A motor gearbox assembly includes a gearbox housing that encloses a motor comprising a stator and a rotor, which is rotatable with respect to the stator. The rotor is rotatably mounted on a main power output shaft and is coupled to a first rotor pinion gear. The assembly further comprises a layshaft rotatably mounted in the gearbox housing outside of the motor, a first layshaft gear at a first axial end of the layshaft on a first side of the rotor and the stator, the first layshaft gear being engaged with the first rotor pinion gear and a second layshaft gear at a second axial end of the layshaft, the second axial end being on a second side of the rotor and the stator that is opposite the first side, the second layshaft gear being engaged with a power output gear coupled to the main power output shaft.
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64D 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
2.
SYSTEMS AND METHODS FOR LIFTER MOTOR COOLING IN EVTOL AIRCRAFT
An apparatus for aircraft propulsion includes a propeller and an electric engine mounted to a support structure and configured to rotate the propeller. The electric engine is located in an enclosure, with a heat transfer element thermally coupled to the electric engine, An air inlet is located at an upper side of the support structure and the air inlet is configured to receive downwash from the propeller. An air outlet is located at the upper side of the support structure, and the air outlet is configured to exhaust the downwash from the heat transfer element.
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.
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
B64D 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
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 system of an aircraft is disclosed, configured to determine one or more desired commands for the aircraft, retrieve engine information for at least one electric propulsion unit (EPU) of a plurality of EPUs of the aircraft, wherein the engine information includes at least one time-based metric for temperature associated with the at least one EPU, generates control commands based on the received engine information, and controls effectors according to the generated control commands to meet the desired commands of the aircraft.
Principles described herein allow for wings to be optimized for aerodynamic and structural efficiency while reducing planform compromises required to address wing tip stall problems. All-moving outboard wings allow the outboard wing local angle of attack to be changed relative to the inner wing region to avoid tip stall at high aircraft angles of attack, such as that which is required for low-speed flight. During high-speed cruise flight, at low aircraft angle of attack, the outboard wing local angle of attack can be increased to achieve an ideal elliptical lift distribution.
The present disclosure relates generally to control of systems with modular devices. In one embodiment, a device is disclosed, comprising: a plurality of electrical contacts; and at least one processor, wherein the plurality of electrical contacts are configured to be coupled to one of: a first voltage source or a second voltage source, wherein the at least one processor is configured to determine an identification (ID) value for the device by determining voltage values that are based on a coupling configuration of the plurality of electrical contacts.
A vertical take-off and landing aircraft includes a fuselage, at least one wing connected to the fuselage, a plurality of rotors connected to the at least one wing for providing lift for vertical take-off and landing of the aircraft and a plurality of proprotors connected to 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.
A vertical take-off and landing aircraft includes a fuselage, at least one wing connected to the fuselage, a plurality of rotors connected to the at least one wing for providing lift for vertical take-off and landing of the aircraft and a plurality of proprotors connected to 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.
A vertical take-off and landing aircraft includes a fuselage, at least one wing connected to the fuselage, a plurality of rotors connected to the at least one wing for providing lift for vertical take-off and landing of the aircraft and a plurality of proprotors connected to 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.
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.
G05B 19/404 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for compensation, e.g. for backlash, overshoot, tool offset, tool wear, temperature, machine construction errors, load, inertia
14.
SYSTEMS AND METHODS FOR AUTOPILOT INTERFACE AND NUDGE CONTROL
The present disclosure relates generally to flight control of aircraft and other powered aerial vehicles. In one embodiment, an aircraft is disclosed, comprising: an autopilot system configured to control the aircraft based on stored flight trajectory information and a flight control system configured to provide a limit to the autopilot system, wherein the limit is based on at least one of: a state of high voltage distribution, a state of an electric engine, or a flight phase of the aircraft. The autopilot system is configured to determine one or more commands based on the limit received from the flight control system and provide the one or more commands to the flight control system to control the aircraft.
