METHOD AND APPARATUS FOR BONDING METAL SKINS TO INTERNAL STRUCTURES

Abstract: 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 diaphragm designed to apply pressure to the skin only along structurally supported area of the skin to prevent damage.

Description: Method and Apparatus for Bonding Metal Skins to Internal Structures Technical Field This invention generally relates to a method and apparatus for adhesive bonding a metal skin to an internal structure as part of the bond tooling in combination with the precise application of pressure to the skin so that a metal skin may be bonded to an internal metal structure using only plastic adhesive without damage to the skin of the resultant structure. Background Art Aluminum and aluminum base alloys have become impor- tant materials in all engineering fields and all the com- mon methods of joining are applied to aluminum and its alloys. With the exception of bolting and riveting and regardless of the considerable differences between them all common joining methods involve the same fundamental property of adhesion, namely, that of bringing ϋhe sur- faces to be into sufficiently close contact for the inter- atomic forces to be effective. In pressure welding, and to a lesser extent in resistance welding, the joints are made entirely between solid phases.; in fusion, welding, the joints are consummated entirely by liquid phases; in brazing and soldering both solid and liquid metals are involved, while when plastic adhesives are used solid metal is joined by a liquid or semi-liquid organic mat- erial. Aluminum was generally regarded as a difficult metal to join by any means other than mechanical. Recent re- search, however, has led to a better understanding of the properties of the metal which do and/or do not promote joining aluminum and today the results of the aforesaid research have led to the proliferation of such methods. The methods used to join aluminum are basically the same as those used to join other metals except that modi- fications in technique have been used to take into account the effect the properties of aluminum. The properties that work against the joining of aluminum by exactly the same techniques that are used to join other metals are: ther- mal properties; the oxide film; gas reactions; and etal- urgical characteristics. Pure aluminum melts at 659°C and the alloys melt over a range of from about 530°C to about 650°C depending upon their composition. When fus- ion welding is used experience with a particular alloy is necessary because no color change occurs on heating. Addi- tionally, a considerable heat input is required to raise the mating surfaces of aluminum to its joining tempera- ture because the specific and latent heats of aluminum are high and because the thermal conductivity of alum- inu is high and varied. The thermal conductivity of aluminum varies from approximately five times that of mild steel in the case of the pure metal to about three times that of mild steel for the alloys. Perhaps the single most important factor to be taken into account when making satisfactory aluminum joints is the the presence of the oxide film which covers the surface of all aluminum-base materials. The rate of oxidation of aluminum is extremely high and the oxide formed does not melt until temperatures above 2000°C are reached and it is also insoluble in liquid and solid aluminum. This oxide layer on pure aluminum is sufficiently continuous and tough to prevent metal to metal contact even when the metal melts. Oxide films on aluminum-base materials are porous and retain significant amounts of substances such as grease, dyes and other compounds with which they may become impregnated. For this reason it is necessary to either remove the oxide film completely before or during the joining operation or the ensure that the sur- face film is uniform in thickness and characteristics over the surface being joined. It is well known that liquid aluminum absorbs consid¬ erable volumes of hydrogen which is less soluble in the solid metal and solidification of a melt into which much 1 hydrogen ' has been dissolved during welding will result in a 2 porous and consequently weak joint. Porosity in a weld 3 could also result from the dissolution of water vapor and 4 constituent gases from the welding flame in the molten metal 5 at the point of joining. 6 Soldering aluminum is not yet as generally practical 7 as are welding and brazing, but it has been successfully 8 used to join aluminum cable sheaths and to fill dents in 9 damaged aluminum car panels. Several methods of soldering 10 have been used in the past. These methods all require a 11 high degree of experience and skill to be successfully 12 practiced. One such method involves rubbing a previously 13 cleaned surface with a hot soldering iron and stick solder 14 to first remove the surface oxide layer and then to tin the 15 surface with melting solder before the surface can re- 16 oxidize. The friction or rubbing method' as this is called 17requires skill and experience and must be used in combina- 18tion with chemical cleaning. Another method known as re¬ daction soldering makes use of the reaction between aluminum 20and zinc chloride whereby volatile aluminum chloride is 21produced and zinc is deposited on the aluminum surface to 22provide a suitable base for subsequent soldering. Another 23soldering method involves immersing aluminum in a bath of 24molten solder and using ultrasonic waves transmitted through 25the molten solder to shatter the oxide film thereby allowing 26the aluminum to be effectively wet by the solder. 