Rotatable control surface assembly for an unmanned aerial vehicle

• US 10,124,880 B1
• Filed: 02/03/2016
• Issued: 11/13/2018
• Est. Priority Date: 02/03/2016
• Status: Active Grant

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Ellzey, Steven J., Copp, James C.
• Primary Examiner(s): Badawi, Medhat
• Application Number:
  US15/014,399
• Time in Patent Office: 1,014 Days
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 5/02 Tailplanes
• CPC Class Codes: B64C 5/12 for retraction against or within fuselage or nacelle
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof
• CPC Class Codes: B64C 9/36 the members being fuselages or nacelles
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/293 Foldable or collapsible rotors or rotor supports
• CPC Class Codes: B64U 40/10 for adjusting control surfaces or rotors
• CPC Class Codes: B64U 70/50 Launching from storage containers, e.g. from submarine missile tubes
• CPC Class Codes: B64U 80/70 in containers B64U80/60 takes precedence

Abstract

A control surface assembly for an unmanned aerial vehicle (UAV) is disclosed. The control surface assembly has a fin configured to be rotatably coupled to a fuselage of the UAV, with a control surface member rotatably coupled to the fin. A control surface linkage is configured to be coupled between the control surface member and an actuator disposed in the fuselage. The fin is rotatable with respect to the fuselage between a stowed configuration and a deployed configuration. In the deployed configuration, the control surface linkage is configured to rotate the control surface member with respect to the fin, when the actuator actuates the control surface linkage. In the stowed configuration, however, the control surface linkage is configured to move with respect to the fin without rotating the control surface member, when the actuator actuates the control surface linkage.

Claims

1. A control surface assembly for an unmanned aerial vehicle (UAV) comprising:

a fin configured for rotatable coupling to a fuselage, the fin rotatable between a stowed configuration and a deployed configuration;

a control surface member rotatably coupled to the fin; and

a control surface linkage coupled to the control surface member, the control surface linkage configured for actuation by an actuator disposed in the fuselage, wherein;

in the deployed configuration, the control surface linkage is configured to rotate the control surface member with respect to the fin responsive to actuation of the actuator, and

in the stowed configuration, the control surface linkage is configured to move with respect to the fin responsive to actuation of the actuator without rotating the control surface member.

2. The control surface assembly of claim 1, wherein the control surface linkage comprises:

a translation member configured to translate with respect to the fuselage in response to the actuator actuating the control surface linkage;

a control link coupled between the translation member and the control surface member.

3. The control surface assembly of claim 2, wherein the control link comprises:

a first end rotatably coupled to the translation member with three degrees of freedom; and

a second end rotatably coupled to the control surface member with three degrees of freedom.

4. The control surface assembly of claim 3, further comprising a pushrod extending in a first direction, the pushrod coupled to the translation member,

wherein the pushrod is configured for coupling to the actuator such that actuating the actuator moves the pushrod substantially in the first direction.

5. The control surface assembly of claim 4, wherein the pushrod is fixed with respect to the translation member.

6. The control surface assembly of claim 4, wherein the control link is substantially parallel to the first direction when the fin is in the deployed configuration.

7. The control surface assembly of claim 4, wherein the control link is rotatable about the second end through an arc comprising a normal to the first direction when the fin is in the stowed configuration.

8. The control surface assembly of claim 3, wherein the first end of the control link comprises a first ball link coupled to the translation member;

and

the second end of the control link comprises a second ball link coupled to the control surface member.

9. The control surface assembly of claim 2, wherein the control surface member comprises:

a control surface rotatable with respect to the fin about an axis substantially parallel to the fin; and

an arm fixed with respect to the control surface, the arm coupled to the control link.

10. The control surface assembly of claim 9, wherein the control link comprises:

a first end rotatably coupled to the translation member with three degrees of freedom; and

a second end rotatably coupled to the arm of the control surface member with three degrees of freedom.

11. The control surface assembly of claim 10, further comprising:

the fuselage extending in a longitudinal direction substantially parallel to a first direction, the fuselage comprising an interior, wherein the fin is rotatably coupled to the fuselage;

the actuator disposed in the interior of the fuselage.

12. An unmanned aerial vehicle (UAV) comprising:

a fuselage having an interior;

an actuator disposed in the interior of the fuselage;

a fin rotatably coupled to the fuselage, the fin rotatable between a stowed configuration and a deployed configuration;

a control surface member rotatably coupled to the fin; and

a control surface linkage coupled between the actuator and the control surface member,

wherein, in the deployed configuration, the actuator is configured to rotate the control surface member with respect to the fin, and in the stowed configuration, the actuator is configured to move the control surface linkage with respect to the control surface member without rotating the control surface member.

13. The UAV of claim 12, wherein the control surface linkage comprises:

a translation member configured to translate with respect to the fuselage in response to the actuator actuating the control surface linkage;

a control link coupled between the translation member and the control surface member.

14. The UAV of claim 13, wherein the control link comprises:

a first end rotatably coupled to the translation member with three degrees of freedom; and

a second end rotatably coupled to the control surface member with three degrees of freedom.

15. The UAV of claim 14, further comprising a pushrod extending in a longitudinal direction with respect to the fuselage, the pushrod coupled between the translation member and the actuator such that actuating the actuator moves the pushrod substantially in the longitudinal direction.

16. The UAV of claim 15, wherein the control link is substantially parallel to the longitudinal direction when the fin is in the deployed configuration.

17. The UAV of claim 15, wherein the control link is rotatable about the second end through an arc comprising a normal to the longitudinal direction when the fin is in the stowed configuration.

18. The UAV of claim 15, wherein the translation member further comprises a protrusion configured to slidably engage a slot disposed in the fuselage, the slot extending substantially parallel to the longitudinal direction.

19. The UAV of claim 13, wherein the control surface member comprises:

a control surface rotatable with respect to the fin about an axis substantially parallel to the fin; and

an arm fixed with respect to the control surface, the arm coupled to the control link.

20. The UAV of claim 12, further comprising:

a spring coupled between the fuselage and the fin, the spring configured to bias the fin toward the deployed configuration.