IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0726867
(1991-07-08)
|
우선권정보 |
AR-0317354 (1990-07-12) |
발명자
/ 주소 |
- Cicare Augusto U. (Buenos Aires ARX)
|
출원인 / 주소 |
- Industrias Cicare S.r.l. (Buenos Aires ARX 03)
|
인용정보 |
피인용 횟수 :
8 인용 특허 :
0 |
초록
▼
Mechanism for controlling pitch changes in helicopter blades, related to the helicopter mast and connected to a lever assembly mounted into the structure, having a pair of command arms, the assembly comprising first and second bars, related by rocker arms, for selective transmission of cyclic and co
Mechanism for controlling pitch changes in helicopter blades, related to the helicopter mast and connected to a lever assembly mounted into the structure, having a pair of command arms, the assembly comprising first and second bars, related by rocker arms, for selective transmission of cyclic and collective pitches.
대표청구항
▼
Mechanism for controlling pitch changes in helicopter blades, particularly for the manual command of small or large span helicopters, of the type comprising a main rotor having at least a pair of blades mounted at the end of a command mast for rotating around the rotational axis of the latter, rotat
Mechanism for controlling pitch changes in helicopter blades, particularly for the manual command of small or large span helicopters, of the type comprising a main rotor having at least a pair of blades mounted at the end of a command mast for rotating around the rotational axis of the latter, rotatorily supported on the helicopter structure, said blades being engaged by corresponding flapping flexural portions to a hub mounted to said mast, said portions defining an axis for changing the cyclic pitch, perpendicular to the rotational axis of the mast, said blades being connected to pitch rocker arms linked to the ends of corresponding connecting rods transmitting cyclic and collective pitch commanded by a mechanism positioning thereof, related to said mast, and connected to a lever assembly mounted at the interior of the structure, including a pair of command arms for said pitches, cyclic and collective, located into the helicopter cabin, wherein said lever assembly comprises a pair of first and second bars, parallel and spaced apart, the first of which is arranged in articulated form and is a cantilever bar with respect of a fixed support of the helicopter structure, said bars being, adjacent said support, related by a first articulated rocker arm to the cantilever bar and engaged to the cyclic pitch command arm, the cantilever bar being coaxially arranged with respect to a bush linked to a third bar, transversal to said pair of bars, supported on fixed points of the structure and connected to the collective pitch command arm, the free ends of the pair of bars being connected by a second rocker arm, linked to the cantilever bar, the latter having a cross member at an intermediate point, acting as a third rocker arm, at the ends of the latter and at the second rocker arm, there being corresponding connecting rods vertically arranged for selectively transmitting said pitches to said blade positioning mechanism, constituted by a transmission part for both pitches, having articulation points for said connecting rods and a yoke mounted rotatorily on said piece, transmitting the cyclic pitch, capable of being positioned angularly and axially by said part, with respect to the mast rotational axis, the yoke being provided with an articulated part, transversal to said mast rotational axis, comprising means for linking a pair of connecting rods parallel said rotational axis and arranged in the interior of a tube constituting the mast linked through a traverse pin to said yoke, the pair of connecting rods being thus connected to said rocker arms for positioning the rotor blades.
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