27 One problem with soldered aluminum joints results 28from the possibility of solder penetrating the aluminum at 9its grain boundaries and causing some risk of embrittle- 0ment and cracking. 31 During the past several years synthetic resin ad- 32hesives have begun to be used for joining like metals, dis- 3similar metals and metals to non metals. The aerospace in- 4dustry has led the way in the development of this method 5for aluminum. The primary characteristic of a plastics 36joining process is the wetting of a cleaned surface by a 7ϋquid or solid of low melting point followed by curing -V- 1 which changes the liquid to a hard infusable resin which 2 will adhere strongly to the metal. Good adhesion depends 3 upon thorough wetting of the surfaces to be joined by the 4 adhesive. Wetting demands thoroughly cleaned and degresed 5 surfaces but in this process the oxide film serves a use- 6 ful base for adhesion. Because corrosion of the metal can- 7 not be tolerated the types of plastics acceptable for use 8 as the adhesive are limited. The processes used to bond 9 aluminum are divided into two classes based upon the method 0 of curing, which in both cases, is carried out at elevated 1 temperatures. One class requires the application of applici- 2 able pressure during curing and the other requires only 3 sufficient pressure to hold the surfaces being joined to- 4 gether and in close contact during curing. One such method 5 uses a phenol formaldehyde resin which is either brushed 6 or sprayed onto clean aluminum to wet the metal and a 7 polyvinyl formaldehyde powder is then sprayed onto it to 8 give toughness and strength after curing. After a period 9 of open exposure before increasing temperature and pres- 0 sure the pressure is increased to about 100 tons per 1 square inch at a temperature of 140 to 150°C for 15 to 2 20 minutes. If the temperature is higher the curing time 3 is shorter. In the other class of plastic bonding pro- 4 cess an epoxyethane resin is applied to a metal at 100- 5 120°C by stroking with a rod or as a powder to cold metal by a flame-spray gun, followed in both cases by an oven 7 cure cycle of one to two hours at approximately 180°C or 8 for a shorter time at a higher temperature. 9 in both of the preceding methods surface preparation 0 is important to the formation of a good bond and the existence of a uniform and consistent oxide layer also 2 promotes good bonding. Therefore, after degreasing with both solvent degreasers and alkaline cleaing agents, the metal is treated with a chromic acid-sulfuric acid pick- -* ling solution. A chromic acid anodizing process may also ° be used to prepare the oxide for bonding. 7 Presssure can be applied either in a suitable press having heated platens or in an autoclave using a rubber blanket. When thin gauge materials are being bonded vacuum bagging techniques can be used to apply pressure. Plastic bonding has allowed substantial design flexi- bility in the aerospace industry by providing for the pro- duction of smooth surfaces because no mechanical fasteners are required. It has also provided for lighter and strong- er structures because stress concentrations which accompany fastener holes are eliminated and load transfer from one structural member to another is less abrupt thereby pro- viding for more favorable stress distribution throughout a structure assembled by plastic bonding. The ability to use plastic bonding techniques to join structural members of aircraft has also reduced the corrosion succeptibility of such structures because the use of such a technique inherently eliminates traps or other unsealed and in- accessible pockets where corrosion could go undetected. Nothwithstanding the obvious advantages of plastic bond- ing procedures,the ability of such a procedure to be successfully put into practice to produce complex shapes using the methods and apparatus of the prior art would require complex and expensive tooling and a complex and inefficient bagging operation. Disclosure of the Invention Accordingly, it is an object of the present invention to provide cost effective plastic bonding tooling that can be easily and economically used to produce complex aero- dynamic shapes. Another object of the present invention is to provide apparatus capable of employing the internal structual components of a complex assembly as a tool for defining the shape of the assembly during plastic adhesive bonding. Another object of the present invention is to provide apparatus for plastic adhesive bonding a metal skin tδ an internal structure the use of which only requires the application of pressure along the bond lines to be formed -c- thereby preventing damage to unsupported areas of the skin. A principal feature of the present invention is the pro- vision of a unique apparatus for the plastic adhesive bond- ing of a metal skin to an internal structure by subjecting the components of the structure being bonded to selective variations in temperature and pressure. In accordance with the present invention the apparatus