Beta Air, LLC

Lord Corporation

Microstrain, Inc.

Beta Technologies, Inc.

Chris Townsend

Andrew Joseph Giroux

Joshua E Auerbach

Timothy Gerard Richter

Steven Willard Arms

David Lawrence Churchill

Michael John Hamel

Matthew John Sheppard

Joseph Trovato

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

Aspects relate to methods and systems for reversionary flight control for an electrical vertical take-off and landing (eVTOL) aircraft. An exemplary system includes a pilot control, a sensor configured to sense and transmit analog control data associated with a pilot interaction with the pilot control, a pilot interface module configured to receive the analog control data, convert the analog control data to digital control data, and transmit digital control, an actuator, and a flight controller. The flight controller may be configured to receive the digital control data, determine a primary command datum as a function of the digital control data, transmit the primary command datum to the actuator, determine that the digital control signal is non-functional, receive the analog control data, determine a reversionary command datum as a function of the analog control data, and transmit the reversionary command datum to the actuator.

Electrical vertical take-off and landing aircraft having reversionary flight control and method of use

A system of fall back flight control configured for use in electric 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 electric 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 electric aircraft

Some aspects relate to systems and methods for fly-by-wire reversionary flight control including a pilot control, a plurality of sensors configured to: sense control data associated with the pilot control, and transmit the control data, a first actuator communicative with the plurality of sensors configured to receive the control data, determine a first command datum as a function of the control data and a distributed control algorithm, and actuate a first control element according to the first command datum.

Systems and methods for fly-by-wire reversionary flight control

An aircraft for fixed pitch lift includes a fuselage, a plurality of flight components attached to the fuselage, 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 a fixed angle of attack, and a pusher component, wherein the pusher component is configured to produce a forward thrust.

A method of obtaining data about a structure includes providing a plurality of sensor modules on the structure. Each of the sensor modules includes a sensor, a processor, a sensor module precision timekeeper, and a sensor module transceiver. One of the plurality of sensor modules includes an energy harvesting device. The processor and the sensor module transceiver of this one of the plurality of sensor modules are powered solely with electricity derived from the energy harvesting device. The method further includes providing a base station. The method further includes periodically wirelessly receiving a broadcast resynchronization timing packet with each of the sensor module transceivers, wherein the broadcast resynchronization timing packet received by each of the sensor module transceivers includes a common resynchronization time value. The method further includes periodically resynchronizing each of the sensor module precision timekeepers based on a signal derived from the resynchronization time value. The method further includes digital sampling of the sensor module sensor in each of the sensor modules to provide digital sensor data, and providing a time stamp to the digital sensor data wherein time in the time stamp is provided by the sensor module precision timekeeper. The method further includes wirelessly transmitting data from each of the plurality of sensor modules to the base station, wherein the data is derived from the time stamped digital sensor data. The method further includes receiving and aggregating the data from each of the plurality of sensor modules in the base station.

Growing community of inventors

Shelburne, VT, United States of America

Chris Townsend