CN113996906B - Preparation method of multilayer board hollow structure containing layered composite material - Google Patents
Preparation method of multilayer board hollow structure containing layered composite material Download PDFInfo
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- CN113996906B CN113996906B CN202111318462.4A CN202111318462A CN113996906B CN 113996906 B CN113996906 B CN 113996906B CN 202111318462 A CN202111318462 A CN 202111318462A CN 113996906 B CN113996906 B CN 113996906B
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- 239000002131 composite material Substances 0.000 title claims abstract description 164
- 238000002360 preparation method Methods 0.000 title claims abstract description 22
- 239000011888 foil Substances 0.000 claims abstract description 290
- 238000000034 method Methods 0.000 claims abstract description 52
- 239000000463 material Substances 0.000 claims abstract description 46
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 claims abstract description 36
- 230000008569 process Effects 0.000 claims abstract description 29
- 229910000943 NiAl Inorganic materials 0.000 claims abstract description 23
- 229910010038 TiAl Inorganic materials 0.000 claims abstract description 23
- 238000013329 compounding Methods 0.000 claims abstract description 17
- 238000001816 cooling Methods 0.000 claims abstract description 17
- 229910000765 intermetallic Inorganic materials 0.000 claims abstract description 14
- 230000007704 transition Effects 0.000 claims abstract description 8
- 238000006243 chemical reaction Methods 0.000 claims abstract description 7
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 6
- 238000005070 sampling Methods 0.000 claims abstract description 5
- 238000003786 synthesis reaction Methods 0.000 claims abstract description 5
- 239000010936 titanium Substances 0.000 claims description 112
- 229910052782 aluminium Inorganic materials 0.000 claims description 84
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 83
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 83
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 81
- 238000010438 heat treatment Methods 0.000 claims description 40
- 238000003466 welding Methods 0.000 claims description 40
- 229910052719 titanium Inorganic materials 0.000 claims description 39
- 239000007789 gas Substances 0.000 claims description 29
- 229910052759 nickel Inorganic materials 0.000 claims description 22
- 238000009792 diffusion process Methods 0.000 claims description 21
- 229910000679 solder Inorganic materials 0.000 claims description 21
- 238000011068 loading method Methods 0.000 claims description 17
- 238000004321 preservation Methods 0.000 claims description 13
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 12
- 238000007731 hot pressing Methods 0.000 claims description 11
- 238000005520 cutting process Methods 0.000 claims description 10
- 238000013461 design Methods 0.000 claims description 8
- 229910052786 argon Inorganic materials 0.000 claims description 6
- 238000002474 experimental method Methods 0.000 claims description 6
- 239000011248 coating agent Substances 0.000 claims description 5
- 238000000576 coating method Methods 0.000 claims description 5
- 238000003825 pressing Methods 0.000 claims description 5
- 229910052582 BN Inorganic materials 0.000 claims description 4
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims description 4
- 238000001035 drying Methods 0.000 claims description 4
- 239000012535 impurity Substances 0.000 claims description 4
- SIWVEOZUMHYXCS-UHFFFAOYSA-N oxo(oxoyttriooxy)yttrium Chemical compound O=[Y]O[Y]=O SIWVEOZUMHYXCS-UHFFFAOYSA-N 0.000 claims description 4
- 238000012545 processing Methods 0.000 claims description 4
- 239000002994 raw material Substances 0.000 claims description 4
- 238000004140 cleaning Methods 0.000 claims description 2
- 238000007599 discharging Methods 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 claims 1
- 238000005260 corrosion Methods 0.000 abstract description 9
- 230000007797 corrosion Effects 0.000 abstract description 9
- 230000009467 reduction Effects 0.000 abstract description 9
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 abstract description 5
- 230000008878 coupling Effects 0.000 abstract description 4
- 238000010168 coupling process Methods 0.000 abstract description 4
- 238000005859 coupling reaction Methods 0.000 abstract description 4
- 229910052751 metal Inorganic materials 0.000 abstract description 3
- 239000002184 metal Substances 0.000 abstract description 3
- 238000000926 separation method Methods 0.000 abstract description 3
- 238000003672 processing method Methods 0.000 abstract description 2
- 238000009423 ventilation Methods 0.000 description 15
- OKKJLVBELUTLKV-UHFFFAOYSA-N Methanol Chemical compound OC OKKJLVBELUTLKV-UHFFFAOYSA-N 0.000 description 6
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 4
- 238000002844 melting Methods 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- 238000007789 sealing Methods 0.000 description 4
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- HZEWFHLRYVTOIW-UHFFFAOYSA-N [Ti].[Ni] Chemical compound [Ti].[Ni] HZEWFHLRYVTOIW-UHFFFAOYSA-N 0.000 description 3
- 230000009471 action Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/02—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by means of a press ; Diffusion bonding
- B23K20/023—Thermo-compression bonding
- B23K20/026—Thermo-compression bonding with diffusion of soldering material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/14—Preventing or minimising gas access, or using protective gases or vacuum during welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/22—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/24—Preliminary treatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/26—Auxiliary equipment
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
Abstract
The invention discloses a preparation method of a hollow structure of a multilayer board containing a layered composite material, and relates to the field of metal structural part processing methods. The titanium aluminum/nickel aluminum functional gradient type layered composite material can be organically combined with the multilayer board hollow structure ballooning forming process, so that the functions of light weight, high strength, vibration reduction, corrosion resistance and high temperature resistance of the hollow structural member are well realized, and the requirements of light weight, high strength, vibration reduction, corrosion resistance and high temperature resistance of the aircraft structure in the aerospace field are met. The preparation method comprises the following steps: step 1, material pretreatment; step 2, performing foil plates; step 3, stacking the foils in a functional gradient manner; step 4, foil compounding and gas bulging forming; step 5, forming a transition intermetallic compound; step 6, NiAl/TiAl high-temperature reaction synthesis; and 7, cooling along with the furnace and sampling. The problems of coupling of the preparation process and the structure forming process of the laminated composite material, separation of foils during gas expansion, gas leakage and blow-by between the foils and the problems of brittleness and difficult plastic forming of titanium aluminum and nickel aluminum are solved.
