Granted Patent B2

US 12,377,999 · App. 18/750,785 · Granted Aug 5, 2025

Inventors: Jeffrey Mark Bosworth (Argyle, TX); Abhishek Vaidya (San Jose, CA); Maicon Secchi (Sao Jose dos Campos, BR); Marcelo Santos (San Jose, CA)

Assignee: Archer Aviation Inc.

B64D31/16B64D45/00B64C29/0008B64D2045/0085

Abstract

Claims (108)

1. An electrical system for an aircraft, comprising:

at least one processor configured to execute instructions to cause the system to:

receive pilot input indicating a commanded aircraft state;

determine an aircraft thrust for achieving the commanded aircraft state;

determine a difference in speed between at least two propellers that reduces a structural vibratory response in the aircraft;

determine a respective command for each propeller of the aircraft to achieve the determined aircraft thrust while also meeting the determined speed difference; and

control each propeller of the aircraft based on the corresponding respective command.

2. The electrical system of claim 1 , wherein the at least one processor is further configured to:

determine whether the commanded aircraft state corresponds to steady state; and

determine the difference in speed between the at least two propellers upon determining the commanded aircraft state corresponds to steady state, wherein the steady state comprises at least one of: roll of the aircraft remains constant, yaw of the aircraft remains constant, or pitch of the aircraft remains constant.

3. The electrical system of claim 1 , wherein the at least one processor is further configured to:

receive sensor data indicating aircraft vibration;

determine whether the aircraft vibration exceeds a threshold based on the received sensor data; and

determine the difference in speed between the at least two propellers upon determining the aircraft vibration exceeds the threshold.

4. The electrical system of claim 1 , wherein the difference in speed between the at least two propellers is a total difference in propeller speed to be applied across all propellers of the aircraft.

5. The electrical system of claim 1 , wherein the respective command for each propeller of the aircraft is determined based on determining a combination of propeller commands that results in each propeller of the aircraft being controlled to a different speed.

6. The electrical system of claim 5 ,

wherein determining the respective command for each propeller of the aircraft to meet the determined aircraft thrust while also meeting the determined speed difference further comprises:

determining, for each propeller of the aircraft, an initial propeller command to meet the determined thrust;

randomly adjusting the initial propeller command based on the determined speed difference; and

determining whether the randomly adjusted propeller commands provide the determined thrust.

7. The electrical system of claim 1 , wherein:

the difference in speed is based on at least one of an airspeed or a propeller angle.

8. The electrical system of claim 7 ,

wherein the difference in speed is increased when the airspeed and the propeller angle indicates an increase in edgewise airflow.

9. The electrical system of claim 1 , wherein the at least one processor is further configured to determine a propeller speed range to avoid.

10. The electrical system of claim 1 ,

wherein the at least one processor is further configured to determine—

at least two propeller speed avoidance ranges; and

increase a propeller speed avoidance range based on an airspeed of the aircraft and a propeller angle indicating an increase in edgewise airflow.

11. The electrical system of claim 1 ,

wherein the at least one processor is further configured to determine

a respective target propeller speed for each propeller of the aircraft; and

wherein determining the respective command for each propeller of the aircraft to meet the determined thrust while also meeting the determined speed difference comprises:

applying the respective target propeller speed as an attractor in an allocation function, wherein the allocation function determines a combination of propeller commands that achieve the determined thrust.

12. The electrical system of claim 1 , wherein the at least one processor is further configured to vary the the difference in speed based on at least one of: an airspeed of the aircraft or a propeller angle.

13. The electrical system of claim 1 , wherein the at least one processor is further configured to:

receive first sensor data indicating an airspeed of the aircraft;

receive second sensor data indicating a propeller angle; and

vary the difference in speed based on the first sensor data and the second sensor data.

14. The electrical system of claim 1 , wherein:

each of the respective commands are a torque command and

the at least one processor is further configured to determine the torque command based on a relationship between propeller speed and torque, wherein the relationship between propeller speed and torque varies based on a flight phase of the aircraft.

15. The electrical system of claim 1 , wherein the at least one processor is further configured to:

receive sensor data indicating a propeller speed of each propeller of the aircraft; and

determine the command for each propeller of the aircraft based on the difference in speed and the sensor data for the corresponding propeller.

16. The electrical system of claim 1 , wherein the at least one processor is further configured to:

receive sensor data indicating a propeller speed of each propeller; and

adjust the determined command based on the received sensor data for the corresponding propeller, wherein controlling each propeller of the aircraft is based on the adjusted command.

