Optimum aircraft body frame to body skin shear tie installation pattern for body skin/stringer circumferential splices

• US 5,518,208 A
• Filed: 12/28/1993
• Issued: 05/21/1996
• Est. Priority Date: 12/28/1993
• Status: Expired due to Term

• Current Assignee: Pemco Aviation Group, Inc. (Alabama Aircraft Industries, Inc.)
• Original Assignee: The Boeing Co.
• Inventors: Roseburg, Lawrence E.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/174,477
• Time in Patent Office: 875 Days
• Field of Search: 244/117 R, 244/119, 244/120, 244/129.1, 244/131, 244/132, 105/399, 105/407, 105/411, 52/729, 52/737, 52/738, 52/739, 52/730.6
• US Class Current: 244/132
• CPC Class Codes: B64C 1/064 Stringers; Longerons
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: B64C 2001/0081 from metallic materials
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

An aircraft construction which enables visual inspection of critical body skin/stringer circumferential splice failure lines from the interior of an aircraft comprises a bulkhead member with an alternating shear tie foot pattern such that in alternating stringer bays the critical failure path along one skin portion of the aircraft is not obscured by the bulkhead shear ties. The skin joint for an adjacent skin is similarly provided with an alternating shear tie foot pattern offset by one stringer bay from the pattern for the first skin such that the critical failure path on the opposite side of the bulkhead member is also visible in alternate stringer bays.

Claims

1. An aircraft fuselage bulkhead member comprising:

a central web member adapted for placement within an aircraft transverse to the longitudinal axis of the aircraft, said central web member having a forward and an aft face;

at least two first shear tie members positioned in spaced relation to one another and extending a substantial extent only away from the forward face of said central web member; and

at least two second shear tie members positioned in spaced relation to one another and extending away from the aft face of said central web member, wherein the longitudinal alignment of a particular first shear tie member is offset from the longitudinal alignment of a corresponding second shear tie member.

2. An aircraft fuselage bulkhead member according to claim 1 wherein said central web member defines an annular shape and said at least two first shear tie members and said at least two second shear tie members define a curved profile.

3. An aircraft fuselage bulkhead member according to claim 1 wherein said at least two first shear tie members and said at least two second shear tie members are located near the crown of the aircraft fuselage.

4. A method of manufacturing an aircraft fuselage bulkhead member comprising the steps of:

providing a central web member having a forward face and an aft face and adapted for placement within an aircraft transverse to the longitudinal axis of the aircraft;

positioning at least two first shear tie members in spaced relation substantially only at the forward face of said central web member; and

positioning at least two second shear tie members in spaced relation to one another at the aft face of said central web member, wherein the longitudinal alignment of a given first shear tie member is offset from the longitudinal alignment of a corresponding second shear tie member.

7. The method according to claim 4 wherein said central web member has at least four pairs of oppositely facing shear tie members and wherein the offset of the longitudinal alignment of said first shear tie members and said second shear tie members is achieved by removing at least two alternating shear tie members from said forward face and removing at least two alternating shear tie members from said aft face wherein the longitudinal alignment of said forward face removed shear tie members is offset from the longitudinal alignment of said aft face removed shear tie members.

5. A fuselage body skin/stringer circumferential splice comprising:

a first skin member and a second skin member positioned in adjacent relation to one another along a join line;

a splice plate adapted to simultaneously overlay a portion of an internal surface of said first skin member and a portion of an internal surface of said second skin member, said splice plate running substantially coextensively with the join line of said first and second skin members;

a bulkhead member disposed substantially coextensively with the join line of said first and second skin members, wherein said splice plate is positioned between said bulkhead member and said first and second skin members, said bulkhead member abutting said splice plate via plural shear tie members, said shear tie members being disposed in an alternating configuration such that a first shear tie member is positioned substantially to the first lateral side of the join line and a second shear tie member is positioned substantially to the second lateral side of the join line.

6. The fuselage body skin/stringer circumferential splice according to claim 5 wherein said bulkhead member carries openings therein in spaced relation along the extent thereof, said openings defining stringer bays and wherein said first shear tie member is associated with a first stringer bay and said second shear tie member is associated with a second stringer bay.