Beta Air, LLC

Beta Technologies, Inc.

Andrew Joseph Giroux

Timothy Gerard Richter

Joshua E Auerbach

Braedon Andrew Lohe

Chris Townsend

Cullen Forrest Jemison

Tom Michael Hughes

Nicholas Moy

Matthew John Sheppard

Joseph Trovato

Herman Wiegman

A system and method for flight control of an aircraft, the flight control system including a plurality of flight components coupled to an aircraft, wherein the plurality of flight components includes a plurality of redundant control surfaces, a plurality of redundant low voltage buses communicatively connected to the plurality of flight components, wherein a failure in a redundant low voltage bus of the plurality of redundant low voltage busses does not impact the operability of the aircraft.

Flight control system and method for an aircraft

The present disclosure is generally directed to a flight control system and method of flight control for an electric aircraft. The system includes a pilot input communicatively connected to an electric aircraft, wherein the pilot input is configured to receive an input datum, and plurality of flight components communicatively connected to the electric aircraft, wherein the plurality of flight components includes a plurality of control surfaces. The system also includes a flight controller, wherein the flight controller is configured to determine a phase of flight, determine a command datum to control a position of the plurality of control surfaces as a function of the input datum, and command, when the phase of flight is determined to be hover, the plurality of control surfaces using the command datum.

System and methods for flight control for an electric aircraft

A system for flight control in electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive prioritization data including a prioritization datum corresponding to each of the plurality of attitude command, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the prioritization data, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.

System and method for flight control in electric aircraft

A battery management system integrated in a battery pack configured for use in electric aircraft, the system comprising a first battery management component comprising a first sensor suite configured to measure a first plurality of battery pack data. The battery management system comprising a second battery management component comprising a second sensor suite configured to measure a second plurality of battery pack data. The battery management system comprising a data storage system configured to store the first plurality of battery pack data and the second plurality of battery pack data.

Systems and methods for a battery management system integrated in a battery pack configured for use in electric aircraft

A system for battery management for electric aircraft batteries includes an energy storage system configured to provide energy to the electric aircraft via a power supply connection, the energy storage system including: a battery pack, a sensor configured to detect a condition parameter of the battery pack and generate a battery datum based on the condition parameter, a pack monitoring unit (PMU) configured to receive the battery datum, and a high voltage disconnect configured to terminate the power supply connection between the battery pack and the electric aircraft; a high voltage bus electrically connected to the high voltage disconnect; a primary functional display configured to display information based on battery datum; and a first controller area network (CAN) bus and a second CAN bus communicatively connected to the PMU, the high voltage bus, and the primary functional display.

Systems and methods for battery management for electric aircraft batteries

An electric aircraft battery pack that includes an integrated battery management component, which determines if a power supply connection between the battery pack and the electric aircraft should be terminated due to a failure, defect, or malfunction of the battery pack, such as a failure of a battery module of the battery pack.

Pack monitoring unit for an electric aircraft battery pack and methods of use for battery management

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. The aircraft component may be configured to receive, from a command sensor attached to the aircraft control, an aircraft command. The aircraft component may further be configured to obtain, from an attitude sensor, an aircraft orientation. The aircraft component may further be configured to command the flight component to produce a response command as a function of a pilot signal.

System and method for distributed pilot control of an aircraft

In an aspect a system for fly-by-wire flight control configured for use in electric aircraft including at least a sensor, wherein the sensor is communicatively connected a pilot control and configured to detect a pilot input from the pilot control and generate, as a function of the pilot input, command datum. A system includes a flight controller, the flight controller including a computing device and configured to perform a voting algorithm, wherein performing the voting algorithm includes determining that the sensor is an allowed sensor, wherein determining that the sensor is an allowed sensor includes determining that the command datum is an active datum, determining the command datum is an admissible datum, generating, as a function of the command datum and the allowed sensor, a control surface datum wherein the control surface datum is correlated to the pilot input.

Method and system for fly-by-wire flight control configured for use in electric aircraft

An electric aircraft having fixed pitch lift includes a plurality of flight components, wherein the plurality of flight components further comprises at least a lift propulsor component, wherein the lift propulsor component comprises a plurality of blades configured at an angle of attack, and a flight controller, wherein the flight controller is configured to calculate a flight element using an intermediate representation, and transmit the flight element to the plurality of flight components.

Aircraft for fixed pitch lift

The present invention is directed to systems and methods for redundant flight control configured for use in an aircraft. More specifically, a system is provided that includes a plurality of actuators that are configured to move a flight component of an aircraft such that one actuator is configured to move the flight component if the other actuator fails to move the flight component upon receipt of an attitude command from a pilot control.

Systems and methods for redundant flight control in an aircraft

A system of fall back flight control configured for use in aircraft includes an input control configured to receive a pilot input and generate a control datum. System includes a flight controller communicatively coupled to the input control and configured to receive the control datum and generate an output datum. The system includes the actuator having a primary mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the output datum and a fall back mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the control datum. The actuator configured to receive the control datum, receive the output datum, detect a loss of communication with the flight controller, and select the fall back mode as a function of the detection.

Methods and systems for fall back flight control configured for use in aircraft

A battery management and monitoring system integrated in a battery pack configured for use in electric aircraft. The system includes a sensor suite configured to measure a plurality of battery pack data. The system includes a battery monitoring component configured to detect a first fault in the battery pack and produce a first fault detection response notifying a user of the first fault in the battery pack. The system includes a battery management component configured to detect a second fault in the battery pack and produce a second fault detection response configured to mitigate the second fault in the battery pack. The system includes an interlock component having a first mode and a second mode, configured to enable the battery monitoring component and disable the battery management component when in the first mode and enable the battery management component and disable the battery monitoring component when in the second mode.

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.

Growing community of inventors

Georgia, VT, United States of America

Andrew Joseph Giroux