[특허]Aircraft with yaw control by differential drag

Airbus Operations S.A.S.

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Aircraft with yaw control by differential drag

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-009/00 B64C-005/08 B64C-023/06
미국특허분류(USC)	244/087; 244/091
출원번호	US-0847108 (2010-07-30)
등록번호	US-8876044 (2014-11-04)
우선권정보	FR-09 55454 (2009-08-03)
발명자 / 주소	Cazals, Olivier Druot, Thierry
출원인 / 주소	Airbus Operations S.A.S.
대리인 / 주소	Lerner, David, Littenberg, Krumholz & Mentlik, LLP
인용정보	피인용 횟수 : 1 인용 특허 : 9

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An aircraft having an elongated fuselage and a lifting surface fastened to the fuselage. The aircraft has a device for controlling the torque around the yaw axis GZ of the aircraft in which aerodynamic forms that have devices to generate aerodynamic drag are fastened to each end of the lifting surface at non-zero distances from each side of a vertical plane of symmetry XZ of the aircraft. The drag-generating devices are commanded to produce a different aerodynamic drag at each of the two ends to generate a yaw torque on the aircraft. The aerodynamic form...

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1. An aircraft comprising: a fuselage;at least a first essentially horizontal lifting surface extending on a first side of a vertical frame of reference of the aircraft, and at least a second essentially horizontal lifting surface extending on a second side of the vertical frame of reference of the aircraft, wherein the vertical axis passes through a center of gravity G of the aircraft to determine a yaw axis GZ, andfirst and second winglets fastened to the first and second lifting surfaces at a non-zero distance from a vertical plane of symmetry XZ of the aircraft, respectively, each of the first and second winglets comprising a first surface extending between the leading edge and the trailing edge and a second surface, opposite to the first surface, extending between the leading edge and the trailing edge, each winglet comprising a through opening delimited between the leading and trailing edges of the winglet and extending between the first and second surfaces of the winglet,the opening substantially occupied by a movable flap having an axis of rotation in a first position thereof, wherein the movable flap extends substantially throughout the through opening in the first position such that a first surface of the movable flap is flush with the first surface of the winglet and a second surface of the movable flap is flush with the second surface of the winglet such that dimensions of the movable flap substantially correspond to dimensions of the through-opening, the movable flap rotatable to extend from a first side of the winglet and a second side of the winglet;wherein each movable flap is operable to generate controlled drag to produce a different aerodynamic drag on each side of the vertical plane of symmetry XZ of the aircraft, so as to generate a yaw torque on the aircraft around the yaw axis GZ. 2. The aircraft according to claim 1, wherein the movable flap has a leading edge axis of rotation. 3. The aircraft according to claim 1, wherein the movable flap has a central axis of rotation. 4. The aircraft according to claim 1, wherein the movable flap has a trailing edge axis of rotation. 5. The aircraft of claim 1, wherein the axis of rotation of the movable flap extends along a longitudinal direction of the corresponding winglet. 6. A winglet configured to be fastened to the end of an aerodynamic lifting surface of an aircraft comprising: a through opening delimited between a leading and trailing edge of the winglet, the opening occupied by a movable flap having an axis of rotation and first and second edges, the movable flap rotatable to extend from a first side of the winglet and a second side of the winglet such that the first edge of the flap extends from the first side of the winglet and the second edge of the flap extends from the second side of the winglet. 7. A winglet configured to be fastened to the end of an aerodynamic lifting surface of an aircraft, the winglet comprising: a through opening delimited between a root rib proximal to the end of the aerodynamic lifting surface and an end rib distal to the end of the aerodynamic lifting surface, the root rib and the end rib extending between a leading edge of the winglet and a trailing edge of the winglet;wherein the opening is occupied by a first movable flap having an axis of rotation and a first edge, the first movable flap rotatable about the axis of rotation, and configured to assume at least first and second positions;wherein in the first position, the first movable flap is flush with the root rib and the end rib and the first edge of the first movable flap is flush with the trailing edge of the winglet;wherein in the second position, the first movable flap is positioned at a predetermined angle relative to the winglet;wherein the first movable flap comprises a second edge;wherein the axis of rotation of the first movable flap is defined intermediate of the first and second edges of the first movable flap; andwherein in the second position, the first movable flap is configured to rotate about the axis of rotation thereof such that the first edge of the first movable flap extends from a first side of the winglet and the second edge of the first movable flap extends from a second side of the winglet. 8. The winglet of claim 7, further comprising a second movable flap having an axis of rotation and a first edge, the second movable flap rotatable about the axis of rotation thereof and configured to assume at least first and second positions; wherein in the first position, the second movable flap is flush with the root rib and the end rib and the first edge is flush with the trailing edge of the winglet; andwherein in the second position, the first movable flap is positioned at a first predetermined angle relative to a first surface of the winglet and the second movable flap is positioned at a second predetermined angle relative to a second surface of the winglet. 9. The winglet of claim 7, further comprising a second movable flap having an axis of rotation; wherein the axes of rotation of the first and second movable flaps are generally parallel to one another in a plane of the winglet.

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이 특허를 인용한 특허 피인용횟수: 1

Lam, Lawrence. Mechanical control mixer and method therefor. USP2015049004411.

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Aircraft with yaw control by differential drag

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Aircraft with yaw control by differential drag

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이 특허에 인용된 특허 (9)

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