Air vehicle, actuator assembly and associated method of manufacture

Patent metadata

Field	Value
Publication number	US-9643716-B2
Application number	US-201414242088-A
Country	US
Kind code	B2
Filing date	Apr 1, 2014
Priority date	Apr 1, 2014
Publication date	May 9, 2017
Grant date	May 9, 2017

Abstract

An air vehicle, an actuator assembly and a method of manufacture are provided in order to incorporate the actuator assembly within the outer mold line of the air vehicle. In regards to an air vehicle, the air vehicle includes a primary structure and a movable structure configured to be controllably moved relative to the primary structure. The air vehicle also includes an actuator assembly configured to cause the movable structure to be positioned relative to the primary structure. The actuator assembly includes an actuator housing and an actuation mechanism. The actuation mechanism is at least partially disposed within the actuator housing and is configured to provide for relative movement between the primary structure and the movable structure. At least a portion of the actuator assembly is built into at least one of the primary structure and the movable structure so as to be within an outer mold line of the air vehicle.

First claim

That which is claimed:

1. An air vehicle comprising:
a primary structure;
a movable structure configured to be controllably moved about a rotation axis relative to the primary structure; and
an actuator assembly configured to cause the movable structure to be positioned relative to the primary structure, wherein the actuator assembly comprises:
an actuator housing; and
an actuation mechanism at least partially disposed within the actuator housing and configured to provide for relative movement between the primary structure and the movable structure;

wherein the actuator housing and the actuation mechanism comprise:
a plurality of rings; and
a plurality of gears, wherein the plurality of rings and the plurality of gears are spaced apart in an axial direction defined by the rotation axis and the plurality of rings are configured to interlace with the plurality of gears to define the actuator housing, wherein each ring and gear comprises:
a housing member; and
an extension extending outwardly from the housing member and configured to be built into the primary structure or the movable structure; and

wherein at least a portion of the actuator assembly is manufactured and built into at least one of the primary structure and the movable structure so as to be within an outer mold line of the air vehicle.

2. An air vehicle according to claim 1 wherein the primary structure comprises at least one of a wing, a horizontal tail, a vertical tail or an airframe body.

3. An air vehicle according to claim 1 wherein different portions of the actuator assembly are manufactured and built into both the primary structure and the movable structure.

4. An air vehicle according to claim 3 wherein the actuation mechanism also comprises a motor configured to interact with the plurality of gears in order to cause movement of the movable structure relative to the primary structure.

5. An air vehicle according to claim 1 wherein the actuator assembly is a rotary electromechanical actuator.

6. An actuator assembly for an air vehicle having a primary structure and a movable structure configured to be controllably positioned about a rotation axis relative to the primary structure, the actuator assembly comprising:
an actuator housing; and
an actuation mechanism at least partially disposed within the actuator housing and configured to provide for relative movement between the primary structure and the movable structure,
wherein the actuator housing and the actuation mechanism comprise
a plurality of rings; and
a plurality of gears, wherein the plurality of rings and the plurality of gears are spaced apart in an axial direction defined by the rotation axis and the plurality of rings are configured to interlace with the plurality of gears to define the actuator housing, wherein each ring and gear comprises
a housing member; and
an extension extending outwardly from the housing member and configured to be built into the primary structure or the movable structure, and

wherein at least a portion of the actuator assembly is configured to be built into at least one of the primary structure and the movable structure so as to be within an outer mold line of the air vehicle.

7. An actuator assembly according to claim 6 wherein the primary structure comprises at least one of
a wing,
a horizontal tail,
a vertical tail or
an airframe body.

8. An actuator assembly according to claim 6 wherein different portions of the actuator assembly are configured to be built into both the primary structure and the movable structure.

9. An actuator assembly according to claim 8 wherein the actuation mechanism also comprises a motor configured to interact with the plurality of gears in order to cause movement of the movable structure relative to the primary structure.

10. An actuator assembly according to claim 6 wherein the actuator assembly is a rotary electromechanical actuator.

11. A method of forming an actuator assembly of an air vehicle, the method comprising:
building at least a portion of the actuator assembly comprising an actuator housing and actuation mechanism into at least one of a primary structure and a movable structure of the air vehicle such that the actuator assembly is within an outer mold line of the air vehicle, wherein the actuator housing and the actuation mechanism comprise
a plurality of rings; and
a plurality of gears, wherein the plurality of rings and the plurality of gears are spaced apart in an axial direction defined by a rotation axis and the plurality of rings are configured to interlace with the plurality of gears to define the actuator housing, wherein each ring and gear comprises
a housing member; and
an extension extending outwardly from the housing member and configured to be built into the primary structure or the movable structure; and

at least partially disposing at least a portion of the actuation mechanism within the actuator housing and operably coupling the actuation mechanism to the movable structure such that the actuation mechanism is configured to cause the movable structure to be positioned about the rotation axis relative to the primary structure.

12. A method according to claim 11 wherein the primary structure comprises at least one of a wing, a horizontal tail, a vertical tail or an airframe body.

13. A method according to claim 11 wherein building at least a portion of an actuator assembly into at least one of a primary structure and a movable structure comprises building different portions of the actuator assembly into both the primary structure and the movable structure.

14. A method according to claim 13 wherein the actuation mechanism also comprises a motor configured to interact with the plurality of gears in order to cause movement of the movable structure relative to the primary structure.

15. A method according to claim 11 wherein the actuator assembly is a rotary electromechanical actuator.

Assignees

• Boeing Co

Inventors

• Sheahan Jr James Joseph
• Drouin Jr Donald V

Classifications

• B64C13/38

  with power amplification · CPC title

• Y02T50/32

  Cross-Sectional Technologies · mapped topic

• B64C13/26 Primary

  without power amplification or where power amplification is irrelevant · CPC title

• Y10T29/49826

  Assembling or joining · CPC title

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title