevented from rotating due to external forces (e.g. an air flow caused by wind, manual rotation of the propeller). When the propeller is powered, and the propeller is providing thrust, the propeller ground stop mechanism automatically disengages and does not provide any drag. Among various benefits, the propeller ground stop mechanism provides added safety to the ground support personnel.
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.
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.
A system is disclosed to detect failure of a diode that is connected in series with a battery and a contactor or other switch configured to connect the battery to a load when the contactor or other switch is in a closed position and to isolate the battery from the load when the contactor or other switch is in an open position. In various embodiments, the system includes a high value resistor connected between the anode terminal of the diode and ground, the connection to the anode terminal being on a load side of the contactor or other switch; and a voltage meter configured to measure a voltage across the high value resistor at least during a test in which a voltage is applied to a bus associated with the load while the contactor or other switch is in the open position.
The embodiments describe a system and the corresponding assembly techniques of a battery submodule top cover. The battery submodule top cover has at least one electrical hybrid interconnect coupled to a substrate. The hybrid interconnect comprises at least a first portion made of a first metal type, and a second portion made of a second metal type. The first portion and the second portion of the hybrid interconnect are joined together such that an electrical connection may be made between two battery cell tabs where each battery cell tab is made of a different type of metal.
H01M 50/509 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing characterised by the type of connection, e.g. mixed connections
C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
C22F 1/04 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
C22F 1/08 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of copper or alloys based thereon
H01M 50/271 - Lids or covers for the racks or secondary casings
H01M 50/287 - Fixing of circuit boards to lids or covers
H01M 50/507 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing comprising an arrangement of two or more busbars within a container structure, e.g. busbar modules
H01M 50/514 - Methods for interconnecting adjacent batteries or cells
H01M 50/516 - Methods for interconnecting adjacent batteries or cells by welding, soldering or brazing
H01M 50/519 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing comprising printed circuit boards [PCB]
H01M 50/528 - Fixed electrical connections, i.e. not intended for disconnection
H01M 50/534 - Electrode connections inside a battery casing characterised by the material of the leads or tabs
H01M 50/55 - Terminals characterised by the disposition of the terminals on the cells on the same side of the cell
H01R 4/62 - Connections between conductors of different materialsConnections between or with aluminium or steel-core aluminium conductors
65.
ROTATABLE SURFACE FOR HEADWIND ALIGNMENT AND VERTIPORT ALIGNMENT
Embodiments provide a vertiport system with rotatable surfaces. The rotatable surfaces can be configured to rotate after an aircraft arrives at the rotatable surface. As a result, the aircraft can be allowed to land with a first orientation facing into a headwind, and then be rotated to have a second orientation that is better suited for reset processes at the vertiport, such as passenger exchange. When ready for a subsequent flight, the rotatable surface can rotate again so that the aircraft faces into the wind again for takeoff.
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.
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.
A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotor assemblies, tandem wings, and forward thrust propellers. The vertical lift rotor assemblies, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotor assemblies and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotor assemblies provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
73.
POWER DISTRIBUTION CIRCUITS FOR ELECTRICALLY POWERED AIRCRAFT
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 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
74.
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).
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).
H01M 10/647 - Prismatic or flat cells, e.g. pouch cells
H01M 10/653 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
H01M 10/659 - Means for temperature control structurally associated with the cells by heat storage or buffering, e.g. heat capacity or liquid-solid phase changes or transition
77.
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 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
H01M 10/04 - Construction or manufacture in general
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 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
H01M 10/659 - Means for temperature control structurally associated with the cells by heat storage or buffering, e.g. heat capacity or liquid-solid phase changes or transition
79.