G05D 109/22 - Aircraft, e.g. drones with fixed wings
G05D 105/22 - Specific applications of the controlled vehicles for transportation of humans
G05D 1/82 - Limited authority control, e.g. enforcing a flight envelope
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
B64C 13/50 - Transmitting means with power amplification using electrical energy
15.
SYSTEMS AND METHODS FOR AIRCRAFT ENERGY OPTIMIZATION
Disclosed embodiments generally relate to systems and methods for flight control of aircrafts. In some embodiments, a flight control system is configured to determine desired commands for the electric aircraft, determine at least one reference command for an effector based on the desired commands and one or more aircraft conditions, monitor energy states of the plurality of battery packs, where 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 effector 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.
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
B64D 31/06 - Initiating means actuated automatically
16.
SYSTEMS, METHODS, AND MECHANICAL DESIGNS FOR INVERTERS FOR EVTOL AIRCRAFT
An inverter assembly for an electrical propulsion system comprises at least one printed circuit board assembly (PCBA) having a plurality of power modules, a thermal plate comprising one or more channels, a plurality of fin arrays thermally coupled to the plurality of power modules, and a housing. The plurality of fin arrays are configured to receive a fluid from the one or more channels. The at least one printed circuit board assembly and the thermal plate are disposed within 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
G01P 3/487 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by rotating magnets
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
17.
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.
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 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
B64D 27/359 - Arrangements for on-board electric energy production, distribution, recovery or storage using capacitors
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-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 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64D 35/026 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants the electric power plant being integral with the propeller or rotor
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
18.
AERODYNAMIC DESIGN OF PROPELLER BLADES IN VTOL AIRCRAFT
A vertical takeoff and landing (VTOL) aircraft lift propeller design achieves high thrust and low noise a lift configuration and low drag when stowed in a cruise configuration. The lift propeller may comprise a two-bladed propeller having specially designed low-drag contours, or may comprise a four-bladed propeller having oblique angles to minimize drag when stowed. The lift propeller may be stowed at a small angle with respect to a fuselage of the VTOL aircraft in the cruise configuration to minimize drag.
19.
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
39 - Transport, packaging, storage and travel services
41 - Education, entertainment, sporting and cultural services
Goods & Services
Airport services; airport services featuring transit lounge
facilities for passenger relaxation (Term considered too
vague by the International Bureau pursuant to Rule 13 (2)
(b) of the Regulations). Flight training; flight training featuring flight
simulators; providing online non-downloadable flight
simulator game software.
21.
SYSTEMS AND METHODS FOR MANAGING EVTOL FLIGHT IN ICING
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 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.
Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
“A tilt apparatus of an aircraft, comprising: a propeller, a motor assembly, a thermal transfer device thermally coupled to the motor assembly, and a nacelle coupled to the motor assembly. The tilt apparatus further comprises a tilt actuator that tilts the nacelle, the motor assembly, and the propeller with respect to a body of the aircraft between a lift configuration and a cruise configuration. The tilt apparatus also comprises a mechanical coupling that actuates a variable portion of the nacelle as a function of a tilt angle of the nacelle with respect to the body. The variable portion is actuated such that an opening size of an air inlet of the nacelle is larger in the lift configuration than in the cruise configuration. When the propeller is in the lift configuration, the air inlet directs a portion of a propwash through the air inlet to the thermal transfer device.”
Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
25.
SYSTEMS AND METHODS FOR MANAGING EVTOL FLIGHT IN ICING
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 generate heat at targeted areas of a propeller assembly by electric heating systems that utilize propeller motion.
A motor gearbox assembly includes a gearbox housing that encloses a motor comprising a stator and a rotor, which is rotatable with respect to the stator. The rotor is rotatably mounted on a main power output shaft and is coupled to a first rotor pinion gear. The assembly further comprises a layshaft rotatably mounted in the gearbox housing outside of the motor, a first layshaft gear at a first axial end of the layshaft on a first side of the rotor and the stator, the first layshaft gear being engaged with the first rotor pinion gear and a second layshaft gear at a second axial end of the layshaft, the second axial end being on a second side of the rotor and the stator that is opposite the first side, the second layshaft gear being engaged with a power output gear coupled to 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
27.
