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Disclosed is a method of enhancing aerodynamic performance of an aircraft wing assembly including a fixed section and a foldable section. The foldable section is hinged to the fixed section at a hinge axis. The method includes turning a torque box extending from the foldable section to rotate the fo

Disclosed is a method of enhancing aerodynamic performance of an aircraft wing assembly including a fixed section and a foldable section. The foldable section is hinged to the fixed section at a hinge axis. The method includes turning a torque box extending from the foldable section to rotate the foldable section about the hinge axis from a stowed position to a deployed position.

대표청구항 ▼

1. A method of enhancing aerodynamic performance of an aircraft wing assembly including a fixed section and a foldable section, the foldable section hinged to the fixed section at a hinge axis, the method comprising: turning a first hollow torque box extending from the foldable section and enclosing

1. A method of enhancing aerodynamic performance of an aircraft wing assembly including a fixed section and a foldable section, the foldable section hinged to the fixed section at a hinge axis, the method comprising: turning a first hollow torque box extending from the foldable section and enclosing an interior void relative to a second hollow torque box extending from the fixed section and enclosing an interior void, the second hollow torque box being hinged to the first hollow torque box at the hinge axis, wherein the hinge axis extends through lateral sides of the first and second torque boxes, thereby to rotate the foldable section about the hinge axis from a stowed position to a deployed position. 2. The method of claim 1, further comprising latching the first hollow torque box after the foldable section has been rotated to the deployed position. 3. The method of claim 2, wherein the first hollow torque box is latched to at least one of the fixed section and the second hollow torque box. 4. The method of claim 2, when latching the first hollow torque box includes using latch pins to engage the first hollow torque box. 5. The method of claim 2, when latching the first hollow torque box includes extending latch pins through a closeout rib of the fixed section to engage the first hollow torque box. 6. The method of claim 1, wherein the aircraft wing assembly is part of an aircraft, and wherein the foldable section is rotated to the deployed position while the aircraft is on a runway prior to takeoff. 7. The method of claim 6, wherein the first hollow torque box is turned about the hinge axis to rotate the foldable section back to the stowed position after the aircraft has landed. 8. The method of claim 6, wherein the foldable section is in the stowed position while the aircraft is moved from a gate area to the runway. 9. The method of claim 1, wherein rotary actuators are used to turn the first hollow torque box about the hinge axis. 10. The method of claim 1, wherein the foldable section is a raked wing tip. 11. A method of enhancing aerodynamic performance of an aircraft, wherein the aircraft has a wing assembly including a wing tip having a first hollow torque box enclosing an interior void, and a fixed section having a second hollow torque box enclosing an interior void and extending outward in a spanwise direction, the first and second hollow torque boxes hinged together about a hinge axis, and wherein enhancing the aerodynamic performance includes: turning the first hollow torque box about the hinge axis to fold the wing tip from a stowed position to a deployed position; andlatching the first hollow torque box after the wing tip has been folded to the deployed position. 12. The method of claim 11, wherein the first hollow torque box is latched to the fixed section. 13. The method of claim 11, when latching the first hollow torque box includes using latch pins to engage the first hollow torque box. 14. The method of claim 11, when latching the first hollow torque box includes extending latch pins through a closeout rib of the wing tip to engage the first hollow torque box. 15. The method of claim 11, wherein rotary actuators are used to turn the first hollow torque box about the hinge axis. 16. The method of claim 11, wherein the wing tip is folded to the deployed position while the aircraft is on a runway prior to takeoff. 17. The method of claim 16, wherein the first hollow torque box is turned about the hinge axis to fold the wing tip back to the stowed position after the aircraft has landed. 18. The method of claim 16, wherein the wing tip is in the stowed position while the aircraft is moved from a gate area to the runway.