Shell structural component made of fiber composite material

• US 5,452,867 A
• Filed: 10/08/1993
• Issued: 09/26/1995
• Est. Priority Date: 10/09/1992
• Status: Expired due to Term

• Current Assignee: Daimlerchrysler North America Corporation (Mercedes-Benz Group AG)
• Original Assignee: Deutsche Aerospace Airbus GmbH
• Inventors: Grunwald, Gero, Hauschildt, Michael
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US08/134,533
• Time in Patent Office: 718 Days
• Field of Search: 244/117 R, 244/119, 244/123, 244/131, 244/132, 244/133, 244/129.4, 428/133, 428/65, 428/105-109, 156/293, 156/253, 156/173, 220/588-590
• US Class Current: 244/117.00R
• CPC Class Codes: B64C 3/24 Moulded or cast structures
• CPC Class Codes: Y10T 156/1057 Subsequent to assembly of laminae
• CPC Class Codes: Y10T 428/24058 including grain, strips, or filamentary elements in respective layers or components in angular relation
• CPC Class Codes: Y10T 428/24322 Composite web or sheet

Abstract

An aircraft structure, such as a wing, is made of fiber composite material and includes a shell structural component also made of fiber composite material. The structural component has at least one access opening closeable by a cover. The shell structural component has a first area containing the access opening closeable by the cover. In the longitudinal direction of the wing the first area is predominantly flexible while a second area surrounding the first area is predominantly stiff, whereby these areas take up different longitudinally effective forces, relative to the length of the wing. Both areas are capable of transferring shear forces in the same manner.

Claims

1. An aircraft construction comprising a shell structure made of fiber composite material, said shell structure including reinforcing members and a skin supported by said reinforcing members, said skin including at least one access opening and a cover for said access opening, said skin of said shell structure comprising a first area wherein said access opening and said cover are located, said first area having a first construction of a fiber reinforced lamination having a first modulus of elasticity that permits yielding in a longitudinal direction of said aircraft structure, said skin of said shell structure further comprising a second area surrounding said first area, said second area including a second construction of a further fiber reinforced lamination having a second modulus of elasticity which is higher than said first modulus of elasticity of said first area, so that said second area is stiff in said longitudinal direction relative to a longitudinally effective force, so that said first area and said cover take up only a small proportion of a total longitudinally effective force applied to said fiber composite aircraft construction, and so that said second area takes up a larger proportion of said applied, longitudinally effective force, thereby substantially relieving said cover of said longitudinally effective force.

2. The aircraft construction of claim 1, wherein said cover is a separable cover panel, said aircraft construction comprising screw connections for securing said separable cover panel to said aircraft construction.

3. The aircraft construction of claim 1, wherein said shell structure of fiber composite material is mounted by rivets to said aircraft structure.

4. The aircraft construction of claim 1, wherein said shell structure of fiber composite material forms a panel which is a monolithic, integral part of said aircraft construction.

5. The aircraft construction of claim 2, wherein said separable cover panel comprises said at least one access opening closeable by said cover.

6. The aircraft construction of claim 1, wherein said fiber composite material of said shell structure comprises reinforcing fibers having a substantially 0°

-fiber orientation.

7. The aircraft construction of claim 1, wherein said cover is made of fiber composite material including reinforcing fibers with a ±

45°

fiber orientation.

8. The aircraft construction of claim 4, wherein said monolithic panel forming said integral part of said aircraft construction comprises said at least one access opening closeable by said cover.

9. The aircraft construction of claim 1, wherein said shell structure is part of an aircraft wing.

10. The aircraft construction of claim 1, wherein said cover is constructed for transferring shear forces.

11. The aircraft construction of claim 1, wherein said first and second areas have approximately equal shear moduli.