CN115156849A - Integrated manufacturing method for metal skin and opening frame structure of airplane - Google Patents
Integrated manufacturing method for metal skin and opening frame structure of airplane Download PDFInfo
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- CN115156849A CN115156849A CN202210801214.3A CN202210801214A CN115156849A CN 115156849 A CN115156849 A CN 115156849A CN 202210801214 A CN202210801214 A CN 202210801214A CN 115156849 A CN115156849 A CN 115156849A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
An integrated manufacturing method of an airplane metal skin and a mouth frame structure belongs to the technical field of metal material machining. According to the method, due to the good diffusion connection effect, the two layers of materials are connected to form an integral material with the overlapped thickness, and under the condition that the same connection strength is required, the large-area connection mode can reduce the overlapping area of the inner layer opening frame and the outer layer skin, so that the size of the outline of the inner layer opening frame of the opening frame blank can be reduced or the integral material selection thickness can be reduced, and the total weight reduction effect of the machine body structure is realized. Compared with the traditional convex-concave die coupling forming structure, the pressure-tight die coupling forming structure has no convex-concave die pressure occlusion contact friction process, the flowing friction force is smaller during material forming, and no loss is caused to a tooling concave die, so that the size characteristic formed by the rigid die is stable, and the batch forming processing is favorably realized.
Description
Technical Field
The invention relates to an integrated connection method for metal plates, belongs to the technical field of metal material machining, and particularly relates to the technical field of metal material plastic forming.
Background
The outer surface profile of the airplane needs to be manufactured through an airframe structure to ensure smooth appearance and form a smooth continuous curved surface aerodynamic appearance. The organism surface will generally arrange the flap that various shapes are different for daily maintenance, maintenance etc. of inside functional unit, and the basic function of structure is: the open state can expose the internal structure, and can allow tools, spare parts and other objects to enter, and after the use of the given function is completed, the cover can be restored to the original position, installed and fixed again.
In order to meet the requirements of pneumatic design and daily internal overhaul and maintenance, the covering cover needs to sink into the covering depth to reduce the protruding amount of the edge of the covering cover, so that the covering cover at the position for installing the covering cover needs to have the sinking depth or an embedded opening frame structure, and the covering cover is combined with the covering cover through a connecting technology to form the appearance of a complete airplane.
Taking the third-generation fighter body structure as an example, the most common installation mode of a metal covering cover is screw connection, the corresponding position of the covering cover is directly formed with a sinking characteristic, a solid hole is cut off by equidistant deviation of 25-35 mm in the sinking contour, the contour of the covering cover is the sinking contour, a lap joint structure is formed by a 25-35 mm sheet material in the sinking contour and the covering cover, a supporting plate nut is riveted and installed in the sheet material of the covering cover, and single-row or staggered double-row bolt pieces are adopted for connection.
The structure is simple, easy and mature, can meet the use requirement of a small maintenance window, but is influenced by the structure bearing capacity, the size of the window cannot be overlarge, the edge of a skin cantilever cannot bear the load of a large-scale cover, and the whole structure is poor in sealing performance. Meanwhile, the sinking of the surface of the skin and the forming of the skin are required to be simultaneously carried out, the forming difficulty of the skin is increased due to the limited stamping direction of the skin, and the centering of a window structure is required to be considered during the skin contour segmentation design, so that the forming difficulty is reduced, and the aircraft with complex aerodynamic shapes is high in constraint. When the skin opening frame is connected by using the rivet standard component, holes need to be made in advance, structural damage is actually formed, and the skin and the opening frame are connected with technical limits particularly at the position of a complex curved surface.
The traditional structure is difficult to meet the requirement of high quality of the surface of a novel fighter plane body, and other innovative connection process means need to be explored.
