Wing structure for aircraft

• US 20080128552A1
• Filed: 10/30/2007
• Published: 06/05/2008
• Est. Priority Date: 11/02/2006
• Status: Active Grant

• Current Assignee: American Honda Motor Co., Inc. (Honda Motor Company)
• Original Assignee: Honda Motor Co., Ltd. (Honda Motor Company)
• Inventors: Hasegawa, Kazuhide, Azuma, Hirohide, Nakazawa, Jun, Namaizawa, Masaki
• Granted Patent: US 7,740,202 B2
• Time in Patent Office: Days
• US Class Current: 244/123.1
• CPC Class Codes: B64C 3/18 Spars; Ribs; Stringers

Abstract

In a wing structure for an aircraft, a rib extends in a chord direction for connecting spars to each other with upper and lower stringer through holes through which stringers of skins pass being formed in upper and lower edges of the rib. A bead is formed on the rib so as to extend between the upper and lower stringer through holes. Upper and lower ends of the bead are formed into arcuate shapes so as to surround the upper and lower stringer through holes, respectively. Thus, it is possible to enhance the buckling strength of the rib against a shear load acting on the wing of the aircraft.

Claims

1. A wing structure for an aircraft, comprising:

a plurality of spars extending in a span direction;

a plurality of stringers arranged between the spars and extending in the span direction;

a rib extending in a chord direction to connect the spars to each other; and

skins for covering upper and lower surfaces of the spars, the stringers and the rib;

wherein upper and lower stringer through holes through which the stringers pass are formed on upper and lower edges of the rib;

wherein a bead is formed on the rib so as to extend between the upper and lower stringer through holes which face each other in a vertical direction; and

wherein upper and lower ends of the bead are formed into arcuate shapes so as to surround the upper and lower stringer through holes, respectively.

2. The wing structure for an aircraft according to claim 1, wherein at least one aperture is formed in said rib for lightening the weight of the rib.

3. The wing structure for an aircraft according to claim 2, wherein an aperture is formed in a portion of said rib adjacent to a front spar and an aperture is formed in a portion of said rib adjacent to a rear spar.

4. The wing structure for an aircraft according to claim 1, wherein said bead is a vertically extending bead that is integrally press-molded between two lightening apertures formed in the rib.

5. The wing structure for an aircraft according to claim 1, wherein the bead includes a vertically-extending substantially straight portion and a pair of arcuate portions formed at opposite ends in the vertical direction of the substantially straight portion.

6. The wing structure for an aircraft according to claim 1, wherein the bead is formed to bulge inwardly in the span direction when the rib is press-molded.

7. The wing structure for an aircraft according to claim 1, and further including a pair of front and rear flanges bent inwardly in the span direction and formed on opposite sides in the front and rear direction of the stringer through holes on a lower edge of the rib for securing the rib to a lower surface of the wing.

8. The wing structure for an aircraft according to claim 7, and further including a mounting portion disposed at a front end of the rib for securing the rib to a portion of a front spar.

9. The wing structure for an aircraft according to claim 7, and further including a pair of front and rear mounting portions provided at an upper edge of the rib for securing the rib to an upper skin of the wing.

10. The wing structure for an aircraft according to claim 7, and further including a mounting portion provided at a rear of the rib for securing the rib to a main spar.

11. A wing structure for an aircraft, comprising:

a plurality of spars extending in a span direction;

a plurality of stringers arranged between the spars and extending in the span direction;

a rib extending in a chord direction to connect the spars to each other;

and

an upper skin for covering an upper surface of the spars, the stringers and the rib;

an lower skin for covering an lower surface of the spars, the stringers and the rib;

an upper stringer through hole for on an upper edge of the rib for enabling a stringer to pass therethrough;

a lower stringer through hole for on a lower edge of the rib for enabling a stringer to pass therethrough;

a bead formed on the rib and extending between the upper and lower stringer through holes which face each other in a vertical direction; and

arcuate shapes being formed in upper and lower ends of the bead for surrounding the upper and lower stringer through holes, respectively.

12. The wing structure for an aircraft according to claim 11, wherein at least one aperture is formed in said rib for lightening the weight of the rib.

13. The wing structure for an aircraft according to claim 12, wherein an aperture is formed in a portion of said rib adjacent to a front spar and an aperture is formed in a portion of said rib adjacent to a rear spar.

14. The wing structure for an aircraft according to claim 11, wherein said bead is a vertically extending bead that is integrally press-molded between two lightening apertures formed in the rib.

15. The wing structure for an aircraft according to claim 11, wherein the bead includes a vertically-extending substantially straight portion and a pair of arcuate portions formed at opposite ends in the vertical direction of the substantially straight portion.

16. The wing structure for an aircraft according to claim 11, wherein the bead is formed to bulge inwardly in the span direction when the rib is press-molded.

17. The wing structure for an aircraft according to claim 11, and further including a pair of front and rear flanges bent inwardly in the span direction and formed on opposite sides in the front and rear direction of the stringer through holes on a lower edge of the rib for securing the rib to a lower surface of the wing.

18. The wing structure for an aircraft according to claim 17, and further including a mounting portion disposed at a front end of the rib for securing the rib to a portion of a front spar.

19. The wing structure for an aircraft according to claim 17, and further including a pair of front and rear mounting portions provided at an upper edge of the rib for securing the rib to an upper skin of the wing.

20. The wing structure for an aircraft according to claim 17, and further including a mounting portion provided at a rear of the rib for securing the rib to a main spar.