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.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
In one aspect the subject matter herein describes a cable tilt actuator for an aircraft propulsion unit. One embodiment comprises: a cable spool, fore and aft cable sections, a compression beam, a compression beam guide, and a linear actuator. As the linear actuator drives the compression beam, relative rotation is imposed between the compression beam and the spool. Described, in one aspect, is an embodiment configured to tilt an aircraft propulsion unit.
A propulsion system, comprising: a motor assembly including a stator and a rotor, a heat exchanger configured to receive air to cool a liquid, and a thermal plate including one or more channels configured to convey the liquid from the heat exchanger to the motor assembly. The heat exchanger is mechanically and fluidically coupled to the thermal plate.
B64D 27/30 - Aircraft characterised by electric power plants
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
31.
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.
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
32.
Systems and methods for distributing fluid in a rotating chamber
A fluid distribution system for an engine including a fluid chamber. The fluid distribution system may include a first control opening in fluid communication with the fluid chamber. A rotor coupled to the fluid chamber may be configured to rotate the chamber about the axis to cause the fluid chamber to distribute fluid through the first control opening. A first channel coupled to the first control opening may be configured to receive the fluid through the first control opening. A second control opening may be formed in the first channel. A relief opening in the first channel may be configured to expose the first channel to an ambient pressure outside the first channel. The relief opening may be located downstream of the first control opening in a fluid flow direction of the first channel and upstream of the second control opening in the fluid flow direction of the first channel.
40 - Treatment of materials; recycling, air and water treatment,
09 - Scientific and electric apparatus and instruments
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Manufacturing of aircraft Flight control systems for aircraft; software for flight control systems for aircraft; hardware for aircraft; navigation apparatus and instruments for aircraft; none of the foregoing for use in the fields of risk and compliance management, or to design, define, automate, monitor, enforce, and track business processes. Aircraft repair and maintenance services Research, design, and development of aircraft, flight control systems for aircraft navigation apparatus and instruments for aircraft, and hardware for aircraft; design, development, installation, and maintenance of flight control software for military and defense aircraft; technological consultation for aircraft; none of the foregoing for use in the fields of risk and compliance management, or to design, define, automate, monitor, enforce, and track business processes
34.
SYSTEMS AND METHODS FOR PROPELLER THRUST PROTECTION
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.
A system for controlling high voltage power comprises: a first controller configured to: receive first sensor data, determine a first circuitry state based on the first sensor data, and output a first signal indicative of the first circuitry state; a second controller configured to: receive second sensor data, determine a second circuitry state based on the second sensor data, and output a second signal indicative of the second circuitry state; and circuitry configured to: receive the first signal and the second signal, maintain a state of a high voltage control device when the first signal and the second signal indicate a different value, and change a state of the high voltage control device when the first signal and the second signal indicate the same value.
36.
SYSTEMS AND METHODS FOR ELECTRICAL MONITORING AND PRE-CHARGING OF CONNECTED BATTERY PACKS
The present disclosure relates generally to methods for pre-charge control, including a. method comprising: receiving a first selection of a first or second battery pack to pre-charge circuitry of a first and second battery pack by a first battery management unit associated with the first battery pack, receiving a second selection of the first or second battery pack to pre-charge the circuitry of the first and second battery packs by a second battery management unit associated with the second battery pack, selecting one of the first and second battery packs to pre-charge the circuitry of the first and second battery packs based on the received battery pack selections, and controlling circuitry of the selected battery pack to perform the pre-charge.
37.
SYSTEMS AND METHODS FOR BATTERY CHARGING MODE SELECTION
A control system for charging an aircraft, comprising: a battery pack, an input device configured to enable a user to select between different charging modes, two main contactors connecting the battery pack to an electric propulsion unit (EPU) load and an auxiliary load, a EPU load contactor connecting the battery pack to the EPU load and a controller configured to receive the selected charge mode and control the contactors, keep the two main contactors open upon receiving a user selection to charge in a first mode, close the two main contactors and keep an EPU load contactor open upon receiving a user selection to charge in a second mode, and close the two main contactors and the EPU load contactor upon receiving a user selection to charge in a third mode.