Disclosure of Invention
In order to overcome the technical problems, the invention provides a novel process method, which utilizes superplastic forming/diffusion connection and a numerical control milling process method to realize physical connection between two parts of a metal skin and a metal opening frame, replaces spot connection structures such as riveting, spot welding and the like, and forms a large-area high-rigidity integral structure. The mouth frame is manufactured with sinking and flanging characteristics by adopting a superplastic forming process, so that the forming effect and the forming limit are improved, a sealing rubber pad is added between the mouth cover and a sinking area interlayer of the mouth frame, and the sealing waterproof effect is improved.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
1. the superplastic forming/diffusion bonding process is utilized to replace the existing riveting and spot welding connection mode, as shown in figure 1, in one processing process, the connection between the inner layer opening frame and the outer layer skin is realized, and simultaneously, the sinking and flanging structure of the opening frame is formed, so that the local point connection form of the inner layer opening frame and the outer layer skin can be avoided, the secondary assembly positioning error is avoided, and the coordination size precision of the inner contour of the skin window and the sinking contour of the opening frame is high;
2. as shown in fig. 2, by means of the upper die 3 and the lower die 4, diffusion connection is realized by using air pressure, the contact areas on the surfaces of the metal materials are in full-profile connection, the effective physical connection area can reach more than 95%, the connection method is completely superior to a point connection mode of a riveting or spot welding type, the risks of hole site deviation, nail head defects and the like caused by manufacturing of a bottom hole of a standard part in a riveting process and the risks of defects of splashing inside of an interlayer, too deep indentation on the outer surface and the like generated by a spot welding process can be avoided, the surface of the connection area is smooth, no structural quality loss exists, the connection effect is firm, and the rigidity of the whole structure is enhanced after the connection area is connected with a skin structure into a whole;
3. firstly, a diffusion connection process is used for carrying out an integrated manufacturing process of a skin and a mouth frame, namely, a method that mutually contact surfaces form metallurgical connection through interatomic solid state diffusion under the condition that the pressure which is not enough to cause plastic deformation and the temperature which is lower than the melting point of a connected workpiece is utilized, as shown in figure 1, an upper die 3 and a lower die 4 are connected in a matched mode through a guide pillar to compress blanks, the upper die 3 is a basic plane, the lower die 4 is a process auxiliary cavity, the skin blank 1 and the mouth frame blank 2 are both plates, high-pressure inert gas is filled into a lower die cavity of a lower die air passage B in a high-temperature state to form uniform pressure, and the skin blank 1 and the mouth frame blank 2 are connected in a diffusion mode;
4. as shown in fig. 3, by utilizing the characteristic of high forming limit of the metal plate under the condition of air expansion and superplastic, the characteristic of larger flanging height can be obtained, so that the rigidity of the opening frame is improved to a certain extent; meanwhile, the metal material of the part can flow freely in a superplastic state and almost can be formed into any shape, so that the inner-layer opening frame can be formed into complex characteristics such as sawtooth sinking, curve profile flanging and the like at one time, the lower die 4 is not worn in the die attaching process of the inflatable material, the part with uniform pressure is formed into stable size, and the part is very suitable for the assembly structure of the opening cover and the opening frame with the characteristic of the sinking profile being a sawtooth stealth structure;
5. after the diffusion connection is completed, the skin blank 1 and the mouth frame blank 2 form a skin mouth frame integral blank 5, and then the sinking and flanging characteristics of the mouth frame blank are manufactured by using a superplastic forming process, as shown in fig. 2, a welding stopping agent with a corresponding area is coated in the middle of an interlayer of skin and mouth frame raw materials, so that the surface of a metal plate in a high-temperature state is not welded and layered, high-pressure gas is filled into the interlayer through a gas path, the skin is continuously attached to an upper die 3 under the action of air pressure, the mouth frame material is thinned and attached to a concave die cavity of a lower die 4, a gas outlet B with the diameter of phi 2 mm is designed at the bottom of the cavity and used for discharging gas in the cavity, and the shape of the concave die cavity of the lower die 4 is finally formed, so that the sinking and flanging characteristics are obtained;