for plastic adhesive bonding a metal skin to an internal structure generally comprises a contour means for imparting a desired contour to a metal skin to form a contoured metal skin; a first bonding means for plastic adhesive bonding stiffening mem- bers inside the contoured metal skin to form a stiffened skin; an assembly means for assembling a lattice of ribs and spars inside the contour of a stiffened skin; a second bonding means for plastic adhesively bonding the lattice of ribs and spars to the stiffened skin to form a skin superstructure assembly; and a third bonding means for plastic adhesively bonding a pair-of skin superstructure assemblies together whereby skin areas not reinforced by internal ribs and spars are subjected to pressures no greater than ambient atmospheric pressure thereby reducing the possibility of pressure induced collapse of the skin. Another feature of the present invention is the ability to produce a plastic adhesively bonded structure having an aerodynamically smooth skin. Another important feature of the present invention is the ability to produce a structure having a skin which is plastic adhesive bonded to an internal structure in a manner which reduces the structures succeptibility to the 'Oil can effect". Still another feature of the present invention is the ability to plastic adhesive bond a skin to an internal structure by using the internal structure of the body being formed as a consumable tool in the manufacturing pro- cess thereby effectively reducing the cost of manufacture by eliminating the expense and complexity of the produc- tion tooling. Yet another feature of the present invention is the ability to selectively pressurize the body during assembly so that pressure is only applied to the skin along bond lines where the skin is supplied by the internal structure of the body being produced. In a preferred embodiment of the invention a segmented bladder is provided to apply pressure along bond lines only. Yet another feature of the present invention is the ability to apply uniform pressure along bond lines when forming subassemblies from which the final structure is fabricated. Yet another feature of the present invention is the ability to combine two subassemblies to form the final bonded structure without the necessity of transferring the subassemblies from the tool in which they are assembl- ed. One advantage of the present invention is the ability to produce aerodynamic structures by a plastic adhesive bonding process without the necessity of using a complex bagging procedure. Another advantage of the present invention is the ability to produce aerodynamic structures by a plastic adhesive bonding process at a reduced cost of manufactur- ing such structures. Another advantage of the present invention is the ability to produce an aerodynamically smooth structure comprising a skin attached to an internal supporting struc- ture. Still another advantge of the present invention is the ability of the method and apparatus of the present in- vention to avoid the hazards of bag bridging. Another important advantage of the present invention is the elimination of the necessity to tailoring a pres- sure bag to fit into all the various voids and pockets in a subassembly thereby saving significant amounts of manufacturing time. Still another very important feature of the present invention is the ability to assemble a structure co - prising a skin attached to an internal supporting struc- ture from which stress concentrations due to fastener holes are eliminated and load transfer from one structural member to another is less abrupt thereby providing for a structure having an improved stress distribution. An additional advantage of the present invention is the provision of an end product which is less succeptible to corrosion because unsealed and inaccessible pockets where corrosion can proceed undetected are eliminated. Still another important advantage of the present invention is the provision of a finished product which weighs less than similar products manufactured by prior art methods. Another advantage of the present invention is the elimination from wet structures of vibration induced leakage around fasteners. In accordance with these and other objects, features and advantages of the present invention there is provided an apparatus for plastic adhesive bonding a metal skin to an internal supporting structure by a process which subjects the bonded articles to variations in temperature and pressure which comprises means for imparting a de- sired contour to a metal skin; a means for plastic ad- hesively bonding stiffening members inside the contour of the contoured skin; a means for assembling a lattice of ribs and spars inside the stiffened contoured skin and mechanically joining the ribs and spars; a means for plastic adhesively bonding the rib and spare assembly to contoured skin; and a means for joining a pair of skin- rib-spar assemblies by plastic adhesion bonding in which skin aras not directly reinforced by internal ribs and spars are subjected to pressures no greater than ambient atmospheric pressure thereby reducing the likelihood of a pressure induced collapse of the skin. Also, in accordance with the present invention there is provided a method of plastic adhesive bonding a metal skin to an