Aircraft skin lap splice

• US 5,297,760 A
• Filed: 08/21/1992
• Issued: 03/29/1994
• Est. Priority Date: 08/21/1992
• Status: Expired due to Fees

• Current Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Original Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Inventors: Hart-Smith, Leonard J.
• Primary Examiner(s): Huppert, Michael S.
• Assistant Examiner(s): BIDWELL, ANNE
• Application Number:
  US07/933,255
• Time in Patent Office: 585 Days
• Field of Search: 244/131, 244/132, 244/117 R, 244/119, 403/41, 52/462, 52/582
• US Class Current: 244/132
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: B64C 2001/0072 from composite materials
• CPC Class Codes: B64C 2001/0081 from metallic materials
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

Fuselage skin lap splice for aircraft formed of metal or composite skin panels. The adjacent skin panels comprise an outer skin and an inner skin, having contacting overlapping longitudinal edge portions, and a plurality of fasteners connecting such overlapping edge portions. A plurality of outwardly extending fingers are integrally connected along the edge portion of the inner skin and at least one longitudinal row of fasteners passes through the fingers and connects the outer skin and the fingers. Preferably the fingers are lollipopped, that is, have one or more protrusions thereon. The fingers at the end of the inner skin are flexible and soften and the load transfer through the fasteners, reducing the peak bearing stress and increasing the fatigue life of the splice. Alternatively, the desired flexibility at the end of the inner skin can be achieved by providing a plurality of large holes near the edge of the inner skin rather than by the provision of the fingers having apertures therebetween.

Claims

1. In a skin lap splice between adjacent skin panels of aircraft which comprises an outer skin having a longitudinal edge portion and an inner skin having a longitudinal edge portion, said edge portions being in contact and overlapping, and a plurality of first longitudinal rows of fasteners connecting said edge portions;

the improvement which comprises means on said inner skin adjacent the longitudinal edge portion thereof and forming a part of said inner skin to provide flexibility at said longitudinal edge portion of said inner skin, and at least one second longitudinal row of fasteners passing through said flexibilizing means and connecting the longitudinal edge portion of said outer skin and the longitudinal edge portion of said inner skin.

2. The ski lap splice of claim 1, wherein said inner and outer skins are metal.

3. The skin lap splice of claim 1, wherein said inner and outer skins are composite.

4. A skin lap splice between adjacent skin panels of aircraft which coprises an outer skin having a longitudinal edge portion and an inner skin having a longitudinal edge portion, said edge portions being in contact and overlapping, a plurality of first longitudinal rows of fasteners connecting said edge portions, a plurality of fingers on said inner skin along said edge portion of said inner skin, forming a part thereof and extending outwardly therefrom, and at least one second longitudinal row of fasteners passing through said fingers and connecting said outer skin and said fingers.

5. The skin lap splice of claim 4, wherein said fingers are lollipopped and wherein the spacing of fasteners in said at least one second longitudinal row of fasteners passing through said lollipopped fingers is greater than between the fasteners in each of said first longitudinal rows of fasteners connecting said edge portions.

6. The skin lap splice of claim 4, wherein the thickness of said outer and inner skins is approximately equal.

7. A skin lap splice between adjacent skin panels of aircraft which comprises an outer skin having a longitudinal edge portion and an inner skin having a longitudinal edge portion, said edge portions being in contact and overlapping, a plurality of first longitudinal rows of fasteners connecting said edge portions, a plurality of holes along the outer edge of the longitudinal edge portion of said inner skin, and at least one second longitudinal row of fasteners passing through said inner skin between said holes and connected to said outer skin.

8. The skin lap splice of claim 7, wherein there are three said first longitudinal rows of fasteners connecting said edge portions, said holes being spaced apart a distance such that the number of fasteners in said at least one second longitudinal row of fasteners is approximately half the number of fasteners in each row of said three first longitudinal rows.

