Method of bonding metal skins to internal support structures

• US 4,783,228 A
• Filed: 07/03/1986
• Issued: 11/08/1988
• Est. Priority Date: 07/03/1986
• Status: Expired due to Fees

• Current Assignee: Edwards Aerospace, Inc.
• Original Assignee: Lockheed Corporation (Martin Marietta Corporation)
• Inventors: Aker, Sam C., Phillips, Pettice M.
• Primary Examiner(s): Massie, Jerome
• Application Number:
  US06/881,810
• Time in Patent Office: 859 Days
• Field of Search: 156/228, 156/245, 156/285, 156/286, 156/307.7, 156/292, 156/382, 156/583.3, 156/583.91, 156/64, 156/91, 156/497, 156/359, 156/500
• US Class Current: 156/64
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: B64C 2001/0081 from metallic materials
• CPC Class Codes: F16B 11/006 by gluing gluing of plastics material B29C65/48

Abstract

Disclosed is a method and apparatus for joining a metal skin to an internal structure comprising forming the metal skin to a permanent desired contour; assembling a lattice of ribs and spars and bonding the lattice to the contoured skin and subsequently forming the completed structure by bonding a pair of skin-superstructure assemblies together. Also disclosed is a diaphram designed to apply pressure to the skin only along structurally supported area of the skin to prevent damage.

Claims

1. A method of adhesive bonding a metal skin to an internal structure comprising the steps of:

(a) providing a pair of metal skin panels;

(b) providing means for forming said metal skin panels whereby said skin panels assume and retain a specific contour;

(c) forming a pair of contoured skin panels;

(d) assembling a lattice of discrete ribs and spars to form a rib and spar subassembly inside one of said contoured skin panels so that said rib and spar subassembly contacts the inner surface of said contoured skin panel;

(e) bonding said rib and spar subassembly to the inner surface of said contoured skin panel to form a skin-superstructure assembly;

(f) assembling a pair of said skin-superstructure assemblies; and

(g) bonding said skin-superstructure assemblies together by applying temperature and pressure thereto so that pressure is only applied to said skin-superstructure assemblies along the line of contact between said skin-superstructure assemblies.

2. The method of adhesive bonding a metal skin to an internal structure of claim 1 wherein the step of forming a pair of contoured skin panels comprises the steps of:

(a) providing stiffening members for stiffening said skin panels;

(b) combining said skin panels and said stiffening members in said means for forming said contoured panels so that the stiffening members contact the inner surface of the contoured skin panels;

(c) applying an adhesive to the inner surface of the contoured skin panel and to one surface of said stiffening members and replacing the stiffening on the inner surface of said skin panel so that the adhesive layers formed thereby are in contact;

(d) enclosing the assembled contoured skin panel and stiffening members in a vacuum bag and reducing the pressure therein while increasing the temperature of the contoured skin panel and stiffening member panel so that the adhesive layers bond the stiffening members to said skin panel.

3. The method of claim 1, wherein the step of assembling a lattice of ribs and spars to form a rib and spar subassembly inside one of said contoured skin panels comprises the additional step of mechanically joining said ribs and spars after said rib and spar subassembly is fitted to the contoured skin assembly.

4. The method of claim 1, wherein the step of bonding said rib and spar subassembly to the inner surface of said contoured skin panel to form a skin-superstructure assembly comprises the steps of:

(a) applying an adhesive to the inner surface of the contoured skin assembly;

(b) fill all voids in the lattice of ribs and spars up to the top of the ribs and spars forming said lattice with a heat and pressure transmitting medium;

(c) enclosing the combined rib and spar and contoured skin assembly thus filled with heat and pressure transmitting medium in a vacuum means; and

(d) evacuating said vacuum means and raising the temperature of the enclosed assembly to a curing temperature for a time sufficient to allow complete curing of said adhesive whereby said rib and spar subassembly is bonded to said contoured skin assembly to form a skin super-structure assembly.

5. The method of claim 4, wherein the step of assembling said skin-superstructure assembly and the second of said contoured skin panels comprises the steps of:

(a) removing said pressure and heat transmitting medium from the voids formed between the lattice of ribs and spars;

(b) applying an adhesive to the surfaces of the rib and spar lattice of the skin-superstructure assembly which will contact the second of said contoured skin panels;

(c) positioning said second contoured skin assembly on the rib and spar lattice of the skin superstructure assembly; and

(d) enclosing the unbonded assembly in a means for applying pressure only to that portion of said second contoured skin panel which contacts and which is to be bonded to said rib and spar lattice whereby unsupported skin areas receive no pressure above ambient atmospheric and wrinkles or bends in said skin are prevented.

6. The method of claim 1, wherein the step of bonding said skin-superstructure assembly and the second contoured skin assembly comprises the steps of:

(a) raising the pressure along the line of contact between said contoured skin panel and said skin-superstructure whereby both bodies are held firmly together and the adhesive between said bodies is evenly distributed; and

(b) increasing the temperature to a curing temperature for sufficient time to bond said second contoured skin assembly to said skin-superstructure assembly.

7. The method of claim 1, further including the steps of continuously measuring the temperature of the contoured skin panel, the stiffening members and the adhesive layers and evaluating the results of said temperature measurements and adjusting the curing temperature in accordance with the results obtained.

8. The method of claim 4, further including the steps of continuously measuring the temperatures of the spar and rib subassembly, the contoured skin panel and the adhesive layer, evaluating the results of said temperature measurements and adjusting the curing temperature in accordance with the results obtained.