A passenger vertical take-off and landing aircraft includes a flying wing comprising a passenger compartment, a first set of rotors positioned at least partially forward of a leading edge of the flying wing, and a second set of rotors positioned at least partially rearward of a trailing edge of the flying wing. The first set of rotors may include at least four rotors and the second set of rotors may comprise at least two rotors. The first set of rotors, the second set of rotors, both, or neither may be tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft.
A electric aircraft power distribution system includes a first battery pack connected to at least a first load and to a common bus that connects the first battery pack in parallel to at least a second battery pack; a first electrical component electrically connected between the first battery pack and the first load and configured to disconnect the first load from the first battery pack in response to current above a first threshold current, wherein the first electrical component has a first disconnection time at the first threshold current; and a second electrical component electrically connected between the first battery pack and the common bus and configured to disconnect the first battery pack from the common bus in response to current above a second threshold current, wherein the second electrical component has a second disconnection time at the second threshold current that is higher than the first disconnection time.
This disclosure relates to flight control of electric aircraft and other vehicles. A computer-implemented method for estimating available range of an aircraft in flight is disclosed, comprising: receiving electrical information of one or more batteries measured using a first sensor; estimating aircraft-level energy based on electrical information of the one or more batteries; receiving one or more of an altitude of the aircraft or a current airspeed of the aircraft measured using a second sensor; estimating a steady-state force based on the one or more of the altitude of the aircraft or the current airspeed of the aircraft; estimating one or more of a vertical landing range or a horizontal landing range based on the one or more of the estimated aircraft-level energy or the estimated steady-state force; and displaying the one or more of the estimated vertical landing range or the estimated horizontal landing range on a display.
4.
SYSTEMS AND METHODS FOR TILT PROPELLERS WITH TILT ACTUATOR GEARBOX AND INTEGRATED INVERTER
A tilt actuation apparatus for tilting a propulsion system of an aircraft, the tilt actuation apparatus comprising: a tilt actuator comprising a rotor; a gear set, wherein the rotor is coupled to the gear set, a worm gear concentrically coupled to an output of the gear set, a worm wheel meshed with the worm gear, a gear shaft concentrically coupled to the worm wheel, a pinion concentrically coupled to the gear shaft, and an output shaft coupled to an output of the pinion, the output shaft configured to be fixed to a frame of the aircraft.
A tilt apparatus of an aircraft, comprising: a first frame, a second frame moveably coupled to the first frame, a propulsion system coupled to the second frame and configured to move with the second frame, the propulsion system comprising: a propeller, a motor configured to rotate the propeller, and a propulsion inverter configured to supply current to the motor. The tilt apparatus further comprises a tilt actuation system coupled to the second frame and configured to tilt with the second frame with respect to the first frame, the tilt actuation system comprising: a tilt actuator; a tilt actuator inverter configured to supply current to the tilt actuator, and a tilt actuator gearbox coupled to the second frame and configured to tilt with the second frame. The tilt actuator is configured to the tilt the second frame with respect to the first frame via the tilt actuator gearbox.
Embodiments are provided for charging system for an aircraft. The charging system may comprise a plurality of electric propeller units (EPUs), a plurality of battery packs configured to power the plurality of EPUs, a charge control unit configured to determine a target charge level for each of the plurality of battery packs, receive charge status information from each of the plurality of battery packs, and upon determining that a target charge level of at least one of the battery packs has been reached, command the at least one battery pack to disconnect from a common charging bus having a high voltage connection to a power source external to the 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
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]
7.
SYSTEMS AND ARCHITECTURES FOR CHARGING INFRASTRUCTURE
Embodiments are provided for charging system for an aircraft. The charging system may comprise a plurality of electric propeller units (EPUs), a plurality of battery packs configured to power the plurality of EPUs, a charge port configured to accept high voltage power to charge the plurality of battery packs, a common high voltage charging bus connected to the charge port, and a charge control unit configured to determine battery pack charge contactor commands based on flight information for an aircraft and a current state of each battery pack of the plurality of battery packs. The plurality of battery packs may be chargeable through the common high voltage charging bus and each of the plurality of battery packs may include a disconnection device configured to disconnect the battery pack from charging.
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
B64D 31/16 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants
H01M 10/46 - Accumulators structurally combined with charging apparatus
H01M 50/249 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders specially adapted for aircraft or vehicles, e.g. cars or trains
A power distribution system for an aircraft, comprising: a plurality of electric propeller units (EPUs), a first paired battery pack unit, the first paired battery pack unit, and a second paired battery pack unit. The first paired battery pack unit may include a first battery electrically connected to a second battery via a first high voltage bus. The first battery may be configured to provide power to a first set of EPUs of the plurality of EPUs, the second battery may be configured to provide power to a second set of EPUs of the plurality of EPUs, the first battery may be configured to act as a backup battery for powering the second set of EPUs, and the first high voltage bus and the second high voltage bus may be electrically separate from one another.
A system for battery management on a vehicle, comprising: a first system associated with a first battery pack, and a second system associated with a second battery pack, where the first battery pack is electrically connected to the second battery pack via a high voltage bus, the first battery pack is configured to power to a first electric engine, and the second battery pack is configured to power to a second electric engine. The first system may be configured to monitor a state of the first battery pack and isolate, by blowing a first fuse, the first battery pack from the second battery pack upon detecting an electrical issue, and the second system may be configured to monitor a state of the second battery pack and isolate, by blowing a second fuse, the second battery pack from the first battery pack upon detecting an electrical issue.
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 50/502 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing
H01M 50/583 - Devices or arrangements for the interruption of current in response to current, e.g. fuses
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H02J 9/06 - 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 with automatic change-over
10.
Balancing and measuring circuit for high voltage systems
The present disclosure relates generally to high voltage systems. In one embodiment, a balancing and measuring circuit is disclosed, comprising: a first capacitor electrically coupled between a first voltage and a chassis voltage, wherein the first voltage is greater than the chassis voltage; a second capacitor electrically coupled between a second voltage and the chassis voltage, wherein the second voltage is less than the chassis voltage; a first circuit associated with the first capacitor; and a second circuit associated with the second capacitor, wherein the first circuit and the second circuit each comprise: a resistive element; a switching element; a voltage circuit configured to generate a reference voltage; and a controller configured to monitor a voltage of a reference capacitor and to control the switching element based on the monitored voltage, wherein the resistive element and the switching element are connected in series.
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a computer-implemented method for command prioritization in an aircraft is disclosed. The method comprises receiving a pilot command, analyzing the pilot command to determine characteristics associated with the pilot command, wherein the characteristics to airspeed and climb of an aircraft, assigning weights to characteristics associated with the pilot command based on constraint data, determining priority of execution between airspeed and climb based on the weights assigned to the characteristics associated with the pilot command, calculating a correction factor to be applied to the characteristics associated with the pilot command based on determined priority and generating at least one actuator command to control the aircraft based on determined priority of execution.
A method of controlling aircraft power distribution comprises: receiving aircraft state information of an aircraft, detecting whether the aircraft state information indicates a crash, and disconnecting supply of high voltage power to the aircraft by at least one battery upon detecting both that the aircraft state information indicates a crash and a loss of continuity in at least one low voltage wire.
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
B60K 1/04 - Arrangement or mounting of electrical propulsion units of the electric storage means for propulsion
B64U 50/19 - Propulsion using electrically powered motors
H01M 50/249 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders specially adapted for aircraft or vehicles, e.g. cars or trains
H01M 50/502 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing
H01M 50/583 - Devices or arrangements for the interruption of current in response to current, e.g. fuses
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 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
13.