6. because the metal superplastic forming process and the diffusion bonding process have forming temperature overlapping intervals, the skin opening frame integrated structure can be simultaneously processed in a thermal cycle process; meanwhile, metal is formed under the high-temperature state of the superplastic forming/diffusion bonding process, the material has very high plasticity, very low deformation resistance and almost no static storage effect of resilience and dynamic strain, so that the characteristics of high precision, good performance and surface quality can be formed in one thermal cycle, the manufacturing precision of the sinking depth dimension of the mouth frame and the flanging aperture dimension is controllable, and the metal can be processed in steps by using the same upper die 3 and the same lower die 4 as shown in figures 2 and 3;
7. as shown in fig. 2, a fixed area between two layers of plate materials is coated with a solder-stopping agent, a diffusion area and a superplastic area are distinguished by controlling the solder-stopping agent coating area, a mouth frame blank 2 sinks and a flanging part needs to be layered to form a cavity, the solder-stopping agent needs to be coated correspondingly in the projection area of a skin blank 1, and meanwhile, the solder-stopping agent is also coated on the joint surfaces of the blank and an upper die and a lower die; the coating area S is calculated as follows:
S＝S 0 +L 0 ×B(1)
wherein S 0 Is the original projected area, L 0 Is S 0 Area perimeter of (d); b is an outward expansion distance of the contour edge method, and is generally 3-6 mm;
8. in order to realize that the inner cavities of the skin woolen 1 and the mouth frame woolen 2 are communicated with the outside, a vent groove is designed between the interlayers, a milling mode is adopted, the depth is not more than 0.2 mm, the width is not more than 2 mm, and then a solder stop agent is coated on the surface of the air passage, so that the phenomenon that diffusion connection welding is not conducted is avoided, and argon blowing and extraction exchange can be conducted in one technological process by utilizing the communication characteristic of the air passage; as shown in the gas circuit parameter table of fig. 8, in the manufacturing process, firstly, the air in the interlayer is exhausted by vacuumizing through the double-layer wool inner gas circuit a by using negative pressure, high-pressure gas is introduced into the lower die 4 for diffusion connection, then, the high-pressure gas is introduced into the interlayer through the double-layer wool inner gas circuit a, a cavity is formed by superplastic forming, and after the temperature is raised once, the temperature is lowered after 2 steps of process processing are sequentially carried out;
9. as shown in fig. 4, 5 and 6, after the skin and the opening frame are formed into the integral rough material 5 of the skin opening frame, firstly, the opening cover 6 is milled and removed, namely, the opening is formed on the skin, a window is obtained, the rough material is turned over, then, the rough material 2 of the opening frame is removed by using a machine milling mode to form the bottom of a convex hull, the height dimension of a turned edge is obtained, finally, the material with the thickness of 8 of the periphery of the opening frame is milled and removed, the outline size of the outer edge of the opening frame is processed, and the integral structure of the skin opening frame is obtained after the completion;
the invention has the beneficial effects that: through using this novel technique, can realize covering mouthful frame structure integration manufacturing, compare riveting, spot welding connected mode, can promote the connection effect by a wide margin, whole bearing capacity is strong. Because the diffusion connection effect is good, the two layers of materials are connected to form an integral material with overlapped thickness, and under the condition of requiring the same connection strength, the large-area connection mode can reduce the overlapping area of the inner layer opening frame and the outer layer skin, so that the inner layer opening frame of the opening frame blank 2 can reduce the outline size or reduce the whole material selection thickness, and the total weight reduction effect of the body structure is realized. Compared with the traditional convex-concave die coupling forming structure, the pressure-tight die coupling forming structure has no convex-concave die pressure occlusion contact friction process, the flowing friction force is smaller during material forming, and no loss is caused to a tooling concave die, so that the size characteristic formed by the rigid die is stable, and the batch forming processing is favorably realized. The superplastic forming/diffusion connection integrated manufacturing improves the mechanical property and fatigue property of the structure, is beneficial to realizing the processing of the window type with large curvature and special-shaped outline, is suitable for the characteristic processing of the window with complex outline, is easy to seal the structure of the whole cover, has small limitation on the manufacturing process of the structural design of the airplane, and is easy to popularize and use similar structures.