Description
Technical Field
The invention relates to the field of metal structural part processing methods, in particular to a method for preparing an intermetallic compound layered composite material formed by different metal foils and processing a structure ballooning forming and diffusion welding at high temperature.
Background
In order to meet the requirements of light weight, high strength, vibration reduction, corrosion resistance and high temperature resistance of an aircraft structure in the aerospace field, composite material members and hollow structural members are widely applied to the field.
The nickel-aluminum and titanium-aluminum materials have the functions of light weight, high strength, corrosion resistance and high temperature resistance, and are materials with good prospects, and the layered composite material can be prepared by foil material superposition and related composite methods. At present, the hot-pressing compounding method, the rolling compounding method and the explosion compounding method are mostly adopted at home and abroad aiming at the preparation of the layered composite material, and because the hot-pressing compounding method has simple process, the related research aiming at the method is relatively mature at home and abroad. The multi-layer hollow structural member has the functions of light weight and vibration reduction, and most of the forming of the structural members at home and abroad adopts a superplastic forming/diffusion bonding process, and the process is widely applied to the field of aerospace at present.
The patent office announces a Chinese invention patent with the name of 'a layered material and a preparation method thereof' and the application number of '201310026951.1' in 2013, 4-24.4.8, and provides a preparation method of a nickel-aluminum layered composite material. The main process comprises the following steps: firstly, performing relevant pretreatment on foil, and then alternately stacking nickel foil and aluminum foil, wherein the upper surface and the lower surface of a laminated plate are both nickel foils; putting the laminated foil into a mold, raising the temperature and applying a certain pressure, and releasing the pressure after keeping the temperature for a period of time to obtain an initial laminated plate material; and continuously raising the temperature, preserving the heat for a period of time, then lowering the temperature to the medium-high temperature, simultaneously increasing the applied pressure, preserving the heat for a period of time, and then cooling the temperature to the room temperature along with the furnace to obtain the nickel-aluminum layered composite material plate. The invention solves the problem of intrinsic brittleness of the nickel-aluminum material prepared by the existing nickel-aluminum material preparation method, provides a good reference for preparing the layered composite material, and particularly provides a good reference for hot-pressing composite preparation of titanium, nickel and aluminum, but the problem that the plasticity of the nickel-aluminum material under any condition is good still needs to be continuously researched.
The national patent office announces a Chinese invention patent with the application number of 201611016005.9, namely a preparation method of a superplastic forming/diffusion connection three-layer hollow component in 2018, 7 and 27, and the preparation method of the three-layer hollow structure is proposed. The main process comprises the following steps: firstly, performing surface treatment on a core plate and a panel, coating a solder resist on the core plate, placing the core plate between an upper panel and a lower panel, and covering sleeves on the upper side and the lower side of the panels to finally form five layers of plates; sealing and welding the five layers of plates, leaving air passages, and then welding air pipes; after detecting the air tightness of the sealing plate, charging the sealing plate, heating the sealing plate, and performing diffusion connection; after diffusion connection is finished, slowly ventilating, pressurizing and bulging, and maintaining pressure for a period of time after bulging is finished; and finally, cooling along with the furnace, and removing the sheath to obtain the final structural part. The invention adopts the hard bag forming method, the hard bag can provide enough surface friction force and coordinate the deformation rate of the panel under the high temperature condition, so that the tensile stress to the panel in the forming process of the internal reinforcing rib is not enough to deform the panel, meanwhile, the variable temperature control is adopted in the forming process to realize the control of the forming rate, and the modes provide good reference for improving the forming precision of the three-layer plate. However, since the panel itself is not a laminated composite material plate, the problem of coupling between the laminated composite material preparation and the three-layer plate structure ballooning forming process still needs to be explored, and meanwhile, the problems of air leakage and air blow-by of the foil material in the ventilation process also need to be considered.
Aiming at the existing requirements, an integrated process combining the preparation of a nickel-aluminum/titanium-aluminum functional gradient type laminated composite material and the forming of a hollow structural member of a multilayer board is provided, namely the nickel-aluminum/titanium-aluminum is prepared by adopting a hot pressing compounding method, and the hollow member of the multilayer board is formed by adopting high-temperature ballooning. However, the following key technical problems still exist in the prior art: 1. how to realize functional gradient type laminated composite materials by overlapping foils; 2. the problems of foil separation during gas expansion, no gas leakage and no gas blowby during pressurization can be solved by adopting any hot-pressing composite process; 3. due to the brittleness problem of the nickel-aluminum/titanium-aluminum material, the bulging process of the core plate can be well realized by adopting which process parameters; 4. how to realize the process coupling of the composite preparation of the material and the gas bulging forming.
