[특허]Air vehicle, actuator assembly and associated method of manufacture

The Boeing Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Air vehicle, actuator assembly and associated method of manufacture

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-009/02 B64C-013/34 B64C-009/00 B64C-013/26 B64C-013/38 B64C-013/40 B64C-013/50
출원번호	US-0242088 (2014-04-01)
등록번호	US-9643716 (2017-05-09)
발명자 / 주소	Sheahan, Jr., James Joseph Drouin, Jr., Donald V.
출원인 / 주소	The Boeing Company
대리인 / 주소	Alston & Bird LLP
인용정보	피인용 횟수 : 0 인용 특허 : 10

초록
▼

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.

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청구항
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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; andan actuator assembly configured to cause the movable structure to be positioned relative to the primary structure, wherein the actuator assembly comprises: an actuator housing; andan 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; anda 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; andan extension extending outwardly from the housing member and configured to be built into the primary structure or the movable structure; andwherein 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; andan 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; anda 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; andan extension extending outwardly from the housing member and configured to be built into the primary structure or the movable structure, andwherein 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 oran 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; anda 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; andan extension extending outwardly from the housing member and configured to be built into the primary structure or the movable structure; andat 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.

이 특허에 인용된 특허 (10)

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Air vehicle, actuator assembly and associated method of manufacture

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Air vehicle, actuator assembly and associated method of manufacture

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이 특허에 인용된 특허 (10)

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