IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0206313
(2005-08-17)
|
등록번호 |
US-8579237
(2013-11-12)
|
우선권정보 |
DE-10 2004 040 313 (2004-08-19) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Lerner, David, Littenberg, Krumholz & Mentlik, LLP
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
9 |
초록
▼
A system for setting a span load distribution of a wing of an aircraft with a base flap system comprises at least one inboard flap element and one outboard flap element, which elements in the direction of the span are arranged on the trailing edge of the wing, and can be positioned relative to the s
A system for setting a span load distribution of a wing of an aircraft with a base flap system comprises at least one inboard flap element and one outboard flap element, which elements in the direction of the span are arranged on the trailing edge of the wing, and can be positioned relative to the span direction of the wing. The flap elements are not mechanically coupled with each other and are controlled independently of each other for the purpose of setting the span load distribution.
대표청구항
▼
1. A system for setting a wing span load distribution of an aircraft wing, comprising: a base flap system with an inner flap element and an outer flap element;an aileron, the aileron positioned adjacent to the outer wing flap;wherein the inner flap element and the outer flap element are arranged in
1. A system for setting a wing span load distribution of an aircraft wing, comprising: a base flap system with an inner flap element and an outer flap element;an aileron, the aileron positioned adjacent to the outer wing flap;wherein the inner flap element and the outer flap element are arranged in a direction of the wing span at a trailing edge of the wing;wherein the inner flap element and the outer flap element are displaceable relative to the wing span direction of the wing;wherein the inner flap element and the outer flap element are not mechanically coupled with each other; andwherein the outer flap element is arranged via a control system at a larger downward angle, the angle being downward with respect to the wing, than the inner flap element, which is also at a downward angle with respect to the wing, for optimising a takeoff or landing lift/drag ratio. 2. The system of claim 1, wherein, for optimising a maximum lift, an excursion of the inner and outer flap elements is reduced in a region in which airflow separation over the wing starts. 3. The system of claim 1, wherein, for reducing downwash in an inboard region of the wing, the excursion of the inner flap element is reduced. 4. An aircraft high lift system employed during takeoff or landing operations, said system comprising: an inner flap associated with a wing of an aircraft, the wing having a tip;an outer flap associated with the wing of the aircraft, the outer flap positioned nearer the tip of the wing than the inner flap;an aileron associated with the wing and positioned between the outer flap and the tip of the wing; anda control system;wherein, during takeoff or landing operations, the control system arranges the outer flap at a downward angle with respect to the wing at an angle greater than that of the inner flap, which is also arranged at a downward angle with respect to the wing. 5. The aircraft high lift system of claim 4, wherein the inner flap and the outer flap are not mechanically coupled. 6. A high lift system employed during takeoff or landing operations for an aircraft having a right wing and a left wing, each wing having a tip, said system comprising: a right inner flap associated with the right wing of the aircraft;a right outer flap associated with the right wing of the aircraft, the right outer flap positioned nearer the tip of the right wing than the right inner flap;a left inner flap associated with the left wing of the aircraft;a left outer flap associated with the left wing of the aircraft, the left outer flap positioned nearer the tip of the left wing than the left inner flap; anda control system;wherein, during takeoff or landing operations, the control system angles the right outer flap downward with respect to the right wing at an angle greater than that of the right inner flap, which is angled downward with respect to the right wing, and the control system angles the left outer flap downward with respect to the left wing at an angle greater than that of the left inner flap, which is angled downward with respect to the left wing. 7. The high lift system of claim 6, wherein the right inner flap is coupled with the left inner flap. 8. The high lift system of claim 6, wherein the right outer flap is coupled with the left outer flap. 9. The high lift system of claim 6, wherein the right inner flap is coupled with the left inner flap and the right outer flap is coupled with the left outer flap. 10. The high lift system of claim 6, wherein, during takeoff or landing operations, the right outer flap is angled downward with respect to the right wing at the same angle as the left outer flap is angled with respect to the left wing.
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