Disclosure of Invention
Aiming at the problems, the invention provides a preparation method of a hollow structure of a laminated composite material multilayer board, which can organically combine the preparation of a titanium aluminum/nickel aluminum functional gradient type laminated composite material with the gas bulging forming process of the hollow structure of the multilayer board, well realizes the functions of light weight, high strength, vibration reduction, corrosion resistance and high temperature resistance of the hollow structural member, and meets the requirements of light weight, high strength, vibration reduction, corrosion resistance and high temperature resistance of the aircraft structure in the aerospace field.
The technical scheme of the invention is as follows: the preparation method comprises the following steps:
step 1, material pretreatment;
step 1.1, cutting a foil to obtain a titanium foil 1, a nickel foil 3 and an aluminum foil 4 with preset areas;
step 1.2, cleaning the cut titanium foil 1, nickel foil 3 and aluminum foil 4, removing surface-related oil stains and impurities, drying by cold air, and placing for later use;
step 3, functionally gradient type superposition of the foil: firstly, stacking a nickel foil 3, a titanium foil 1 and an aluminum foil 4 according to the design requirements of functional gradient type materials to form a composite lower panel 7, a composite core board 6 and a composite upper panel 5, wherein whether the composite core board 6 is stacked or not is determined according to whether the composite core board 6 is arranged in a forming piece or not, and then placing a Ti/Ti foil plate 2 at the contact position of the panels; meanwhile, an upper vent pipe is welded at the mouth of each air passage;
step 4, foil compounding and gas bulging forming: putting the stacked foil into an expansion mould in a vacuum furnace, heating and pressurizing, and slowly pressurizing the interior of the Ti/Ti foil plate 2 by a vent pipe;
and 5, forming a transition intermetallic compound: maintaining the pressure inside and outside the material, heating to 600-650 ℃, and carrying out low-temperature heat treatment;
and 7, furnace cooling and sampling: and cooling the structure along with the furnace, and demolding and taking the part after cooling to room temperature.
The raw materials used in step 1.1 are pure nickel foil, pure titanium foil and pure aluminum foil respectively, the thickness ratio of the foil is titanium foil to aluminum foil to nickel foil =1:1:0.6, and the cutting area of the foil is 200mm × 200 mm.
The step 2 specifically comprises the following steps:
2.1, respectively coating a plurality of solder resists on the upper surface and the lower surface of the two layers of titanium foils 1, wherein the solder resists are boron nitride or yttrium oxide; a gap is reserved between two adjacent solder resists, so that a plurality of air passages are formed at the positions of the solder resists after welding;
step 2.2, stacking the two titanium foils 1 coated with the solder resist;
and 2.3, placing the two stacked titanium foils 1 into a hot-pressing mold in a vacuum diffusion furnace, heating the mold to 880 plus 960 ℃, wherein the heating rate is 10 ℃/min, then loading the mold with the pressure of 1-5MPa, preserving the heat for 0.5-1h, and cooling to obtain the Ti/Ti foil plate 2 which is subjected to diffusion connection.
The low-temperature heat treatment time of the step 5 is 1-10h, and the high-temperature heat treatment time of the step 6 is 1-10 h.
When the two-layer hollow integral wallboard is processed, the step 3 and the step 4 are specifically as follows:
step 3, stacking the foils in a functional gradient manner;
step 3.1a, firstly, stacking the nickel foil 3, the titanium foil 1 and the aluminum foil 4 according to the design requirements of functional gradient materials to form a composite lower panel 7 and a composite upper panel 5;
the composite upper panel and the composite lower panel are divided into an upper half part and a lower half part;
the upper half part of the composite upper panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite upper panel are respectively nickel foils and aluminum foils;
the lower half part of the composite upper panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite upper panel are respectively the titanium foils and the titanium foils;
the upper half part of the composite lower panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite lower panel are respectively aluminum foil and titanium foil;
the lower half part of the composite lower panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite lower panel are respectively made of the aluminum foils and the nickel foils;
step 3.2a, sequentially stacking the composite lower panel 7, the Ti/Ti foil plate 2 and the composite upper panel 5 from bottom to top;
3.3, performing spot welding on the periphery of the stacked foil by using argon arc welding to prevent the foil from being dislocated, and welding an upper vent pipe at the opening of each air passage;
step 4, foil compounding and gas bulging forming;
step 4.1a, placing the stacked foils into an expansion mold in a vacuum furnace, slowly heating the mold, pressurizing an upper mold after the temperature is reached, and then preserving heat to enable the foils to be fully welded;
and 4.2, after the heat preservation is finished, increasing the pressure of the upper die to be larger than the bulging pressure, maintaining the pressure of the upper die until the experiment is finished, and slowly loading pressure into the Ti/Ti foil plate 2 through the vent pipe and maintaining the pressure.
Step 4, the hot-pressing composite loading pressure is 3-10MPa, the temperature rise temperature is 450-; after the heat preservation is finished, the bulging loading pressure is 1-2MPa, and the pressure maintaining time is 1-5 h.