9. The skin lap splice of claim 8, wherein there are two said second longitudinal rows of fasteners passing through said inner skin between said holes.

10. The skin lap splice of claim 9, wherein the adjacent fasteners in all of said longitudinal rows of fasteners are substantially in transverse alignment.

11. The skin lap splice of claim 7, wherein said holes are of substantially the same diameter.

12. The skin lap splice of claim 7, wherein the thickness of said outer and inner skins is approximately equal.

13. A skin lap splice between adjacent skin panels of aircraft and particularly adapted as an aircraft fuselage skin lap splice, which comprises an outer skin having a longitudinal edge portion and an inner skin having a longitudinal edge portion, said edge portions being in contact and overlapping, a plurality of first longitudinal rows of fasteners connecting said edge portions, a plurality of lollipopped fingers integrally connected along said edge portion of said inner skin and extending outwardly therefrom, and at least one second longitudinal row of fasteners passing through said fingers and connecting said outer skin and said fingers, and wherein there are three said first longitudinal rows of fasteners connecting said edge portions, said lollipopped fingers being spaced apart from each other a distance such that the number of fasteners in said at least one longitudinal row of fasteners passing through said lollipopped fingers is approximately half the number of fasteners in row of said three longitudinal rows of fasteners connecting said edge portions.

14. The skin lap splice of claim 13, wherein there are two said longitudinal rows of fasteners passing through said lollipopped fingers.

15. The skin lap splice of claim 14, wherein the fasteners in each of said three first longitudinal rows of fasteners are substantially equally spaced, and the fasteners in each of the two longitudinal rows of fasteners passing through said lollipopped fingers are substantially equally spaced a distance approximately twice the distance between the fasteners in said three first longitudinal rows of fasteners connecting said edge portions, and the adjacent fasteners in all of said longitudinal rows of fasteners are substantially in transverse alignment.

16. The skin lap splice of claim 15, wherein the thickness of said outer and inner skins is unequal, and including a lollipopped finger doubler disposed in contact with and adjacent to the thinner of said skins, said doubler being fastened to each of said skins.

17. The skin lap splice of claim 14, wherein the fasteners in each of said three first longitudinal rows of fasteners are substantially equally spaced, and the fasteners in each of the two longitudinal rows of fasteners passing through said lollipopped fingers are substantially equally spaced a distance approximately twice the distance between the fasteners in said three first longitudinal rows of fasteners connecting said edge portions, and the adjacent fasteners in each of the two longitudinal rows of fasteners passing through said lollipopped fingers is displaced laterally by about half a fastener pitch between the fasteners in each of said three first longitudinal rows of fasteners.

18. The skin lap splice of claim 13, wherein the fasteners in each of said three first longitudinal rows of fasteners are substantially equally spaced and the adjacent fasteners in each of said rows of fasteners are substantially in transverse alignment.

19. The skin lap splice of claim 13, wherein the fasteners in the middle row of said three first longitudinal rows of fasteners are displaced longitudinally about half the fastener pitch between the fasteners in each of the other said first longitudinal rows.

20. A skin lap splice between adjacent skin panels of aircraft which comprises an outer skin having a longitudinal edge portion and an inner skin having a longitudinal edge portion, said edge portions being in contact and overlapping, a plurality of first longitudinal rows of fasteners connecting said edge portions, a plurality of lollipopped fingers integrally connected along said edge portion of said inner skin and extending outwardly therefrom, and at least one second longitudinal row of fasteners passing through said fingers and connecting said outer skin and said fingers, and wherein the spacing of fasteners in said at least one second longitudinal row of fasteners passing through said lollipopped fingers is greater than between the fasteners in each of said first longitudinal rows of fasteners connecting said edge portions, and wherein the thickness of said outer and inner skins is unequal, and including an additional lollipopped finger doubler disposed in contact with said adjacent to the thinner of said skins, said doubler being fastened to each of said skins.