internal structure comprising the steps of: providing a pair of metal skin panels, providing means for forming the metal skin panels so that each skin panel assumes and retains a desired contour and forming the skin panels having the desired contour; assembling a lattice of ribs and spars inside each contoured skin panel and bonding rib-spar lattices to the inner surface of the contoured skin panels; and joining the rib-spar- skin assemblies by a plastic adhesive bonding process by applying temperature and pressure to a mated pair of such assemblies in a way which causes pressure to only be applied to the skin along lines directly supported by ribs and spars. In accordance with the present invention the method of bonding a metal skin to an internal structure further comprises the steps of providing stiffening members for affixing to the contoured skin panels to become somewhat rigid and hold the Contour which had been imposed on it; combining the stiffeners and the skin panel in a means for forming contoured panels and adhesively bonding the stiffening members to the skin with an adhesive resin using temperature and pressure to cure the adhesive. In accordance with the present invention the method of bonding a metal skin to an internal structure com- prises the additional step of mechanically joining ribs and spars to form a rib and spar subassembly prior to the step of bonding the ribs and spars to the inside of the skin. i accordance with the present invention the step of bonding the ribs and spars to the inner surface of the contoured skin with an adhesive resin comprises applying an adhesive resin to a portion of the inner surface of the contoured skin, positioning the rib and spar lattice over the adhesive coated area of the contoured skin; filling the spaces between the contoured skin and the rib and spar lattice to the top of the lattice with a heat and pressure transmitting medium; enclosing the - 0 - filled assembly in a vacuum bag and evaluating the vacuum bag while raising the temperature of the total system to a curing temperature so that the proper temper*- ature and pressure conditions are maintained for a time sufficient to bond the lattice to the contoured skin. These and other objects, features and advantages of the present invention will become more readily apparent with a reading of the following more detailed description of the preferred embodiment in conjunction with the accompanying drawings and claims. The drawings in which like reference characters indicate corresponding parts in all views are not necessarily to scale, emphasis in- stead being placed on illustrating the principals of the invention. Brief Description of the Drawings Figure 1 shows a cross-section of a contoured skin panel. Figure 2 shows a cross-section of a contoured skin panel having stiffening members bonded thereto. Figure 3 is a cross-sectional view of the means for joining a pair of skin-superstructure assemblines. Figure 4 is stylized representation of a rib and spar subassembly. Figure 5 is a stylized representation of skin panel having stiffening members affixed thereto. Figure 6 is a pictorial representation of a skin- superstructure assembly. Figure 7 is a pictorial representation of a skin- superstructure assembly with the heat and trans- mitting medium in place. Best Mode of Carrying Out the Invention Referring now to Figure 1, which shows a skin panel 10 without stiffening members being shaped to a desired contour in contour forming means 11. Figure 2 shows skin panel 10 in contour forming means 11 with stiffening - / ■ — members 12 bonded to the inner surface of the contoured skin panel 10. Figure 3 shows a pair of skin-superstrue- ture assemblies 30 being joined in a means for applying temperature and pressure 31 so that pressure is applied only along bond lines thereby preventing damage to the skin 10 due to crumpling or bending as would happen if pressure were to be applied to unsupported areas of skin 10. Means for applying temperature and pressure 31 com- prises a pair of contour forming means 11, bladders 32 and fastening means 33 which cooperate to bring the mating surfaces of the skin-superstructure assemblies 30 into contact under the proper conditions of time te per- ature and pressure to promote cure of an adhesive which has been applied to the mating surfaces and cause the pair of subassemblies to be bonded together. Shown in Figure 4 is a rib and spar lattice 40 which comprises ribs 41 and spars 42 which are mechani- cally joined before being attached to a stiffened skin panel 10, Figure 5, by a plastic adhesive bonding pro- cess to form a skin-superstructure assembly 30 shown in Figure 6. To bond rib-spar lattice 40 to skin 10 the lattice 40 is positioned on skin 10 and a plastic resin adhesive is placed between lattice 40 and skin 10 and the cavity formed between the skin 10 and lattice 40 is filled with a pressure transmitting medium 70 such as glass or metal balls and the entire assembly is enclosed in a vacuum bag and placed in an oven to autoclave so that the volume inside the vacuum bag may be evacuated thereby causing a pressure to be applied to skin 10 and lattice 40 thereby compressing the subassemblies being bonded together to form a firm bond when the resin ad- hesive is cured by exposure to the elevated temperatures