[특허]Deployable flap edge fence

The Boeing Company

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Deployable flap edge fence

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-023/06
미국특허분류(USC)	244/199.4; 244/204.1
출원번호	UP-0741713 (2007-04-27)
등록번호	US-7753316 (2010-08-02)
발명자 / 주소	Larssen, Jon V. Calkins, Frederick T.
출원인 / 주소	The Boeing Company
대리인 / 주소	Tung & Associates
인용정보	피인용 횟수 : 12 인용 특허 : 11

초록

A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions.

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What is claimed is: 1. A system for reducing airflow noise for an aircraft having a wing main element, the system comprising: a flap coupled to the wing main element; a moveable flap edge fence coupled to the flap, said flap edge fence independently moveable with respect to said flap; and a control mechanism for the flap edge fence, the control mechanism being configured to: deploy the flap edge fence by moving said flap edge fence to a first position for a first set of flight conditions; and stow the flap edge fence by moving said flap edge fence to a second position for a second set of flight conditions. 2. The system according to claim 1, wherein: the flap has a tip, a trailing edge, a leading edge, an upper surface, and a lower surface; and the flap edge fence is coupled to the leading edge and to the trailing edge near the tip. 3. The system according to claim 1, wherein: the control mechanism is configured to deploy the flap edge fence into a deployed shape and position that reduces the airflow noise by preventing rollover of vortices from a lower surface of the flap to an upper surface of the flap; and the control mechanism is configured to stow the flap edge fence into a stowed shape and position that reduces drag by reducing interaction of the flap edge fence with a local air-flow over the wing main element. 4. The system according to claim 1, further comprising a trained shape memory torque tube coupled to the flap edge fence and to the flap, and configured to change the position of the flap edge fence in response to a temperature change. 5. The system according to claim 4, further comprising a controller configured to: monitor temperature of the trained shape memory torque tube; and provide the temperature change by heating/cooling of the trained shape memory torque tube based on a flight condition. 6. The system according to claim 4, wherein the temperature change is passively provided by ambient temperature corresponding to an altitude at a flight condition. 7. The system according to claim 4, wherein: the trained shape memory torque tube is thermally activated at a first temperature range to drive towards an austenitic trained shape; the trained shape memory torque tube generates a moment between the flap edge fence and the flap with sufficient torque to deploy the flap edge fence for the first set of flight conditions; and the trained shape memory torque tube is thermally deactivated at a second temperature range to return to its martensitic shape which allows the flap edge fence to stow on the flap for the second set of flight conditions. 8. The system according to claim 4, wherein: the trained shape memory torque tube is thermally activated to drive towards an austenitic trained shape which allows the flap edge fence to stow on the flap, and the trained shape memory torque tube is thermally deactivated to return to its martensitic shape which allows the flap edge fence to deploy. 9. The system according to claim 1, wherein the flap edge fence is made of a shape memory alloy that is configured to change shape in response to a temperature change. 10. The system according to claim 9, further comprising a controller configured to: monitor temperature of the flap edge fence; and provide the temperature change by heating/cooling of the flap edge fence based on a flight condition. 11. The system according to claim 9, wherein the temperature change is passively provided by ambient temperature corresponding to an altitude at a flight condition. 12. The system according to claim 9, wherein: the flap edge fence is thermally deployed at a predetermined bending angle at a first temperature range for the first set of flight conditions; and the flap edge fence is thermally stowed along a direction of a streamlined air flow at a second temperature range for the second set of flight conditions. 13. The system according to claim 1, wherein the flap edge fence is mounted to a lower surface of the flap. 14. The system according to claim 1, wherein the flap edge fence is mounted to an upper surface of the flap. 15. The system according to claim 1, wherein a first flap edge fence is mounted to an upper surface of the flap and a second flap edge fence is mounted to a lower surface of the flap. 16. A system for reducing airflow noise for an aircraft having a wing main element, the system comprising: a flap coupled to the wing main element; a flap edge fence coupled to the flap; a trained shape memory torque tube coupled to the flap edge fence and to the flap, the trained shape memory torque tube being configured to actuate the flap edge fence in response to a temperature change, said actuation causing movement of said flap edge fence independent of movement of said flap; and a controller coupled to the trained shape memory torque tube, the controller being configured to: actively control temperature of the trained shape memory torque tube into a first temperature range to drive the trained shape memory torque tube towards an austenitic trained shape, wherein the trained shape memory torque tube generates a moment between the flap edge fence and the flap with sufficient torque to deploy the flap edge fence for a first set of flight conditions; and actively control the temperature of the trained shape memory torque tube into a second temperature range to return the trained shape memory torque tube to its martensitic shape which allows the flap edge fence to stow on the flap for a second set of flight conditions. 17. The system according to claim 16, wherein the temperature change is passively provided by changes in ambient temperature. 18. A system for reducing airflow noise for an aircraft having a wing main element, the system comprising: a flap coupled to the wing main element, wherein the flap has a tip, a flap trailing edge, a flap leading edge, an upper surface and a lower surface; a shape memory flap edge fence coupled to the flap trailing edge and the flap leading edge near the tip of the flap, the shape memory flap edge fence being configured to morph, in response to a temperature change, into a deployed position with a predetermined bending angle at a first temperature range for a first set of flight conditions, and into a stowed position along a direction of a streamlined air flow at a second temperature range during a second set of flight conditions, said morphing causing movement of said flap edge fence independent of movement of said flap. 19. The system according to claim 18, further coin rising a controller configured to: monitor temperature of the shape memory flap edge fence; and provide the temperature change by heating/cooling of the shape memory flap edge fence. 20. The system according to claim 18, wherein the temperature change is passively provided by changes in ambient temperature.

이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 12

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Deployable flap edge fence

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이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 12

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특허 상세정보

Deployable flap edge fence

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이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 12

IPC 상위 출원인

상세정보조회

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IPC 상세정보(version : 201201)

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