SYSTEMS AND METHODS FOR CONTROLLING AIRCRAFT SUBSYSTEMS IN DIFFERENT MODES AND STATES
A method of controlling aircraft power distribution, comprising: receiving, at a control circuit in an aircraft, a selection of one of at least three aircraft modes of operation from a user input device, and controlling, via the control circuit, power distribution within the aircraft based on the selected mode of operation, wherein controlling power distribution based on the selected mode of operation comprises: separately controlling via the control circuit, based on the selected mode of operation, high voltage power to at least one electric propulsion unit and high voltage power to at least one non-propulsion load.
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
B60K 1/04 - Arrangement or mounting of electrical propulsion units of the electric storage means for propulsion
B64U 50/19 - Propulsion using electrically powered motors
H01M 50/249 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders specially adapted for aircraft or vehicles, e.g. cars or trains
H01M 50/502 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing
H01M 50/583 - Devices or arrangements for the interruption of current in response to current, e.g. fuses
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 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
14.
INVERTER CIRCUITS AND ELECTRICAL PROPULSION SYSTEMS FOR EVTOL AIRCRAFT
An electrical propulsion system includes an electrical motor configured to drive one or more propellers of the aircraft, a capacitor configured to stabilize a direct current (DC) bus voltage, a first inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to alternate current (AC) voltages to drive a first set of stator windings of the electrical motor, in response to a first pulse width modulation (PWM) vector, and a second inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to AC voltages to drive a second set of stator windings of the electrical motor, in response to a second PWM vector. The first PWM vector and the second PWM vector are substantially equal and opposite vectors.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/30 - Aircraft characterised by electric power plants
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
15.
SYSTEMS AND METHODS FOR OIL MAINTENANCE IN GEARBOXES FOR eVTOL AIRCRAFT
A motor assembly for a propulsion system, the motor assembly including a motor housing; a rotor; a power inverter; a main shaft; wherein the main shaft extends through the rotor; and a fluid distribution system including a fluid reservoir; a pump configured to distribute a fluid to a component of the motor assembly; and a filter having a circumferential side, wherein the filter is configured to filter the fluid through the circumferential side, wherein the filter is located adjacent to the main shaft.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
16.
SYSTEMS AND METHODS FOR OIL MANAGEMENT IN GEARBOXES FOR EVTOL AIRCRAFT
An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/30 - Aircraft characterised by electric power plants
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
“A battery pack assembly, comprising: a battery pack, the battery pack comprising: a battery pack enclosure, and one or more battery cells within the battery pack enclosure, and a junction box, the junction box comprising: a junction box enclosure including one base wall, four side walls connected to the base wall, and one open end, and a battery management unit, at least one fuse, and at least one switch, each located within the junction box enclosure and mounted to the base wall. The four side walls of the junction box enclosure are removably secured to the battery pack enclosure at the open end.”
B64C 3/32 - Wings specially adapted for mounting power plant
B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
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
H01M 50/204 - Racks, modules or packs for multiple batteries or multiple cells
H01M 50/249 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders specially adapted for aircraft or vehicles, e.g. cars or trains
H02G 3/08 - Distribution boxesConnection or junction boxes
18.
SYSTEMS AND METHODS FOR HIGH VOLTAGE BATTERY CHARGING AND VERTIPORT OPERATIONS
Aspects of the present disclosure generally relate to systems and methods for the configuration and control of charging and cooling systems for aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a method of charging an aircraft is disclosed comprising: receiving a mode of operation indicating whether battery packs of the aircraft are connected in parallel prior to joining a charging bus, receiving charging protocol information, and controlling charging operations of the battery packs based on the mode of operation and the charging protocol information.
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
B60K 1/04 - Arrangement or mounting of electrical propulsion units of the electric storage means for propulsion
B64U 50/19 - Propulsion using electrically powered motors
H01M 50/249 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders specially adapted for aircraft or vehicles, e.g. cars or trains
H01M 50/502 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing
H01M 50/583 - Devices or arrangements for the interruption of current in response to current, e.g. fuses
H01M 50/48 - Spacing elements inside cells other than separators, membranes or diaphragmsManufacturing processes thereof characterised by the material
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
19.
SYSTEMS AND METHODS FOR OIL MANAGEMENT IN GEARBOXES FOR EVTOL AIRCRAFT
An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/30 - Aircraft characterised by electric power plants
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
20.
SYSTEMS AND METHODS FOR MANAGING ICE ACCRETIONS DURING FLIGHT OF AIRCRAFT
Embodiments of the present disclosure provide systems and methods for averting, shedding, or otherwise managing ice accretions that may develop during flight of an aircraft. Example systems and methods selectively modulate propeller parameters in a way that does not disrupt a flight trajectory; direct oil from a lubrication and cooling path to targeted sections of ice-prone surfaces to manage ice accretion in a way that does not unduly increase the total volume of oil, require larger pumps, or complicate the system; or generate heat at targeted areas of a propeller assembly by electric heating systems that utilize propeller motion.
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a computer-implemented method for controlling an aircraft is disclosed, comprising: receiving, from a source processor, a first copy of a signal corresponding to an input device; sending a second copy of the signal to all other processors; receiving a number of second copies of the signal from all other processors, the number of second copies being equal to the number of all other processors excluding the source processor; determining a consensus signal based on the first copy and the second copies of the signal; and determining a command signal for an effector of the aircraft based on the consensus signal, and wherein no two processors are configured to receive signals from a same input device.
An aircraft wing, comprising: a plurality of ribs, each rib including a plurality of wire openings, wherein each of the plurality of wire openings are enclosed by one of the plurality of ribs and a skin of the aircraft; and a plurality of high voltage wires disposed in the wire openings in the plurality of ribs such that each wire opening receives only one high voltage wire, and the each wire opening has an opening size larger than a size of the one high voltage wire, the opening size being smaller than a size of a connector mounted to an end of the one high voltage wire and configured to allow mating with another high voltage wire or an electrical component.
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a flight control system of an aircraft is disclosed, configured to receive one or more signals to control movement of the aircraft, determine at least one flight condition of the aircraft, wherein the at least one flight condition includes at least a phase of flight, calculate at least one or more loads associated with the aircraft based on the determined at least one flight condition; determine an optimized flight configuration to alleviate loads on one or more components of the aircraft based on the received one or more signals and the calculated loads, generate one or more effector commands based on the optimized flight configuration; and actuate one or more aircraft effectors based on the one or more effector commands.
An apparatus for aircraft propulsion includes a propeller and a hybrid-cooled electric engine mounted to a support structure and configured to rotate the propeller. The electric engine is located in an enclosure, with a first heat transfer element thermally coupled to the electric engine via a fluid flow path, partially located outside the enclosure. A second heat transfer element, integral to or thermally coupled to the electric engine, provides air cooling. Both heat transfer elements are housed within the aircraft's support structure. At least one air inlet on the upper side of the support structure receives propeller downwash. A first cooling path directs a portion of the downwash from the air inlet to the first heat transfer element, and a first air outlet exhausts the downwash.
“A tilting apparatus for an aircraft, comprising: a tiltable aircraft component which tilts between a first and second position, at least one actuator for adjusting a tilt angle of the tiltable aircraft component, and at least one passive damper connected to the tiltable aircraft component and configured to limit a rate of change of the tilt angle of the tiltable aircraft component. The at least one passive damper is on a load path separate from a load path of the at least one actuator.”
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/30 - Aircraft characterised by electric power plants
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
28.
SYSTEMS AND METHODS FOR VIBRATION ATTENUATION IN FLIGHT CONTROL OF AN AIRCRAFT
The present disclosure relates generally to flight control of electric aircraft and other powered aerial vehicles. In one embodiment, an electrical system for an aircraft is disclosed, comprising: at least one processor configured to: receive pilot input indicating a commanded aircraft state, determine an aircraft thrust for achieving the commanded aircraft state, retrieve at least one propeller parameter associated with propeller speeds, wherein the propeller parameter is determined to reduce a structural vibratory response in the aircraft. The at least one processor is further configured to determine a respective command for each propeller of the aircraft to achieve the determined aircraft thrust based on the at least one propeller parameter and control each propeller of the aircraft based on the corresponding respective command.