of the oven or autoclave. The advantage of using balls as the pressure transmitting medium 70 is that the balls will conform almost exactly to the shape of the cavity and behave as a fluid pressure transmitting medium which will not leak as is common with pressurized air bags. The ability of balls to conform to the shape of the cavity elminates the need to tailor an intricately shape a bag to fit the numerous pockets formed by the intersecting ribs 42 and spars 40. In production operation the ' balls 70 can be loaded in and out of the bond fixture with a pneumatic conveying system thereby providing for auto- mated transfer of the pressure medium to and from a central storage facility. When a solid pressure trans- mitting medium such as metal or ceramic balls is used, thin detailed parts and areas exposed to adhesive flush mount must be covered to prevent surface marring caused by direct contact with the balls and also to prevent the balls from becoming bonded to the structure. In order to bond the elements of a structure to- gether by a plastic adhesive resin bonding process the adhering surfaces of the parts to be bonded should first be prepared using a technique such as phospheric acid anodizing. This procedure produces a stable, inspectable and verifiable surface on aluminum. The anodized surface should then be treated with a heat curing corrosion in- hibiting adhesive primer which in combination with a phospheric acid anodizing of the adhering surfaces pro- duces a stable, storable surface with exceptional environ- mental durability and predictable bondability. The appli- cation of a baked-on primer is essential because parts should have a shelf life of several months so that schedul- ing flexibility is necessary when a complex structure such as an aircraft wing is being assembled from numerous sub-parts. In actual practice a thin layer film is cured to the mating surfaces of parts to be bonded together. This adhesive film layer is then covered with a protec- tive medium such as the material known in the industry as pul-ply and a caul sheet. When the part is ready for bonding the pul-ply and caul sheet is removed exposing a fresh bondable surface. All surfaces of the parts were coated with corrosion inhibiting primer and baked at 225°F. This primed surface outside the bond area then becomes the first coat of primer corrosion inhibitor applied to the interior surfaces of a structure such as a wing. Prior to mating of both halves of an assembly each receives a coat of corrosion resistant epoxy poly- amide finish to provide the maximum corrosion protection for the internal surface. Figure 3 shows in cross-section the final bonding operation wherein two skin-superstructures 30 are joined by plastic adhesive bonding by using two such superstruc- tures to bring the mating surfaces together and holding the two skin-superstructure assemblies 30 together while the rib or lattice functions as ar. inexpensive func- tional tool to promote rapid filling thereafter. Although the present invention has been described and discussed with primary emphasis on one preferred em- bodiment, it should be obvious that adaptations and modi- facations can be made thereto without departing from the spirit and scope of the invention.

Claims: Claims 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 speci- fie contour; c) forming a pair of contoured skin panels; d) assembling a lattice of 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 asse bly; and g) bonding said skin-superstructure assemblies to- gether by applying temperature and pressure there- to so that pressure is only applied to said skin- superstructure assemblies along the line of con- tact between said skin-superstructure assemblies. - ι5 - 1 2. The method of adhesive bonding a metal skin to an 2 internal structure of Claim 1 wherein the step of 3 forming a pair of contoured skin panels comprises 4 the steps of: 5 a) providing stiffening members for stiffening said 6 skin panels; 7 b) combining said skin panels and said stiffening 8 members in said means for forming said contoured 9 panels so that the stiffening members contact 10 the inner surface of the contoured skin panels; 11 c) applying an adhesive to the inner surface of the 12 contoured skin panel and to one surface of said 13 stiffening members and replacing the stiffening 14 on the inner surface of siad skin panel so that 15 the adhesive layers formed thereby are in contact; 16 d) enclosing the assembled contoured skin panel and 17 stiffening members in a vacuum bag and reducing 18 the pressure therein while increasing the temper- 19 ature of the contoured skin panel and stiffening 20 member panel so that the adhesive layers bond the 21 stiffening members to said skin panel. 22 233. The method of Claim 1, wherein the step of assembling 4 lattice of ribs and spars to form a rib and spar 5 supassembly inside one of said contoured skin panels 26 comprises the additional step f mechanically join- 7 ing said ribs and spars after said rib and spar sub- 8 assembly is fitted to the contoured skin assembly. 