Abstract: An assembly of an electric propulsion system with power harvesting system and a method of manufacturing the electric propulsion system are disclosed. The electric propulsion system may include a propulsor configured to generate thrust. The electric propulsion system may include an electric motor configured to power the propulsor. The electric motor may include a stator configured to produce a magnetic field, wherein the stator may include a winding comprising an electrically conductive material. The electric motor may further include a rotor configured to be rotated by the magnetic field from the stator, wherein the rotor may include a coil attached to the rotor configured to induce an electric potential and an airgap between the stator and the coil.
Abstract: A visual system for an electric vertical takeoff and landing (eVTOL) aircraft is illustrated. The system comprises an exterior visual device, a flight controller, and a pilot display. The exterior visual device is attached to the aircraft and is configured to detect an input of views of the exterior environment of the electric aircraft. The flight controller is communicatively connected to the aircraft, receives input from the exterior visual device, and generates an output of the view of the exterior environment of the aircraft as a function of the input. The pilot display is in the aircraft, receives the output of the view of exterior environment of the electric aircraft, and displays the output to a user.
Abstract: Aspects relate to systems and methods of use for a crash safe battery pack that includes a case, a first battery module located within the case and mounted to the case with at least a breakaway mount, a second battery module located within the case, a frangible connection configured to provide electrical conduction between the first battery module and the second battery module, and a die configured to contact and separate the frangible connection when the crash safe battery pack is impacted with a sufficiently great connection breaking force.
Type:
Grant
Filed:
June 30, 2022
Date of Patent:
January 9, 2024
Assignee:
BETA AIR, LLC
Inventors:
Sean Richard Donovan, Sam Wagner, Peter Adam Gottlieb
Abstract: A distributed control system with supplemental attitude adjustment including an aircraft control having an engaged state and a disengaged state. The system also including a plurality of flight components and a plurality of aircraft components communicatively connected to the plurality of flight components, wherein each aircraft component is configured to receive an aircraft command and generate a response command directing the flight components as a function of supplemental attitude. The supplemental attitude based at least in part on the engagement datum and generating a supplemental attitude includes choosing a position supplemental attitude if the aircraft control is disengaged and choosing a velocity supplemental attitude if the aircraft control is engaged. In generating the response command, the aircraft attitude is combined with the supplemental attitude to obtain an aggregate attitude, and the aircraft component is configured to generate the response command based on the aggregate attitude.
Abstract: In an aspect, a system for displaying synoptic information is provided. A processor of the system may retrieve and/or receive operation data related to the use of a corresponding electric aircraft. Operation data may be displayed on a display of the system using one or more visual representations or audio presentations.
Abstract: In an aspect, this disclosure is related to apparatus and method for optimizing motor performance in an electric vertical takeoff and landing aircraft. Apparatus includes a motor, an inverter, a sensor, and a flight controller. Flight controller is configured to receive an operational datum from a sensor, which detects a physical phenomenon and generates an operational datum. Flight controller is configured to generate an optimized switching frequency for the inverter based on the operational datum. Flight controller is configured to adjust the switching frequency of the inverter based on the optimized switching frequency.
Type:
Application
Filed:
June 29, 2022
Publication date:
January 4, 2024
Applicant:
BETA AIR, LLC
Inventors:
Zach Pan, Chris Woodalll, Jeffrey K. Petter
Abstract: An aircraft monitoring system for an electric aircraft is disclosed. The monitoring system may include at least a sensor configured to generate a failure datum. The failure datum includes a datum regarding a condition of an electric motors. An electronic checklist may include a crew alerting system (CAS). A CAS may be in electronic communication a sensor, wherein the CAS is comprised of at least a computing device. A CAS may generate a plurality of remedy data as a function of the failure datum. A CAS then may display the plurality of remedy data using a pilot display. A pilot may be prompted to apply the remedy datum using a pilot display as a function of the plurality of remedy data. The CAS provides an indication of the condition of the electric motor using a pilot display as a function of the application of the plurality of remedy data.
Abstract: A system for managing residual energy for an electric aircraft, wherein the system includes a battery pack incorporated in the electric aircraft, wherein the battery pack includes a plurality of battery modules and at least a pack monitor unit configured to generate a battery pack datum. The system further includes a charging component connected to the battery pack and a sensor connected to the charging component and configured to detect at least an electrical parameter of the charging component and the electric aircraft and generate a residual datum as a function of the at least an electrical parameter and the battery pack datum. The system further includes a computing device configured to receive the residual datum from the sensor, identify a residual element, generate an alert datum as a function of the residual element, and execute a security measure as a function of the alert datum.
Abstract: An apparatus for determining a resource remaining datum of an electric aircraft is disclosed. The apparatus includes a processor and a memory communicatively connected to the processor. The memory contains instructions configuring the processor to receive aircraft data from at least a sensing device, wherein the at least a sensing device is configured to measure at least a parameter of a battery pack of the electric aircraft and generate aircraft data as a function of the at least a parameter of the battery pack of the electric aircraft. The memory contains instructions configuring the processor to determine a reserve energy as a function of a flight mode of the electric aircraft and determine a resource remaining datum as a function of the aircraft data and the reserve energy, wherein the resource remaining datum is related to the battery pack of the electric aircraft.
