Rotor blade with integrated passive surface flap
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/72
B64C-023/00
출원번호
US-0237075
(2011-09-20)
등록번호
US-9193456
(2015-11-24)
우선권정보
DE-10 2010 041 111 (2010-09-21)
발명자
/ 주소
Höfinger, Marc
출원인 / 주소
Deutsches Zentrum fuer Luft-und Raumfahrt e.V.
대리인 / 주소
Thomas | Horstemeyer, LLP
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A rotor blade for a driven horizontal rotor of a rotary-wing aircraft comprises an elongated main body which includes a leading edge, a trailing edge, and an upper surface extending between the leading edge and the trailing edge. The rotor blade further comprises at least one flap having a front end
A rotor blade for a driven horizontal rotor of a rotary-wing aircraft comprises an elongated main body which includes a leading edge, a trailing edge, and an upper surface extending between the leading edge and the trailing edge. The rotor blade further comprises at least one flap having a front end and a rear end and mounted to the main body at its front end swiveling about a swiveling axis running in parallel to the radial or spanwise axis of the rotor blade. The flap has a basic position in which it lies flat against the upper surface of the main body. Further, the flap is passively swiveled by aerodynamic forces and inertial forces about its swivel axis to raise above the upper surface of the main body, and a reset force acts upon the flap to reset it into its basic position on the surface of the main body.
대표청구항▼
1. A driven horizontal rotor of a rotary-wing airplane comprising a rotor axis and a plurality of rotor blades rotating about the rotor axis, the incidence angle of each of the rotor blades increasing and decreasing over each rotation of the respective rotor blade about the rotor axis, each of the r
1. A driven horizontal rotor of a rotary-wing airplane comprising a rotor axis and a plurality of rotor blades rotating about the rotor axis, the incidence angle of each of the rotor blades increasing and decreasing over each rotation of the respective rotor blade about the rotor axis, each of the rotor blades comprising: an elongated main body, the main body including: a leading edge,a trailing edge, andan upper surface extending between the leading edge and the trailing edge, and having a profile comprising a curvature,at least one flap, having a front end and a rear end, andmounted to the main body at its front end swiveling about a swiveling axis running in parallel to the radial axis of the rotor blade,wherein the flap has a basic position in which it lies flat against the upper surface of the main body such that the flap follows the curvature of the profile of the upper surface, wherein the flap is swivel mounted to the main body in such a way that a reset force acts upon the flap, wherein the flap is designed to be passively swiveled by aerodynamic forces and inertial forces acting against the reset force about its swivel axis to raise the upper surface of the main body with increasing incidence angle of the rotor blade, and wherein the reset force acts upon the flap to reset it into its basic position. 2. The rotor blade of claim 1, wherein the flap is made of an elastic material. 3. The rotor blade of any of claim 1, wherein the flap is mounted to the main body via a pivot joint. 4. The rotor blade of claim 3, wherein the joint is a solid body joint. 5. The rotor blade of claim 1, wherein the flap, in a direction of a profile chord of the rotor blade, has a length of 10 to 30% of the profile chord of the rotor blade. 6. The rotor blade of claim 5, wherein several flaps are provided one behind the other in the direction of a profile chord of the rotor blade at the upper surface of the main body. 7. The rotor blade of claim 1, wherein the flap, in a direction of a longitudinal axis of the rotor blade, has a width of 5 to 30% of the length of the rotor blade. 8. The rotor blade of claim 7, wherein the flap is arranged adjacent to the rotor axis of the horizontal rotor. 9. The rotor blade of claim 7, wherein the flap is arranged adjacent to a blade tip of the rotor blade. 10. The rotor blade of claim 7, wherein several flaps are provided at the upper surface of the main body, the flaps being distributed in the radial direction of the rotor blade. 11. The rotor blade of claim 1, wherein several flaps are provided at the upper surface of the main body in a two-dimensional array both extending in a direction of a profile chord of the rotor blade and in a direction of a longitudinal axis of the rotor blade.
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이 특허에 인용된 특허 (4)
Campbell Thomas G. (Cheshire CT), Aircraft rotor blade with passive tuned tab.
McVeigh, Michael A.; Maciolek, Robert F., Vortex generators on rotor blades to delay an onset of large oscillatory pitching moments and increase maximum lift.
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