When the three-layer plate hollow rudder wing is processed, the steps 3 and 4 are specifically as follows:
step 3, functionally gradient stacking the foils;
3.1b, stacking the nickel foil 3, the titanium foil 1 and the aluminum foil 4 according to the design requirements of the functional gradient type materials to form a composite lower panel 7, a composite core plate 6 and a composite upper panel 5;
the composite upper panel and the composite lower panel are divided into an upper half part and a lower half part;
the upper half part of the composite upper panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite upper panel are respectively nickel foils and aluminum foils;
the lower half part of the composite upper panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite upper panel are both titanium foils;
the composite core plate comprises titanium foils and aluminum foils which are alternately stacked, and the top layer of the composite core plate is the aluminum foil, and the bottom layer of the composite core plate is the titanium foil;
the upper half part of the composite lower panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite lower panel are respectively an aluminum foil and a titanium foil;
the lower half part of the composite lower panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite lower panel are respectively made of the aluminum foils and the nickel foils;
step 3.2b, sequentially stacking the composite lower panel 7, the first Ti/Ti foil plate 2, the composite core plate 6, the second Ti/Ti foil plate 2 and the composite upper panel 5 from bottom to top;
3.3, performing spot welding on the periphery of the stacked foil by using argon arc welding to prevent the foil from being misplaced, and welding an upper vent pipe at the opening of each air passage;
step 4, foil compounding and gas bulging forming;
step 4.1b, putting the stacked foil into a bulging die in a vacuum furnace, firstly pressurizing an upper die to enable the pressure to be larger than the bulging pressure, maintaining the pressure of a pressing die until the experiment is finished, further vacuumizing the die, slowly heating the die after vacuumizing is finished, inflating and pressurizing after the temperature is reached, and then preserving heat to enable the foil to be fully welded;
and 4.2, after the heat preservation is finished, unloading the pressure in the mold to zero, and slowly pressurizing the interior of the Ti/Ti foil plate 2 through a vent pipe and maintaining the pressure.
Step 4, the vacuum degree of the mould is 1 multiplied by 10 -3 Below Pa, after vacuumizing, firstly heating to 450-500 ℃, wherein the heating rate is 10 ℃/min, after reaching the temperature, loading pressure is 3-10MPa, and then preserving heat for 1-5 h; after the heat preservation is finished, the loading pressure is 1-2MPa, and the pressure maintaining time is 1-5 h.
The invention can meet the requirements of light weight, high strength, vibration reduction, corrosion resistance and high temperature resistance of the aircraft structure in the aerospace field, and simultaneously aims to solve the problems of coupling of the preparation of the layered composite material and the structure forming process, foil separation during gas expansion, gas leakage and blow-by between foils and brittle and difficult-plastic forming of titanium aluminum and nickel aluminum.
Overall, the present invention has the following beneficial effects:
the invention can realize the integrated process of the preparation of the three-layer plate hollow structure laminated composite material and the structural inflatable forming, and the integrated forming is the first innovation of the scheme and can save the processing time and the processing cost.
The invention adopts a method for preforming the foil plate, and the method is the innovation point of the scheme, and can solve the problems that the titanium alloy cannot be subjected to diffusion welding at low temperature, the foil is separated during gas expansion and the phenomena of gas leakage and gas blowby during ventilation. Firstly, pure titanium can not be subjected to diffusion welding at low temperature, and the welding problem can be solved by performing; the contact positions of the upper, middle and lower panels are areas for ventilation during gas expansion, and foils at the contact positions of the upper, middle and lower panels are pre-welded into foil plates, so that the welding quality of the ventilation areas is ensured, and no gas leakage or gas blowby is caused during ventilation; even if the foil between the upper, middle and lower composite panels is not welded well, the foil is preformed, so that the welding quality of the ventilation part between the foil is good, the gas expansion process can be normally carried out, and the unwelded foil can be continuously welded under the action of pressure when the bulging is finished.
Thirdly, the invention adopts a method of forming foil by air bulging during low-temperature compounding, and then forms the NiAl/TiAl layered composite material at high temperature, thereby well solving the problem that the NiAl/TiAl material is difficult to deform greatly due to large brittleness, which is the innovation point of the scheme. At the temperature of 450-550 ℃, no intermetallic compound or a small amount of intermetallic compound is generated between the foils, and at the moment, the whole material has better plasticity performance and is the best time for finishing the bulging of the core plate.
The upper, middle and lower laminated panel foils are in a functional gradient type in a laminated mode, so that the upper and lower panels can realize high temperature resistance of the outer surfaces, and a high temperature resistant temperature gradient type structure is not needed inside, which is the innovation point of the scheme. The hypersonic aircraft needs to meet the requirement of high temperature resistance, the upper surface of the laminated panel adopts a Ni/Al foil material superposition mode, the lower surface adopts a Ti/Al foil material superposition mode, and the middle part adopts an Al foil as a transition material, so that the obtained composite material can well meet the functional requirement.
The invention adopts a multi-layer plate hollow structure, adopts NiAl/TiAl functional gradient type laminated composite material, and can enable the structure to meet the requirements of light weight, high strength, vibration reduction, corrosion resistance and oxidation resistance. The hollow structure of the multilayer board has the functions of light weight and vibration reduction, and the NiAl/TiAl functionally gradient layered composite material has the functions of small density, high strength, corrosion resistance and oxidation resistance.
Drawings
FIG. 1 is a flow chart of the operation of the present invention;
FIG. 2 is a flow chart of a Ti/Ti foil plate preforming process;
FIG. 3 is a flow chart of a process for making a two-ply hollow monolithic panel;
FIG. 4 is a process flow diagram of a three-layer hollow rudder wing;
FIG. 5 is a schematic view of a two-layer hollow unitary panel final form;
fig. 6 is a structure diagram of the final forming of the three-layer hollow rudder wing.
In the figure, 1 is titanium foil, 2 is a Ti/Ti foil plate, 3 is nickel foil, 4 is aluminum foil, 5 is a composite upper panel, 6 is a composite core plate, 7 is a composite lower panel, 8 is an upper die, and 9 is a lower die.
Detailed Description
In order to clearly explain the technical features of the present patent, the following detailed description is given in conjunction with the accompanying drawings.
