Patents by Inventor Nicholas Moy
Nicholas Moy has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
SYSTEM AND METHOD FOR THE AUTONOMOUS TRANSITION OF AN ELECTRIC VERTICAL TAKEOFF AND LANDING AIRCRAFT
Publication number: 20230054436Abstract: A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a pusher component, a lift component, a flight controller, and a pilot override switch. The pusher component is mechanically coupled to the eVTOL aircraft. The lift component is mechanically coupled to the eVTOL aircraft. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a transition point, initiate operation of the pusher component, and terminate operation of the lift component. A method for flight control of an eVTOL aircraft is also provided.Type: ApplicationFiled: July 22, 2022Publication date: February 23, 2023Applicant: BETA AIR, LLCInventors: Joshua E. Auerbach, Nicholas Moy -
Patent number: 11584543Abstract: A system for monitoring sensor reliability in an electric aircraft is provided. The system includes a computing device communicatively connected to a first sensor and an electric aircraft. The first sensor is mechanically connected to the electric aircraft and is configured to detect a first flight datum of the electric aircraft. The computing device is configured to receive the first flight datum from the first sensor, compare the first flight datum to at least a corroboratory datum, and tag the first sensor as a function of the comparison of the first flight datum and the at least a corroboratory datum. A method for monitoring sensor reliability in an electric aircraft is also provided.Type: GrantFiled: April 28, 2022Date of Patent: February 21, 2023Assignee: BETA AIR, LLCInventors: Nicholas Moy, Collin Freiheit, Joshua E. Auerbach
-
Patent number: 11584534Abstract: Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.Type: GrantFiled: February 16, 2022Date of Patent: February 21, 2023Assignee: BETA AIR, LLCInventors: Nicholas Moy, Riley Griffin, Lochie Ferrier, Collin Freiheit
-
Patent number: 11584542Abstract: Systems and methods for lag optimization of pilot intervention is provided. A critical event may be identified while an electric aircraft is in an autopilot mode and operating primarily under autonomous functions; as a result, a flight controller of the system may switch from an autopilot mode to a manual mode, allowing pilot intervention. System made determine a lag duration as a function of the critical event and a phase of operation of the electric aircraft to determine a lag duration before pilot intervention occurs.Type: GrantFiled: December 27, 2021Date of Patent: February 21, 2023Assignee: BETA AIR, LLCInventors: Nicholas Moy, Collin Freiheit, Joshua E. Auerbach
-
Publication number: 20230042008Abstract: A system for flight control configured for use in an electric aircraft includes a sensor configured to capture an input datum. The system includes an inertial measurement unit (IMU) and configured to detect an aircraft angle and an aircraft angle rate. The system includes a flight controller including an outer loop controller configured to receive the input datum from the sensor, receive the aircraft angle from the IMU, and generate a rate setpoint as a function of the input datum. The system includes an inner loop controller configured to receive the aircraft angle rate, receive the rate setpoint from the outer loop controller, and generate a moment datum as a function of the rate setpoint. The system includes a mixer configured to receive the moment datum, map vehicle level control torques, received from the inner loop controller, to actuator output and generate a motor command datum as a function of the torque allocation.Type: ApplicationFiled: October 25, 2022Publication date: February 9, 2023Applicant: BETA AIR, LLCInventors: Nicholas Moy, Joshua E. Auerbach
-
Publication number: 20230019396Abstract: A system for autonomous flight collision avoidance in ana electric aircraft, where the system includes an electric aircraft. The electric aircraft includes a at least a sensor coupled to the electric aircraft, where the at least a sensor coupled to the aircraft is configured to detect an obstacle in the electric aircraft's flight path and transmit the obstacle to a flight controller. The electric aircraft also includes a flight controller where the flight controller is configured to receive the obstacle from the at least a sensor coupled to the electric aircraft, determine an adjusted flight path as a function of the obstacle, and transmit the adjusted flight path to a pilot display. The system further includes a pilot display, where the pilot display is configured to receive the adjusted flight path form the flight controller and display the adjusted flight path to a user.Type: ApplicationFiled: July 13, 2021Publication date: January 19, 2023Applicant: BETA AIR, LLCInventors: Joshua E. Auerbach, Nicholas Moy
-
Publication number: 20230002068Abstract: A system for fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.Type: ApplicationFiled: June 30, 2022Publication date: January 5, 2023Applicant: BETA AIR, LLCInventors: Nicholas Moy, Hamid-Reza Ossareh
-
Patent number: 11542003Abstract: A system for remote pilot control of an electric aircraft in autopilot mode including a remote computing device configured to receive a user input and generate a control datum as a function of the pilot input, a flight controller configured to receive the control datum from the remote computing device, and generate a command datum as a function of the control datum and an authority status, and the remote computing device configured to receive the command datum from the flight controller, and display the command datum.Type: GrantFiled: March 22, 2022Date of Patent: January 3, 2023Assignee: BETA AIR, LLCInventors: Nicholas Moy, Collin Freiheit, Joshua E. Auerbach
