초록 ▼

Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position

Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path. An outboard trailing edge device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.

대표청구항 ▼

We claim: 1. An aircraft system, comprising: a wing; an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path, wherein an airflow gap exists between the inboard trailing edge device a

We claim: 1. An aircraft system, comprising: a wing; an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path, wherein an airflow gap exists between the inboard trailing edge device and the wing when the inboard trailing edge device is in the first deployed position; an outboard trailing edge device coupled to the wing outboard of the inboard trailing edge device, and being movable relative to the wing between a second stowed position and a second deployed position along a second motion path that is non-parallel to the first motion path, wherein an airflow gap exists between the outboard trailing edge device and the wing when the outboard trailing edge device is in the second deployed position; and an intermediate trailing edge device coupled to the wing between the inboard and outboard trailing edge devices, and being movable relative to the wing between a third stowed position and a third deployed position along a third motion path that is non-parallel to both the first and second motion paths, wherein an airflow gap exists between the intermediate trailing edge device and the wing when the intermediate trailing edge device is in the second deployed position, and wherein the wing does not include fixed upwardly facing external surfaces (a) between the inboard trailing edge device and the intermediate trailing edge device, and (b) between the intermediate trailing edge device and the outboard trailing edge device. 2. The aircraft system of claim 1 wherein: the inboard trailing edge device has a first leading edge, the outboard trailing edge device has a second leading edge and the intermediate trailing edge device has a third leading edge; the first, second and third leading edges are offset from each other when the trailing edge devices are in their stowed positions; the first deployed position is one of multiple first deployed positions, the second deployed position is one of multiple second deployed positions, and the third deployed position is one of multiple third deployed positions; and for at least one combination of a first deployed position, a second deployed position and a third deployed position, the first, second and third leading edges form a composite leading edge profile that follows a generally monotonic function. 3. The aircraft system of claim 1 wherein the first, second and third motion paths converge toward each other in an aft direction. 4. The aircraft system of claim 1 wherein intermediate trailing edge device has a generally trapezoidal planform shape. 5. The aircraft system of claim 1 wherein the inboard trailing edge device has a first leading edge, the outboard trailing edge device has a second leading edge and the intermediate trailing edge device has a third leading edge, and wherein the first, second and third leading edges are offset from each other when the trailing edge devices are in their stowed positions. 6. The aircraft system of claim 1 wherein the inboard trailing edge device has a first trailing edge, the outboard trailing edge device has a second trailing edge and the intermediate trailing edge device has a third trailing edge, and wherein the first, second and third trailing edges form a composite trailing edge profile that follows a generally monotonic function when the trailing edge devices are in their stowed positions. 7. The aircraft system of claim 1 wherein the wing has a longitudinal axis and wherein the inboard trailing edge device has a first leading edge with a first sweep angle relative to the longitudinal axis, the outboard trailing edge device has a second leading edge with a second sweep angle greater than the first sweep angle, and the intermediate trailing edge device has a third leading edge with a third sweep angle (a) greater than the first sweep angle and less than or equal to the second sweep angle, or (b) greater than or equal to the first sweep angle and less than the second sweep angle. 8. The aircraft system of claim 1 wherein the wing has a longitudinal axis and wherein the inboard trailing edge device has a first leading edge with a first sweep angle relative to the longitudinal axis, the outboard trailing edge device has a second leading edge with a second sweep angle, and wherein the inboard trailing edge device moves generally normal to the first leading edge and the outboard trailing edge device moves generally normal to the second leading edge. 9. The aircraft system of claim 1, further comprising: an inboard spoiler positioned forward of the inboard trailing edge device; an outboard spoiler positioned forward of the outboard trailing edge device; and an intermediate spoiler positioned forward of the intermediate trailing edge device, wherein each of the spoilers is movable between a stowed position, a downwardly deflected position, and an upwardly deflected position. 10. The aircraft system of claim 9 wherein the wing has a longitudinal axis and wherein the inboard spoiler has a first hinge line with a first sweep angle relative to the longitudinal axis, the outboard spoiler has a second hinge line with a second sweep angle relative to the longitudinal axis, and the intermediate spoiler has a third hinge line with a third sweep angle relative to the longitudinal axis, and wherein the third sweep angle is greater than the first sweep angle and less than the second sweep angle. 11. The aircraft system of claim 9 wherein the inboard spoiler has a first trailing edge, the outboard spoiler has a second trailing edge, and the intermediate spoiler has a third trailing edge, and wherein the first, second and third trailing edges form a composite trailing edge profile that follows a generally monotonic function when the spoilers are in their stowed positions. 12. The aircraft system of claim 9 wherein the inboard spoiler has a first trailing edge, the outboard spoiler has a second trailing edge, and the intermediate spoiler has a third trailing edge, and wherein the first, second and third trailing edges form a generally continuous composite trailing edge when the spoilers are in their downwardly deflected positions. 13. The aircraft system of claim 9 wherein each of the spoilers is movable to multiple downwardly deflected positions, and wherein the inboard spoiler has a first trailing edge, the outboard spoiler has a second trailing edge, and the intermediate spoiler has a third trailing edge, and wherein the first, second and third trailing edges form a composite trailing edge profile that follows a generally monotonic function when the spoilers are moved in a coordinated fashion to any of their downwardly deflected positions. 14. The aircraft system of claim 1, further comprising a control system operatively coupled to the trailing edge devices to control motion of the trailing edge devices. 15. The aircraft system of claim 1 wherein the wing includes a wing fuel volume and wherein the outboard trailing edge device has a chord length and wherein the system further comprises a rear wing spar positioned aft of the wing fuel volume, and wherein the rear wing spar is located at a distance forward of the outboard trailing edge device, with a ratio of the distance to the chord length having a value of about 0.5 or higher. 