The first embodiment is as follows: this case is the formation of a two-ply hollow monolithic panel structure, as shown in fig. 1-3 and 5, wherein the foils used are N6 pure nickel foil, TA2 pure titanium foil and 1060 pure aluminum foil, which are described in detail below with reference to the accompanying drawings, and are prepared by the following steps:
step 1, pre-treating materials;
step 1.1, cutting the foil to obtain a titanium foil 1, a nickel foil 3 and an aluminum foil 4 with preset areas; the raw materials are respectively N6 pure nickel foil, TA2 pure titanium foil and 1060 pure aluminum foil, the thickness ratio of the foil is titanium foil to aluminum foil to nickel foil =1:1:0.6, the thickness of the three foils is 0.1mm of titanium foil, 0.1mm of aluminum foil, 0.06mm of nickel foil and 200mm multiplied by 200mm of cutting area of the foil.
And step 1.2, performing ultrasonic vibration on the cut titanium foil 1, the cut nickel foil 3 and the cut aluminum foil 4 for 15-30min by using acetone or methanol to remove surface-related oil stains and impurities, drying by cold air, and then placing for later use.
2.1, respectively coating a plurality of solder resists on the upper surface and the lower surface of the two layers of titanium foils 1, wherein the solder resists are boron nitride or yttrium oxide; and a gap is reserved between two adjacent solder resists, so that a plurality of air channels are formed at the positions of the plurality of solder resists after welding.
And 2.2, stacking the two titanium foils 1 coated with the solder resist.
And 2.3, placing the two stacked titanium foils 1 into a hot-pressing mold in a vacuum diffusion furnace, heating the mold to 880 plus 960 ℃, wherein the heating rate is 10 ℃/min, then loading the mold with the pressure of 3-5MPa, preserving the heat for 0.5-1h, and cooling to obtain the Ti/Ti foil plate 2 which is subjected to diffusion connection.
The method for preforming the Ti/Ti foil plate is an innovative point of the case, and can solve the problems that the titanium alloy cannot be subjected to diffusion welding at low temperature, the foil is separated during gas expansion and the phenomena of gas leakage and gas blowby during ventilation. Firstly, pure titanium can not be subjected to diffusion welding at low temperature, and the welding problem can be solved by performing; the foil between the upper panel and the lower panel is pre-welded into the foil plate, so that the welding quality of the ventilation area can be effectively ensured, and no air leakage or air blowby occurs during ventilation; even if the upper composite panel, the lower composite panel and the foil plates are not welded well, the foil plates are preformed, so that the welding quality of the ventilation parts between the foil plates is good, the air expansion process can be normally carried out, and the unwelded foil can be continuously welded under the action of pressure when the bulging is finished.
Step 3, stacking the foils in a functional gradient manner;
step 3.1a, firstly, stacking the nickel foil 3, the titanium foil 1 and the aluminum foil 4 according to the design requirements of functional gradient materials to form a composite lower panel 7 and a composite upper panel 5;
the composite upper panel and the composite lower panel are divided into an upper half part and a lower half part;
the upper half part of the composite upper panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite upper panel are respectively nickel foils and aluminum foils;
the lower half part of the composite upper panel comprises titanium foil and aluminum foil which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite upper panel are respectively titanium foil and titanium foil;
the upper half part of the composite lower panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite lower panel are respectively aluminum foil and titanium foil;
the lower half part of the composite lower panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite lower panel are respectively an aluminum foil and a nickel foil;
and 3.2a, sequentially stacking the composite lower panel 7, the Ti/Ti foil plate 2 and the composite upper panel 5 from bottom to top.
And 3.3, performing spot welding on the periphery of the stacked foil by using argon arc welding to prevent the foil from being misplaced, and welding an upper vent pipe at the opening of the air passage.
In the case, the foil overlapping mode of the upper composite panel and the lower composite panel is in a functional gradient type, so that the upper panel and the lower panel can realize a temperature gradient type structure with high temperature resistance on the outer surface and no high temperature resistance inside, which is another innovation point of the case. The hypersonic aircraft needs to meet the requirement of high temperature resistance, the upper part of the laminated panel adopts a Ni/Al foil material superposition mode, the lower part of the laminated panel adopts a Ti/Al foil material superposition mode, and the middle part of the laminated panel adopts Al foil as a transition material, so that the obtained composite material can well meet the functional requirement.
Step 4, foil compounding and gas bulging forming;
and 4.1a, placing the stacked foils into an expansion mold in a vacuum furnace, wherein the mold comprises an upper mold 8 and a lower mold 9, slowly heating the mold to 450-550 ℃, pressurizing the upper mold to 5-10MPa after the temperature is reached, and preserving the heat for 3-5h to ensure that the foils can be fully welded.
And 4.2, after the heat preservation is finished, increasing the pressure of the upper die to be larger than the bulging pressure, maintaining the pressure of the upper die until the experiment is finished, slowly loading the pressure of 1-2MPa in the Ti/Ti foil plate 2 through the vent pipe, and maintaining the pressure for 3-5 hours.
In the case, a method of forming by air inflation during foil compounding is adopted, and then the NiAl/TiAl layered composite material is formed at high temperature, so that the problem that the NiAl/TiAl material is difficult to deform greatly due to large brittleness is solved well, and the method is another innovation point of the case. At the temperature of 450-550 ℃, no intermetallic compound or a small amount of intermetallic compound is generated between the foils, and at the moment, the whole material has better plasticity performance and is the best time for finishing the bulging of the core plate.
after the pressure maintaining is finished, the temperature in the furnace is continuously raised to 600-650 ℃, the pressure in the Ti/Ti foil plate 2 is kept unchanged, and the heat treatment is carried out for 5-10h at the temperature.