29 30 31 32 33 34 35 36 7 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-super- structure 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 com- plete curing of said adhesive whereby said rib and spar subassembly is bonded to said contoured skin assembly to form a skin super-struc ure assembly. The method of Claim 1, 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 assem- bly which will contact the second of said contour- ed skin panels; c) positioning said second contoured skin assembly on the rib and spar lattice of the skin super- structure 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 tine of contact between said contoured skin panel and said skin- superstructure whereby both bodies are held firm- ly 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 cur- ing temperature in accordance with the results ob- tained. 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 cur- ing temperature in accordance with the results ob- tained. - - 9. An apparatus for adhesive bonding a metal skin to an internal structure by a process which subjects the bonded articles to variations in temperature and pressure comprising: a) contour means for imparting a desired contour to a metal skin to form a contoured metal skin; b) a first bonding means for adhesively bonding stiffening members inside the contour of a con- toured metal skin to form a stiffened skin; c) assembly means for assembling a lattice of ribs and spars inside the contour of the stiffened skin; d) a second bonding means for adhesively bonding the lattice of ribs and spars to the stiffened skin to form a skin superstructure assembly; and e) a third bonding means for adhesively bonding a pair of skin-superstructure assemblies whereby skin areas not reinforced by internal ribs and spars are subjected to pressures no greater than ambient atmospheric pressure thereby re- ducing the possibility of pressure induced collapse of the skin. 10. The apparatus of Claim 9, wherein said first bond- ing means comprises: a) vacuum means capable of enclosing the contoured metal skin and said stiffening members as the contoured metal skin is held by said contour means; b) means for applying pressure to said stiffening members and said contoured skin whereby said pressure is directed along the area of contact between the contoured skin and the stiffening member; and c) temperature means for raising the temperature of the contoured metal, skin and the stiffening mem- bers to a curing temperature for an adhesive placed between the two. - Z\ - 11. The apparatus of Claim 9, wherein the second bonding means comprises : a) a contoured base for receiving and supporting the stiffened contoured skin assembly and retaining it in the desired contour; b) pressure transmitting means for transmitting an externally applied pressure to junctions between the rib-spar lattice and the interior of the stiff- ened contoured skin assembly; c) pressure means for applying pressure to the pres- sure transmitting means and the contoured base; and d) temperature means for raising the temperature of the stiffened contoured skin assembly, the pres- sure transmitting means, the rib-spar lattice and an adhesive to a curing temperature of the ad- hesive and maintaining the temperatures at said curing temperature until the adhesive cures and bond is formed between the stiffened-contoured skin and the rib-spar lattice and a skin-super- structure assembly formed. - 2Z- 1 12. The apparatus of Claim 9, wherein the third bond- 2 ing means comprises: 3 a) a pair of contoured bases containing bonded skin- 4 superstructure assemblies; 5 b) means for joining said contoured bases to form 6 a closed container so that the skin-superstructure 7 assemblies contact each other along the unbonded 8 surfaces of the rib and spar lattices to form bond 9 lines; 0 c) means for applying pressure to the contoured bases 1 only along bond lines so that the unsupported por- 2 tion of said contoured skins are not subjected to 13 pressure greater than ambient one atmosphere there- 14 by reducing the possibility of bending the un- 15 supported skins; and 16 d) temperature means for raising the temperature of 17 of contoured bases and the contents thereof to a 18 curing temperature for the adhesive for a period 19 of time for complete bonding to occur. 20 21 13. The apparatus of Claim 11, wherein the pressure means 22 for applying pressure to the pressure transmitting 23 means and the contoured base comprises vacuum bag 24 means for enclosing the contoured base and the rib- 25 spar lattice and vacuum means for evacuating the 26 enclosed volume. 27 2814. The apparatus of Claim 13, wherein the pressure trans- 29 mitting means comprises spherical beads. 30 3115. The apparatus of Claim 12, wherein the means for 32 applying pressure to the contoured bases only along 33 bond lines comprises inflatable bladder means adapt- 34 ed to inflate only in those portions thereof that 35 are in contact with supported sections of contoured 36 base so that when said bladder is inflated no pres- 37 sure is applied to unsupported contoured base sections and pressure sufficient to aid bonding is applied along bond lines. - Z.V 16. The apparatus of Claim 12, wherein the temperature means comprises an autoclave. 17. The apparatus of Claim 12, wherein the temperature means comprises an oven.

Inventors: AKER SAM COOPER, PHILLIPS PETTICE MALCOLM, AKER, SAM, COOPER, PHILLIPS, PETTICE, MALCOLM
Applicants: LOCKHEED CORP, LOCKHEED CORPORATION
Application year: 1987
Main classification: C09J5
IPC codes: B64C1, C09J5, F16B11