Systems and methods for backlash measurement and monitoring are disclosed for an actuator having a motor end and an output end. The method may include: driving the motor end of the actuator to one endpoint; measuring, using a first sensor, a motor-end initial position value associated with the motor end; measuring, using a second sensor, an output-end initial position value associated with the output end; driving the motor end of the actuator to another endpoint; measuring a motor-end final position value using the first sensor and an output-end final position value using the second sensor; determining a backlash value based on the motor-end initial position value, output-end initial position value, motor-end final position value, and output-end final position value; generating a signal based on comparing the backlash value to a predetermined threshold; and displaying a notification indicative of an operational condition of the actuator based on the signal.
A VTOL aircraft includes a lift propeller configured to provide lift during takeoff, landing and hover operations. The lift propeller is configured to be stowed close to a boom surface when not in use during, e.g., cruise flight, to minimize drag around propeller surfaces. The lift propeller may be displaced vertically with respect to the boom when switching to a lift configuration to provide greater separation from the boom to improve lift efficiency and reduce unwanted vibrations. The lift propeller may have a fail-safe configuration that allows the propeller to move passively between lift and stowed configurations, and to fully rotate even when fully retracted.
A motor gearbox assembly for an aircraft may comprise a layshaft configured to transmit torque from a rotor to a main power output shaft. The motor gearbox assembly may comprise a gearbox housing, a stator mounted inside the gearbox housing, a rotor rotatably mounted inside the stator on a main power output shaft and a layshaft rotatably mounted in the gearbox housing outside of the stator. The motor gearbox assembly may comprise a first ear reduction between the rotor and the layshaft, and a second gear reduction between the layshaft and the main power output shaft.
F16H 3/091 - Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion without gears having orbital motion exclusively or essentially with continuously- meshing gears, that can be disengaged from their shafts characterised by the disposition of the gears including a single countershaft
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
“An electrical propulsion system comprises an inverter, an electrical motor assembly, an assembly, and a rotor position sensor. The inverter comprises a printed circuit board assembly (PCBA). The electrical motor assembly comprises a stator and a rotor. The assembly is configured to rotate a propeller and comprises a moving component and a stationary component. The rotor position sensor comprises at least one sensor coupled to the PCBA, and a magnet located on the moving component. The at least one sensor is configured to detect a magnetic field of the magnet through the stationary component.”
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
41.
SYSTEMS AND METHODS FOR IMPROVED GEARBOXES FOR EVTOL AIRCRAFT
A method for balancing a rotor of an electric engine, comprising: identifying an axis of rotation of the rotor, determining an imbalance present in the rotor by rotating the rotor about the axis of rotation, wherein determining the imbalance includes rotating the rotor and detecting an amplitude of the imbalance. The method further comprising: calculating an amount of mass to remove at a position along an inner circumference of the rotor such that a center of mass of the rotor coincides with the axis of rotation of the rotor and removing the amount of mass from the inner circumference of the rotor.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/30 - Aircraft characterised by electric power plants
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
42.
Systems and methods for active-light based precision localization of aircrafts in GPS-denied environments
Systems and methods of providing guidance to assist eVTOL aerial vehicles in performing landing and takeoff operations at landing locations in GPS-denied environments are disclosed. An exemplary system includes an aerial vehicle comprising a camera configured to generate images based on information transmitted by a plurality of light sources located adjacent a landing surface for the aerial vehicle and a controller circuit configured to receive the generated images and determine a position and an orientation of the aerial vehicle based on the received images, wherein the light sources are arranged in a predetermined pattern on the landing surface, and wherein a characteristic of light emitted from each of the light sources is modulated with respect to time.
An electrical system for an aircraft is disclosed, comprising: at least one processor configured to: receive first sensor data from at least one inertial sensor of the aircraft, wherein the first sensor data is indicative of a state of the aircraft, receive second sensor data from at least one of an airspeed sensor indicating an airspeed of the aircraft or a propeller speed sensor indicating a propeller speed of at least one propeller of the aircraft, and determine the state of the aircraft based on the first sensor data, wherein determining the state of the aircraft comprises filtering aircraft state measurements based on the second sensor data to lessen influence of propeller vibrations on at least one aircraft signal. The at least one processor is further configured to control the aircraft based on a pilot input command and the determined state of the aircraft.
The present disclosure relates generally to flight control of electric aircraft and other powered aerial vehicles. In one embodiment, a method is disclosed, comprising: receiving a descent rate command from a pilot input device, determining a proximity of each propeller of at least two propellers to a vortex ring state; and controlling the aircraft's descent rate to be less than the commanded descent rate when at least one of the at least two propellers is within a first threshold proximity to the vortex ring state.
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a flight control system of an aircraft is disclosed, configured to determine one or more desired commands for the electric aircraft, determine at least one reference command based on the desired commands and one or more aircraft conditions, monitor energy states of the plurality of battery packs, wherein at least a first battery pack of the plurality of battery packs is electrically isolated from at least a second battery pack of the plurality of battery packs, adjust the at least one reference command based on the monitored energy states of the plurality of battery packs, generate control commands for the plurality of effectors based on the adjusted at least one reference command, and control the plurality of effectors according to the generated control commands to meet the one or more desired commands of the electric aircraft.
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a computer-implemented method for command prioritization in an aircraft is disclosed. The method comprises receiving a pilot command, analyzing the pilot command to determine characteristics associated with the pilot command, wherein the characteristics to airspeed and climb of an aircraft, assigning weights to characteristics associated with the pilot command based on constraint data, determining priority of execution between airspeed and climb based on the weights assigned to the characteristics associated with the pilot command, calculating a correction factor to be applied to the characteristics associated with the pilot command based on determined priority and generating at least one actuator command to control the aircraft based on determined priority of execution.
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In one embodiment, a computer-implemented method is disclosed, comprising: measuring one or more state variables of the aircraft; inputting the one or more measured state variables to a prioritization scheme configured to determine an optimized actuator setting; determining one or more actuator commands based at least in part on inputting the one or more measured state variables to the prioritization scheme; and automatically controlling at least one actuator of the aircraft based on the determined one or more actuator commands.
Systems and methods for flight control of aircrafts driven by electric propulsion systems and other types of vehicles are disclosed, including method for allocating power to components of a high-voltage bus of an aircraft. The method comprises receiving an input indicative of an operation command; calculating, based on the received input, a total power demand associated with a plurality of components connected to the high-voltage bus, each component having a respective component power demand; comparing the total power demand to a high-voltage bus power limit assigned to the high-voltage bus to determine a difference between the high-voltage bus power limit and the total power demand; determining power allocation to each of the components connected to the high-voltage bus based on the difference between the high-voltage bus power limit and the total power demand; and allocating power to each component connected to the high-voltage bus using the determined power allocation.
An electrical system for an aircraft is disclosed, comprising: at least one processor configured to: receive first sensor data from at least one inertial sensor of the aircraft, wherein the first sensor data is indicative of a state of the aircraft, receive second sensor data from at least one of an airspeed sensor indicating an airspeed of the aircraft or a propeller speed sensor indicating a propeller speed of at least one propeller of the aircraft, and determine the state of the aircraft based on the first sensor data, wherein determining the state of the aircraft comprises filtering aircraft state measurements based on the second sensor data to lessen influence of propeller vibrations on at least one aircraft signal. The at least one processor is further configured to control the aircraft based on a pilot input command and the determined state of the aircraft.