The heat treatment process is to make the foil react fully to generate NiAl 3 And TiAl 3 Intermetallic compound NiAl 3 And TiAl 3 Has high melting point, can effectively avoid the melting of the aluminum foil when the temperature is higher than 660 ℃, thus preparing for generating NiAl and TiAl through subsequent high-temperature reaction.
after the low-temperature heat treatment is finished, the temperature in the furnace is continuously increased to 1100-1300 ℃, the pressure in the Ti/Ti foil plate 2 is kept unchanged, and the temperature is kept for 5-10 h.
After the heat preservation is finished, the foils react fully to generate NiAl and TiAl, and finally a two-layer plate hollow integral wall plate structure with the NiAl and TiAl laminated composite materials is formed.
and cooling the structure along with the furnace, and demolding and taking the part after cooling to room temperature.
Finally, the blank pressing part can be cut off by means of wire cutting, and the final multilayer board hollow structural member is obtained.
The second embodiment: the present case is a three-layer hollow rudder wing structure, as shown in fig. 1, 2, 4 and 6, wherein the foils used are N6 pure nickel foil, TA2 pure titanium foil and 1060 pure aluminum foil, which are described in detail below with reference to the accompanying drawings, and are prepared by the following steps:
step 1, pre-treating materials;
step 1.1, cutting the foil to obtain a titanium foil 1, a nickel foil 3 and an aluminum foil 4 with preset areas; the raw materials are n6 pure nickel foil, TA2 pure titanium foil and 1060 pure aluminum foil respectively, the thickness ratio of the foil is titanium foil to aluminum foil to nickel foil =1:1:0.6, the thickness of the three foils is 0.1mm of titanium foil, 0.1mm of aluminum foil, 0.06mm of nickel foil and 200mm multiplied by 200mm of cutting area of the foil.
And step 1.2, ultrasonically vibrating the cut titanium foil 1, the cut nickel foil 3 and the cut aluminum foil 4 for 15-30min by using acetone or methanol to remove surface-related oil stains and impurities, drying by cold air, and then placing for later use.
2.1, respectively coating a plurality of solder resists on the upper surface and the lower surface of the two layers of titanium foils 1, wherein the solder resists are boron nitride or yttrium oxide; and a gap is reserved between two adjacent solder resists, so that a plurality of air channels are formed at the positions of the plurality of solder resists after welding.
And 2.2, stacking the two titanium foils 1 coated with the solder resist.
And 2.3, placing the two superposed titanium foils 1 into a hot-pressing mold in a vacuum diffusion furnace, heating the mold to 880 plus 960 ℃, wherein the heating rate is 10 ℃/min, then loading the mold with the pressure of 3-5MPa, preserving the heat for 0.5-1h, and cooling to obtain the Ti/Ti foil plate 2 subjected to diffusion connection.
The method for preforming the Ti/Ti foil plate is an innovation point of the case, and can solve the problems that the titanium alloy cannot be subjected to diffusion welding at low temperature, the foil is separated during gas expansion and the phenomena of gas leakage and gas blowby during ventilation. Firstly, pure titanium can not be subjected to diffusion welding at low temperature, and the welding problem can be solved by performing; the upper, middle and lower panels are all provided with ventilation areas during air inflation, and foil materials between the upper, middle and lower panels are pre-welded into foil plates, so that the welding quality of the ventilation areas is ensured, and air leakage and air blowby are avoided during ventilation; even if the upper, middle and lower composite panels and the foil plates are not welded well, the foil plates are preformed, so that the welding quality of the ventilation parts among the foil plates is good, the gas expansion process can be normally carried out, and the unwelded foil can be continuously welded under the pressure action when the bulging is finished.
Step 3, stacking the foils in a functional gradient manner;
3.1b, stacking the nickel foil 3, the titanium foil 1 and the aluminum foil 4 according to the design requirements of the functional gradient type materials to form a composite lower panel 7, a composite core plate 6 and a composite upper panel 5;
the composite upper panel and the composite lower panel are divided into an upper half part and a lower half part;
the upper half part of the composite upper panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite upper panel are respectively nickel foils and aluminum foils;
the lower half part of the composite upper panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite upper panel are both titanium foils;
the composite core plate comprises titanium foils and aluminum foils which are alternately stacked, and the top layer of the composite core plate is the aluminum foil, and the bottom layer of the composite core plate is the titanium foil;
the upper half part of the composite lower panel comprises titanium foils and aluminum foils which are alternately stacked, the top layer of the upper half part of the composite lower panel is the aluminum foil, and the bottom layer of the upper half part of the composite lower panel is the titanium foil;
the lower half part of the composite lower panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite lower panel are respectively made of the aluminum foils and the nickel foils;
and 3.2b, sequentially stacking the composite lower panel 7, the first Ti/Ti foil plate 2, the composite core plate 6, the second Ti/Ti foil plate 2 and the composite upper panel 5 from bottom to top.
And 3.3, performing spot welding on the periphery of the stacked foil by using argon arc welding to prevent the foil from being dislocated, and welding an upper vent pipe at the opening of the air passage.
In the case, the upper and lower composite panels and the composite core board are stacked in a functional gradient manner, so that the upper and lower panels can realize a temperature gradient structure with high temperature resistance on the outer surface and no high temperature resistance inside, which is another innovation point of the case. The hypersonic aircraft needs to meet the requirement of high temperature resistance, the upper part of the laminated panel adopts a Ni/Al foil material overlapping mode, the lower part of the laminated panel adopts a Ti/Al foil material overlapping mode, and the middle part of the laminated panel adopts Al foil as a transition material, so that the obtained composite material can well meet the functional requirement.
