Distributed flight control system

Patent metadata

Field	Value
Publication number	US-12228946-B2
Application number	US-202318125025-A
Country	US
Kind code	B2
Filing date	Mar 22, 2023
Priority date	Dec 22, 2016
Publication date	Feb 18, 2025
Grant date	Feb 18, 2025

Abstract

A set of commands for each of a plurality of actuators to alter an aircraft's state responsive to one or more inputs is produced. The set of commands is provided to fewer than all actuators comprising the plurality of actuators.

First claim

What is claimed is:

1. A flight control system, comprising:
a processor configured to:
produce a set of commands for each of a plurality of actuators to alter an aircraft's state responsive to one or more inputs; and
provide the set of commands to fewer than all actuators comprising the plurality of actuators, wherein the plurality of actuators are configured to enable flight in the aircraft in the event zero or one actuators of the plurality of actuators are inactive, wherein:
the processor is able to switch between an automatic mode and a pilot control mode;
the processor receives inputs from a higher level processor in the automatic mode and receives inputs from pilot controls in pilot control mode; and
in the event that an irregularity is detected or a malfunction in the higher level processor is detected, the processor switches from the automatic mode to the pilot control mode.

2. The system of claim 1 , wherein the processor has a corresponding set of sensors.

3. The system of claim 1 , wherein the processor has a corresponding set of sensors and the set of commands are produced responsive to sensor data from the set of sensors.

4. The system of claim 1 , wherein the processor has a corresponding set of sensors comprising a rate gyro, accelerometer, magnetometer, or barometer.

5. The system of claim 1 , wherein the processor is physically connected to only one actuator.

6. The system of claim 1 , comprising one or more additional processors configured to produce a set of commands for the plurality of actuators and provide the set of commands to fewer than all actuators comprising the plurality of actuators.

7. The system of claim 6 , comprising an equal number of processors and actuators.

8. The system of claim 6 , wherein the processors are electrically isolated.

9. The system of claim 1 , wherein an actuator of the plurality of actuators receives commands from only one corresponding processor.

10. The system of claim 1 , wherein the processor provides basic autopilot capabilities.

11. The system of claim 1 , wherein the processor performs attitude control and attitude rate control.

12. The system of claim 11 , wherein the processor receives inputs from a pilot.

13. The system of claim 11 , wherein the processor receives inputs from a processor configured to handle high level flight instructions.

14. The system of claim 1 , wherein the processor and one or more additional processors are configured to switch modes simultaneously.

15. The system of claim 1 , wherein the processor and one or more additional processors are configured to switch modes based on pilot indication.

16. The system of claim 1 , wherein an actuator of the plurality of actuators reports a status to the higher level processor.

17. The system of claim 1 , wherein the aircraft comprises a multicopter.

Assignees

• Kitty Hawk Corp

Inventors

• Cutler Mark Johnson
• Reichert Todd
• Jackson James

Classifications

• B64U10/10

  Rotorcrafts · CPC title

• B64U50/19

  using electrically powered motors · CPC title

• B64U10/16

  with five or more distinct rotor axes, e.g. octocopters · CPC title

• G05D1/485

  Control of rate of change of altitude or depth · CPC title

• B64D31/09

  in response to power plant failure · CPC title