IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0505065
(2009-07-17)
|
등록번호 |
US-8534611
(2013-09-17)
|
발명자
/ 주소 |
- Pitt, Dale M.
- Eckstein, Nicholas Stephen
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
6 인용 특허 :
22 |
초록
▼
A method and apparatus for managing a flight control surface system. A leading edge section on a wing of an aircraft is extended into a deployed position. A deformable section connects the leading edge section to a trailing section. The deformable section changes from a deformed shape to an original
A method and apparatus for managing a flight control surface system. A leading edge section on a wing of an aircraft is extended into a deployed position. A deformable section connects the leading edge section to a trailing section. The deformable section changes from a deformed shape to an original shape when the leading edge section is moved into the deployed position. The leading edge section on the wing is moved from the deployed position to an undeployed position. The deformable section changes to the deformed shape inside of the wing.
대표청구항
▼
1. An apparatus comprising: a leading edge section;a trailing section, the trailing section comprising an upper skin and a lower skin, the leading edge section and the upper skin being discontinuous, the leading edge section and the lower skin being discontinuous; anda deformable section connecting
1. An apparatus comprising: a leading edge section;a trailing section, the trailing section comprising an upper skin and a lower skin, the leading edge section and the upper skin being discontinuous, the leading edge section and the lower skin being discontinuous; anda deformable section connecting the leading edge section to the trailing section, the deformable section comprising an upper deformable section and a lower deformable section, the upper deformable section positioned between the leading edge section and the upper skin, the lower deformable section positioned between the leading edge section and the lower skin, wherein the deformable section has an original shape that is configured to deform when the leading edge section moves into an undeployed position and to return substantially to the original shape when the leading edge section extends into a deployed position, wherein at least a portion of the upper deformable section and a portion of the lower deformable section are positioned in an interior of the leading edge section, the trailing section, or both the leading edge section and the trailing section, in the undeployed position. 2. The apparatus of claim 1 further comprising: an actuator system configured to move the leading edge section between the undeployed position and the deployed position. 3. The apparatus of claim 1, wherein the deformable section comprises a number of flexible panels. 4. The apparatus of claim 1, wherein the upper deformable section comprises a first flexible panel and the lower deformable section comprises a second flexible panel. 5. The apparatus of claim 4, wherein the first flexible panel and the second flexible panel are comprised of a material selected from one of a shape memory alloy, nitinol, and a nickel-titanium alloy. 6. The apparatus of claim 1 further comprising: an aircraft, wherein the leading edge section, the trailing section, and the deformable section are part of a wing on the aircraft and cause a change in airflow that reduces a stalling speed of the aircraft in the deployed position as compared to the undeployed position. 7. The apparatus of claim 1 further comprising: a wing, wherein the leading edge section, the trailing section, and the deformable section connecting the leading edge section to the trailing section are part of the wing. 8. The apparatus of claim 2, wherein the actuator system comprises: a number of actuators; anda slide system. 9. The apparatus of claim 1, wherein the deformable section has the original shape that is configured to deform when the leading edge section moves into the undeployed position and to return substantially to the original shape when the leading edge section extends and lowers into the deployed position. 10. The apparatus of claim 1 further comprising: a platform, wherein the leading edge section, the trailing section, and the deformable section are associated with the platform. 11. The apparatus of claim 10, wherein the platform is selected from one of a mobile platform, an aircraft, and a spacecraft. 12. A flight control surface system comprising: a skin panel connected to a wing structure of an aircraft;a leading edge section, the skin panel comprising an upper skin and a lower skin, the leading edge section and the second upper skin being discontinuous, the leading edge section and the lower skin being discontinuous;a flexible panel comprised of a shape memory alloy, wherein the flexible panel has an original shape and is connected to the skin panel and the leading edge section, the flexible panel comprising an upper deformable section and a lower deformable section, the upper deformable section positioned between the leading edge section and the upper skin, the lower deformable section positioned between the leading edge section and the lower skin, wherein the skin panel, the flexible panel, and the leading edge section form a surface for the wing structure; andan actuator system connected to the leading edge section, wherein the actuator system is configured to move and extend the leading edge section from an undeployed position to a deployed position and move the leading edge section back to the undeployed position, wherein the flexible panel has the original shape when the leading edge section is deployed and has a deformed shape when the leading edge section is in the undeployed position, and wherein the skin panel in the original shape, the flexible panel, and the leading edge section cause a change in air flow that reduces a stalling speed of the aircraft in the deployed position as compared to the undeployed position, wherein at least a portion of the upper deformable section and a portion of the lower deformable section are positioned in an interior of the leading edge section, the trailing section, or both the leading edge section and the trailing section, in the undeployed position. 13. The flight control surface system of claim 12, wherein the shape memory alloy is comprised of a material selected from one of nitinol and a nickel-titanium alloy. 14. A method for managing a flight control surface system, the method comprising: extending a leading edge section on a wing of an aircraft into a deployed position, a deformable section connecting the leading edge section to a trailing section, the trailing section comprising an upper skin and a lower skin, the leading edge section and the upper skin being discontinuous, the leading edge section and the lower skin being discontinuous, and wherein the deformable section changes from a deformed shape to an original shape when the leading edge section is moved into the deployed position, the deformable section comprising an upper deformable section and a lower deformable section, the upper deformable section positioned between the leading edge section and the upper skin, the lower deformable section positioned between the leading edge section and the lower skin; andmoving the leading edge section on the wing from the deployed position to an undeployed position, wherein the deformable section changes to the deformed shape inside of the wing, wherein at least a portion of the upper deformable section and a portion of the lower deformable section are positioned in an interior of the leading edge section, the trailing section, or both the leading edge section and the trailing section, in the undeployed position. 15. The method of claim 14, wherein the leading edge section is moved using an actuator system. 16. The method of claim 14, wherein the deformable section comprises at least one of a number of flexible panels, a plurality of folding panels configured to fold with respect to each other, and a plurality of sliding panels configured to slide with respect to each other. 17. The method of claim 14, wherein the upper deformable section comprises a first flexible panel and the lower deformable section comprises a second flexible panel. 18. The method of claim 17, wherein the first flexible panel and the second flexible panel are comprised of a material selected from a shape memory alloy, nitinol, and a nickel-titanium alloy. 19. The method of claim 14, wherein the leading edge section is moved into the deployed position during a landing phase of flight. 20. The method of claim 14, wherein the leading edge section is moved into the deployed position to cause a change in airflow that reduces a stalling speed of an aircraft in the deployed position as compared to the undeployed position. 21. The method of claim 14, wherein the step of extending the leading edge section on the wing of the aircraft into the deployed position comprises: extending and lowering the leading edge section on the wing of the aircraft into the deployed position. 22. The apparatus of claim 1, wherein the deformable section comprises a plurality of folding panels configured to fold with respect to each other. 23. The apparatus of claim 1, wherein the deformable section comprises a plurality of sliding panels configured to slide with respect to each other.
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