IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0488317
(2002-09-04)
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국제출원번호 |
PCT//US02/28033
(2004-03-01)
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§371/§102 date |
20040301
(20040301)
|
국제공개번호 |
WO03//02058
(2003-03-13)
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발명자
/ 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
43 인용 특허 :
4 |
초록
▼
A tail rotor system for a helicopter includes a gear box housing retainer (66) coupled to the tail boom (16) of the helicopter. The tail rotor system also includes a power-limiting device (50) configured to disconnect the tail rotor from a power plant for driving the tail rotor about a rotor axis of
A tail rotor system for a helicopter includes a gear box housing retainer (66) coupled to the tail boom (16) of the helicopter. The tail rotor system also includes a power-limiting device (50) configured to disconnect the tail rotor from a power plant for driving the tail rotor about a rotor axis of rotation.
대표청구항
▼
1. An aircraft rotor system comprisinga tail boom made of a deformable material and formed to include an interior region containing a rotatable drive shaft, a gear box associated with the tail boom, the gear box including a housing formed to include a tail boom receiver and a retainer aperture openi
1. An aircraft rotor system comprisinga tail boom made of a deformable material and formed to include an interior region containing a rotatable drive shaft, a gear box associated with the tail boom, the gear box including a housing formed to include a tail boom receiver and a retainer aperture opening into the tail boom receiver, a rotatable bevel gear mounted for rotation in an interior region of the housing and in spaced-apart relation to the tail boom and adapted to rotate tail rotor blades associated with the rotatable bevel gear, and a bushing arranged to support the drive shaft for rotation inside the tail boom receiver, a portion of the tail boom being located to lie between the bushing and the tail boom to confront the opening of the retainer aperture, and a housing retainer configured to move in the retainer aperture in a direction toward the bushing located in the tail boom receiver, the housing retainer including a force receiver adapted to mate with a force-producer tool and means for engaging an exterior surface of the tail boom and deforming the tail boom to move a deformed portion of the tail boom toward the bushing into a bushing channel formed in the bushing in response to movement of the housing retainer in the retainer aperture toward the bushing so that the housing is retained in a fixed position on the tail boom without hindering rotation of the drive shaft, and bevel gear within the housing. 2. A rotor system for an aircraft having a fuselage, a rotor for moving air, the rotor system comprisinga housing for supporting the rotor for rotation about a rotor rotation axis and a tail boom for supporting the housing in spaced-apart relation to the body, and retainer means for securing the housing to the tail boom, the retainer means comprising at least one retaining screw engaging a wall of the housing in perpendicular relation to the tail boom and one end of the retaining screw presses against the surface of the tail boom to secure the housing to the tail boom and the retaining screw deforms the surface of the tail boom inward into a bushing channel in an interior portion of the tail boom to produce a retainer indentation in the tail boom. 3. In a rotor system for an aircraft having a body, a rotor for moving air, a housing for supporting the rotor for rotation about a rotor rotation axis, and a tail boom for supporting the housing in spaced-apart relation to the body,a method for fixedly coupling the housing to the tail boom comprising the steps of moving a retaining mechanism to engage a wall of the housing abutting the tail boom, to cause the tail boom to deform the surface of the tail boom into a bushing channel and create a recess in the tail boom receiving the retaining mechanism therein to secure the housing to the tail boom against axial and rotational motion of the housing relative to the tail boom. 4. A rotor system for an aircraft having a rotor for moving air, the rotor system comprisinga rotor hub connected to a rotor shaft and supported for rotation about a rotor axis of rotation, the rotor hub having a first side and a second side located in spaced-apart relation to the rotor axis of rotation and diametrically opposed to each other, a first rotor blade grip extending in perpendicular relation to the rotor axis of rotation and having a finger part abutting a first side of the rotor hub, a root part in proximity to a second side of the rotor hub, and the root part and finger part of the first rotor blade grip each contain a coaxial passage receptive to a pitch axle, a second rotor blade grip extending in perpendicular relation to the rotor axis of rotation and having a finger part abutting the second side of the rotor hub, a root part in proximity to the first side of the rotor hub, and the root part and finger part of the second rotor blade grip each contain a coaxial passage receptive to a pitch axle, a pitch axle extending through the root part of the first rotor blade and the finger part of the second rotor blade and into a side of the rotor hub and the first and second rotor blade grips are rotatable on the pitch axle for rotation about a rotor blade pitch axis, the pitch axle being fixedly coupled to the rotor hub and free of rotation about its longitudinal axis. 5. A rotor system for an aircraft, the rotor system comprisinga rotor for moving air, a power plant for driving the rotor about a rotor axis of rotation, and a power transmission system for transmitting power from the power plant to the rotor, the power transmission system including power-limiting device means for disconnecting the power plant from the rotor in response to application of a force to the rotor above a desired value as by impact of the rotor against an obstacle or the ground to cause the power plant to disconnect from the rotor so that power available from the power plant to the rotor is reduced. 6. The rotor system of claim 5, wherein the power-limiting device means includes a clutch, and application of a torque force to the rotor above a desired value as by impact of the rotor with the ground causes the clutch to slip relative to the power plant thereby limiting the torque available to drive the rotor.7. The rotor system of claim 4, wherein the pitch axle abuts the rotor shaft and fixedly secures the rotor hub to the rotor shaft.8. The rotor system of claim 7, wherein the pitch axle is a setscrew having a threaded exterior and the rotor hub has at least one threaded cross hole in one of the first side and second side and the pitch axle screws into the threaded cross hole and against the rotor shaft.9. The rotor system of claim 5, wherein the power-limiting device means includes a clutch coupled to the rotors and configured to slip relative to the power plant in response to application of a torque force to an affected rotor above a desired value as by impact of the rotor with the ground thereby limiting the torque available to drive the affected rotor without limiting the torque available to drive the remaining rotors.10. A rotor system for an aircraft, the rotor system comprisinga rotor for moving air, a power plant for driving the rotor about a rotor axis of rotation, and the power transmission system including power-limiting device means for disconnecting the power plant from at least one affected rotor in response to application of a force to the affected rotor above a desired value as by impact of the affected rotor against an obstacle or the ground to cause the power plant to disconnect from the affected rotor so that power available from the power plant to the affected rotor is reduced while the power available to the remaining rotors is not substantially reduced. 11. The rotor system of claim 9 wherein the aircraft is a helicopter having a main rotor supported for rotation about a main rotor axis by a main rotor shaft, a tail rotor supported for rotation about a tail rotor axis by a tail rotor shaft, a tail rotor drive shaft operably connecting the main rotor shaft and tail rotor shaft to transmit motive power from the main rotor shaft to the tail rotor shaft, and the power-limiting device means is a slip-clutch located between the main rotor shaft and the tail rotor drive shaft and configured to disconnect the tail rotor drive shaft from the main rotor shaft upon application of a force to the tail rotor above a desired value as by impact of the tail rotor with the ground.12. An aircraft rotor system comprisinga main rotor supported for rotation about a main rotor axis and driven by a power plant to lift the helicopter into the air, a tail rotor supported for rotation about a tail rotor axis substantially perpendicular to and in spaced apart relation to the main rotor axis and driven by a power plant to counter the torque produce by the main rotor, a tail rotor power transmission system for transmitting power from the power plant to the tail rotor, and power-limiting device means for disconnecting the tail rotor from the power plant in response to application of a force to the tail rotor above a desired value as by impact of the tail rotor against an obstacle or the ground to cause the tail rotor to disconnect from the power plant to reduce damage to the tail rotor and tail rotor power transmission system.
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