Step 4, foil compounding and gas bulging forming;
4.1b, placing the stacked foil into a bulging die in a vacuum furnace, wherein the die comprises an upper die 8 and a lower die 9, pressurizing the upper die to enable the upper die to be larger than the bulging pressure, maintaining the pressure of the pressing die until the experiment is finished, further vacuumizing the die, and enabling the vacuum degree to be 1 x 10 -3 And below Pa, after the vacuum pumping is finished, slowly heating the mould to 500 ℃ of 450 plus materials at the heating rate of 10 ℃/min, inflating and loading the mould with the pressure of 5-10MPa after the mould reaches the temperature, and then preserving the heat for 3-5h to ensure that the foil materials can be fully welded.
And 4.2, after the heat preservation is finished, unloading the pressure in the mold to zero, slowly loading the pressure of 1-2MPa in the Ti/Ti foil plate 2 through a vent pipe, and maintaining the pressure for 3-5 hours.
In the case, a method of forming the foil by air inflation during compounding is adopted, and then the NiAl/TiAl layered composite material is formed at high temperature, so that the problem that the NiAl/TiAl material is difficult to deform greatly due to high brittleness is solved well, and the method is another innovation point of the case. At the temperature of 450-550 ℃, no intermetallic compound or a small amount of intermetallic compound is generated between the foils, and at the moment, the whole material has better plasticity performance and is the best time for finishing the bulging of the core plate.
after the pressure maintaining, the temperature in the furnace is continuously raised to 600-650 ℃, the pressure in the Ti/Ti foil plate 2 is kept unchanged, and the heat treatment is carried out for 5-10h at the temperature.
The heat treatment process is to make the foil react fully to generate NiAl 3 And TiAl 3 Intermetallic compound NiAl 3 And TiAl 3 Has high melting point, can effectively avoid the melting of the aluminum foil at the temperature of more than 660 ℃, thus preparing for generating NiAl and TiAl through subsequent high-temperature reaction.
after the low-temperature heat treatment is finished, the temperature in the furnace is continuously increased to 1100-1300 ℃, the pressure in the Ti/Ti foil plate 2 is kept unchanged, and the temperature is kept for 5-10 h.
After the heat preservation is finished, the foils react fully to generate NiAl and TiAl, and finally a three-layer plate hollow rudder wing structure with the NiAl/TiAl laminated composite material is formed.
and cooling the structure along with the furnace, and demolding and taking the workpiece after the structure is cooled to the room temperature.
Finally, the blank pressing part can be cut off by means of wire cutting, and the final multilayer board hollow structural part is obtained.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (8)
1. A method for preparing a hollow structure of a multilayer board containing a layered composite material is characterized by comprising the following steps:
step 1, pre-treating materials;
step 1.1, cutting a foil to obtain a titanium foil (1), a nickel foil (3) and an aluminum foil (4) with preset areas;
step 1.2, cleaning the cut titanium foil (1), nickel foil (3) and aluminum foil (4), removing surface-related oil stains and impurities, drying by cold air, and placing for later use;
step 2, foil plate preforming: two titanium foils (1) are stacked together to form a Ti/Ti foil plate (2) through diffusion connection, and a plurality of air passages are reserved in the Ti/Ti foil plate (2);
step 3, stacking the functional gradients of the foils: firstly, stacking a nickel foil (3), a titanium foil (1) and an aluminum foil (4) according to the design requirements of functional gradient materials to form a composite lower panel (7), a composite core plate (6) and a composite upper panel (5), wherein whether the composite core plate (6) is stacked is determined according to whether the composite core plate (6) is arranged in a forming piece, and then placing a Ti/Ti foil plate (2) at the contact position of the panels; meanwhile, an upper vent pipe is welded at the mouth of each air passage;
step 4, foil compounding and gas bulging forming: putting the stacked foil into an expansion mould in a vacuum furnace, heating and pressurizing, and slowly pressurizing the interior of the Ti/Ti foil plate (2) by introducing air;
and 5, forming a transition intermetallic compound: maintaining the pressure inside and outside the material, heating to 600-650 ℃, and performing low-temperature heat treatment;
step 6, NiAl/TiAl high-temperature reaction synthesis: maintaining the pressure inside and outside the material, heating to 1100-1300 ℃, and carrying out high-temperature heat treatment;
step 7, furnace cooling and sampling: and cooling the structure along with the furnace, and demolding and taking the workpiece after the structure is cooled to the room temperature.
2. The method for preparing a hollow structure of a multi-layer plate comprising a layered composite material according to claim 1, wherein the raw materials used in step 1.1 are pure nickel foil, pure titanium foil and pure aluminum foil respectively, the ratio of the thickness of the foil is titanium foil to aluminum foil to nickel foil =1:1:0.6, and the cutting area of the foil is 200mm x 200 mm.
3. The process for the preparation of the hollow structure of multilayer sheet comprising a laminar composite according to claim 1, characterized in that step 2 is in particular:
2.1, respectively coating a plurality of solder resists on the upper surface and the lower surface of the two layers of titanium foils (1), wherein the solder resists are boron nitride or yttrium oxide; a gap is reserved between two adjacent solder resists, so that a plurality of air passages are formed at the positions of the plurality of solder resists after welding;
2.2, stacking two titanium foils (1) coated with the solder resist;
and 2.3, placing the two superposed titanium foils (1) into a hot-pressing mould in a vacuum diffusion furnace, heating the mould to 880 plus 960 ℃, wherein the heating rate is 10 ℃/min, then loading the mould with the pressure of 1-5MPa, preserving the heat for 0.5-1h, and cooling to obtain the Ti/Ti foil plate (2) through diffusion connection.