17. The electrical system of claim 1 ,

wherein the at least one processor is further configured to determine a propeller speed avoidance range; and

determine a respective command for each propeller of the aircraft by prioritizing the propeller speed avoidance range over the difference in speed.

18. The electrical system of claim 1 ,

wherein the difference in speed varies based on a flight condition of the aircraft; and

wherein the at least one processor is further configured to:

repeatedly determine the difference in speed and control the aircraft based on the difference in speed during a flight of the aircraft.

19. The electrical system of claim 1 ,

wherein the difference in speed is based on experimental testing or modeling impacts of propeller speeds on the structural vibratory response of at least one of: a body of the aircraft, a boom of the aircraft, a propeller of the aircraft, or a wing of the aircraft.

20. The electrical system of claim 1 ,

wherein the respective command is determined to maintain a trim state of the aircraft.

21. The electrical system of claim 1 ,

wherein the at least one processor is further configured to:

determine a propeller parameter to reduce a noise emission of the aircraft;

determine whether the aircraft can be controlled according to the propeller parameter without increasing a structural vibratory response in the aircraft; and

control each propeller of the aircraft based on the propeller parameter upon determining the structural vibratory response in the aircraft will not increase.

22. The electrical system of claim 1 ,

wherein the at least one processor is further configured to:

receive sensor data indicating aircraft vibration;

determine whether the aircraft vibration is in a range of 1 Hz to 5,000 Hz based on the received sensor data; and

determine the difference in speed between the at least two propellers upon determining the aircraft vibration is in the range.

23. The electrical system of claim 1 ,

wherein the at least one processor is further configured to:

receive sensor data indicating an aircraft noise;

determine whether the noise is in a range of 20 Hz to 10,000 Hz;

determine an effect that controlling propellers of the aircraft to reduce the noise will have on the structural vibratory response in the aircraft; and

control each propeller of the aircraft to reduce the noise upon determining that the noise is in the range and the control of the propellers will have a positive or neutral effect on reducing a structural vibratory response.

24. An aircraft, comprising:

at least two propellers;

at least one processor configured to:

receive pilot input indicating a commanded aircraft state;

determine an aircraft thrust for achieving the commanded aircraft state;

determine a difference in speed between the at least two propellers that reduces a structural vibratory response in the aircraft;

determine a respective command for each propeller of the aircraft to achieve the determined aircraft thrust while also meeting the determined speed difference; and

control each propeller of the aircraft based on the corresponding respective command.

25. A method for controlling an aircraft, comprising:

receiving, using at least one hardware processor, pilot input indicating a commanded aircraft state;

determining, using the at least one hardware processor, an aircraft thrust for achieving the commanded aircraft state;

determining, using the at least one hardware processor, a difference in speed between at least two propellers that reduces a structural vibratory response in the aircraft;

determining, using the at least one hardware processor, a respective command for each propeller of the aircraft to achieve the determined aircraft thrust while also meeting the determined speed difference; and

controlling, using the at least one hardware processor, each propeller of the aircraft based on the corresponding respective command.

26. The method of claim 25 , further comprising:

receiving, using the at least one hardware processor, sensor data indicating aircraft vibration;

determining, using the at least one hardware processor, whether the aircraft vibration exceeds a threshold based on the received sensor data; and

determining, using the at least one hardware processor, the difference in speed between the at least two propellers upon determining the aircraft vibration exceeds the threshold.

27. The method of claim 25 , wherein the difference in speed is based on at least one of an airspeed or a propeller angle.

28. The method of claim 25 , further comprising determining, using the at least one hardware processor, a propeller speed range to avoid.

29. An electrical system for an aircraft, comprising:

at least one processor configured to execute instructions to cause the system to:

receive pilot input indicating a commanded aircraft state;

determine an aircraft thrust for achieving the commanded aircraft state;

determine a standard deviation in propeller speed across propellers of the aircraft that reduces a structural vibratory response in the aircraft;

determine a respective command for each propeller of the aircraft to achieve the determined aircraft thrust while also meeting the standard deviation in propeller speed; and

control each propeller of the aircraft based on the corresponding respective command.

30. The electrical system of claim 29 , wherein the at least one processor is further configured to:

randomly allocate torque values to each of the propellers to meet the determined thrust;

determine whether the random allocation of propeller torques meets the standard deviation of propeller speed;

repeat the random allocation of torque values upon determining the standard deviation of propeller speed is not met; and

determine a respective command for each propeller of the aircraft upon determining the standard deviation of propeller speed is met.

Assignments (2)

Continuity (4)

References Cited (32)