-
Publication number: 20220411089Abstract: An electric aircraft for generating a yaw force includes a fuselage, a plurality of laterally extending elements secured to the fuselage, a plurality of lift components attached to the plurality of laterally extending elements, and at least a longitudinal thrust component attached to the plurality of laterally extending elements, wherein the longitudinal thrust component is configured to generate a yaw force.Type: ApplicationFiled: June 29, 2021Publication date: December 29, 2022Applicant: BETA AIR, LLCInventors: Nicholas Moy, Riley Griffin, Lochie Ferrier, Collin Freiheit
-
Publication number: 20220411090Abstract: Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.Type: ApplicationFiled: February 16, 2022Publication date: December 29, 2022Applicant: BETA AIR, LLCInventors: Nicholas Moy, Riley Griffin, Lochie Ferrier, Collin Freiheit
-
Publication number: 20220413514Abstract: In an aspect, a system for a guidance interface for a vertical take-off and landing (VTOL) aircraft comprises a plurality of flight components that are mechanically coupled to the VTOL aircraft. The VTOL aircraft also comprises an output device that is configured to present a display of the outside environment. The output device may overlay the display with a datum, a focal point, and a guidance symbol. The datum may be associated with the flight components of the VTOL aircraft. The focal point may be indicative of a desired landing location for the VTOL aircraft. The focal point may be determined by at least a predetermined flight plan. The guidance symbol may be a symbol that includes an optimal flight path to the focal point.Type: ApplicationFiled: June 29, 2021Publication date: December 29, 2022Applicant: BETA AIR, LLCInventors: Nicholas Moy, Collin Freiheit
-
Publication number: 20220402602Abstract: An aircraft for vectoring a plurality of propulsors includes a longitudinal component attached to a fuselage, a plurality of downward directed propulsors attached to a plurality of laterally extending elements secured to the fuselage, a sensor attached to the plurality of downward directed propulsors, a flight controller, wherein the flight controller is configured to receive a flight datum as a function of the sensor, and vector the plurality of downward directed propulsors along a boom axis as a function of the flight datum.Type: ApplicationFiled: June 16, 2021Publication date: December 22, 2022Applicant: BETA AIR, LLCInventors: Nicholas Moy, Riley Griffin, Lochie Ferrier, Collin Freiheit
-
Publication number: 20220402630Abstract: Aspects relate to method and systems for wrapping simulated intra-aircraft communication to a physical controller area network. An exemplary method includes receiving simulator data from an aircraft simulator, disaggregating a simulated digital message from the simulator data, abstracting a simulated signal as a function of the simulated digital message, transmitting the simulated signal on at least a controller area network (CAN), receiving, using at least an aircraft component communicative with the at least a CAN, the simulated signal by way of the at least a CAN, transmitting a phenomenal signal by way of the at least a CAN, receiving the phenomenal signal by way of the at least a CAN, converting a phenomenal digital message as a function of the phenomenal signal, and inputting the phenomenal digital message to the aircraft simulator.Type: ApplicationFiled: June 16, 2021Publication date: December 22, 2022Applicant: BETA AIR, LLCInventors: Nicholas Granger Warren, Charles C. Guthrie, Nicholas Moy, Alexander Hoekje List
-
Publication number: 20220406213Abstract: Aspects relate to augmented reality (AR) methods and systems for simulated operation of an electric vertical take-off and landing (eVTOL) aircraft. An exemplary AR system includes at least an aircraft component of an eVTOL aircraft, a computing device configured to operate a flight simulator to simulate flight in an environment and simulate at least a virtual representation interactive with the flight simulator, where the at least a virtual representation includes an aircraft digital twin of the at least an aircraft component, and a mesh network configured to communicatively connect the at least an aircraft component and the computing device and communicate encrypted data.Type: ApplicationFiled: June 16, 2021Publication date: December 22, 2022Applicant: BETA AIR, LLCInventors: Nicholas Granger Warren, Charles C. Guthrie, Nicholas Moy, Alexander Hoekje List
-
Patent number: 11524767Abstract: A system for flight control configured for use in an electric aircraft includes a sensor configured to capture an input datum. The system includes an inertial measurement unit (IMU) and configured to detect an aircraft angle and an aircraft angle rate. The system includes a flight controller including an outer loop controller configured to receive the input datum from the sensor, receive the aircraft angle from the IMU, and generate a rate setpoint as a function of the input datum. The system includes an inner loop controller configured to receive the aircraft angle rate, receive the rate setpoint from the outer loop controller, and generate a moment datum as a function of the rate setpoint. The system includes a mixer configured to receive the moment datum, perform a torque allocation as a function of the moment datum, and generate a motor command datum as a function of the torque allocation.Type: GrantFiled: March 31, 2021Date of Patent: December 13, 2022Assignee: BETA AIR, LLCInventors: Nicholas Moy, Joshua E Auerbach
