CN111673377A - Manufacturing process of single-curve aircraft skin - Google Patents
Manufacturing process of single-curve aircraft skin Download PDFInfo
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- CN111673377A CN111673377A CN202010440798.7A CN202010440798A CN111673377A CN 111673377 A CN111673377 A CN 111673377A CN 202010440798 A CN202010440798 A CN 202010440798A CN 111673377 A CN111673377 A CN 111673377A
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- aircraft skin
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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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Abstract
The invention relates to a manufacturing process of a single-curved aircraft skin, which comprises the following steps: the plate is rolled to a preset radian which is consistent with the shape of the skin finished product; flattening the rolled plate, and milling in a flattened state to obtain a skin plate blank; and roll-bending the skin slab to a preset radian to obtain a skin finished product. And finally obtaining a skin finished product by sequentially carrying out the processing steps of roll bending, flattening, milling and roll bending correction on the plate. The conventional equipment that all uses in above each step has reduced equipment cost to panel milling process has certain radian after, only needs to apply less effort and makes it resume to predetermineeing the radian, and the effort of applying can not lead to the fact the harm to panel, and the at utmost has guaranteed the off-the-shelf quality of covering.
Description
Technical Field
The invention relates to the field of aircraft manufacturing, in particular to a manufacturing process of a single-curved aircraft skin.
Background
The airplane skin type part is an important stressed component forming the appearance structure of an airplane, has the shapes of single curvature and double curvature, has the characteristics of large and complex structure, thin wall and easy deformation, has high requirement on shape precision, contains structural characteristics of surfaces, subsidence, through windows, holes and the like, and has the characteristic of unequal thickness of the cross section, thereby having high manufacturing difficulty. The processing method generally adopted by the airplane skin part comprises the following steps: spreading the skin, performing vacuum adsorption, then performing several mills, and then performing shot blasting forming. The method can not finish the processing of the through hole and the through window on the skin part in the process of numerical milling, and needs numerical milling equipment and shot blasting equipment, the process flow is complex, and the shot blasting belongs to a special process, needs to obtain special process quality, and can not ensure the finish requirement of the outer surface of the skin according to the principle of shot blasting forming. Secondly, after the skin is formed, a molded surface tool is adopted for vacuum adsorption, and then the skin is subjected to milling. When the method is adopted to mill the formed skin, each skin part needs to be customized with a corresponding special tool, and a large-scale 5-axis gantry numerical control milling system is needed. Because the skin part is an ultra-large aircraft structural part, the high tooling cost is not suitable for the production requirements of the aircraft skin for small-batch and multiple varieties. The manufacturing process combining chemical milling and digital milling is adopted after the skin is formed, the method considers factors of processing efficiency, processing quality and processing cost, and is widely used for finishing the precise processing of the skin of the airplane, the manufacturing process combining chemical milling and digital milling needs at least twice clamping in the skin processing, the processing problems of complex through windows, sinking and the like are solved through chemical milling, the vacuum skin absorption gantry milling system solves the skin trimming and drilling process, and relates to a plurality of process links such as chemical milling, forming, numerical control processing and the like, the efficiency is lower, the manufacturing process flow combining chemical milling and digital milling is complex, the process coordination is poor, the waste chemical milling liquid pollutes the environment, and the method does not meet the requirement of green manufacturing. And fourthly, a mirror image milling manufacturing process is adopted after the skin is formed, the method needs an expensive special mirror image milling system to process complex subsidence, the equipment investment is large, the manufacturing process development is difficult, the manufacturing efficiency is relatively low, and the method is suitable for manufacturing the skin with small yield.
Due to the shortcomings of the prior art, the aerospace industry has been seeking green, precise skin fabrication techniques that can replace chemical milling.
Disclosure of Invention
In view of the above, there is a need to provide a manufacturing process for a single-curved aircraft skin that can solve at least one of the above problems.