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a flight control system of an aircraft is disclosed, configured to receive one or more signals to control movement of the aircraft, determine at least one flight condition of the aircraft, wherein the at least one flight condition includes at least a phase of flight, calculate at least one or more loads associated with the aircraft based on the determined at least one flight condition; determine an optimized flight configuration to alleviate loads on one or more components of the aircraft based on the received one or more signals and the calculated loads, generate one or more effector commands based on the optimized flight configuration; and actuate one or more aircraft effectors based on the one or more effector commands.
Aspects of this present disclosure relate to systems and methods for dynamically moving graphical elements of a user interface of a flight control system. In one, a method is disclosed comprising: determining aircraft authority limits based on at least one state signal indicating an aircraft state, wherein the aircraft authority limits indicate an extent to which one or more control signals can command the aircraft; determining one or more proximities between the aircraft state and the determined aircraft authority limits; and automatically moving the graphical elements of the user interface to one or more positions on the user interface based on the determined one or more proximities.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
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
52.
SYSTEMS AND METHODS FOR RETRACTING LIFT PROPELLER IN VTOL AIRCRAFT
A VTOL aircraft (300, 600) includes a lift propeller (312, 612) configured to provide lift during takeoff, landing and hover operations. The lift propeller (312, 612) is configured to be stowed close to a boom surface (323, 623) when not in use during, e.g., cruise flight, to minimize drag around propeller (312, 612) surfaces. The lift propeller (312, 612) may be displaced vertically with respect to the boom (322, 622) when switching to a lift configuration to provide greater separation from the boom (322, 622) to improve lift efficiency and reduce unwanted vibrations. The lift propeller (312, 612) may have a fail-safe configuration that allows the propeller (312, 612) to move passively between lift and stowed configurations, and to fully rotate even when fully retracted.
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, an aircraft is disclosed, comprising: at least one electric propulsion unit; at least one sensor configured to measure at least one aircraft condition; and at least one flight control computer configured to dynamically vary at least one torque command to the at least one electric propulsion unit based at least on the at least one aircraft condition; wherein the at least one electric propulsion unit is configured to generate thrust based on the at least one dynamically varied torque command.
B64D 31/16 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants
B64D 31/06 - Initiating means actuated automatically
B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
Aspects of this present disclosure relate to systems and methods for dynamically moving graphical elements of a user interface of a flight control system. In one embodiment, a method is disclosed comprising: determining aircraft authority limits based on at least one state signal indicating an aircraft state, wherein the aircraft authority limits indicate an extent to which one or more control signals can command the aircraft; determining one or more proximities between the aircraft state and the determined aircraft authority limits; and automatically moving the graphical elements of the user interface to one or more positions on the user interface based on the determined one or more proximities.
B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage
B64D 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
55.
SYSTEMS AND METHODS FOR VIBRATION ATTENUATION IN FLIGHT CONTROL OF AN AIRCRAFT
The present disclosure relates generally to flight control of electric aircraft and other powered aerial vehicles. In one embodiment, an electrical system for an aircraft is disclosed, comprising: at least one processor configured to: receive pilot input indicating a commanded aircraft state, determine an aircraft thrust for achieving the commanded aircraft state, retrieve at least one propeller parameter associated with propeller speeds, wherein the propeller parameter is determined to reduce a structural vibratory response in the aircraft. The at least one processor is further configured to determine a respective command for each propeller of the aircraft to achieve the determined aircraft thrust based on the at least one propeller parameter and control each propeller of the aircraft based on the corresponding respective command.
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, an aircraft is disclosed, comprising: at least one electric propulsion unit; at least one sensor configured to measure at least one aircraft condition; and at least one flight control computer configured to dynamically vary at least one torque command to the at least one electric propulsion unit based at least on the at least one aircraft condition; wherein the at least one electric propulsion unit is configured to generate thrust based on the at least one dynamically varied torque command.
Aspects of this present disclosure relate to flight control of electric aircrafts and other vehicles. In one embodiment, an aircraft is disclosed comprising: a fuselage; two wings; a plurality of lift propellers, the lift propellers disposed aft of the wings during forward flight; plurality of tilt propellers that are tiltable between vertical lift and forward propulsion configurations, the tilt propellers disposed forward of the wings during forward flight; a plurality of tilt propellor actuators that tilt propellers between vertical lift and forward propulsion configurations, the tilt propellor actuators on opposite sides of the fuselage; and a plurality of electrical buses coupled to a flight control computer; wherein the flight control computer is configured to provide control signals for at least one of the lift propellers mounted to one of the wings and one of the tilt propellers mounted to the other wing via the same electrical bus.
Aspects of this present disclosure relate to flight control of electric aircrafts and other vehicles. In one embodiment, an aircraft is disclosed comprising: a fuselage; one or more flight control computers configured to provide control signals; four sets of electrically powered propellers, wherein a first set is disposed forward of a second set both on one side of the fuselage, and wherein a third set is disposed forward of a fourth set both on another side of the fuselage; and a plurality of electrical buses; wherein the one or more flight control computers are configured to provide control signals via one electrical bus of the plurality of electrical buses to: at least one of the first set of propellers and at least one of the fourth set of propellers; and to at least one of the third set of propellers and at least one of the second set of propellers.
B64D 31/16 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants
B64D 31/06 - Initiating means actuated automatically
B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
An electric engine for a vertical takeoff-and-landing aircraft comprising an electric motor assembly including a stator and a rotor. The electric engine may comprise an inverter assembly, a gearbox assembly including a sun gear, and a main shaft including a length of the main shaft that extends from a first end of the main shaft through the gearbox assembly and through the electric motor assembly to a second end of the main shaft. The electric engine may include a hydrodynamic bearing located between the main shaft and sun gear, and a bearing including an inner race mechanically coupled to the main shaft and an outer race mechanically coupled to the rotor. The electric engine may include a bearing including an outer race mechanically coupled to an inner surface of the rotor.
F16H 57/08 - General details of gearing of gearings with members having orbital motion
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 27/30 - Aircraft characterised by electric power plants
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
61.
SYSTEMS AND METHODS FOR ROTOR ASSEMBLIES AND MANUFACTURING THEREOF
A rotor assembly has a sleeve, a rotor hub, and a plurality of tapered magnets disposed circumferentially around an inner diameter of the sleeve. The plurality of tapered magnets are configured to abut on one another. The plurality of tapered magnets includes a first set of tapered magnets and a second set of tapered magnets. Insertion of the first set of tapered magnets axially relative to the second set of tapered magnets is configured to increase a diameter of the sleeve. The rotor hub is configured to retain at least one of the plurality of tapered magnets or the sleeve.
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
62.
SYSTEMS AND METHODS FOR ENHANCING LEAKAGE INDUCTANCE OF POWER TRANSFORMERS
The embodiments of the present disclosure provide systems and methods of forming a transformer with enhanced leakage inductance for power conversion. The transformer may include a toroidal core, a primary winding around a first portion of the toroidal core, a secondary winding around a second portion of the toroidal core different from the first portion, and a magnetic material disposed within a cavity formed by the toroidal core. The magnetic material may comprise a ferrite. The method of forming a transformer may include the steps of providing a toroidal core, winding a primary coil around a first portion of the toroidal core, winding a secondary coil around a second portion of the toroidal core, and disposing a magnetic material within the cavity formed by the toroidal core to enhance the leakage inductance of the transformer.