B60L 53/62 - Monitoring or controlling charging stations in response to charging parameters, e.g. current, voltage or electrical charge
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
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
The present disclosure relates generally to controlling an aircraft to avoid overheating components. In one embodiment, a method is disclosed, comprising: receiving first sensor data indicating at least one attribute of high voltage wiring of the aircraft; receiving a state of operation of the aircraft; determining a proximity of a temperature of the high voltage wiring to a temperature limit based on the first sensor data and the state of operation of the aircraft; and controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit based on the determined proximity.
A method for manufacturing a rotor assembly of an electric engine, comprising: loading a first and second plurality of magnets in a magnet insertion tool, loading a sleeve in the magnet insertion tool, performing a first insertion movement using the magnet insertion tool, wherein the first insertion movement comprises moving one of the first plurality of magnets or the second plurality of magnets in a radial direction of the sleeve, and performing a second insertion movement using the magnet insertion tool, wherein the second insertion movement comprises moving one of the first plurality of magnets or the second plurality of magnets with respect to the sleeve in an axial direction of the sleeve. The radius of the sleeve is expanded in a radial direction during one of the first insertion movement or the second insertion movement.
H02K 15/035 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets on the 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, 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.
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Downloadable computer programs using artificial intelligence (AI) for use in aviation safety, autonomous aircraft operation, assisting pilots in aircraft navigation, and air traffic control (ATC); downloadable computer programs using artificial intelligence (AI) for use in flight training, aeronautical decision-making (ADM) related to the operation of aircraft, simulation software for modeling and analyzing weather; downloadable computer programs using artificial intelligence (AI) for machine learning for use in robots and robotics applications; downloadable computer programs using artificial intelligence (AI) for machine learning for use in the field of military, defense, security, and military aviation autonomy, and planning, conducting, and simulating flight missions; none of the foregoing for use in the fields of risk and compliance management or to design, define, automate, monitor, enforce, and track business processes. Software as a Service (SaaS) services featuring software using artificial intelligence (AI) for use in flight training, aeronautical decision-making (ADM) related to the operation of aircraft; Software as a Service (SaaS) services featuring software using artificial intelligence (AI) for use in flight training, aeronautical decision-making (ADM) related to the operation of aircraft, simulation software for modeling weather, analyzing weather; Software as a Service (SaaS) services featuring software using artificial intelligence (AI) for machine learning for use in robots and robotics applications; Software as a Service (SaaS) services featuring software using artificial intelligence (AI) for machine learning for use in the field of military, defense, security, and military aviation autonomy, and planning, conducting, and simulating flight missions; Research and development of software using artificial intelligence (AI) in the fields of military, defense, security, and military aviation; Design and development of computer software for use in the field of artificial intelligence (AI) and autonomy in the field of military, defense, security, and military aviation; none of the foregoing for use in the fields of risk and compliance management or to design, define, automate, monitor, enforce, and track business processes.
42.
FLYING WING VERTICAL TAKE-OFF AND LANDING AIRCRAFT
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.
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
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]
45.
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]
48.
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
51.
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
54.
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
55.
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 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
56.
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
57.
Aircraft propulsion system including pump gear driven by planetary gearbox assembly
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.
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 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
B64D 27/359 - Arrangements for on-board electric energy production, distribution, recovery or storage using capacitors
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-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 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64D 35/026 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants the electric power plant being integral with the propeller or rotor
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
H02K 15/035 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets on the rotor
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
“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
59.
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
60.
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
61.
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.
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
68.
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.
B64C 27/24 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
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
G01P 3/487 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by rotating magnets
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
83.
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.
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
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
84.
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 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
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.
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
97.
SYSTEMS AND METHODS FOR FLIGHT CONTROL OF 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, 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.
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 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