A process for manufacturing a single-curved aircraft skin, comprising:
the plate is rolled to a preset radian which is consistent with the shape of the skin finished product;
flattening the rolled plate, and milling in a flattened state to obtain a skin plate blank;
and roll-bending the skin slab to a preset radian to obtain a skin finished product.
Preferably, the flattening of the sheet comprises:
fixing the first side edge of the plate on the supporting surface;
and gradually pushing and grinding the plate towards the second side edge direction of the plate, so that the plate is flattened on the supporting surface.
Preferably, the first side of the sheet material is secured to the support surface with the outwardly convex side of the sheet material acting as the base surface and facing the support surface.
Preferably, the rolled plate is curled around an axis of the space, and the first side edge and the second side edge are located at the head side and the tail side of the curling respectively.
Preferably, when the plate is pushed and rolled, the side edge of the flattened part is fixed to the support surface by using a clamp.
Preferably, when the plate is pushed and rolled, the flattened part is immediately adsorbed and fixed on the supporting surface in a vacuum adsorption mode.
Preferably, after the plate is completely flattened, the plate is adsorbed and fixed on the supporting surface in a vacuum adsorption mode.
Preferably, the sheet material is pushed and rolled using a follower which is a sliding or rolling fit relative to the sheet material.
Preferably, a protective layer is arranged at the contact part of the heavy pressing part and the plate.
Preferably, a vacuum adsorption tool is used for providing the supporting surface, and the plate and the vacuum adsorption tool are mounted to milling equipment together during milling.
According to the manufacturing process of the single-curved aircraft skin, the finished skin product is finally obtained by sequentially carrying out the processing steps of roll bending, flattening, milling and roll bending correction on the plate. The conventional equipment that all uses in above each step has reduced equipment cost to panel milling process has certain radian after, only needs to apply less effort and makes it resume to predetermineeing the radian, and the effort of applying can not lead to the fact the harm to panel, and the at utmost has guaranteed the off-the-shelf quality of covering.
Drawings
FIG. 1 is a process flow diagram of a process for manufacturing a single curved aircraft skin according to one embodiment;
FIG. 2 is a schematic view of a plate placed on a vacuum adsorption tool in one embodiment;
FIG. 3 is a schematic view of a cut-in angle during milling in one embodiment;
FIG. 4 is a schematic illustration of roll bending correction performed on a skin slab in one embodiment;
the reference numerals in the figures are illustrated as follows:
1. a plate material; 2. vacuum adsorption tooling; 21. a fixture clamping block;
3. a re-pressing member; 4. a lower roll; 5. and (7) an upper roller.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
As shown in fig. 1, the present application provides a process for manufacturing a single-curved aircraft skin, comprising the steps of:
and 300, roll-bending the skin slab to a preset radian to obtain a skin finished product.
In this embodiment, the sheet is first roll bent to achieve the desired curvature. And flattening the plate, keeping the plate in a flattened state by adopting a vacuum adsorption mode, and milling. The sheet material having the elastic properties will return from the flattened state to the bent state after being taken off the machine after the desorption. And correcting the roll bending of the plate to the preset radian to finally obtain a skin finished product because the radian of the plate is possibly inconsistent with the preset radian.
All the steps can be completed by conventional equipment, so that the process difficulty and the equipment cost are reduced. And after milling the panel, because the panel has certain radian, when carrying out the second roll bending, only need less effort just can make the panel resume to predetermineeing the radian, and the effort of applying can not lead to the fact the harm to the panel, and the at utmost has guaranteed the off-the-shelf quality of covering. In step 200, the plate is processed by using a plurality of mills to avoid environmental pollution.
In step 100, a multi-roll bending machine (e.g., a four-roll bending machine) is used to roll bend the sheet in a segmented and progressive manner until the radian of the sheet meets a preset radian. In the process, the roll bending machine is controlled by a numerical control program, a preset radian is input in the roll bending program, and after charging, the roll bending machine automatically finishes the whole roll bending process according to the preset radian.