H01F 41/02 - Apparatus or processes specially adapted for manufacturing or assembling magnets, inductances or transformersApparatus or processes specially adapted for manufacturing materials characterised by their magnetic properties for manufacturing cores, coils or magnets
The embodiments of the present disclosure provide systems and methods of forming a transformer with enhanced leakage inductance for power conversion. The transformer may include a toroidal core, a primary winding around a first portion of the toroidal core, a secondary winding around a second portion of the toroidal core different from the first portion, and a magnetic material disposed within a cavity formed by the toroidal core. The magnetic material may comprise a ferrite. The method of forming a transformer may include the steps of providing a toroidal core, winding a primary coil around a first portion of the toroidal core, winding a secondary coil around a second portion of the toroidal core, and disposing a magnetic material within the cavity formed by the toroidal core to enhance the leakage inductance of the transformer.
A method of controlling a powered lift aircraft comprises receiving, from a pilot input device, an input indicative of one of a powered lift enabled mode or a powered lift disabled mode and controlling the at least one powered lift element to operate the aircraft in a selected one of the powered lift enabled mode or the powered lift disabled mode based on the received input, wherein in the powered lift enabled mode, the at least one powered lift element is controlled based on a state of the aircraft and, wherein in the powered lift disabled mode, the at least one powered lift element is controlled to disable powered lift.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Aircraft engines. Downloadable software and mobile applications; downloadable
software for transportation logistics management;
downloadable software for developing and implementing
algorithms and computer programs in the fields of artificial
intelligence, machine learning, deep learning, high
performance computing, distributed computing,
virtualization, statistical learning, supervised learning,
unsupervised learning, data mining, predictive analytics and
business intelligence; downloadable software for accessing
and booking transportation services; downloadable
communications software for transmitting and receiving
electronic data, texts, images, and video; downloadable
software for the collection, editing, organizing, modifying,
book marking, transmission, storage, and sharing of data and
information; downloadable software for geolocation tracking
of vehicles and transportation passengers; downloadable
software for operating and piloting vehicles; downloadable
ridesharing software; navigation apparatus and instruments
for vehicles; downloadable computer software for the
collection, analysis, editing, organizing, modifying, book
marking, transmission, storage, and sharing of data and
information related to air travel, air travel
infrastructure, air taxi services, and air travel passenger
behavior; downloadable software for collecting and analyzing
customer travel behavior and evaluating customer travel
experiences; downloadable software for designing and
planning air travel routes and comparing travel ease, speed,
efficiency, and cost among and between travel routes;
downloadable software for designing and planning air travel
infrastructure networks and determining optimal placement
for electric vertical takeoff and landing aircraft landing
zones; downloadable customer relationship management
software for use in the field of air travel and air taxi
services; downloadable software for evaluating weather and
related travel conditions; batteries for vehicles; charging
stations for electric vehicles; charging stations for
electric vehicles incorporating landing pads; on-board
computers. Aircraft; airplanes; helicopters; electric vertical takeoff
and landing aircraft; jet electric vertical takeoff and
landing aircraft; vertical air takeoff and landing vehicles;
air vehicles; drones; unmanned and autonomous aerial
vehicles; parts and fittings for the aforesaid goods,
included in this class. Aircraft and air taxi transportation services; providing
aircraft taxi booking services via mobile applications;
airline transportation services; airline ticket reservation
services; airline check-in services; transport by aircraft;
aircraft rental; arranging, coordinating and managing
transfer and transit of electric vertical takeoff and
landing aircraft passengers, crew and luggage; air
transportation of freight; air freight shipping services;
air transportation of passengers and freight; providing
automated check-in and ticketing services for air travelers;
booking of transport; booking of tickets for air travel;
booking of transportation via a website; airport and
heliport services; travel route planning; providing flight
crew services for operating electric vertical takeoff and
landing aircraft; travel, transport and air taxi travel and
transportation information, and booking services of tickets
for travel by air taxi; making reservations and bookings for
transportation by electrically powered aircraft, including
electrically powered aircraft with vertical, short, or
conventional takeoff; air traffic control services; air
navigation services; parking services; providing information
and consulting services relating to the aforesaid services. Providing online non-downloadable software; software as a
service (SaaS) services; providing online non-downloadable
software for transportation logistics management; providing
online non-downloadable software for developing and
implementing algorithms and computer programs in the fields
of artificial intelligence, machine learning, deep learning,
high performance computing, distributed computing,
virtualization, statistical learning, supervised learning,
unsupervised learning, data mining, predictive analytics and
business intelligence; providing online non-downloadable
software for accessing and booking transportation services;
providing online non-downloadable communications software
for transmitting and receiving electronic data, texts,
images, and video; providing online non-downloadable
software for the collection, editing, organizing, modifying,
book marking, transmission, storage, and sharing of data and
information; providing online non-downloadable software for
geolocation tracking of vehicles and transportation
passengers; providing online non-downloadable software for
operating and piloting vehicles; providing online
non-downloadable ridesharing software; research and design
in the fields of aircraft, air travel, and transportation
services; technical support services, namely,
troubleshooting of computer software problems; design and
development of software, vehicle navigation apparatus, and
vehicle navigation equipment; electronic monitoring of
aerial vehicles using computers and sensors to ensure proper
functioning; providing online non-downloadable software for
the collection, analysis, editing, organizing, modifying,
book marking, transmission, storage, and sharing of data and
information related to air travel, air travel
infrastructure, air taxi services, and air travel passenger
behavior; providing online non-downloadable software for
collecting and analyzing customer travel behavior and
evaluating customer travel experiences; providing online
non-downloadable software for designing and planning air
travel routes and comparing travel ease, speed, efficiency,
and cost among and between travel routes; providing online
non-downloadable software for designing and planning air
travel infrastructure networks and determining optimal
placement for electric vertical takeoff and landing aircraft
landing zones; providing online non-downloadable customer
relationship management software for use in the field of air
travel and air taxi services; providing online
non-downloadable software for evaluating weather and related
travel conditions; transportation, traffic and air taxi
planning services, namely, technical consultancy in the
field of transportation, traffic, and air taxi planning
services; data automation and collection service using
proprietary software to evaluate, analyze and collect
service data in the field of electric vertical takeoff and
landing aircraft, air travel, air travel infrastructure and
air taxi services; planning, design and operation of
electric aircraft transportation systems and infrastructure,
including infrastructure for aircraft landing, facilities
and parking; providing information and consulting services
in the field of sustainable urban planning, transportation
planning, and traffic planning.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Aircraft engines. Downloadable software and mobile applications; downloadable
software for transportation logistics management;
downloadable software for developing and implementing
algorithms and computer programs in the fields of artificial
intelligence, machine learning, deep learning, high
performance computing, distributed computing,
virtualization, statistical learning, supervised learning,
unsupervised learning, data mining, predictive analytics and
business intelligence; downloadable software for accessing
and booking transportation services; downloadable
communications software for transmitting and receiving
electronic data, texts, images, and video; downloadable
software for the collection, editing, organizing, modifying,
book marking, transmission, storage, and sharing of data and
information; downloadable software for geolocation tracking
of vehicles and transportation passengers; downloadable
software for operating and piloting vehicles; downloadable
ridesharing software; navigation apparatus and instruments
for vehicles; downloadable computer software for the
collection, analysis, editing, organizing, modifying, book
marking, transmission, storage, and sharing of data and
information related to air travel, air travel
infrastructure, air taxi services, and air travel passenger
behavior; downloadable software for collecting and analyzing
customer travel behavior and evaluating customer travel
experiences; downloadable software for designing and
planning air travel routes and comparing travel ease, speed,
efficiency, and cost among and between travel routes;
downloadable software for designing and planning air travel
infrastructure networks and determining optimal placement
for electric vertical takeoff and landing aircraft landing
zones; downloadable customer relationship management
software for use in the field of air travel and air taxi
services; downloadable software for evaluating weather and
