A wing is provided, including a high-lift flap arranged on the wing such that it is movable by means of at least two adjustment mechanisms arranged side-by-side in the spanwise direction of the wing and adjustable by means of a drive device. Each adjustment mechanism includes a first adjustment leve
A wing is provided, including a high-lift flap arranged on the wing such that it is movable by means of at least two adjustment mechanisms arranged side-by-side in the spanwise direction of the wing and adjustable by means of a drive device. Each adjustment mechanism includes a first adjustment lever, articulated on a main wing surface via a first pivotal articulation, with the formation of a first rotation axis; a second adjustment lever, articulated on the high-lift flap via a second pivotal articulation, with the formation of a second rotation axis; and a central articulation, linking together the first and the second adjustment levers, with the formation of a third rotation axis. An intermediate articulated part is arranged on at least one of the adjustment mechanisms for coupling the first adjustment lever and the main wing surface, or for coupling the second adjustment lever and the high-lift flap.
대표청구항▼
1. A wing comprising a main wing surface, a high-lift flap, which is arranged on the wing such that it can be moved by means of at least two adjustment mechanisms arranged side-by-side in the spanwise direction of the main wing surface and adjustable by means of a drive device, each of the adjustmen
1. A wing comprising a main wing surface, a high-lift flap, which is arranged on the wing such that it can be moved by means of at least two adjustment mechanisms arranged side-by-side in the spanwise direction of the main wing surface and adjustable by means of a drive device, each of the adjustment mechanisms having: a first adjustment lever, which is articulated on the main wing surface via a first pivotal articulation, with the formation of a first axis of rotation,a second adjustment lever, which is articulated on the high-lift flap via a second pivotal articulation, with the formation of a second axis of rotation,a central articulation, which links together the first and the second adjustment levers, with the formation of a third axis of rotation, whereinthe first, second and third axes of rotation pass through a common pole, which is fixed while the high-lift flap is adjusted with reference to the location of the main wing surface, whereincharacterised in that on at least one of the adjustment mechanisms an intermediate articulated part with a base body, and at least one first and one second shaft mounting spaced apart in the transverse direction of the base body, is arranged and designed such that two shaft elements running in the longitudinal direction of the base body, spaced apart from one another in the transverse direction of the base body, are accommodated such that they can rotate,wherein the intermediate articulated part with the first shaft mounting supports a first shaft element with the formation of the first axis of rotation such that it can rotate, and with the second shaft mounting supports a fourth shaft element with the formation of a fourth axis of rotation such that it can rotate, for purposes of coupling the first adjustment lever and the main wing surface to the intermediate articulated part, with an axial separation distance between the first axis of rotation, and the fourth axis, or whereinthe intermediate articulated part, with the first shaft mounting supports a second shaft element with the formation of the second axis of rotation such that it can rotate, and with the second shaft mounting supports a fourth shaft element with the formation of a fourth axis of rotation such that it can rotate, for purposes of coupling the second adjustment lever and the high-lift flap to the intermediate articulated part, with an axial separation distance between the first axis of rotation and the fourth axis. 2. The wing in accordance with claim 1, wherein the base body is constituted in one piece. 3. The wing in accordance with claim 1, wherein the base body is constituted in two pieces from two intermediate levers, wherein each of the two intermediate levers has a pair of shaft mountings. 4. The wing in accordance with claim 1, wherein intermediate articulated part is designed such that the first axis of rotation and the fourth axis of rotation, or the second axis of rotation and the fourth axis of rotation respectively, in each case run parallel to one another. 5. The wing in accordance with claim 1, wherein the intermediate articulated part is constituted from a base body and arranged thereupon two pairs of shaft mountings, in each case with a first and a second shaft mounting, in each case for purposes of forming a pivotal bearing with an axis, wherein the first shaft mounting respectively accommodates a shaft element such that it can rotate to form the first axis of rotation or the second axis of rotation, and wherein the second shaft mounting respectively accommodates shaft elements such that they can rotate to form the fourth axis of rotation respectively, and the first and the second shaft mounting in each case of a pair of shaft mountings are spaced apart from one another in the transverse direction of the intermediate articulated part to form the axial separation distance between the respective axes of rotation. 6. The wing in accordance with claim 5, wherein the shaft mountings of the intermediate articulated part (Z) are arranged displaced relative to one another in the longitudinal direction of the intermediate articulated part. 7. The wing in accordance with claim 1, wherein the base body of the intermediate articulated part is constituted from two intermediate levers extending in the transverse direction, wherein the first intermediate lever has a pair of shaft mountings with a first and a second shaft mounting, in each case designed as a spherical bearing, in each case to accommodate a shaft section, in order to couple the intermediate articulated part at a first end to the high-lift flap or the main wing surface, and at a second end to the first adjustment lever or the second adjustment lever, and wherein the second intermediate lever at the first end is connected such that it cannot rotate with the high-lift flap or the main wing surface, and at the second end has a shaft mounting designed as a spherical bearing, with which the second end of the second intermediate lever is coupled with a shaft section of the first adjustment lever or the second adjustment lever. 