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Veteran Member - Level 1

Posts: 52
Date: Jul 11, 2010
Boeing
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Structure for cooling helicopter tail rotor gearbox:

A structure is provided for cooling the tail rotor gearbox of a single rotor helicopter having an anti-torque tail rotor mounted to a vertical stabilizer. The gearbox is mounted within the vertical stabilizer inside an air passage passing through the stabilizer. An air inlet is located in the...
Inventor: Robert Wiesner
Assignee: The Boeing Company
Primary Examiner: Galen L. Barefoot
U.S. Classification

244/171.1; 244/57

International Classification
B64D 3310

 

 

What is claimed is:

1. In a helicopter comprising a fuselage, a rotary wing system and a vertical stabilizer comprising a spar, a first skin connected to said spar and forming one side of said stabilizer and a second skin connected to said spar and forming the other side of said stabilizer, the combination of an anti-torque tail rotor and cooling system comprising a tail rotor connected to said vertical stabilizer, a gear box located within said stabilizer and operably connected to said tail rotor, an air passage located within said stabilizer and in communication with said gear box, wherein said air passage is formed by said spar, said first skin and said second skin air inlet means located in the vertical stabilizer and at one end of said passage, air outlet means located in said stabilizer and located at the other end of said passage, whereby cooling air flows into said inlet means through said passage and about said gear box, and out/said outlet means upon rotation of said tail rotor.

2. The helicopter of claim 1 wherein said outlet means is located in said stabilizer at a point within the radius of said tail rotor.

3. The helicopter of claim 2 wherein said point is located substantially at three-fourths of said radius of said tail rotor from the center of rotation.

 

Drawing



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Former Deputy Administrator

Posts: 897
Date: Jul 12, 2010
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This helo looks pretty much like the UTTAS contender, the Model 179 or YUH-61A.

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Stéphane



Veteran Member - Level 1

Posts: 27
Date: Jul 12, 2010
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Low maintenance, advanced technology swashplate

In the control system for a helicopter rotor a rotating diaphragm driveably connects a rotating swashplate ring to the rotor shaft or to the underside of the rotor hub. The diaphragm is flexible with respect to displacement along and rotation about the rotor shaft axis. A centering plate connecte...

Inventor: Hugh A. McCafferty

Assignee: The Boeing Company

Primary Examiner: Hoang Nguyen

U.S. Classification
416/134A; 416/230

International Classification
B64C 2710; B64C 2752

 

 

What is claimed is:

1. A rotor assembly for a helicopter comprising:

 

a rotor;
a rotor shaft for transmitting power to the rotor;
a swashplate including a stationary ring, a rotating ring and a bearing supporting the rotating ring on the stationary ring for rotation relative to the stationary ring; and
a rotating disc-shaped flexible diaphragm located along the rotor shaft between the rotor and the swashplate and extending between the rotor shaft and the swashplate, driveably connecting the rotor shaft and the rotating ring, said diaphragm being flexible in the direction normal to its extent.

2. The assembly of claim 1 wherein the rotating flexible diaphragm is fabricated from composite material having a fiber reinforced polymer resin matrix.

3. The assembly of claim 1 wherein the rotating flexible diaphragm has a central hole through which the rotor shaft passes, and wherein the rotating diaphragm driveably connects the rotor and the rotating ring.

4. The assembly of claim 1 further comprising a stationary disc-shaped diaphragm, encircling the rotor shaft, located between the swashplate and the airframe of the helicopter, connecting the stationary ring and the airframe and providing a torsional load path therebetween.

5. The assembly of claim 1 further comprising a stationary disc-shaped diaphragm, encircling the rotor shaft, located between the swashplate and the transmission cover of the helicopter, connecting the stationary ring and the transmission cover and providing a torsional load path.

6. The assembly of claim 5 wherein the stationary diaphragm is fabricated from composite material having a fiber reinforced polymer resin matrix.

7. The assembly of claim 5 wherein the stationary ring has a central hole through which the rotor shaft passes.

8. A rotor assembly for a helicopter comprising:

 

a rotor;
a rotor shaft for transmitting power to the rotor;
a swashplate including a stationary ring, a rotating ring and a bearing supporting the rotating ring on the stationary ring for rotation relative to the stationary ring;
a rotating disc-shaped flexible diaphragm located between the rotor and the swashplate and extending between the rotor shaft and the swashplate, driveably connecting the rotor shaft and the rotating ring, said diaphragm being flexible in the direction normal to the extent; and
a plate fixed to the swashplate and extending radially inward toward the rotor shaft, encircling the rotor shaft, and providing an adjacent surface for centering the swashplate about the axis of the rotor shaft.

9. The assembly of claim 8 wherein the plate is connected to the stationary ring of the swashplate.

10. The assembly of claim 8 wherein the plate is fabricated from composite material having a fiber reinforced polymer resin matrix.

11. A rotor assembly for a helicopter comprising:

 

a rotor;
a rotor shaft for transmitting power to the rotor;
a swashplate including a stationary ring, a rotating ring and a bearing supporting the rotating ring on the stationary ring for rotation relative to the stationary ring;
a rotating disc-shaped flexible diaphragm located between the rotor and the swashplate and extending between the rotor shaft and the swashplate, driveably connecting the rotor shaft and the rotating ring, said diaphragm being flexible in the direction normal to the extent;
a plate fixed to the swashplate and extending radially inward toward the rotor shaft, encircling the rotor shaft, and providing an adjacent surface for entering the plate about the axis of the rotor shaft; and
a stationary disc-shaped diaphragm, encircling the rotor shaft, located between the swashplate and the airframe of the helicopter, connecting the rotating ring and the airframe and providing a torsional load path therebetween.

12. A rotor assembly for a helicopter comprising:

 

a rotor;
a rotor shaft for transmitting power to the rotor;
a swashplate including a stationary ring, a rotating ring and a bearing supporting the rotating ring on the stationary ring for rotation relative to the stationary ring;
a rotating disc-shaped flexible diaphragm located between the rotor and the swashplate and extending between the rotor shaft and the swashplate, driveably connecting the rotor shaft and the rotating ring, said diaphragm being flexible in the direction normal to the extent; and
pitch links connected to the rotating ring and the rotor and wherein the rotating disc-shaped flexible diaphragm has holes through which the pitch links extend and on the surfaces of which the pitch links are located angularly and radially with respect to the rotor.

13. A rotor assembly for a helicopter comprising:

 

a rotor;
a rotor shaft for transmitting power to the rotor;
a swashplate including a stationary ring, a rotating ring and a bearing supporting the rotating ring on the stationary ring for rotation relative to the stationary ring;
a rotating disc-shaped flexible diaphragm located between the rotor and the swashplate and extending between the rotor shaft and the swashplate, driveably connecting the rotor shaft and the rotating ring, said diaphragm being flexible in the direction normal to the extent;
a stationary disc-shaped flexible, encircling the rotor shaft, located between the swashplate and the transmission cover of the helicopter, connecting the stationary ring and the transmission cover and providing a torsional load path; and
a lateral link and a longitudinal link connected to the rotating ring, and wherein the rotating diaphragm has holes through which a lateral link and a longitudinal link extend.


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Administrator

Posts: 3381
Date: Feb 21, 2012
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Roadable aircraft (US patent #20090081043):



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