related travel conditions; batteries for vehicles; charging
stations for electric vehicles; charging stations for
electric vehicles incorporating landing pads; on-board
computers. Aircraft; airplanes; helicopters; electric vertical takeoff
and landing aircraft; jet electric vertical takeoff and
landing aircraft; vertical air takeoff and landing vehicles;
air vehicles; drones; unmanned and autonomous aerial
vehicles; parts and fittings for the aforesaid goods,
included in this class. Aircraft and air taxi transportation services; providing
aircraft taxi booking services via mobile applications;
airline transportation services; airline ticket reservation
services; airline check-in services; transport by aircraft;
aircraft rental; arranging, coordinating and managing
transfer and transit of electric vertical takeoff and
landing aircraft passengers, crew and luggage; air
transportation of freight; air freight shipping services;
air transportation of passengers and freight; providing
automated check-in and ticketing services for air travelers;
booking of transport; booking of tickets for air travel;
booking of transportation via a website; airport and
heliport services; travel route planning; providing flight
crew services for operating electric vertical takeoff and
landing aircraft; travel, transport and air taxi travel and
transportation information, and booking services of tickets
for travel by air taxi; making reservations and bookings for
transportation by electrically powered aircraft, including
electrically powered aircraft with vertical, short, or
conventional takeoff; air traffic control services; air
navigation services; parking services; providing information
and consulting services relating to the aforesaid services. Providing online non-downloadable software; software as a
service (SaaS) services; providing online non-downloadable
software for transportation logistics management; providing
online non-downloadable software for developing and
implementing algorithms and computer programs in the fields
of artificial intelligence, machine learning, deep learning,
high performance computing, distributed computing,
virtualization, statistical learning, supervised learning,
unsupervised learning, data mining, predictive analytics and
business intelligence; providing online non-downloadable
software for accessing and booking transportation services;
providing online non-downloadable communications software
for transmitting and receiving electronic data, texts,
images, and video; providing online non-downloadable
software for the collection, editing, organizing, modifying,
book marking, transmission, storage, and sharing of data and
information; providing online non-downloadable software for
geolocation tracking of vehicles and transportation
passengers; providing online non-downloadable software for
operating and piloting vehicles; providing online
non-downloadable ridesharing software; research and design
in the fields of aircraft, air travel, and transportation
services; technical support services, namely,
troubleshooting of computer software problems; design and
development of software, vehicle navigation apparatus, and
vehicle navigation equipment; electronic monitoring of
aerial vehicles using computers and sensors to ensure proper
functioning; providing online non-downloadable software for
the collection, analysis, editing, organizing, modifying,
book marking, transmission, storage, and sharing of data and
information related to air travel, air travel
infrastructure, air taxi services, and air travel passenger
behavior; providing online non-downloadable software for
collecting and analyzing customer travel behavior and
evaluating customer travel experiences; providing online
non-downloadable software for designing and planning air
travel routes and comparing travel ease, speed, efficiency,
and cost among and between travel routes; providing online
non-downloadable software for designing and planning air
travel infrastructure networks and determining optimal
placement for electric vertical takeoff and landing aircraft
landing zones; providing online non-downloadable customer
relationship management software for use in the field of air
travel and air taxi services; providing online
non-downloadable software for evaluating weather and related
travel conditions; transportation, traffic and air taxi
planning services, namely, technical consultancy in the
field of transportation, traffic, and air taxi planning
services; data automation and collection service using
proprietary software to evaluate, analyze and collect
service data in the field of electric vertical takeoff and
landing aircraft, air travel, air travel infrastructure and
air taxi services; planning, design and operation of
electric aircraft transportation systems and infrastructure,
including infrastructure for aircraft landing, facilities
and parking; providing information and consulting services
in the field of sustainable urban planning, transportation
planning, and traffic planning.
67.
SYSTEMS, METHODS, AND MECHANICAL DESIGNS FOR INVERTERS FOR EVTOL AIRCRAFT
An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
In one aspect, this application describes a blade retention system—for a variable pitch aircraft proprotor system—comprising a double conical blade root encapsulated by a split sleeve. Some embodiments described additionally include fail-operational features. The preload of the blade pitch bearings pushes the metallic split sleeve into the bond line with the blade root.
Apparatus, systems, and methods for a propeller blade retention system. The retention system may include a hub including a socket formed by an inner surface of the hub, a blade extending into the socket and a retention sleeve having a first portion and a second portion. The retention system may include a filler sleeve disposed between the blade and the second portion of the retention sleeve, a first bearing disposed between the second portion of the retention sleeve and the inner surface of the hub, the first bearing having a first race, and a second bearing disposed between the first portion of the retention sleeve and the inner surface of the hub, the second bearing having a second race. The retention system may include a cap comprising a body portion and a flange portion. The retention system may include a shim carrier.
Systems and methods for backlash measurement and monitoring are disclosed for an actuator having a motor end and an output end. The method may include: driving the motor end of the actuator to one endpoint; measuring, using a first sensor, a motor-end initial position value associated with the motor end; measuring, using a second sensor, an output-end initial position value associated with the output end; driving the motor end of the actuator to another endpoint; measuring a motor-end final position value using the first sensor and an output-end final position value using the second sensor; determining a backlash value based on the motor-end initial position value, output-end initial position value, motor-end final position value, and output-end final position value; generating a signal based on comparing the backlash value to a predetermined threshold; and displaying a notification indicative of an operational condition of the actuator based on the signal.
An aircraft system for damping movement of a structural flight element. The aircraft system including a moveable aircraft structure, a power source, a controller, a resistor, and a first transistor connected in series to the resistor. When the power source of the aircraft is providing power, the controller controls the first transistor to prevent current flow through its terminals and through the resistor. Further, when the power source of the aircraft is not providing power, the first transistor allows current generated by a back EMF (electromotive force) voltage to flow through its terminals and through the resistor, the back EMF voltage being created by movement of the moveable aircraft structure.
H03K 17/56 - Electronic switching or gating, i.e. not by contact-making and -breaking characterised by the use of specified components by the use, as active elements, of semiconductor devices
72.
SYSTEMS AND METHODS FOR ELECTRIC DAMPING OF AIRCRAFT FLIGHT CONTROL SURFACES AND PROPELLERS
An aircraft system for damping movement of a structural flight element. The aircraft system including a moveable aircraft structure, a power source, a controller, a resistor, and a first transistor connected in series to the resistor. When the power source of the aircraft is providing power, the controller controls the first transistor to prevent current flow through its terminals and through the resistor. Further, when the power source of the aircraft is not providing power, the first transistor allows current generated by a back EMF (electromotive force) voltage to flow through its terminals and through the resistor, the back EMF voltage being created by movement of the moveable aircraft structure.
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
B64C 13/50 - Transmitting means with power amplification using electrical energy
H02P 3/22 - Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters for stopping or slowing an individual dynamo-electric motor or dynamo-electric converter for stopping or slowing an AC motor by short-circuit or resistive braking
An electrical system for an aircraft, comprising at least one processor configured to: receive aircraft movement information, detect that the movement information indicates a potential crash, detect a loss of continuity in at least one low voltage wire, and blow a battery pack fuse to disconnect supply of the high voltage power to the aircraft.
B60L 3/04 - Cutting-off the power supply under fault conditions
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
H01M 50/583 - Devices or arrangements for the interruption of current in response to current, e.g. fuses
H02H 7/20 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for electronic equipment
74.
SYSTEMS AND METHODS FOR HIGH VOLTAGE BATTERY CHARGING AND VERTIPORT OPERATIONS
Aspects of the present disclosure generally relate to systems and methods for the configuration and control of charging and cooling systems for aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a method of charging an aircraft is disclosed comprising: receiving a mode of operation indicating whether battery packs of the aircraft are connected in parallel prior to joining a charging bus, receiving charging protocol information, and controlling charging operations of the battery packs based on the mode of operation and the charging protocol information.
