High performance tilt rotor aircraft in which nacelle tilt angle and flaperon angle mechanically interwork with each other

• US 8,544,787 B2
• Filed: 05/21/2012
• Issued: 10/01/2013
• Est. Priority Date: 07/29/2011
• Status: Active Grant

• Current Assignee: Korea Aerospace Research Institute
• Original Assignee: Korea Aerospace Research Institute
• Inventors: Choi, Seong Wook, Lee, Myeong Kyu, Chang, Sung Ho, Koo, Sam Ok, Kim, Jai Moo
• Primary Examiner(s): Bonzell, Philip J
• Application Number:
  US13/476,274
• Publication Number:
  US 20130026302A1
• Time in Patent Office: 498 Days
• Field of Search: 244/7.R, 244/7.A, 244/12.4, 244/23.B, 244/56, 244/99.2, 244/99.3, 701 3- 6
• US Class Current: 244/7.R
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 3/385 Variable incidence wings

Abstract

Provided is a high performance tilt rotor aircraft in which a nacelle tilt angle and a flaperon angle mechanically interlock with each other. In the tilt rotor aircraft having nacelles in which rotors are mounted in left and right main wings and configured so that the nacelles rotate according to whether the tilt rotor aircraft conducts forward flight or vertical take-off and landing flight, each of the main wings is provided with a flaperon, and the nacelle and the flaperon are connected to each other by a power transfer unit, such that the flaperon also rotates together with the nacelle at the time of rotation of the nacelle, thereby allowing a change in a nacelle tilt angle to lead to a change in a flaperon angle.

Claims

1. A high performance tilt rotor aircraft in which a nacelle tilt angle and a flaperon angle mechanically interlock with each other, the high performance tilt rotor aircraft having nacelles in which rotors are mounted on an outboard edge of left and right main wings and configured so that the nacelles rotate with respect to the main wings according to whether the tilt rotor aircraft conducts forward flight or vertical take-off and landing flight,

wherein each of the main wings is provided with a flaperon, and the nacelle and the flaperon are connected to each other by a power transfer unit, such that the flaperon also rotates together with the nacelle at the time of rotation of the nacelle, thereby allowing a change in a nacelle tilt angle to lead to a change in a flaperon angle,

wherein the nacelle includes:

an auxiliary wing having a shape in which it is extended in a direction opposite to a body and rotatably installed so that an angle of attack thereof is changed,

wherein the power transfer unit is a link device including a link directly connected to the nacelle, a link directly connected to the flaperon, and a connection link connecting the link directly connected to the nacelle and the link directly connected to the flaperon to each other, and

wherein each of the auxiliary wing positioned at the left nacelle and the auxiliary wing positioned at the right nacelle is separately rotatable.

2. The high performance tilt rotor aircraft of claim 1, wherein when the nacelle rotates from 90 degrees vertical to a flight direction so as to become 0 degree horizontal to the flight direction, the flaperon rotates from a state in which it rotates by 70 to 80 degrees toward a direction vertical to the flight direction to 0 degree horizontal to the flight direction, and when the nacelle rotates from 0 degree horizontal to the flight direction so as to become 90 degrees vertical to the flight direction, the flaperon rotates from 0 degree horizontal to the flight direction by 70 to 80 degrees toward the direction vertical to the flight direction.