Systems and methods for isolation resistance monitoring in a battery bank
Systems and methods for monitoring isolation resistance of individual batteries in a battery bank enable measurement of isolation resistance to be performed for different batteries at different times, thereby preventing the measurements from interfering with each other. In some embodiments, each battery in a battery bank has a battery monitoring system controller, and each battery monitoring system controller operates independently of the other battery monitoring system controllers in the battery bank. Each battery monitoring system controller can perform measurements of isolation resistance at regular intervals. Each battery monitoring system controller determines a start time for its measurements in a manner such that no two controllers perform isolation resistance measurements at the same time.
G01R 31/52 - Testing for short-circuits, leakage current or ground faults
G01R 27/02 - Measuring real or complex resistance, reactance, impedance, or other two-pole characteristics derived therefrom, e.g. time constant
G01R 31/36 - Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
G01R 31/3835 - Arrangements for monitoring battery or accumulator variables, e.g. SoC involving only voltage measurements
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
80.
BATTERY WITH COMPRESSION AND PREVENTION OF THERMAL RUNAWAY PROPAGATION FEATURES
A battery includes a metal can having a bottom, a top opening, and four sides. The battery also includes a plurality of cells stacked inside the metal can, wherein at least two opposing sides of the four sides of the metal can are biased inward against the plurality of cells to provide compression.
H01M 50/24 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by physical properties of casings or racks, e.g. dimensions adapted for protecting batteries from their environment, e.g. from corrosion
H01M 50/271 - Lids or covers for the racks or secondary casings
H01M 50/284 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders with incorporated circuit boards, e.g. printed circuit boards [PCB]
H01M 50/296 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by terminals of battery packs
H01M 50/375 - Vent means sensitive to or responsive to temperature
H01M 50/502 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing
Embodiments provide a propeller ground stop mechanism configured to keep an unpowered propeller of an aircraft (e.g. when the aircraft is on the ground and not operating) static. The propeller is prevented from rotating due to external forces (e.g. an air flow caused by wind, manual rotation of the propeller). When the propeller is powered, and the propeller is providing thrust, the propeller ground stop mechanism automatically disengages and does not provide any drag. Among various benefits, the propeller ground stop mechanism provides added safety to the ground support personnel.
B64U 40/10 - On-board mechanical arrangements for adjusting control surfaces or rotorsOn-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
83.
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.
F16F 15/02 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system
84.
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.
B64U 40/10 - On-board mechanical arrangements for adjusting control surfaces or rotorsOn-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
B64U 10/20 - Vertical take-off and landing [VTOL] aircraft
Techniques to control flight of an aircraft are disclosed. In various embodiments, a set of inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is determined.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
G05D 1/46 - Control of position or course in three dimensions
Embodiments of the invention are directed to systems and methods for reducing drag on an aircraft. The aircraft can include at least one propulsion system with rotor blades configured to reduce aerodynamic drag when the propulsion system is deactivated. To reduce the amount of drag, the rotor blades can be locked into an aerodynamic position, and prevented from passively spinning. Additionally, the rotor blades can be configured to have angular positions that reduce drag. For example, the rotor blades as a group may be configured to generally point toward and/or away from an airflow current.
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.
A battery system includes a battery cell, a thermally insulating layer, and a thermally conducting layer which includes a fin. The fin pushes against an interior surface of a case which surrounds the battery cell, the thermally insulating layer, and the thermally conducting layer. The thermally conducting layer includes a discontinuity where the discontinuity is configured to reduce a capacitance associated with the thermally conducting layer compared to when the thermally conducting layer does not include the discontinuity.
H01M 10/647 - Prismatic or flat cells, e.g. pouch cells
H01M 10/653 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
H01M 10/6551 - Surfaces specially adapted for heat dissipation or radiation, e.g. fins or coatings
H01M 10/658 - Means for temperature control structurally associated with the cells by thermal insulation or shielding
H01M 50/211 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for pouch cells
H01M 50/233 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by physical properties of casings or racks, e.g. dimensions
H01M 50/291 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by spacing elements or positioning means within frames, racks or packs characterised by their shape
89.