8. The wing in accordance with claim 1, wherein the base body of the intermediate articulated part is constituted from two intermediate levers extending in the transverse direction, wherein the first intermediate lever has a pair of shaft mountings with a first and a second shaft mounting, in each case designed as a spherical bearing, in each case to accommodate a shaft section, in order to couple the intermediate articulated part at a first end to the first adjustment lever or the second adjustment lever, and at a second end to the high-lift flap or the main wing surface, and wherein the second intermediate lever at the first end is connected such that it cannot rotate with the first adjustment lever or the second adjustment lever, and at the second end has a shaft mounting designed as a spherical bearing, with which the second end of the second intermediate lever is coupled with a shaft section of the high-lift flap or the main wing surface. 9. The wing in accordance with claim 1, wherein the base body of the intermediate articulated part is constituted from two intermediate levers extending in the transverse direction, wherein the first intermediate lever has shaft mountings, spaced apart from one another in the transverse direction, with a first and a second shaft mounting, in each case designed as a spherical bearing, in each case to accommodate a shaft section such that it can rotate, wherein the intermediate articulated part at a first end is coupled with a shaft section of the high-lift flap or a shaft section of the main wing surface, and at a second end is coupled with a shaft section of the first adjustment lever or the second adjustment lever, and wherein the second intermediate lever has a pair of shaft mountings, spaced apart from one another in the transverse direction, with at least one first shaft mounting designed as a spherical bearing, and with at least one second shaft mounting designed as a non-spherical bearing, in each case to accommodate a shaft section such that it can rotate, wherein the intermediate articulated part at a first end is coupled with a shaft section of the high-lift flap or a shaft section of the main wing surface, and at a second end is coupled with a shaft section of the first adjustment lever or the second adjustment lever. 10. The wing in accordance with claim 9, wherein the second intermediate lever of the intermediate articulated part has shaft mountings spaced apart from one another in the transverse direction, with a first shaft mounting and two second shaft mountings, which in each case are designed as non-spherical bearings and to accommodate a shaft section such that it can rotate, wherein the intermediate articulated part at a first end is coupled with a shaft section of the high-lift flap or a shaft section of the main wing surface, and at a second end is coupled with a shaft section of the first adjustment lever or the second adjustment lever. 11. The wing in accordance with claim 9, wherein the second intermediate lever of the intermediate articulated part has shaft mountings spaced apart from one another in the transverse direction, with two first shaft mountings and one second shaft mounting, which in each case are designed as non-spherical bearings and to accommodate a shaft section such that it can rotate, wherein the intermediate articulated part at a first end is coupled with a shaft section of the high-lift flap or a shaft section of the main wing surface, and at a second end is coupled with a shaft section of the first adjustment lever or the second adjustment lever. 12. The wing in accordance with claim 1, wherein the high-lift flap is a leading-edge flap. 13. The wing in accordance with claim 12, wherein the leading-edge flap is a Krüger flap, which in its retracted setting lies against the underside of the main wing surface. 14. The wing in accordance with claim 12, wherein the leading-edge flap is a slat. 15. The wing in accordance with claim 1, wherein the high-lift flap is a trailing-edge flap. 16. The wing in accordance with claim 1, wherein the drive device is constituted from a linear drive. 17. The wing in accordance with claim 1, wherein the drive device is constituted from a rotary drive. 18. The wing in accordance with claim 1, wherein the wing has a stop device for purposes of limiting the maximum extended setting of the high-lift flap, and wherein the stop device is constituted with a stop lever acting between the first and the second adjustment lever, which is constituted in one piece with the first adjustment lever, or with the second adjustment lever, and as an extension of the same in the direction towards the second axis, or the first axis, and which is configured such that the free end of the stop lever can be brought into a stop setting with a bearing surface device on the second adjustment lever, or on the first adjustment lever so as to define the maximum extended setting of the respective adjustment mechanism. 19. The wing in accordance with claim 1, wherein the wing has a stop device for purposes of limiting the maximum extended setting of the high-lift flap, and wherein the stop device is constituted with a stop lever to limit the maximum extended setting of the high-lift flap, which is constituted in one piece with the first adjustment lever, or with a fitting on the main wing surface, and as an extension of the same in the direction towards the fitting on the main wing surface, or towards the third articulation, and is configured such that the free end of the stop lever can be brought into a stop setting with the fitting on the main wing surface, or the first adjustment lever so as to define the maximum extended setting of the respective adjustment mechanism. 20. The wing in accordance with claim 1, wherein the wing has a stop device for purposes of limiting the maximum extended setting of the high-lift flap, and wherein the stop device is constituted with a stop lever to limit the maximum extended setting of the high-lift flap, which is constituted in one piece with the second adjustment lever, or with a fitting on the high-lift flap, and as an extension of the same in the direction towards the fitting on the high-lift flap, or towards the third articulation, and is configured such that the free end of the stop lever can be brought into a stop setting with the fitting on the high-lift flap, or the second adjustment lever, so as to define the maximum extended setting of the respective adjustment mechanism.
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이 특허에 인용된 특허 (6)
Perez Sanchez,Juan, Actuation apparatus for a control flap arranged on a trailing edge of an aircraft airfoil.
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