Mechanism for at least regionally adjusting the curvature of airfoil wings
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-003/48
출원번호
US-0008779
(2001-11-13)
우선권정보
DE-0055961 (2000-11-11)
발명자
/ 주소
Perez, Juan
출원인 / 주소
EADS Deutschland GmbH
대리인 / 주소
Kenyon & Kenyon
인용정보
피인용 횟수 :
54인용 특허 :
9
초록▼
A variable wing section having an adjustable profile shape extending in the wing-span direction, includes a plurality of torsion boxes, which are positioned in the longitudinal direction, are torsionally stiff about the wing-span direction, and are each constituted of a first wing skin, a second win
A variable wing section having an adjustable profile shape extending in the wing-span direction, includes a plurality of torsion boxes, which are positioned in the longitudinal direction, are torsionally stiff about the wing-span direction, and are each constituted of a first wing skin, a second wing skin opposite to it, and at least one spar. The variable wing section includes at least one vertebra, which has a transmission element that is connected to the first wing skin by a pendulum joint in order to compensate for a relative movement between the first wing skin and the at least one vertebra, and which has a vertically spaced-apart point of connection to a drive chord, the length of which may be changed, using a control command. The length of the drive chord is changed as a function of a control signal, and the at least one vertebra is rotated about the wing-span direction, so that the shape of the torsion boxes, and thus the profile shape, are changed in a predetermined manner.
대표청구항▼
1. A variable wing section having an adjustable profile shape extending in a wing-span direction, comprising: a plurality of torsion boxes arranged in a longitudinal direction of the wing section and torsionally stiff about the wing-span direction, each torsion box including a first wing skin, a
1. A variable wing section having an adjustable profile shape extending in a wing-span direction, comprising: a plurality of torsion boxes arranged in a longitudinal direction of the wing section and torsionally stiff about the wing-span direction, each torsion box including a first wing skin, a second wing skin opposite the first wing skin and at least one spar; and at least one vertebra including a transmission element connected to the first wing skin by a pendulum joint configured to compensate for a relative movement between the first wing skin and the at least one vertebra, the at least one vertebra including a vertically spaced-apart point of connection to at least one drive chord having a length changeable in accordance with a control command; wherein the length of the drive chord is configured to change as a function of a control signal; and wherein the at least one vertebra is configured to rotate about the wing-span direction so that a shape of the torsion boxes and the profile shape are changed in a predetermined manner. 2. The variable wing section according to claim 1, wherein the at least one vertebra includes a plurality of vertebrae positioned one behind another in the longitudinal direction, each of the plurality of vertebrae connected to the drive chord. 3. The variable wing section according to claim 1, wherein the at least one vertebra and the at least one drive chord are arranged inside the torsion boxes. 4. The variable wing section according to claim 1, wherein the at least one vertebra and the at least one drive chord are arranged outside the torsion boxes. 5. The variable wing section according to claim 1, wherein the pendulum joint includes an elastic joint and wherein each transmission element is connected on one side via elastic connections to an upper wing skin and to a spar. 6. The variable wing section according to claim 1, wherein the pendulum joint includes an eccentric joint, each vertebra being eccentrically supported in an eccentric bushing. 7. The variable wing section according to claim 1, wherein the pendulum joint includes a pendulum connecting each vertebra to one of a spar and the first wing skin. 8. The variable wing section according to claim 1, wherein the variable wing section includes a trailing-edge flap of an airfoil wing. 9. The variable wing section according to claim 1, wherein the variable wing section includes a leading-edge flap of an airfoil wing.
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