Cell matching across multiple characteristics during battery assembly
For each cell in a plurality of cells from a same manufacturing run, a first and a second cell characteristic are received in order to obtain a plurality of cell characteristics. For each cell, a batch compatibility number that is associated with a number of compatible cells that that cell is compatible with is determined based at least in part on the plurality of cell characteristics. The plurality of cells is sorted according to the batch compatibility numbers to obtain a sorted list of cells. A plurality of compatible cells to include in a battery is selected from the plurality of cells, including by evaluating the plurality of cells according to the order of the sorted list of cells and beginning with the lowest batch compatibility number.
G01R 31/367 - Software therefor, e.g. for battery testing using modelling or look-up tables
G01R 31/396 - Acquisition or processing of data for testing or for monitoring individual cells or groups of cells within a battery
G06F 7/08 - Sorting, i.e. grouping record carriers in numerical or other ordered sequence according to the classification of at least some of the information they carry
H01M 6/50 - Methods or arrangements for servicing or maintenance, e.g. for maintaining operating temperature
H01M 10/04 - Construction or manufacture in general
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
Embodiments provide scissoring mechanisms for a vertical lift fan of an electric aircraft (e.g., a vertical take-off-landing eVTOL aircraft) where the blades of the vertical lift fan can be opened at almost zero speed. Exemplary scissoring mechanisms have position locking features that keep the collapsed blades in the low drag orientation once closed (e.g., in the stowed position). As a result, the scissoring mechanisms do not cause large impulses during opening and closing that cause large stresses and noise. In addition, the scissoring mechanisms provide an opportunity to check that the fans are opened properly prior to spinning them to the full operating speed. The scissoring mechanisms may not require an extra actuator, and rely on the propulsion motor.
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 - Means for temperature control structurally associated with the cells by heat storage or buffering, e.g. heat capacity or liquid-solid phase changes or transition
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.
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.
G06F 3/04817 - Interaction techniques based on graphical user interfaces [GUI] based on specific properties of the displayed interaction object or a metaphor-based environment, e.g. interaction with desktop elements like windows or icons, or assisted by a cursor's changing behaviour or appearance using icons
G01C 21/00 - NavigationNavigational instruments not provided for in groups
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G06F 3/01 - Input arrangements or combined input and output arrangements for interaction between user and computer
G06F 3/02 - Input arrangements using manually operated switches, e.g. using keyboards or dials
G06F 3/04847 - Interaction techniques to control parameter settings, e.g. interaction with sliders or dials
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 - Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G06F 3/01 - Input arrangements or combined input and output arrangements for interaction between user and computer
G06F 3/02 - Input arrangements using manually operated switches, e.g. using keyboards or dials
G06F 3/04847 - Interaction techniques to control parameter settings, e.g. interaction with sliders or dials
G01C 21/00 - NavigationNavigational instruments not provided for in groups
B60L 50/15 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines with additional electric power supply
B64C 13/50 - Transmitting means with power amplification using electrical energy
B64C 27/68 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using electrical energy, e.g. having electrical power amplification
H02J 9/00 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
H02J 9/04 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
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.
G08G 5/02 - Automatic landing aids, i.e. systems in which flight data of incoming planes are processed to provide landing data
G06F 3/04817 - Interaction techniques based on graphical user interfaces [GUI] based on specific properties of the displayed interaction object or a metaphor-based environment, e.g. interaction with desktop elements like windows or icons, or assisted by a cursor's changing behaviour or appearance using icons
G06F 3/04845 - Interaction techniques based on graphical user interfaces [GUI] for the control of specific functions or operations, e.g. selecting or manipulating an object, an image or a displayed text element, setting a parameter value or selecting a range for image manipulation, e.g. dragging, rotation, expansion or change of colour
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 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
H02J 9/04 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
B64C 27/68 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using electrical energy, e.g. having electrical power amplification
B60L 50/15 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines with additional electric power supply
B64C 13/50 - Transmitting means with power amplification using electrical energy
