An aerofoil wing with a main aerofoil, a high-lift flap movably arranged on the aerofoil wing by adjustment mechanisms. Each of the adjustment mechanisms including a first adjustment lever hinged to the main aerofoil via a first rotary linkage, with the formation of a first axis of rotation, a secon
An aerofoil wing with a main aerofoil, a high-lift flap movably arranged on the aerofoil wing by adjustment mechanisms. Each of the adjustment mechanisms including a first adjustment lever hinged to the main aerofoil via a first rotary linkage, with the formation of a first axis of rotation, a second adjustment lever hinged to the high-lift flap via a second rotary linkage, with the formation of a second axis of rotation, and a central linkage, with the formation of a third axis of rotation, such that the first, second and third axes of rotation pass through a common pole. The aerofoil wing further includes a drive device with a drive module mounted on the main aerofoil, and movable with respect to the drive module a drive lever coupled to the high-lift flap, and a stop device to limit the maximum extended setting of the high-lift flap.
대표청구항▼
1. An aerofoil wing comprising a main aerofoil and a high-lift flap, which is movably arranged on the aerofoil wing by at least two adjustment mechanisms arranged side-by-side in a spanwise direction of the aerofoil wing, each of the adjustment mechanisms having: a first adjustment lever, which is h
1. An aerofoil wing comprising a main aerofoil and a high-lift flap, which is movably arranged on the aerofoil wing by at least two adjustment mechanisms arranged side-by-side in a spanwise direction of the aerofoil wing, each of the adjustment mechanisms having: a first adjustment lever, which is hinged to the main aerofoil via a first rotary linkage, forming a first axis of rotation,a second adjustment lever, which is hinged to the high-lift flap via a second rotary linkage, forming a second axis of rotation, anda central linkage, which links together the first and the second adjustment levers, forming a third axis of rotation,wherein the aerofoil wing has a drive device with a drive module mounted on the main aerofoil and movable with respect to the drive module a drive lever, which is coupled to the high-lift flap to exert force between the main aerofoil and the high-lift flap in a manner bypassing the adjustment mechanism,the aerofoil wing having a stop device to limit a maximum extended setting of the high-lift flap. 2. The aerofoil wing in accordance with claim 1, wherein the high-lift flap is a leading-edge flap. 3. The aerofoil wing in accordance with claim 2, wherein the leading-edge flap is a Krüger flap, which in its retracted position lies against the underside of the main aerofoil. 4. The aerofoil wing in accordance with claim 3, wherein the leading-edge flap is a slat. 5. The aerofoil wing in accordance with claim 1, wherein the high-lift flap is a trailing-edge flap. 6. The aerofoil wing in accordance with claim 1, wherein the drive device comprises a linear drive. 7. The aerofoil wing in accordance with claim 1, wherein the drive device comprises a rotary drive. 8. The aerofoil wing in accordance with claim 1, wherein the stop device comprises a stop lever acting between the first and the second adjustment lever, which is integrally constituted with the first adjustment lever, or with the second adjustment lever, and as an extension of the same in a direction towards the second axis, or the first axis, and is configured such that a free end of the stop lever can be brought into a stop setting with a bearing device on the second adjustment lever, or on the first adjustment lever so as to define a maximum extended setting of the respective adjustment mechanism. 9. The aerofoil wing in accordance with claim 1, wherein the stop device comprises a stop lever to limit the maximum extended setting of the high-lift flap, which is integrally constituted with the first adjustment lever, or with a fitting of the main aerofoil, and as an extension of the same in a direction towards the fitting of the main aerofoil, or towards the third linkage, and is configured such that a free end of the stop lever can be brought into a stop setting with the fitting on the main aerofoil, or the first adjustment lever so as to define a maximum extended setting of the respective adjustment mechanism. 10. The aerofoil wing in accordance with claim 1, wherein the stop device comprises a stop lever to limit the maximum extended setting of the high-lift flap, which is integrally constituted with the second adjustment lever, or with a fitting of the high-lift flap, and as an extension of the same in a direction towards the fitting of the high-lift flap, or towards the third linkage, and is configured such that a 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 a maximum extended setting of the respective adjustment mechanism. 11. The aerofoil wing in accordance with claim 2, wherein the stop device is configured such that with the latter a maximum extended setting of the leading-edge flap is limited, whereby directions of action of the adjustment lever have an angle of less than 180 degrees relative to one another. 12. The aerofoil wing in accordance with claim 8, wherein a spring device acts together with the stop lever so as to cushion the respective adjustment mechanism as it attains the maximum extended setting. 13. The aerofoil wing in accordance with claim 9, wherein a spring device acts together with the stop lever so as to cushion the respective adjustment mechanism as it attains the maximum extended setting. 14. The aerofoil wing in accordance with claim 10, wherein a spring device acts together with the stop lever so as to cushion the respective adjustment mechanism as it attains the maximum extended setting.
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이 특허에 인용된 특허 (9)
Perez Sanchez,Juan, Actuation apparatus for a control flap arranged on a trailing edge of an aircraft airfoil.
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