Drawings
FIG. 1: integrated structural schematic diagram of typical sawtooth profile skin opening frame
FIG. 2: schematic diagram for diffusion connection processing of metal skin and mouth frame blank
FIG. 3: metal covering and mouth frame wool superplastic forming processing schematic diagram
FIG. 4: schematic view of opening processing of metal skin
FIG. 5 is a schematic view of: schematic view of opening processing of metal opening frame
FIG. 6: schematic diagram for removing redundant materials around mouth frame
FIG. 7: integrated structure schematic diagram of metal skin and opening frame
FIG. 8: gas path parameter diagram of forming process
Wherein: the device comprises a skin rough material 1, a mouth frame rough material 2, an upper die 3, a lower die 4, a skin mouth frame integral rough material 5, a mouth cover 6, a base 7, a mouth frame circumference thickness 8, an internal gas circuit of A double-layer rough material, a lower die gas circuit B and an upper die gas circuit C.
Detailed Description
1. Designing a welding flux stopping coating area graph aiming at a non-welding area of the skin rough material 1 and the mouth frame rough material 2, carrying out curved surface expansion on the welding flux stopping coating area graph by normal projection to the surface of the skin according to a formula (1) and the maximum edge of a mouth frame sunken area, and finally obtaining a plane graph of the welding flux stopping coating area, wherein the welding flux stopping coating area graph is shown as a thickened black line in a double-layer interlayer in fig. 2, and simultaneously projecting and expanding the outer edge outlines of the skin rough material 1 and the mouth frame rough material 2 to obtain a rough material blanking graph; the upper die 3 needs to be provided with an air passage C, and the lower die 4 needs to be provided with an air passage B;
S＝S 0 +L 0 ×B(1)
wherein S 0 Is the original projected area, L 0 Is S 0 Area perimeter of (d); and B is the outward expansion distance of the contour edge method.
2. Manufacturing a coating sample plate according to the obtained plane graph of the welding stopping agent coating area, and designing a corresponding double-layer blank internal gas circuit A on the coating sample plate; the coating sample plate and the lower die 4 form a positioning relation by the shape edge, so that the coating area is aligned and coordinated with the profile of the female die cavity conveniently;
3. the method comprises the steps of carrying out laser cutting blanking on a skin blank 1 and a mouth frame blank 2, positioning a welding stopping agent coating sample plate and the outline outside the skin blank 1, carving a closed area line on the surface of one side, needing to be connected, of the skin blank 1 according to the coating sample plate, showing a welding stopping agent coating area, and drawing a double-layer blank internal air path A, wherein the length of an air path of the double-layer blank internal air path A is from the edge of the maximum outline of the skin blank 1 to the inside of the outline of the coating area, so that an internal and external communicated air path is formed;
4. positioning a welding stopping agent coating sample plate and the outline or positioning hole outside the mouth frame blank 2, and engraving a double-layer blank internal gas path A route on the surface of one side, needing to be connected, of the mouth frame blank 2 according to the coating sample plate, wherein the position and the length of a gas path of the double-layer blank internal gas path A correspond to those of the skin blank 1;
5. the skin woolen 1 and the mouth frame woolen 2 are respectively milled and processed into an internal air path A of the double-layer woolen, the depth of a single-piece groove of the skin woolen 1 and the mouth frame woolen 2 is not more than 0.2 mm, and the width of the single-piece groove is not more than 2 mm, so that an air passage is formed in the middle of an interlayer after the skin woolen 1 and the mouth frame woolen 2 are jointed;
6. carrying out surface oil removal and acid cleaning on the skin blank 1 and the mouth frame blank 2 which are milled, removing surface impurities, dirt and the like, avoiding influencing the welding rate, and preparing before forming;