Type:
Grant
Filed:
August 17, 2022
Date of Patent:
January 2, 2024
Assignee:
BETA AIR, LLC
Inventors:
Steven J. Foland, Thomas Henck, Herman Wiegman
Abstract: In an aspect, a system for monitoring a battery system in-flight. The system includes at least a battery pack and a pack monitoring unit (PMU) communicatively connected with a battery pack. The battery pack includes a plurality of battery packs. The PMU may include at least a sensor and a controller. At least a sensor is configured to detect battery datum. A controller is communicatively connected with at least a sensor. A controller is configured to receive battery datum, detect a significant event as a function of battery datum, and transmit the significant event to a remote device.
Type:
Grant
Filed:
January 26, 2023
Date of Patent:
January 2, 2024
Assignee:
BETA AIR, LLC
Inventors:
Braedon Lohe, Cullen Jemison, Andrew Giroux, Tom Michael Hughes
Abstract: A system and method for pilot assistance in an electric vertical takeoff and landing (eVTOL) aircraft. The system generally includes a pilot control and a flight controller. The pilot control is attached to the eVTOL aircraft. The pilot control is configured to transmit an input relating to the flight path of the aircraft. The flight controller is communicatively connected to the pilot control. The flight controller is configured to receive the input relating to the flight path, generate an output of a recommended flight maneuver as a function of the input, and display the recommended flight maneuver.
Abstract: A system for determining remaining useful energy in an electric aircraft, the system including a computing device where the computing device is configured to measure a internal state datum of a battery as a function of at least a sensor, receive the internal state datum from the at least a sensor, generate a useful energy remaining datum as a function of the internal state datum and a battery model, and display the useful energy remaining datum to a user.
Abstract: The present invention is directed to systems and methods for managing thermal energy of an electric vertical takeoff and landing aircraft. The system comprises of a multilayer laminate that includes a rigid layer and an insulation layer. The multilayer laminate may be laid on a structural element of an aircraft. The aircraft comprises an active component.
Abstract: In an aspect, an assembly for gauging fuel of an electric aircraft is presented. A assembly includes a plurality of battery packs of an electric aircraft. Each battery pack of a plurality of battery packs includes a plurality of battery modules. An assembly include at least a battery sensor in electronic communication with a battery pack of a plurality of battery packs. At least a battery sensor is configured to measure battery data. An assembly includes a computing device communicatively connected to at least a battery sensor. A computing device is configured to receive battery data from at least a battery sensor. A computing device is configured to determine a landing energy as a function of battery data. A computing device is configured to provide landing energy to a user through a display.
Type:
Application
Filed:
June 28, 2022
Publication date:
December 28, 2023
Applicant:
BETA AIR, LLC
Inventors:
Cullen Jemison, Braedon Lohe, Nathan William Joseph Wiegman, Steven J. Foland
Abstract: An electric vertical takeoff and landing aircraft including a teetering propulsor assembly is provided. Teetering propulsor assembly may include a propeller that includes a hub and blades. Hub of propeller may be mechanically connected to a teeter mechanism of propulsor assembly that may be configured to allow the propeller to pivot about a teeter axis relative to the electric aircraft. Thus, teeter mechanism allows for a rotational axis of propeller to move during teetering of propeller. Teeter mechanism may include one or more springs that reduce teetering or prevent teetering of the propulsor at certain rotational speeds of propeller.
Type:
Application
Filed:
April 6, 2023
Publication date:
December 28, 2023
Applicant:
BETA AIR, LLC
Inventors:
Daniel Spira, Kyle Brookes, David Churchill, Mark Page
Abstract: In an aspect, a propulsor gauge is provide that provides guidance during a transition of a mode of operation of an electric aircraft. Propulsor gauge may include a processor configured to identify a current thrust envelope parameter of one or more propulsors of electric aircraft. Processor may also determine a recommended range as a function of the propulsor parameter, where the recommended range includes a lower threshold and an upper threshold. The recommended range and thrust envelope parameter may then be shown on a display of propulsor gauge, where a measurement of current thrust envelope parameter relative to recommended range may be represented by an indicator.
Type:
Application
Filed:
June 28, 2022
Publication date:
December 28, 2023
Applicant:
BETA AIR, LLC
Inventors:
Nicholas Moy, Collin Freiheit, Lochie Ferrier, Pranav Krishnamurthy, Richard Donnelly
Abstract: The present invention is systems and methods for preflight temperature management of an energy source of an electric aircraft. The system may include a sensor attached to an energy source of an electric aircraft, where the sensor is configured to detect a temperature of the energy source and generate a corresponding temperature datum. A computing device communicatively connected to the sensor may receive the temperature datum and determine the readiness of the electric aircraft for flight based on the temperature of the energy source. If the electric aircraft is not considered ready by the computing device, then an energy source modification may be initiated that changes the temperature of the energy source.
Abstract: A system for charger management for electrical vertical takeoff and landing aircrafts includes a sensor connected to the first charger. The sensor is configured to detect a battery metric and transmit the metric to a computing device. The computing device is connected to a mesh network. The mesh network contains many aircrafts connected to chargers. The charger management system manages the charging of the aircraft.
Abstract: The system and method for defining boundaries of a simulation of an electric aircraft is illustrated. The system comprises a sensor, a computing device, and a remote device. The sensor is configured to detect an aircraft location datum, detect a boundary datum associated with a three-dimensional flying space, and transmit the aircraft location datum and boundary datum to a computing device. The computing device is configured to receive the aircraft location datum and boundary datum from the sensor, determine a distance datum between the aircraft location and boundary as a function of the aircraft location datum and boundary datum generate a recommended aircraft adjustment as a function of the distance datum, and transmit the distance datum and recommended aircraft adjustment to a remote device. The remote device is configured to receive the distance datum and recommended aircraft adjustment and display them to a user.