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
B64F 1/35 - Ground or aircraft-carrier-deck installations for supplying electrical power to stationary aircraft
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
75.
SYSTEMS AND METHODS FOR ROUTING ELECTRICAL WIRING THROUGH AN AIRCRAFT STRUCTURE
The embodiments of the present disclosure provide an aircraft assembly. The aircraft assembly includes an aircraft structure comprising a component with a plurality of wire openings. A plurality of high voltage wires are disposed in the wire openings in the component such that each wire opening receives one high voltage wire, and the each wire opening has an opening size larger than a size of the one high voltage wire, the opening size being smaller than a size of a connector attached to an end of the one high voltage wire. The high voltage wires are installed in the wire openings before curing the aircraft structure.
A control system for a powered lift aircraft includes a pilot input device, at least one powered lift element configured to provide powered lift support to the aircraft, and a processor. The processor is configured to receive, from the pilot input device, an input indicative of one of a powered lift enabled mode or a powered lift disabled mode and control the at least one powered lift element to operate the aircraft in a selected one of the powered lift enabled mode or the powered lift disabled mode based on the received input. When the aircraft is in the powered lift enabled mode, the at least one processor is configured to control the at least one powered lift element based on a state of the aircraft. When the aircraft is in the powered lift disabled mode, the at least one processor is configured to control the at least one powered lift element to disable powered lift.
The embodiments of the present disclosure provide an aircraft assembly. The aircraft assembly includes an aircraft structure comprising a component with a plurality of wire openings. A plurality of high voltage wires are disposed in the wire openings in the component such that each wire opening receives one high voltage wire, and the each wire opening has an opening size larger than a size of the one high voltage wire, the opening size being smaller than a size of a connector attached to an end of the one high voltage wire. The high voltage wires are installed in the wire openings before curing the aircraft structure.
A system includes a first frame for mounting to the aircraft; a second frame for mounting the proprotor, the second frame being rotatably mounted to the first frame; a first gear located along the rotation axis of the second frame and fixed in position relative to the first frame; a pinion that moves with the second frame and engages the first gear such that the pinion revolves around the first gear, causing the pinion to rotate; a cam that is fixedly connected to the pinion such that the cam rotates with the pinion; and a control rod operatively coupled at a first end with the cam such that rotation of the cam can cause translation of the control rod, wherein the control rod can be coupled at a second end to the blades of the proprotor such that translation of the control rod alters the pitch of the blades.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
80.
Inverter circuits and electrical propulsion systems for eVTOL aircraft
An electrical propulsion system includes an electrical motor configured to drive one or more propellers of the aircraft, a capacitor configured to stabilize a direct current (DC) bus voltage, a first inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to alternate current (AC) voltages to drive a first set of stator windings of the electrical motor, in response to a first pulse width modulation (PWM) vector, and a second inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to AC voltages to drive a second set of stator windings of the electrical motor, in response to a second PWM vector. The first PWM vector and the second PWM vector are substantially equal and opposite vectors.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
81.
SYSTEMS AND METHODS FOR IMPROVED BATTERY ASSEMBLIES FOR EVTOL AIRCRAFT
This disclosure relates generally to high voltage power supply (HVPS) systems and battery assemblies for aircraft that use electrical propulsion systems. In one embodiment, an apparatus for safely venting battery cells in thermal runaway is provided. The apparatus includes: a mechanical support layer, the mechanical support layer configured to be attached to a battery assembly; and a vent flap layer attached to the mechanical support layer, the vent flap layer including vent flaps corresponding to battery cells in the battery assembly. Each vent flap includes one or more portions configured to deform to permit flow of gas from the battery cell corresponding to the vent flap.
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 50/367 - Internal gas exhaust passages forming part of the battery cover or caseDouble cover vent systems
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
82.
SYSTEMS AND METHODS FOR IMPROVED BATTERY ASSEMBLIES FOR EVTOL AIRCRAFT
This disclosure relates generally to an apparatus for organizing battery cells. The apparatus includes a block including: sleeves forming chambers, a first sheet configured to locate the sleeves, and a foam structure surrounding the sleeves. Each chamber is configured to accommodate a battery cell. The block is configured to: organize the battery cells into battery cell groups, separate each battery cell group from its adjacent battery cell groups using a thermally insulating material, and prevent gas from entering into each battery cell group from its adjacent battery cell groups. Each battery cell group includes a plurality of the battery cells, each of the battery cells in the battery cell group is adjacent to at least another of the battery cells in the battery cell group. Each battery cell group is adjacent to at least another battery cell group.
H02H 5/04 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal non-electric working conditions with or without subsequent reconnection responsive to abnormal temperature
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
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
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
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
H01M 50/209 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for prismatic or rectangular cells
H01M 50/213 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for cells having curved cross-section, e.g. round or elliptic
H01M 50/229 - Composite material consisting of a mixture of organic and inorganic materials
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 50/242 - 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 50/291 - 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
H01M 50/383 - Flame arresting or ignition-preventing means
H01M 50/583 - Devices or arrangements for the interruption of current in response to current, e.g. fuses
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Downloadable software and mobile applications; downloadable
software for transportation logistics management;
downloadable software for developing and implementing
algorithms and computer programs in the fields of artificial
intelligence, machine learning, deep learning, high
performance computing, distributed computing,
virtualization, statistical learning, supervised learning,
unsupervised learning, data mining, predictive analytics and
business intelligence; downloadable software for accessing
and booking transportation services; downloadable
communications software for transmitting and receiving
electronic data, texts, images, and video; downloadable
software for the collection, editing, organizing, modifying,
book marking, transmission, storage, and sharing of data and
information; downloadable software for geolocation tracking
of vehicles and transportation passengers; downloadable
software for operating and piloting vehicles; downloadable
ridesharing software; navigation apparatus and instruments
for vehicles; downloadable computer software for the
collection, analysis, editing, organizing, modifying, book
marking, transmission, storage, and sharing of data and
information related to air travel, air travel
infrastructure, air taxi services, and air travel passenger
behavior; downloadable software for collecting and analyzing
customer travel behavior and evaluating customer travel
experiences; downloadable software for designing and
planning air travel routes and comparing travel ease, speed,
efficiency, and cost among and between travel routes;
downloadable software for designing and planning air travel
infrastructure networks and determining optimal placement
for electric vertical takeoff and landing aircraft landing
zones; downloadable customer relationship management
software for use in the field of air travel and air taxi
services; downloadable software for evaluating weather and
related travel conditions; batteries for vehicles; charging
stations for electric vehicles; charging stations for
electric vehicles incorporating landing pads; on-board
computers. Providing online non-downloadable software; software as a
service (saas) services; providing online non-downloadable
software for transportation logistics management; providing
online non-downloadable software for developing and
implementing algorithms and computer programs in the fields
of artificial intelligence, machine learning, deep learning,
high performance computing, distributed computing,
virtualization, statistical learning, supervised learning,
unsupervised learning, data mining, predictive analytics and
business intelligence; providing online non-downloadable
software for accessing and booking transportation services;
providing online non-downloadable communications software
for transmitting and receiving electronic data, texts,
images, and video; providing online non-downloadable
software for the collection, editing, organizing, modifying,
book marking, transmission, storage, and sharing of data and
information; providing online non-downloadable software for
geolocation tracking of vehicles and transportation
passengers; providing online non-downloadable software for
operating and piloting vehicles; providing online
non-downloadable ridesharing software; research and design
in the fields of aircraft, air travel, and transportation
services; technical support services, namely,
troubleshooting of computer software problems; design and
development of software, vehicle navigation apparatus, and
vehicle navigation equipment; electronic monitoring of
aerial vehicles using computers and sensors to ensure proper
functioning; providing online non-downloadable software for
the collection, analysis, editing, organizing, modifying,
book marking, transmission, storage, and sharing of data and
information related to air travel, air travel
infrastructure, air taxi services, and air travel passenger
behavior; providing online non-downloadable software for
collecting and analyzing customer travel behavior and
evaluating customer travel experiences; providing online
non-downloadable software for designing and planning air
travel routes and comparing travel ease, speed, efficiency,
and cost among and between travel routes; providing online
non-downloadable software for designing and planning air
travel infrastructure networks and determining optimal
placement for electric vertical takeoff and landing aircraft
landing zones; providing online non-downloadable customer
relationship management software for use in the field of air
travel and air taxi services; providing online
non-downloadable software for evaluating weather and related
travel conditions; transportation, traffic and air taxi
planning services, namely, technical consultancy in the
field of the science of transportation, traffic, and air
taxi planning services; data automation and collection
service using proprietary software to evaluate, analyze and
collect service data in the field of electric vertical
takeoff and landing aircraft, air travel, air travel
infrastructure and air taxi services; planning, design and
operation of electric aircraft transportation systems and
infrastructure, including infrastructure for aircraft
landing, facilities and parking; providing information and
consulting services in the field of sustainable urban
planning, transportation planning, and traffic planning.
