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
2.
INTER-MODULE BATTERY BALANCING USING MINIMUM CELL VOLTAGES TO SELECT BATTERY SUB-MODULES TO POWER LOADS
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
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
6.
BATTERY CELL WITH THERMALLY CONDUCTIVE SIDE WALLS, BATTERY MODULE ASSEMBLY, AND TOOLING ASSEMBLY
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
7.
DAMPING UNIT AS A SECONDARY LOAD PATH FOR A MOVABLE ELEMENT WITH ACTUATOR
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
8.
SYSTEM AND METHODS FOR IMPROVED SITUATIONAL AWARENESS IN AVIATION
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
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
12.
DISTRIBUTED LOW VOLTAGE POWER GENERATION ARCHITECTURE FOR BATTERY ELECTRIFIED AIRCRAFT
Embodiments provide an animated graphical user interface for simultaneously monitoring multiple autonomous aircraft. More specifically, techniques disclosed herein provide a GUI that allows for one-to-many supervision where a remote supervisor (e.g., human or artificial intelligence) may continuously monitor and/or interact with a plurality of autonomous aircraft. For example, the autonomous aircraft may include one or more autonomous electric vertical takeoff landing (eVTOL) aircraft. Embodiments provide command input system and techniques that reduce human error by assigning an input mechanism and a command input menu to a unique flight parameter.
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.
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
G08G 5/06 - Traffic control systems for aircraft for control when on the ground
F03D 3/04 - Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor having stationary wind-guiding means, e.g. with shrouds or channels
F03D 7/02 - Controlling wind motors the wind motors having rotation axis substantially parallel to the air flow entering the rotor
H02K 1/22 - Rotating parts of the magnetic circuit
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
Embodiments provide a VTOL aircraft including a plurality of tilting propeller assemblies each coupled to a support structure and configured to transition between a vertical flight and a forward flight position. Each tilting propeller assembly comprising a propeller and a movable fairing provided downstream of the propeller. The movable fairing is configured to extend along an axis of rotation of the propeller. When the tilting propeller assembly transitions between the vertical and forward flight position, the movable fairing is configured to swivel to extend parallel to the direction of resultant airflow over the tilting propeller assembly into a minimum drag orientation. The movable fairing is damped enough to prevent any oscillations from the propeller wake shedding, and at the same time, keep the propeller aligned in a minimum-drag orientation with the resultant flow.
B64C 27/28 - 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
B64C 27/52 - Tilting of rotor bodily relative to fuselage
17.
COMPACT VERTIPORT WITH EFFICIENT SPACE UTILIZATION
Embodiments provide a compact vertiport system. The vertiport system may be efficient and compact by combining, into one space and time period, multiple activities that typically take place in different spaces and different times. For example, when an aircraft is being moved from a landing zone to a takeoff zone, the aircraft may also be charged simultaneously. Also, passenger exchange may take place while the aircraft is being moved. As a result, compact vertiport systems may fit into smaller spaces (e.g., tops of buildings, or smaller plots of land).
An electrically powered propulsion system for an aircraft includes batteries, electric propulsion assemblies, and power distribution circuits. Each battery is coupled with two or more of the electric propulsion assemblies via a respective one of the power distribution circuits. The electric propulsion assemblies are positioned on the aircraft and operable to apply balanced forces to the aircraft such that in the event of a failure, the aircraft is not subjected to large changes in roll, pitch, and/or yaw.
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
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 3/32 - Wings specially adapted for mounting power plant
B64C 19/00 - Aircraft control not otherwise provided for
B64C 27/22 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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 10/6552 - Closed pipes transferring heat by thermal conductivity or phase transition, e.g. heat pipes
H01M 10/6569 - Fluids undergoing a liquid-gas phase change or transition, e.g. evaporation or condensation
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
Embodiments provide an electric aircraft with a plurality of lift fan assemblies that are configured to provide vertical lift, and one or more pusher propellers that are configured to provide forward thrust. The lift fan assemblies may be coupled to the wings of the aircraft via one or more support structures, and the wings may be coupled to an upper region of the fuselage. The pusher propeller(s) may be coupled to a tailing end of the fuselage. The lift fan assemblies and the pusher propeller(s) may provide thrust and movement in directions that are orthogonal to one another. A control system coupled to the aircraft may control the lift fan assemblies and the one or more pusher propellers to activate, increase in power, and decrease in power. The lift fan assemblies and the one or more pusher propellers may be operated separately, and may be active at different times.
