Flap drive device and blades of rotary-wing aircraft

Patent metadata

Field	Value
Publication number	US-11667378-B2
Application number	US-202117327348-A
Country	US
Kind code	B2
Filing date	May 21, 2021
Priority date	May 22, 2020
Publication date	Jun 6, 2023
Grant date	Jun 6, 2023

Abstract

Provided are a flap drive device and a rotorcraft blade, and more particularly, a flap drive device using a two-section link mechanism, which may be applied to a rotorcraft blade, and a rotorcraft blade including the same.

First claim

What is claimed is:

1. A flap drive device installed on a blade body of a rotorcraft, the flap drive device comprising:
a drive module;
a flap drive link arm arranged behind the drive module and extending by a length in a front-rear direction; and
a flap module arranged behind the flap drive link arm and capable of performing a pitch movement around a rotation center axis,
wherein the drive module comprises an actuator shaft capable of changing a position thereof in the front-rear direction,
wherein the flap drive link arm comprises a front hinge connection portion provided at a front end of the flap drive link arm and a rear hinge connection portion provided at a rear end of the flap drive link arm,
the front hinge connection portion is pivotably-connected to the actuator shaft to pivot about an axis,
the rear hinge connection portion is pivotably-connected to the flap module;

the flap module comprising:
a flap body;
a rotation center hinge segment at a front end of the flap body; and
a flap pivot hinge segment at the front end of the flap body,
wherein the rotation center hinge segment connects a rotorcraft blade to the flap body,
the flap pivot hinge segment hinge-connects the rear hinge connection portion of the flap drive link arm to the flap body,
the rotation center hinge segment has a first hinge axis on the rotation center axis of the flap module,
the flap pivot hinge segment has a second hinge axis,
the first hinge axis is at a position on a chord line of the flap body, the second hinge axis aligned with the first hinge axis on a line perpendicular to the chord line, and
a center of the first hinge axis and a center of the second hinge axis are apart from each other by a distance,

wherein when a position of the actuator shaft changes in the front-rear direction, the flap module performs the pitch movement around the rotation center axis.

2. A rotorcraft blade comprising:
the flap drive device of claim 1 ; and
a blade body provided with the flap drive device.

3. The flap drive device of claim 1 , wherein
the second hinge axis is at a center of a span of the flap body.

4. A rotorcraft blade comprising:
the flap drive device of claim 3 ; and
a blade body provided with the flap drive device.

Assignees

• Seoul Nat Univ R&Db Foundation

Inventors

• Shin Sang Joon
• Eun Won Jong
• Im Byeong Uk
• Lee Chang Bae
• Shin Jin Wook

Classifications

• B64C2027/7294

  actuated mechanically, e.g. by means of linkages · CPC title

• B64C27/615 Primary

  including flaps mounted on blades · CPC title

• Y02T50/30

  Wing lift efficiency · CPC title

• B64C2027/7266

  actuated by actuators · CPC title

• B64C27/72 Primary

  Means acting on blades · CPC title