84.
Systems and methods for improved battery assemblies for EVTOL aircraft
This disclosure relates generally to high voltage power supply (HVPS) systems and battery assemblies for aircraft that use electrical propulsion systems. In one embodiment, an apparatus for safely venting battery cells in thermal runaway is provided. The apparatus includes: a mechanical support layer, the mechanical support layer configured to be attached to a battery assembly; and a vent flap layer attached to the mechanical support layer, the vent flap layer including vent flaps corresponding to battery cells in the battery assembly. Each vent flap includes one or more portions configured to deform to permit flow of gas from the battery cell corresponding to the vent flap.
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 50/367 - Internal gas exhaust passages forming part of the battery cover or caseDouble cover vent systems
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
85.
SYSTEMS AND METHODS FOR OIL MAINTENANCE IN GEARBOXES FOR eVTOL AIRCRAFT
An electric propulsion system comprising an electric motor assembly. The electric motor assembly may include a housing having an internal volume, a stator ring disposed about a perimeter of the internal volume, and a rotor positioned within the stator. The electric motor assembly may include a main shaft connected to the rotor via a gear reduction, wherein the main shaft extends through the rotor. The electric motor assembly may include a collar connected to the main shaft, wherein the collar encircles the main shaft, and at least a portion of the collar is configured to direct a fluid away from the main shaft and toward the stator ring.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
86.
Systems and methods for oil maintenance in gearboxes for eVTOL aircraft
An electric propulsion system comprising an electric motor assembly. The electric motor assembly may include a housing having an internal volume, a stator ring disposed about a perimeter of the internal volume, and a rotor positioned within the stator. The electric motor assembly may include a main shaft connected to the rotor via a gear reduction, wherein the main shaft extends through the rotor. The electric motor assembly may include a collar connected to the main shaft, wherein the collar encircles the main shaft, and at least a portion of the collar is configured to direct a fluid away from the main shaft and toward the stator ring.
H02K 11/33 - Drive circuits, e.g. power electronics
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
87.
Aircraft electric propulsion system with overlapping shafts for gearbox oil distribution
An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/30 - Aircraft characterised by electric power plants
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
88.
Systems and methods for improved gearboxes for evtol aircraft
The present disclosure relates generally to a method for balancing a rotor of an electrical engine of an electrical propulsion system comprising: identifying an axis of rotation of a rotor, wherein the rotor comprises a sacrificial layer having a mass M formed along a circumference of the rotor; determining an imbalance present in the rotor by rotating the rotor about the axis of rotation, wherein determining an imbalance includes marking the rotor, rotating the rotor, and detecting an amplitude of the imbalance; calculating an amount of mass k to add or remove at a position p along the sacrificial layer such that a center of mass of the rotor coincides with the axis of rotation of the rotor; and removing an amount of mass r from the sacrificial layer such that an amount of remainder mass n is present along the circumference of the rotor.
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
89.
Systems, methods, and mechanical designs for inverters for EVTOL aircraft
An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
90.
Systems and methods for oil management in gearboxes for eVTOL aircraft
An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.
An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 27/30 - Aircraft characterised by electric power plants
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
92.
Systems, methods, and mechanical designs for inverters for eVTOL aircraft
An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
93.
Systems, methods, and mechanical designs for inverters for eVTOL aircraft
An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
94.
Systems, methods, and mechanical designs for inverters for eVTOL aircraft
An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 15/06 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train characterised by the form of the current used in the control circuit using substantially-sinusoidal AC
B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
F16B 2/06 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action
F16H 57/08 - General details of gearing of gearings with members having orbital motion
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
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
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
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
95.
Systems and methods for power distribution in electric aircraft
A electric aircraft power distribution system includes a first battery pack connected to at least a first load and to a common bus that connects the first battery pack in parallel to at least a second battery pack; a first electrical component electrically connected between the first battery pack and the first load and configured to disconnect the first load from the first battery pack in response to current above a first threshold current, wherein the first electrical component has a first disconnection time at the first threshold current; and a second electrical component electrically connected between the first battery pack and the common bus and configured to disconnect the first battery pack from the common bus in response to current above a second threshold current, wherein the second electrical component has a second disconnection time at the second threshold current that is higher than the first disconnection time.
An electric propulsion system for a vertical takeoff-and-landing aircraft having an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, a gearbox assembly, and electric motor assembly may each abut at least one of the others. The electric engine may use a liquid, such as oil, for cooling and lubricating components of the inverter assembly, gearbox assembly, and electric motor assembly. Further, the electric engine may use volumes of oil for cooling and lubricating components below a threshold volume so that the electric engines do not require a fire protective barrier.
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
97.
SYSTEMS AND METHODS FOR LOW VOLTAGE WIRING FOR EVTOL AIRCRAFT
In an embodiment, a system may comprise at least two power supplies which may comprise a first power source, a first step-down converter, a first switching device, a first bus, a second power source, a second step-down converter, a second switching device, and a second bus, the first and second buses being electrically separate. An exemplary system may further comprise an alternate power supply comprising a third power source and an alternate step-down converter connected to at least the first and second buses via at least a third switching device, the alternate power supply acting as a backup power supply configured to be used after a failure of one or more of the at least two power supplies. In some embodiments, the first and second switching devices may be controlled by at least a first controller and the at least third switching device may be controlled by an alternate controller.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 58/21 - 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 having the same nominal voltage
09 - Scientific and electric apparatus and instruments
39 - Transport, packaging, storage and travel services
41 - Education, entertainment, sporting and cultural services
Goods & Services
Flight simulators; downloadable software for pilot training; downloadable flight simulator software Air transport; booking of transport; arranging, coordinating, and managing transfer and transit of electric vertical takeoff and landing aircraft passengers and crew Flight training; flight training featuring flight simulators; online downloadable and non-downloadable flight simulator game software
99.
VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH AFT ROTOR TILTING
A vertical take-off and landing aircraft may include a fuselage; at least one wing connected to the fuselage; a first plurality of proprotors mounted to the at least one wing, positioned at least partially forward of a leading edge of the at least one wing, and tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft; and a second plurality of proprotors mounted to the at least one wing, positioned at least partially rearward of a trailing edge of the at least one wing, and tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft; wherein the first plurality of proprotors and the second plurality of proprotors are independently tiltable.
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
A rotor blade pitch actuator has a first and second motor configured to control the rotor blade pitch. An actuator control system is configured to drive the first and second motor such that backlash is either eliminated from the system or minimized to an acceptable level.
B64C 27/625 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including rotating masses or servo rotors
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
