High-lift device of flight vehicle

Patent metadata

Field	Value
Publication number	US-9623956-B2
Application number	US-201615052472-A
Country	US
Kind code	B2
Filing date	Feb 24, 2016
Priority date	Mar 30, 2011
Publication date	Apr 18, 2017
Grant date	Apr 18, 2017

Abstract

A high-lift device of a flight vehicle includes: a flap main body provided at a trailing edge portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in a wing span direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of a tip end portion of the flap main body to an upper surface of the tip end portion.

First claim

The invention claimed is:

1. A high-lift device of a flight vehicle,
the high-lift device comprising:
a flap main body provided at a trailing portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing portion and extending in a wing span direction of the main wing; and
a vortex suppressing portion provided at a tip end portion of the flap main body in an extending direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of the tip end portion of the flap main body to an upper surface of the tip end portion of the flap main body, wherein:
the vortex suppressing portion includes
a side surface ventilation structure provided at a side end surface of the tip end portion of the flap main body and
a cavity provided in the tip end portion of the flap main body; and

the side surface ventilation structure is provided so as to cover the entire side end surface of the tip end portion of the flap main body and constitutes a side wall defining cavity.

2. The high-lift device according to claim 1 , wherein a porous material is provided in the cavity.

3. The high-lift device according to claim 1 , wherein:
the vortex suppressing portion includes an upper surface ventilation structure provided so as to cover an upper end surface of the tip end portion of the flap main body and constituting an upper wall defining the cavity.

4. The high-lift device according to claim 1 , wherein the side surface ventilation structure is continuous with the upper surface of the flap main body to form a corner together with the upper surface.

5. The high-lift device according to claim 3 , wherein the lower surface of the flap main body does not include holes.

6. The high-lift device according to claim 3 , wherein the upper surface ventilation structure is formed such that a size of the upper surface ventilation structure in the wing span direction increases toward a trailing edge of the upper surface ventilation structure.

7. A high-lift device of a flight vehicle,
the high-lift device comprising:
a flap main body provided at a trailing portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing portion and extending in a wing span direction of the main wing; and
a vortex suppressing portion provided at a tip end portion of the flap main body in an extending direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of the tip end portion of the flap main body to an upper surface of the tip end portion of the flap main body, wherein:
the vortex suppressing portion includes
a side surface ventilation structure provided at a side end surface of the tip end portion of the flap main body and
a cavity provided in the tip end portion of the flap main body; and

the side surface ventilation structure is continuous with the upper surface of the flap main body to form a corner together with the upper surface and constitutes a side wall defining the cavity.

8. A high-lift device of a flight vehicle,
the high-lift device comprising:
a flap main body provided at a trailing portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing portion and extending in a wing span direction of the main wing; and
a vortex suppressing portion provided at a tip end portion of the flap main body in an extending direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of the tip end portion of the flap main body to an upper surface of the tip end portion of the flap main body, wherein:
the vortex suppressing portion includes
an upper surface ventilation structure provided at an upper end surface of the tip end portion of the flap main body and
a cavity provided in the tip end portion of the flap main body; and

the upper surface ventilation structure is formed such that a size of the upper surface ventilation structure in the wing span direction increases toward a trailing edge of the upper surface ventilation structure, and the upper surface ventilation structure constitutes an upper wall defining the cavity.

Assignees

• The Soc Of Japanese Aerospace Companies
• Kawasaki Heavy Ind Ltd

Inventors

• Isotani Kazuhide
• Hayama Kenji

Classifications

• B64C21/02

  by use of slot, ducts, porous areas or the like · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• B64C2230/22

  by using a surface having multiple apertures of relatively small openings other than slots · CPC title

• B64C9/18 Primary

  by single flaps · CPC title

• B64C3/58

  provided with fences or spoilers (adjustable for control purposes B64C9/00) · CPC title