초록 ▼

A method and apparatus for managing a flight control surface system. A leading edge device is moved on a leading edge from an undeployed position to a deployed position. The leading edge device has an outer surface, an inner surface, and a deformable fairing attached to the leading edge device such

A method and apparatus for managing a flight control surface system. A leading edge device is moved on a leading edge from an undeployed position to a deployed position. The leading edge device has an outer surface, an inner surface, and a deformable fairing attached to the leading edge device such that the deformable fairing covers at least a portion of the inner surface. The deformable fairing changes from a deformed shape to an original shape when the leading edge device is moved to the deployed position. The leading edge device is then moved from the deployed position to the undeployed position, wherein the deformable fairing changes from the original shape to the deformed shape.

대표청구항 ▼

1. An apparatus comprising: a leading edge device having an outer surface and an inner surface, the outer surface being farther from, and the inner surface being nearer to, a structure connected to an actuator, the actuator configured to deploy the leading edge device away from the structure and to

1. An apparatus comprising: a leading edge device having an outer surface and an inner surface, the outer surface being farther from, and the inner surface being nearer to, a structure connected to an actuator, the actuator configured to deploy the leading edge device away from the structure and to remove a mechanical load from a fairing when the leading edge device is in a deployed position; andthe fairing, attached to the leading edge device such that the fairing is configured to cover at least a portion of the inner surface, the fairing configured in an original shape, wherein the original shape comprises a solid form comprising a yield strain level adequate to return the fairing to the original shape, from a deformed shape that occurs when the leading edge device is in an undeployed position. 2. The apparatus of claim 1 further comprising: the structure being a wing, wherein the leading edge device is moveably attached to the wing. 3. The apparatus of claim 2 further comprising: a leading edge surface on the wing, wherein the fairing is configured to change from the original shape to the deformed shape when the fairing is pushed against the leading edge surface when moving into the undeployed position. 4. The apparatus of claim 3, wherein the fairing is comprised of a layer of a shape memory alloy and a coating configured to reduce wear on at least one of the fairing and the leading edge surface. 5. The apparatus of claim 1, wherein the fairing with the original shape reduces noise caused by air flowing over the leading edge device when the leading edge device is in the deployed position. 6. The apparatus of claim 1, wherein the leading edge device is configured to cause a change in airflow that increases lift of an aircraft when the leading edge device is in the deployed position as compared to the undeployed position. 7. The apparatus of claim 1, wherein a space is present between the fairing and the inner surface when the leading edge device is in the deployed position. 8. The apparatus of claim 1, wherein the actuator comprises: a number of actuators; anda slide system. 9. The apparatus of claim 1, wherein the fairing is comprised of a material selected from one of a shape memory alloy, a nickel-titanium alloy, nitinol, aluminum, titanium, steel, a plastic, a synthetic composite, a polyurethane, a metal, and a metal alloy. 10. The apparatus of claim 1, wherein the leading edge device is a slat. 11. The apparatus of claim 2, wherein the wing is associated with a platform. 12. The apparatus of claim 11, wherein the platform is selected from one of an aircraft and a spacecraft. 13. A flight control surface system comprising: a slat having an outer surface and an inner surface, the outer surface being farther from, and the inner surface being nearer to, a wing;a fairing attached to the slat, the fairing configured to cover at least a portion of the inner surface, wherein the fairing is comprised of a shape memory alloy configured in an original shape when the slat is in a deployed position, wherein the original shape comprises a solid form comprising a yield strain level adequate to autonomously return the fairing to the original shape, from a deformed shape that occurs when the slat is in an undeployed position;the wing having a leading edge, wherein the slat is moveably attached to the leading edge of the wing; andan actuator system configured to move the slat between the deployed position and the undeployed position, and to remove a mechanical load from the deformable fairing as the actuator system moves the slat from the undeployed position to the deployed position. 14. The flight control surface system of claim 13, wherein the wing is associated with a platform selected from one of an aircraft and a spacecraft. 15. An apparatus comprising an edge device having an outer surface and an inner surface, the outer surface being farther from, and the inner surface being nearer to, a structure adjacent to the edge device; a fairing attached to the edge device, the fairing configured to cover at least a portion of the inner surface, wherein the fairing has an original shape, the fairing comprising a component configured to autonomously return the fairing to the original shape, from a deformed state, when the edge device is in a deployed position, and a deformed shape when the edge device is in an undeployed position; andan actuator, the actuator attached to the structure and the edge device, and configured to deploy the edge device away from the structure and to remove a mechanical load from the fairing when the edge device is in the deployed position. 16. The apparatus of claim 15, wherein the edge device is selected from one of a leading edge device and a trailing edge device. 17. The apparatus of claim 15, wherein the component is a spring system. 18. The apparatus of claim 15, wherein the component is a shape metal alloy comprising a yield strain level adequate to return the fairing to the original shape.