# US 11,999,467 B2 · Methods and systems for fall back flight control configured for use in aircraft

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- Number: US 11,999,467 B2
- Document ID: US11999467B2
- Status: Granted
- Kind: B2
- Application number: 17/877,993
- Filed: 2022-07-31
- Published: 2022-11-17
- Granted: 2024-06-04
- Earliest claimed: 2021-02-19
- Assignees: BETA Technologies, Inc.
- Applicants: Beta Air, LLC
- Inventors: Timothy Gerard Richter; Andrew Giroux; Joseph Trovato; Chris Townsend
- Web page: https://patentgrep.com/patent/US11999467B2

## CPC

- B64C 13/505: {having duplication or stand-by provisions}
- B64C 13/042: {operated by hand}
- B64C 13/16: actuated automatically, e.g. responsive to gust detectors
- B64C 13/503: {Fly-by-Wire}
- B64C 13/506: {overriding of personal controls; with automatic return to inoperative position}
- B64D 27/34: All-electric aircraft
- B64D 31/04: actuated personally
- B64D 31/06: actuated automatically
- B64D 31/16: for electric power plants
- B64C 29/0025: {the propellers being fixed relative to the fuselage}
- B64D 45/0005: {Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear}
- B64C: AEROPLANES; HELICOPTERS
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT

## Abstract

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.

## Claims

### Claim 1

A system of fall back flight control configured for use in aircraft, the system comprising:
a flight controller, wherein the flight controller is configured to:
determine an autonomous operation input as a function of at least a sensor;
produce a control datum as a function of the autonomous operation input; and
transmit a datum, wherein transmitting the datum further comprises transmitting at least one of the control datum or an output datum, wherein the flight controller is configured to generate the output datum as a function of the control datum; and
an actuator, the actuator communicatively coupled to the flight controller, the actuator configured to:
receive at least one of the control datum or the output datum from the flight controller; and move at least a portion of the aircraft as a function of the at least one of the control datum or the output datum.

### Claim 2 (depends on 1)

The system of claim 1, wherein the flight controller includes a manual override manipulation of an inceptor stick.

### Claim 3 (depends on 1)

The system of claim 1, The system of claim 1, wherein the flight controller includes a manual override manipulation of a throttle.

### Claim 4 (depends on 1)

The system of claim 1, wherein the actuator is configured to detect, as a function of time, that communication with the flight controller is lost by determining a maximum time without receiving the output datum from the flight controller.

### Claim 5 (depends on 4)

The system of claim 4, wherein the maximum time the actuator waits before detecting communication is lost with the flight controller is configurable.

### Claim 6 (depends on 5)

The system of claim 5, wherein the maximum time the actuator waits before detecting communication is lost with the flight controller is input by a user.

### Claim 7 (depends on 1)

The system of claim 1, wherein the actuator includes a servomotor.

### Claim 8 (depends on 1)

The system of claim 1, wherein the actuator includes a device configured to convert electrical signals into mechanical movement.

### Claim 9 (depends on 1)

The system of claim 1, wherein the at least a portion of the aircraft includes a propulsor.

### Claim 10 (depends on 1)

The system of claim 1, wherein the at least a portion of the aircraft includes a control surface.

### Claim 11

A method of fall back flight control configured for use in aircraft, the method comprising:
determining, by a flight controller, an autonomous operation input as a function of at least a sensor;
producing, by the flight controller, a control datum as a function of the autonomous operation input;
transmitting a datum, wherein transmitting the datum further comprises transmitting at least one of the control datum or an output datum, wherein the flight controller is configured to generate the output datum as a function of the control datum;
receiving, at an actuator, at least one of the control datum or the output datum from the flight controller; and
moving at least a portion of the aircraft as a function of the at least one of the control datum or the output datum.

### Claim 12 (depends on 11)

The method of claim 11, wherein the output datum is manually overridden as a function of an inceptor stick.

### Claim 13 (depends on 11)

The method of claim 11, wherein the output datum is manually overridden as a function of a throttle.

### Claim 14 (depends on 11)

The method of claim 11, wherein the actuator is configured to detect, as a function of time, loss of communication with the flight controller by detecting as a function of determining a maximum amount of time without receiving the output datum from the flight controller.

### Claim 15 (depends on 14)

The method of claim 14, wherein determining a maximum amount of time without receiving the output datum from the flight controller is configurable.

### Claim 16 (depends on 15)

The method of claim 15, wherein determining a maximum amount of time without receiving the output datum from the flight controller is input by a user.

### Claim 17 (depends on 11)

The method of claim 11, wherein the actuator includes a servomotor.

### Claim 18 (depends on 11)

The method of claim 11, wherein the actuator includes a device configured to convert electrical signals into mechanical movement.

### Claim 19 (depends on 11)

The method of claim 11, wherein the at least a portion of the aircraft includes a propulsor.

### Claim 20 (depends on 11)

The method of claim 11, wherein the at least a portion of the aircraft includes a control surface.