7. placing the skin blank 1 and the mouth frame blank 2 on a platform with the marking surfaces facing upwards, coating a solder-stopping agent in the largest marking area, coating the solder-stopping agent at the position corresponding to the air path A in the double-layer blank, after the solder-stopping agent coating is dried, positioning the skin blank 1 and the mouth frame blank 2 according to the shape and aligning the ventilating notches of the air path A in the double-layer blank, and fixing and clamping by using a clamp or other tools;
8. sealing and welding the peripheries of the fixed outer skin blank 1 and the inner layer opening frame blank 2 by using a manual argon arc welding process, welding a ventilating titanium pipe at the notch position of an inner gas path A of the double-layer blank, communicating with the inner gas path, and polishing and flattening redundant welding beading and surface oxidation color after welding;
9. welding a blank pocket formed by the skin blank 1 and the mouth frame blank 2, then performing gas tightness inspection, filling high-pressure gas into a titanium pipe to perform tightness inspection, and determining that all welding parts are airtight by using a surface-sprayed foam observation method;
10. coating a welding stopping agent on two sides of a blank pocket formed by welding and sealing the skin blank 1 and the opening frame blank 2, and coating the welding stopping agent on the lower molded surface of the upper die 3 and the upper molded surface of the lower die 4;
11. sleeving the sealed skin wool 1 and the mouth frame wool 2 into guide posts of a superplastic forming die according to positioning holes, closing the upper die 3 and the lower die 4 according to the guide posts, sending the die into a superplastic forming machine after the completion of the assembly, communicating all pipelines with corresponding pipelines of equipment, introducing high-pressure gas to carry out airtight inspection on connecting parts, and confirming that all pipelines have no gas leakage phenomenon;
12. pressurizing and heating the equipment, as shown in a parameter curve shown in fig. 8, introducing protective argon gas P1 into an upper die 3 through an upper die gas path C, introducing protective argon gas P2 into a lower die 4 through a lower die gas path B, vacuumizing a wool sealing pocket through a double-layer wool internal gas path A to remove internal air, so that the whole wool is in an argon protection atmosphere, when the superplastic forming die reaches a superplastic forming/diffusion connection temperature (titanium alloy 890-920 ℃), firstly starting diffusion connection, and introducing high-pressure argon gas P4 into the lower die 4, so that the mouth frame wool 2 is attached to the upper die 3 on the outer-layer skin wool 1 to form atomic diffusion connection;
13. as shown in fig. 8, after the diffusion connection is completed, the mouth frame superplastic forming process is performed, the blank pocket is vacuumized and stopped, the lower die 4 cuts off high-pressure gas, the high-pressure gas P3 is gradually introduced into the blank pocket of the gas path a in the double-layer blank, and the blank pocket is superplastically formed by virtue of gas pressure, so that the cavity of the female die of the lower die 4 is gradually filled, and complete sinking and flanging are formed, thereby obtaining the skin mouth frame integral blank 5;
14. after the superplastic forming/diffusion connection is finished, the whole body is cooled along with a furnace, protective pressure argon is introduced into an upper die air path C of an upper die 3, a lower die air path B of a lower die 4 and a double-layer blank internal air path A, a final workpiece is kept, and the die temperature is up to about 500 ℃ so as to open a die and take the workpiece;
15. cleaning a surface welding stopping agent of the skin opening frame overall blank 5 after taking a workpiece, and carrying out ultrasonic internal defect detection on the annular connecting part of the outer-layer skin blank 1 and the inner-layer opening frame blank 2;
16. as shown in fig. 4, an opening is milled on the surface of the skin blank 1, and the redundant flap 6 is removed;
17. as shown in fig. 5, milling the flanging height at the flanging position of the mouth frame blank 2, and removing the base 7;
18. as shown in fig. 6, the thickness 8 of the periphery of the opening frame is removed by milling, and the profile characteristics of the local opening frame are obtained;
19. and as shown in fig. 7, after milling, obtaining the skin and frame integrated structural member.
