Ganged servo flight control system for an unmanned aerial vehicle

Patent metadata

Field	Value
Publication number	US-12054249-B2
Application number	US-202318136727-A
Country	US
Kind code	B2
Filing date	Apr 19, 2023
Priority date	Aug 25, 2015
Publication date	Aug 6, 2024
Grant date	Aug 6, 2024

Abstract

A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.

First claim

What is claimed is:

1. A flight control system for a helicopter comprising:
a swashplate having more than one connection portions including a first connection portion and a third connection portion;
a first control assembly coupled to the first connection portion and having at least two first servo-actuators;
a third control assembly coupled to the third connection portion and having at least two third servo-actuators, wherein the at least two third servo-actuators are arranged in a facing relationship across a vertical midline of the helicopter such that a first servo arm attached to one of the at least two third servo-actuators and a second servo arm attached to the other of the at least two third servo-actuators move within parallel planes.

2. The flight control system of claim 1 , wherein the first control assembly comprises:
a first servo arm,
a second servo arm,
a linkage assembly connecting the second servo arm to the first servo arm, and
wherein the linkage assembly operatively couples the first and the second servo arms to the first connection portion of the swashplate such that the first servo arm and the second servo arm rotate in unison to control the swashplate.

3. The flight control system of claim 1 , wherein the at least two first servo-actuators and the at least two third servo-actuators are each connected to the swashplate by a linkage member.

4. The flight control system of claim 1 , wherein the third connection portion includes an anti-rotation boss extending radially outward from the swashplate and a linkage assembly is coupled to the anti-rotation boss and the third control assembly.

5. The flight control system of claim 1 , further comprising:
a second control assembly connected to a second connection portion of the more than one connection portions of the swashplate and including at least two second servo-actuators connected to rotate in unison; and
wherein the second control assembly directly moves the second connection portion by the unified rotation of the at least two second servo-actuators.

6. The flight control system of claim 5 , wherein the at least two first servo-actuators or the at least two second servo-actuators are arranged in parallel.

7. The flight control system of claim 5 , further comprising:
a control signal generator electrically coupled to the first control assembly by a first output, the third control assembly by a third output, and the second control assembly by a second output; and
wherein the control signal generator outputs a single signal to manipulate both of the at least two first servo-actuators, the at least two third servo-actuators, or the at least two second servo-actuators.

8. The flight control system of claim 1 , further comprising:
a control signal generator electrically coupled to the first control assembly by a first output and electrically coupled to the third control assembly by a third output; and
wherein the control signal generator manipulates both of the two or more servo-actuators of the first control assembly or the third control assembly with a single signal output.

9. A flight control system for a helicopter comprising
a swashplate;
a first control assembly coupled to a first connection portion of the swashplate and having at least two first servo-actuators;
a third control assembly coupled to a third connection portion of the swashplate and having at least two third servo-actuators, the two or more third servo-actuators are arranged in a facing relationship across a vertical midline of the helicopter such that a first servo arm attached to one of the at least two third servo-actuators and a second servo arm attached to the other of the at least two third servo-actuators move within parallel planes;
a control signal generator electrically coupled to the first control assembly by a first output and the third control assembly by a third output; and
wherein the control signal generator manipulates each of the at least two first servo-actuators or the at least two third servo-actuators with a single signal output.

10. The flight control system of claim 9 , further comprising:
a second control assembly coupled to a second connection portion of the swashplate and having at least two second servo-actuators;
wherein the control signal generator is electrically coupled to the second control assembly by a second output; and
wherein the control signal generator manipulates each of the at least two second servo-actuators with a single second signal output.

11. The flight control system of claim 9 , wherein the single signal output includes the individual controls for roll, pitch, and collective control of the swashplate.

12. The flight control system of claim 9 , wherein the control signal generator generates a known input signal and at least one of the at least two first servo-actuators or the at least two third servo-actuators are positioned in a known configuration to calibrate the flight control system.

13. The flight control system of claim 9 , wherein the single signal output manipulates the at least two first servo-actuators or the at least two third servo-actuators to move in unison to control the swashplate.

14. The flight control system of claim 9 , wherein one of the first control assembly comprises:
a first servo arm,
a second servo arm,
a linkage assembly connecting the second servo arm to the first servo arm, and
wherein the linkage assembly operatively couples the first and the second servo arms to the first connection portion of the swashplate such that the first servo arm and the second servo arm rotate in unison to control the swashplate.

15. The flight control system of claim 9 , wherein:
the at least two third servo-actuators are coaxially arranged, and
the at least two second servo-actuators are arranged in parallel.

16. An aerial vehicle, wherein the aerial vehicle is in a form of a helicopter comprising:
a swashplate having a plurality of connection portions;
two or more control assemblies each having two or more servo-actuators, each of the two or more control assemblies operatively coupled to one of the plurality of connection portions, wherein the two or more servo-actuators of one of the two or more control assemblies are arranged in a facing relationship across a vertical midline of the helicopter such that a first servo arm attached to one of the two or more servo-actuators and a second servo arm attached to the other of the two or more servo-actuators move within parallel planes;
a rotor assembly including a plurality of rotor blades operably controlled by the swashplate;
a control signal generator having two or more outputs each electrically coupled to the two or more control assemblies; and
wherein the control signal generator controls both of the two or more servo-actuators of one of the two or more control assemblies by providing a respective single signal to change an orientation of the swashplate, the change in orientation of the swashplate changing a pitch of the one or more rotor blades.

17. The aerial vehicle of claim 16 , further comprising:
a plurality of frame structures, each of the plurality of frame members coupled together by a plurality of connection members; and
wherein each of the plurality of connection members include a base portion having tabs extending from opposing ends of the base portion, each of the tabs attached to an interior surface of the plurality of frame members.

18. The aerial vehicle of claim 17 , wherein:
the swashplate, the rotor assembly, the two or more control assemblies, and

Assignees

• Aerovironment Inc

Inventors

• Holly Lance
• Donovan William

Classifications

• B64C39/024

  of the remote controlled vehicle type, i.e. RPV · CPC title

• B64U10/10

  Rotorcrafts · CPC title

• B64U2201/20

  Remote controls · CPC title

• B64U2101/30

  for imaging, photography or videography · CPC title

• B64U2201/104

  using satellite radio beacon positioning systems, e.g. GPS · CPC title