16. An aircraft, comprising: a fuselage having a longitudinal axis; a wing coupled to the fuselage; and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path, wherein an airflow gap exists between the inboard trailing edge device and the wing when the inboard trailing edge device is in the first deployed position, the inboard trailing edge device having (a) a first leading edge with a first sweep angle relative to the longitudinal axis, and (b) a first trailing edge; an outboard trailing edge device coupled to the wing outboard of the inboard trailing edge device, and being movable relative to the wing between a second stowed position and a second deployed position along a second motion path that is non-parallel to the first motion path, wherein an airflow gap exists between the outboard trailing edge device and the wing when the outboard trailing edge device is in the second deployed position, the outboard trailing edge device having (a) a second leading edge with a second sweep angle relative to the longitudinal axis, and (b) a second trailing edge; and an intermediate trailing edge device coupled to the wing between the inboard and outboard trailing edge devices, and being movable relative to the wing between a third stowed position and a third deployed position along a third motion path that is non-parallel to both the first and second motion paths, wherein an airflow gap exists between the intermediate trailing edge device and the wing when the intermediate trailing edge device is in the third deployed position, the intermediate trailing edge device having (a) a third leading edge with a third sweep angle relative to the longitudinal axis, the third sweep angle being greater than the first sweep angle and less than the second sweep angle, and (b) a third trailing edge; wherein the first, second and third leading edges are offset from each other when the trailing edge devices are in their stowed positions; the first, second and third leading edges form a generally monotonic leading edge profile when the trailing edge devices are in their deployed positions; the first, second and third trailing edges are offset from each other when the trailing edge devices are in their deployed positions; and the first, second and third trailing edges form a generally monotonic trailing edge profile when the trailing edge devices are in their deployed positions; and wherein the wing does not include fixed upwardly facing external surfaces (a) between the inboard trailing edge device and the intermediate trailing edge device, and (b) between the intermediate trailing edge device and the outboard trailing edge device. 17. The system of claim 16 wherein the first, second and third motion paths converge toward each other in an aft direction. 18. A method for operating an aircraft wing, comprising: moving an inboard trailing edge device relative to an aircraft wing between a first stowed position and a first deployed position along a first motion path to open a gap between the inboard trailing edge device and the wing; moving an outboard trailing edge device relative to the wing between a second stowed position and a second deployed position along a second motion path that is non-parallel to the first motion path to open a gap between the outboard trailing edge device and the wing; and moving an intermediate trailing edge device relative to the wing between a third stowed position and a third deployed position along a third motion path that is non-parallel to the first and second motion paths to open a gap between the intermediate trailing edge device and the wing, wherein the intermediate trailing edge device is positioned between the inboard and outboard trailing edge devices, and wherein the wing does not include fixed upwardly facing external surfaces (a) between the inboard trailing edge device and the intermediate trailing edge device, and (b) between the intermediate trailing edge device and the outboard trailing edge device. 19. The method of claim 18 wherein moving the trailing edge devices includes moving the trailing edge devices along motion paths that converge toward each other in an aft direction. 20. The method of claim 18 wherein the inboard trailing edge device has a first trailing edge, and a first leading edge with a first sweep angle, the outboard trailing edge device has a second trailing edge, and a second leading edge with a second sweep angle greater than the first sweep angle, and the intermediate leading edge device has a third trailing edge, and a third leading edge with a third sweep angle greater than the first sweep angle and less than the second sweep angle, and wherein the method further comprises: offsetting the first, second, and third leading edges from each other when the trailing edge devices are in their stowed positions; aligning the first, second and third leading edges to form a generally monotonic leading edge profile when the trailing edge devices are in their deployed positions; offsetting the first, second and third trailing edges when the trailing edge devices are in their deployed positions; and aligning the first, second and third trailing edges form a generally monotonic composite trailing edge profile when the trailing edge devices are in their stowed positions. 21. The method of claim 18 wherein the inboard trailing edge device has a first leading edge, the outboard trailing edge device has a second leading edge and the intermediate trailing edge device has a third leading edge, and wherein stowing the trailing edge devices includes positioning the first, second and third leading edges to be offset from each other. 22. The method of claim 18 wherein: the first deployed position is one of multiple first deployed positions, the second deployed position is one of multiple second deployed positions, and the third deployed position is one of multiple third deployed positions; and wherein moving the trailing edge devices includes moving the trailing edge devices to at least one combination of a first deployed position, a second deployed position and a third deployed position where the first, second and third leading edges form a generally continuous composite leading edge. 23. The method of claim 18 wherein the inboard trailing edge device has a first trailing edge, the outboard trailing edge device has a second trailing edge and the intermediate trailing edge device has a third trailing edge, and wherein moving the trailing edge devices includes moving the first, second and third trailing edges to form a composite trailing edge profile that follows a generally monotonic function when the trailing edge devices are their stowed positions, and moving the first, second and third trailing edges be offset from each other when the trailing edge devices are in their deployed positions. 24. The method of claim 18, further comprising: downwardly deflecting an inboard spoiler located forward of the inboard trailing edge device, the inboard spoiler having a first trailing edge; downwardly deflecting an outboard spoiler located forward of the outboard trailing edge device, outboard spoiler having a second trailing edge; and downwardly deflecting an intermediate spoiler located forward of the intermediate trailing edge device so that a third trailing edge of the intermediate spoiler forms a generally continuous, composite trailing edge with the first and second trailing edges. 25. The method of claim 24 wherein each of the trailing edge devices is movable to multiple deployed positions, and wherein each of the spoilers is movable to corresponding multiple downwardly deflected positions, and wherein for each of the multiple downwardly deflected positions, the spoilers are moved so that the first, second and third trailing edges form a composite trailing edge profile that follows a generally monotonic function.