Claims (1)
1. The integrated manufacturing method of the metal skin and the opening frame structure of the airplane is characterized by comprising the following steps:
1) Designing a welding flux stopping coating area graph aiming at a non-welding area of a skin blank (1) and a mouth frame blank (2), projecting the welding flux stopping coating area graph to the normal direction of the surface of the skin according to a formula (1) and the maximum edge of a mouth frame sunken area, unfolding a curved surface to finally obtain a plane graph of the welding flux stopping coating area, and projecting and unfolding the outer edge profiles of the skin blank (1) and the mouth frame blank (2) to obtain a blank blanking graph; the upper die (3) needs to be provided with an air passage (C), and the lower die (4) needs to be provided with an air passage (B);
S＝S 0 +L 0 ×B (1)
wherein S 0 Is the original projected area, L 0 Is S 0 Area perimeter of (d); b is the outward expansion distance of the contour edge method;
2) Manufacturing a coating sample plate according to the obtained plane graph of the welding stopping agent coating area, and designing a corresponding double-layer blank internal gas circuit (A) on the coating sample plate; the outer shape edge of the coating sample plate and the lower die (4) form a positioning relation, so that the coating area and the outline of the female die cavity are aligned and coordinated conveniently;
3) The method comprises the steps that laser cutting blanking is conducted on skin rough materials (1) and mouth frame rough materials (2), a welding flux stopping coating sample plate and the outline outside the skin rough materials (1) are located, a closed area line is carved on the surface of one side, needing to be connected, of the skin rough materials (1) according to the coating sample plate, a welding flux stopping coating area is shown, an internal gas circuit (A) of a double-layer rough material is drawn, the length of a gas channel of the internal gas circuit (A) of the double-layer rough material is from the edge of the maximum outline of the skin rough materials (1) to the outline of the coating area, and an internal and external communicated gas circuit is formed;
4) Positioning a welding stopping agent coating sample plate and the outline or a positioning hole outside the mouth frame blank (2), and engraving a double-layer blank internal gas path (A) route on the surface of one side, needing to be connected, of the mouth frame blank (2) according to the coating sample plate, wherein the position and the length of a gas path of the double-layer blank internal gas path (A) correspond to those of the skin blank (1);
5) The skin woolen (1) and the mouth frame woolen (2) are milled and processed into an internal air passage (A) of the double-layer woolen respectively, the depth of a single groove of the skin woolen (1) and the mouth frame woolen (2) is not more than 0.2 mm, and the width of the single groove is not more than 2 mm, so that an air passage is formed in the middle of an interlayer after the skin woolen (1) and the mouth frame woolen (2) are attached;
6) Performing surface oil removal and acid cleaning on the milled skin blank (1) and the milled opening frame blank (2), removing surface impurities, dirt and the like, avoiding influencing the welding rate, and preparing before forming;
7) Placing the skin rough material (1) and the mouth frame rough material (2) on a platform with the marking surfaces facing upwards, coating a solder stopping agent in the largest marking area, coating the solder stopping agent at the position corresponding to the air passage (A) in the double-layer rough material, after the solder stopping agent coating is dried, positioning the skin rough material (1) and the mouth frame rough material (2) according to the appearance and aligning the ventilating notches of the air passage (A) in the double-layer rough material, and fixing and clamping the skin rough material and the mouth frame rough material by using a clamp or other tools;
8) Sealing and welding the peripheries of the fixed outer skin blank (1) and the inner layer opening frame blank (2) by using a manual argon arc welding process, welding a ventilating titanium pipe at the notch position of an inner air path (A) of the double-layer blank, communicating with the inner air path, and polishing and flattening redundant welding beading and surface oxidation color after welding;
