Flap deploying device and aircraft

Patent metadata

Field	Value
Publication number	US-9963220-B2
Application number	US-201314105814-A
Country	US
Kind code	B2
Filing date	Dec 13, 2013
Priority date	Dec 26, 2012
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

The flap deploying device for a flap disposed at a leading edge or a trailing edge of a main wing of the aircraft, the deploying device including: a drive source; a moving mechanism with a moving body advancing and retracting by power of the drive source; a carriage mechanism that carries advancing and retracting motion of the moving body to the flap so as to deploy the flap between a retracted position and a deployed position; and a rail that guides the carriage mechanism. Since the moving mechanism is arranged lateral to the rail in the wingspan direction of the main wing, the dimension of the wing in a thickness direction can be reduced at least by a dimension corresponding to the moving mechanism. Therefore, the wing can be made thinner, or the projecting height of a flap track fairing can be reduced.

First claim

What is claimed is:

1. A flap deploying device which deploys a flap provided at a leading edge or a trailing edge of a main wing of an aircraft, the deploying device comprising:
a drive source;
a moving mechanism including a screw jack, the screw jack comprises a moving body advancing and retracting by power of the drive source;
a carriage mechanism that carries advancing and retracting motion of the moving body to the flap so as to deploy the flap between a retracted position and a deployed position; and
a rail that guides the carriage mechanism,
wherein the drive source is an electric motor,
the rail is a track rail,
the screw jack including a screw that is rotationally driven by the drive source, the moving body meshing with the screw so as to be relatively rotatable, and
the moving body and a gimbal are elements of a gimbal mechanism arranged lateral to the track rail in a wingspan direction of the main wing, the gimbal mechanism including at least two axes of rotation and being configured to smoothly maintain a meshing between the screw and the moving body.

2. The flap deploying device according to claim 1 ,
wherein the flap is connected only to the carriage mechanism.

3. The flap deploying device according to claim 1 ,
wherein the carriage mechanism includes a first carriage section and a second carriage section that are rotatably coupled to each other,
the first carriage section and the second carriage section integrally moving along the rail.

4. The flap deploying device according to claim 1 ,
wherein at least a portion of the flap deploying device is covered with a flap track fairing.

5. The flap deploying device according to claim 1 ,
wherein the rail is provided substantially along a wing chord direction.

6. The flap deploying device according to claim 1 ,
wherein the rail is supported on an upper surface of a support body with rigidity, and the support body is fixed to a lower surface of a main wing body of the main wing at least at two positions.

7. The flap deploying device according to claim 6 ,
wherein the carriage mechanism is configured to move along the rail while supporting the flap on a lower surface of the flap, and thereby move the flap between the retracted position and the deployed position.

8. The flap deploying device according to claim 1 ,
wherein the carriage mechanism is configured to move along the rail while supporting the flap on a lower surface of the flap, and thereby move the flap between the retracted position and the deployed position.

9. An aircraft comprising a flap at a leading edge or a trailing edge of a main wing,
wherein the flap is driven by a deploying device, the deploying device comprising:
a drive source;
a moving mechanism including a screw jack, the screw jack comprises a moving body advancing and retracting by power of the drive source;
a carriage mechanism that carries advancing and retracting motion of the moving body to the flap so as to deploy the flap between a retracted position and a deployed position; and
a rail that guides the carriage mechanism,
wherein the drive source is an electric motor,

the rail is a track rail,
the screw jack including a screw that is rotationally driven by the drive source, the moving body meshing with the screw so as to be relatively rotatable, and
the moving body and a gimbal device are elements of a gimbal mechanism arranged lateral to the track rail in a wingspan direction of the main wing, the gimbal mechanism including at least two axes of rotation and being configured to smoothly maintain a meshing between the screw and the moving body.

Assignees

• Mitsubishi Aircraft Corp

Inventors

• Ishihara Kenya
• Sugawara Zenta

Classifications

• B64C9/16 Primary

  at the rear of the wing · CPC title

• B64C13/30

  using cable, chain, or rod mechanisms · CPC title

• B64C9/22

  at the front of the wing · CPC title

• B64C13/28

  mechanical · CPC title