-
Publication number: 20220371724Abstract: A system for distributed pilot control of an aircraft includes a plurality of flight components, an aircraft control located within the aircraft, and an aircraft component attached to a flight component of the plurality of flight components, wherein the aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command, obtain, from an attitude sensor, an aircraft orientation, receive, as a function of a notification unit, a pilot signal, and command the flight component to produce a response command as a function of the pilot signal.Type: ApplicationFiled: June 16, 2021Publication date: November 24, 2022Applicant: BETA AIR, LLCInventors: Andrew Giroux, Timothy Gerard Richter, Nicholas Moy
-
Publication number: 20220326704Abstract: A system for flight control configured for use in an electric aircraft includes an inertial measurement unit (IMU) and configured to detect an aircraft angle and an aircraft angle rate. The system includes a flight controller including an outer loop controller configured to receive the input datum from the sensor, receive the aircraft angle from the IMU, and generate a rate setpoint as a function of the input datum. The system includes an inner loop controller configured to receive the aircraft angle rate, receive the rate setpoint from the outer loop controller, and generate a moment datum as a function of the rate setpoint. The system includes a mixer configured to receive the moment datum, perform a torque allocation as a function of the moment datum, and generate a motor command datum as a function of the torque allocation.Type: ApplicationFiled: September 17, 2021Publication date: October 13, 2022Applicant: BETA AIR, LLCInventors: Nicholas Moy, Joshua E. Auerbach
-
Publication number: 20220317706Abstract: An aircraft motion observer configured for use in electric aircraft includes an actuator model configured to receive at least an aircraft command, wherein the aircraft command comprises a desired change in aircraft trajectory as a function of a plurality of flight components, generate a performance datum for the flight components as a function of the aircraft command. System includes a plant model configured to generate a predictive datum for the flight components as a function of the actuator model and the performance datum. System includes a sensor communicatively connected to the aircraft configured to detect a measured state datum. System includes a controller configured to compare the predictive datum and the measured state datum, generate an inconsistency datum wherein the inconsistency datum comprises a mathematical function to compensate for the difference between the predictive state datum and the measured state datum, and transmit the inconsistency datum to the plant model.Type: ApplicationFiled: October 30, 2021Publication date: October 6, 2022Applicant: BETA AIR, LLCInventor: Nicholas Moy
-
Publication number: 20220315205Abstract: A system for flight control configured for use in an electric aircraft includes a sensor configured to capture an input datum. The system includes an inertial measurement unit (IMU) and configured to detect an aircraft angle and an aircraft angle rate. The system includes a flight controller including an outer loop controller configured to receive the input datum from the sensor, receive the aircraft angle from the IMU, and generate a rate setpoint as a function of the input datum. The system includes an inner loop controller configured to receive the aircraft angle rate, receive the rate setpoint from the outer loop controller, and generate a moment datum as a function of the rate setpoint. The system includes a mixer configured to receive the moment datum, perform a torque allocation as a function of the moment datum, and generate a motor command datum as a function of the torque allocation.Type: ApplicationFiled: March 31, 2021Publication date: October 6, 2022Applicant: BETA AIR, LLCInventors: Nicholas Moy, Joshua E. Auerbach
-
Publication number: 20220319257Abstract: An aircraft motion observer configured for use in electric aircraft includes an actuator model configured to receive at least an aircraft command, wherein the aircraft command comprises a desired change in aircraft trajectory as a function of a plurality of flight components, generate a performance datum for the flight components as a function of the aircraft command. System includes a plant model configured to generate a predictive datum for the flight components as a function of the actuator model and the performance datum. System includes a sensor communicatively connected to the aircraft configured to detect a measured state datum. System includes a controller configured to compare the predictive datum and the measured state datum, generate an inconsistency datum wherein the inconsistency datum comprises a mathematical function to compensate for the difference between the predictive state datum and the measured state datum, and transmit the inconsistency datum to the plant model.Type: ApplicationFiled: March 31, 2021Publication date: October 6, 2022Applicant: BETA AIR, LLCInventor: Nicholas Moy