4. The method for preparing the hollow structure of the multilayer plate comprising the layered composite material according to claim 1, wherein the low temperature heat treatment time of step 5 is 1 to 10 hours, and the high temperature heat treatment time of step 6 is 1 to 10 hours.
5. The method for producing a multilayer plate hollow structure comprising a laminar composite according to any of claims 1 to 4, wherein, in the processing of a two-layer plate hollow integral wall plate, the steps 3 and 4 are specifically as follows:
step 3, functionally gradient stacking the foils;
step 3.1a, firstly, stacking the nickel foil (3), the titanium foil (1) and the aluminum foil (4) according to the design requirements of functional gradient type materials to form a composite lower panel (7) and a composite upper panel (5);
the composite upper panel and the composite lower panel are divided into an upper half part and a lower half part;
the upper half part of the composite upper panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite upper panel are respectively nickel foil and aluminum foil;
the lower half part of the composite upper panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite upper panel are respectively the titanium foils and the titanium foils;
the upper half part of the composite lower panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite lower panel are respectively aluminum foil and titanium foil;
the lower half part of the composite lower panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite lower panel are respectively made of the aluminum foils and the nickel foils;
step 3.2a, sequentially stacking the composite lower panel (7), the Ti/Ti foil plate (2) and the composite upper panel (5) from bottom to top;
3.3, performing spot welding on the periphery of the stacked foil by using argon arc welding to prevent the foil from being misplaced, and welding an upper vent pipe at the opening of an air passage;
step 4, foil compounding and gas bulging forming;
step 4.1a, placing the stacked foils into an expansion mold in a vacuum furnace, slowly heating the mold, pressurizing an upper mold after the temperature is reached, and then preserving heat to enable the foils to be fully welded;
and 4.2, after the heat preservation is finished, increasing the pressure of the upper die to be larger than the bulging pressure, maintaining the pressure of the upper die until the experiment is finished, and slowly loading pressure into the Ti/Ti foil plate (2) through the vent pipe and maintaining the pressure.
6. The method as claimed in claim 5, wherein the step 4 is carried out under a condition of a hot-pressing composite loading pressure of 3-10MPa, a temperature rise temperature of 450-500 ℃, a temperature rise rate of 10 ℃/min, and a heat preservation time of 1-5h after reaching the temperature; after the heat preservation is finished, the bulging loading pressure is 1-2MPa, and the pressure maintaining time is 1-5 h.
7. The method for preparing a multi-layer plate hollow structure containing a layered composite material according to any one of claims 1 to 4, wherein when the three-layer plate hollow rudder wing is processed, the steps 3 and 4 are specifically as follows:
step 3, functionally gradient stacking the foils;
3.1b, stacking the nickel foil (3), the titanium foil (1) and the aluminum foil (4) according to the design requirements of functional gradient type materials to form a composite lower panel (7), a composite core plate (6) and a composite upper panel (5);
the composite upper panel and the composite lower panel are divided into an upper half part and a lower half part;
the upper half part of the composite upper panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite upper panel are respectively nickel foil and aluminum foil;
the lower half part of the composite upper panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite upper panel are both titanium foils;
the composite core plate comprises titanium foils and aluminum foils which are alternately stacked, and the top layer of the composite core plate is the aluminum foil, and the bottom layer of the composite core plate is the titanium foil;
the upper half part of the composite lower panel comprises titanium foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the upper half part of the composite lower panel are respectively an aluminum foil and a titanium foil;
the lower half part of the composite lower panel comprises nickel foils and aluminum foils which are alternately stacked, and the top layer and the bottom layer of the lower half part of the composite lower panel are respectively an aluminum foil and a nickel foil;
3.2b, sequentially stacking the composite lower panel (7), the first Ti/Ti foil plate (2), the composite core plate (6), the second Ti/Ti foil plate (2) and the composite upper panel (5) from bottom to top;
3.3, performing spot welding on the periphery of the stacked foil by using argon arc welding to prevent the foil from being dislocated, and welding an upper vent pipe at the opening of the air passage;
step 4, foil compounding and gas bulging forming;
step 4.1b, putting the stacked foil into a bulging die in a vacuum furnace, firstly pressurizing an upper die to enable the pressure to be larger than the bulging pressure, maintaining the pressure of a pressing die until the experiment is finished, further vacuumizing the die, slowly heating the die after vacuumizing is finished, inflating and pressurizing after the temperature is reached, and then preserving the heat to enable the foil to be fully welded;
and 4.2, after the heat preservation is finished, discharging the pressure in the die to zero, and slowly pressurizing and maintaining the pressure in the Ti/Ti foil plate (2) through the vent pipe.
8. The process for the preparation of a multilayer sheet hollow structure comprising a layered composite according to claim 7, characterized in that the die vacuum in step 4 is 1X 10 -3 Below Pa, after vacuumizing, firstly heating to 450-500 ℃, wherein the heating rate is 10 ℃/min, after reaching the temperature, loading pressure is 3-10MPa, and then preserving heat for 1-5 h; and after the heat preservation is finished, the loading pressure is 1-2MPa, and the pressure maintaining time is 1-5 h.
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