B64C 5/08 - Stabilising surfaces mounted on, or supported by, wings
B64C 27/22 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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
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 method for monitoring status of a battery cell. The method involves determining current values of one or more state-of-health parameters of the battery cell and measuring values of a plurality of operating-state parameters of the battery cell, including measuring an actual potential of the battery cell. The method also involves computing an optimistic potential based on a cell state model, the measured values of a first subset of the operating-state parameters, and optimistic values for the one or more state-of-health parameters, the optimistic values corresponding to a better state of health than the current values of the one or more state-of-health parameters. The method also involves computing a pessimistic potential based on the cell state model, the measured values of the first subset of operating-state parameters, and pessimistic values for the one or more state-of-health parameters, the pessimistic values corresponding to a worse state of health than the current values of the one or more state-of-health parameters. The method further involves determining whether the actual potential of the battery cell is substantially within an envelope defined by the optimistic potential and the pessimistic potential, and generating a model fault notification in the event that the actual potential is not substantially within the envelope.
G01R 31/367 - Software therefor, e.g. for battery testing using modelling or look-up tables
G01R 31/389 - Measuring internal impedance, internal conductance or related variables
G01R 31/392 - Determining battery ageing or deterioration, e.g. state of health
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
24.
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
Embodiments provide an aircraft with one or more tilting fan assemblies that are configured to tilt between a forward flight position and a vertical lift position. The aircraft may also include a plurality of lift fan assemblies for vertical movement. The tilting fan assemblies may be coupled to the fuselage or wings of the aircraft via one or more tilting mechanisms. A control system coupled to the aircraft may control the one or more tilting mechanisms to move the tilting fan assemblies between the forward flight position and the vertical lift position. The tilting fan assemblies may be coupled to one or more support structures that are coupled the fuselage or wings of the aircraft.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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
B64C 27/52 - Tilting of rotor bodily relative to fuselage
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
G05D 1/46 - Control of position or course in three dimensions
G05D 1/611 - Station keeping, e.g. for hovering or dynamic anchoring
A desired departure temperature is determined for a battery, having a temperature, in a vehicle based at least in part on trip information associated with a trip. A temperature controlling system is used to bring the temperature of the battery towards the desired departure temperature, wherein the vehicle begins the trip with the battery at the desired departure temperature.
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
B60L 58/24 - 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
27.
BATTERY WITH LIQUID TEMPERATURE CONTROLLING SYSTEM
A liquid temperature controlling system is used to circulate a temperature controlled liquid between the liquid temperature controlling system and a battery to produce a temperature controlled battery. The battery and the liquid temperature controlling system are detachably coupled at least while the temperature controlled liquid is circulated. The temperature controlled liquid is removed from the temperature controlled battery. The battery and the liquid temperature controlling system are decoupled after the temperature controlled liquid is removed. A charger is used to charge the temperature controlled battery.
B60L 53/18 - Cables specially adapted for charging electric vehicles
B60L 53/80 - Exchanging energy storage elements, e.g. removable batteries
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 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.
For each battery sub-module in a plurality of battery sub-modules, a voltage associated with a cell in that battery sub-module is received where in each battery sub-module in the plurality of battery sub-modules includes a plurality of cells. A battery sub-module is selected based at least in part on the received voltages and a set of one or more loads, which draws power from the selected battery sub-module and is not powered by any other battery sub-module in the plurality of battery sub-modules, is configured so that the set of loads at least temporarily does not draw power from the selected battery sub-module.
30.