9) After a blank pocket formed by the skin blank (1) and the mouth frame blank (2) is welded, carrying out gas tightness inspection, carrying out tightness inspection by filling high-pressure gas into a titanium pipe, and confirming that all welding parts are airtight by using a surface foam spraying observation method;
10 Coating a welding stopping agent on two sides of a blank pocket formed by welding and sealing the skin blank (1) and the opening frame blank (2), and coating the welding stopping agent on the lower molded surface of the upper die (3) and the upper molded surface of the lower die (4) at the same time;
11 Sleeving the sealed skin wool (1) and the mouth frame wool (2) into guide posts of a superplastic forming die according to positioning holes, closing the upper die (3) and the lower die (4) according to the guide posts, sending the die into the superplastic forming machine after the completion of the die closing, communicating all pipelines with corresponding pipelines of equipment, introducing high-pressure gas to carry out airtight inspection on connecting parts, and confirming that all pipelines have no gas leakage phenomenon;
12 Pressurizing and heating the equipment, introducing protective argon into an upper die (3) through an upper die gas circuit (C), introducing protective argon into a lower die (4) through a lower die gas circuit (B), vacuumizing a wool sealing pocket through a double-layer wool internal gas circuit (A) to remove internal air, so that the whole wool is in an argon protective atmosphere, when the superplastic forming die reaches the superplastic forming/diffusion connection temperature, firstly starting diffusion connection, introducing high-pressure argon into the lower die (4), and enabling the mouth frame wool (2) to be attached to the upper die (3) and attached to the outer skin wool (1) to form atomic diffusion connection;
13 After the diffusion connection is finished, performing an opening frame superplastic forming process, stopping vacuumizing a blank pocket, cutting off high-pressure gas by the lower die (4), gradually introducing the high-pressure gas into the blank pocket of the internal gas path (A) of the double-layer blank, and gradually filling the cavity of the female die of the lower die (4) by virtue of gas pressure superplastic forming to form complete sinking and flanging to obtain the integral blank (5) of the covering opening frame;
14 Cooling the whole body along with a furnace after the superplastic forming/diffusion connection is finished, introducing protective pressure argon into an upper die air passage (C) of an upper die (3), a lower die air passage (B) of a lower die (4) and a double-layer wool inner air passage (A), and keeping until a finished product is obtained;
15 Cleaning the surface of the integral rough material (5) of the skin opening frame after taking the workpiece, and carrying out ultrasonic internal defect detection on the annular connecting part of the outer-layer skin rough material (1) and the inner-layer opening frame rough material (2);
16 Milling an opening on the surface of the skin blank (1) and removing the redundant covering cover (6);
17 Milling the flanging height at the flanging position of the mouth frame blank (2), and removing the base (7);
18 Milling to remove the thickness (8) of the periphery of the opening frame to obtain the profile characteristics of the local opening frame;
19 Milling to obtain the integral structural member of the skin and the opening frame.
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|---|---|---|---|---|
| US20010038057A1 (en) * | 1999-05-31 | 2001-11-08 | Frank Palm | Stressed-skin component made of metal |
| CN106271439A (en) * | 2016-08-30 | 2017-01-04 | 北京普惠三航科技有限公司 | The superplastic forming of the heat-resisting eyelid covering of titanium alloy/diffusion joint forming method |
| CN114273854A (en) * | 2020-10-30 | 2022-04-05 | 哈尔滨哈飞航空工业有限责任公司 | Method for forming special-shaped opening frame skin reinforcement part |
| CN112588956A (en) * | 2020-12-14 | 2021-04-02 | 江西洪都航空工业集团有限责任公司 | Method for forming double-curved-surface skin opening frame |
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