Stiffening structures, wing structures, and methods for manufacturing stiffening structures

Patent metadata

Field	Value
Publication number	US-9919791-B2
Application number	US-201514687022-A
Country	US
Kind code	B2
Filing date	Apr 15, 2015
Priority date	Apr 15, 2015
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

Abstract

Stiffening structures, wing structures and methods for manufacturing stiffening structures are provided. In accordance with an exemplary embodiment, a stiffening structure includes a first longitudinal member, a second longitudinal member, and a first rib that extends from the first longitudinal member to the second longitudinal member and is integral with the first longitudinal member and the second longitudinal member. The first longitudinal member has a first wall, a second wall and a joining wall that joins the first wall and second wall. The first wall, the second wall and the joining wall form a space having a trapezoidal shape.

First claim

What is claimed is:

1. An aircraft stiffening structure of composite material comprising: a first longitudinal member and a second longitudinal member; a first rib that extends from the first longitudinal member to the second longitudinal member and is directly integral with the first longitudinal member and the second longitudinal member; wherein the first longitudinal member has a first wall, a second wall and a joining wall that joins the first wall and the second wall, and wherein the first wall, the second wall and the joining wall form a space having a trapezoidal shapes wherein the first rib has a first wall, a second wall and a joining wall that joins the first wall and the second wall of the first rib, and wherein the first wall, the second wall and the joining wall of the first rib form a space having a trapezoidal shape; wherein the joining wall of the first rib shares a first plie of the composite material with the joining wall of the first longitudinal member.

2. The aircraft stiffening structure of claim 1 , wherein the second longitudinal member has a first wall, a second wall and a joining wall that joins the first wall and the second wall, and wherein the first wall, the second wall and the joining wall forming a space having a trapezoidal shape.

3. The aircraft stiffening structure of claim 2 , wherein the joining wall of the first rib shares a second plie of the composite material with the joining wall of the second longitudinal member.

4. The aircraft stiffening structure of claim 1 , wherein the stiffening structure comprises carbon fiber reinforced plastic.

5. The aircraft stiffening structure of claim 1 , wherein the first longitudinal member and the second longitudinal member are curvilinear.

6. The aircraft stiffening structure of claim 1 , further comprising a panel attached to the first longitudinal member and the second longitudinal member.

7. An aircraft wing structure comprising: a first wing panel having a first end and a longitudinal axis; and a stiffening structure of composite material fixedly attached to the first wing panel and comprising: a first spar and a second spar that each extends from the first end along the longitudinal axis of the first wing panel, the first spar and the second spar each having a length; a third spar that lies between the first spar and the second spar and that extends along at least a portion of the length of the first spar and/or the second spar; a first rib that extends from the first spar to the third spar and is directly integral with the first spar and the third spar, and a second rib that extends from the third spar to the second spar and is directly integral with the third spar and the second spars wherein the first spar and the first rib each has a first wall, a second wall and a joining wall that joins the first wall and the second wall, and wherein the first wall, the second wall and the joining wall form a space having a trapezoidal shape, and wherein the joining wall of the first spar shares a plie of the composite material with the joining wall of the first rib.

8. The aircraft wing structure of claim 7 , wherein the third spar has a first wall, a second wall and a joining wall that joins the first wall and the second wall, and wherein the first wall, the second wall and the joining wall of the third spar form a space having a trapezoidal shape, and wherein the joining wall of the third spar shares a plie of the composite material with the joining wall of the first rib.

9. The aircraft wing structure of claim 7 , wherein the second spar has a first wall, a second wall and a joining wall that joins the first wall and the second wall, and wherein the first wall, the second wall and the joining wall form a space having a trapezoidal shape; and wherein the joining wall of the second spar shares a plie of the composite material with the joining wall of the second rib.

10. The aircraft wing structure of claim 7 , wherein the joining wall of the third spar shares a plie of the composite material with the joining wall of the second rib.

11. The aircraft wing structure of claim 7 , wherein the stiffening structure comprises carbon fiber reinforced plastic.

12. The aircraft wing structure of claim 7 , wherein the wing structure is a main wing, a winglet, or a horizontal tail.

13. A method for manufacturing an aircraft stiffening structure, the method comprising the steps of. depositing a plurality of plies of a flexible and drapable composite material into a cavity of a mold; inserting the mold into a bag; effecting a vacuum in the bag; curing the flexible and drapable composite material to form the stiffening structure within the mold; and removing the stiffening structure from the mold, the stiffening structure comprising: a first longitudinal member and a second longitudinal member; a first rib that extends from the first longitudinal member to the second longitudinal member and is directly integral with the first longitudinal member and the second longitudinal member; and a second rib that extends from the first longitudinal member to the second longitudinal member and is directly integral with the first longitudinal member and the second longitudinal member, wherein the first longitudinal member and the first rib each has a first wall, a second wall and a joining wall that joins the first wall and second wall, and wherein the first wall, the second wall and the joining wall form a space having a trapezoidal shape, wherein the joining wall of the first rib shares a first plie of the plurality of plies of the flexible and drapable composite material with the first longitudinal member.

14. The method of claim 13 , wherein the second longitudinal member has a first wall, a second wall and a joining wall that joins the first wall and the second wall, wherein the first wall, the second wall and the joining wall form a space having a trapezoidal shape, and wherein the joining wall of the first rib shares a second plie of the plurality of plies of the flexible and drapable composite material with the second longitudinal member.

15. The method of claim 13 , wherein depositing comprises depositing a carbon fiber reinforced plastic (CFRP).

16. The method of claim 15 , wherein depositing comprises depositing a CFRP triaxial braid.

17. The method of claim 13 , further comprising, prior to depositing, fabricating the mold such that the first longitudinal member and the second longitudinal member are formed curvilinear.

18. The method of claim 13 , wherein depositing comprises depositing into the mold fabricated from the flexible and drapable composite material.

19. The method of claim 13 , further comprising attaching the stiffening structure to a skin panel.

20. The aircraft stiffening structure of claim 1 , wherein the first plie and the second plie are the same plie.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Autry Brenden
• Williams Bryan
• Cope Travis
• Daggett Susan
• Mcguire John
• Mckee Michael
• Aitken Charles

Classifications

• B29D99/0014

  provided with ridges or ribs, e.g. joined ribs · CPC title

• Y02T50/433

  Cross-Sectional Technologies · mapped topic

• B29C70/00

  Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts · CPC title

• B32B37/1018

  using only vacuum · CPC title

• B29C70/342 Primary

  using isostatic pressure · CPC title