CAPACITANCE REDUCING BATTERY SUBMODULE WITH THERMAL RUNAWAY PROPAGATION PREVENTION AND CONTAINMENT FEATURES
A battery system includes a can with a lip around an opening. At least an interior surface of the can is anodized and the lip of the can includes a longer and shorter side. The can further includes a flange on the longer side of the lip and a plurality of layers that are inserted into the can. The plurality of layers includes a battery cell and a thermally conducting layer with a fin and the fin has a spring force that pushes the fin towards the anodized interior surface. The battery system further includes a lid that is configured to cover the opening of the can, where the flange is configured to wrap around the lid when the lid covers the opening of the can.
H01M 10/6551 - Surfaces specially adapted for heat dissipation or radiation, e.g. fins or coatings
H01M 50/207 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape
H01M 50/258 - Modular batteriesCasings provided with means for assembling
H01M 50/262 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders with fastening means, e.g. locks
H01M 50/271 - Lids or covers for the racks or secondary casings
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
31.
CAPACITANCE REDUCING BATTERY SUBMODULE WITH THERMAL RUNAWAY PROPAGATION PREVENTION AND CONTAINMENT FEATURES
A system which includes a can with an opening and a plurality of layers that are inserted into the can. The plurality of layers includes a battery cell and a thermally conducting layer with a multi-fold fin with a plurality of folds. The multi-fold fin has a spring force that pushes the multi-fold fin towards an interior surface of the can. A compressible material is placed between the multi-fold fin and the plurality of layers. The compressible material provides an additional spring force that pushes the multi-fold fin towards the interior surface of the can. The system also includes a lid that is configured to cover the opening of the can.
H01M 10/6551 - Surfaces specially adapted for heat dissipation or radiation, e.g. fins or coatings
H01M 50/207 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape
H01M 50/258 - Modular batteriesCasings provided with means for assembling
H01M 50/271 - Lids or covers for the racks or secondary casings
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
A corrugated lift fan rotor is disclosed. In various embodiments, a rotor includes an upper skin, a lower skin, and an at least partly corrugated core encased between the upper skin and the lower skin. In some embodiments, the core comprises a composite material, such as carbon fiber reinforced polymer composite material, and includes an upper cap portion, a lower cap portion, and a web portion extending between the upper and lower cap portions.
B32B 3/28 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer comprising a deformed thin sheet, e.g. corrugated, crumpled
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
A lift fan includes a stator which is configured to output a magnetic field. The lift fan also includes a first housing which in turn includes a blade, a second housing, and a magnet array. The magnet array is coupled to either the first housing or the second housing and the housing, which is coupled to the magnet array, rotates in response to the magnet array responding magnetically to the magnetic field output by the stator.
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
B64D 35/06 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
A vertical takeoff and landing aircraft includes rotors that provide vertical and horizontal thrust. During forward motion, the vertical lift system is inactive. A lift fan mechanism positions the fan blades of the aircraft in a collapsed configuration when the vertical lift system is inactive and positions the fan blades of the aircraft in a deployed configuration when the vertical lift system is active.
A mechanical mechanism is used to prevent a rotor of an aircraft from rotating when the rotor is not in use. The mechanical mechanism disengages when the speed of the rotor exceeds a speed threshold and the mechanism reengages when the speed of the rotor is below the speed threshold.
F16D 43/18 - Internally controlled automatic clutches actuated entirely mechanically controlled by angular speed with centrifugal masses actuating the clutching members directly in a direction which has at least a radial componentInternally controlled automatic clutches actuated entirely mechanically controlled by angular speed with centrifugal masses themselves being the clutching members with friction clutching members
36.
PREVENTING CELL THERMAL RUNAWAY PROPAGATION WITHIN A BATTERY
A cell undergoing a thermal runaway process is characterized by high local temperatures at the cell. Thermal insulator prevents the high temperatures from dissipating to nearby cells such that thermal runaway is triggered in the nearby cells. In addition, thermal conductors are provided that form conduction paths that draw heat from a cell undergoing thermal runaway and distribute the heat to other cells in manner that thermal runaway is not triggered in cells that are near the failing cell. If sufficient heat is drawn away from a failing cell, temperatures of the cells surrounding the failed cell can remain low enough to prevent the surrounding cells from undergoing the thermal runaway process.
patents