In the roll bending process, the roll bending machine can be suspended at any time according to requirements, and an inner section template is used for checking whether the radian of the plate reaches a preset radian. After the plate enters the roll bending machine and is about to be separated from the roll bending machine, the distance between rollers of the roll bending machine is considered, allowance is reserved at two ends of the plate along the length direction of the plate, and a hoisting hole is formed in the edge of one end of the plate and used for hoisting and clamping the plate in the subsequent processing process.
In step 200, the method includes two steps of flattening the plate and milling.
In this embodiment, the plate material includes, when flattened: fixing the first side edge of the plate on the supporting surface; and gradually pushing and grinding the plate towards the second side edge direction of the plate, so that the plate is flattened on the supporting surface.
The rolled plate is curled around an axis of the space, and the first side edge and the second side edge are respectively positioned at the head side and the tail side of the curling. In this embodiment, the first side edge and the second side edge are two ends of the plate material in the length direction.
And when the first side edge of the plate is fixed on the supporting surface, the convex side of the plate is used as the bottom surface and faces the supporting surface.
In one embodiment, a vacuum adsorption tool is used for providing a supporting surface, and when the milling process is carried out, the plate and the vacuum adsorption tool are installed on the milling equipment together.
As shown in fig. 2, the sheet material 1 is fixed by a fixture based on one end edge in the length direction, wherein the fixture may be a fixture block 21 disposed on the vacuum adsorption fixture 2. When fixing a position panel 1, for the convenience of fixing and subsequently pressing from both sides tight panel 1 edge, place the protruding one side of 1 radian of panel towards vacuum adsorption frock 1.
When the plate 1 is pushed and rolled, the side edge of the flattened part is fixed on the supporting surface by using a clamp, or the flattened part is immediately adsorbed and fixed on the supporting surface by adopting a vacuum adsorption mode, or the plate is adsorbed and fixed on the supporting surface by adopting a vacuum adsorption mode after being completely flattened.
When flattening is carried out, the plate is pushed and rolled by the heavy pressing piece 3, and the heavy pressing piece 3 is matched with the plate 1 in a sliding or rolling mode.
In this embodiment, the contact part of the heavy pressing member 3 and the plate 1 is provided with a protective layer.
In one embodiment, the sheet 1 is rolled out using a presser 3 which is moved stepwise from the fixed end of the sheet 1 to the other end after one end of the sheet 1 is positioned. The vacuum adsorption tooling 2 positioned at the corresponding positions on the two sides of the width of the plate 1 is also provided with tooling clamping blocks 21, and in the moving process of the heavy pressing piece 3, the tooling clamping blocks 21 are matched to clamp and fix the two side edges of the plate 1 which is already flattened until the whole plate 1 is flattened on the vacuum adsorption tooling.
In order to maintain the flattening part, the top surface of the vacuum adsorption tool 2 is provided with a vacuum adsorption hole, and the bottom surface of the plate 1 is fixed in a vacuum adsorption mode. Vacuum adsorption can be synchronously applied in the process of flattening part, and the vacuum adsorption can be integrally applied after the flattening is completely carried out.
In the process that the heavy pressing piece 3 flattens the top surface of the plate 1, the heavy pressing piece 3 moves towards the other end of the plate at a certain speed, so that the tooling clamping block 21 can be matched with the heavy pressing piece to clamp the plate 1.
Wherein, the length of the heavy pressing piece 3 along the width direction of the plate is adapted to the width of the plate, and the two sides of the plate are reserved with allowance for clamping by the tool clamping blocks.
In one embodiment, as shown in FIG. 2, the weight 3 is a sliding fit on the top surface of the sheet. The heavy pressing piece can adopt a heavy pressing block 3 which is in surface contact with the plate 1, and a nylon block is attached to one side, which is close to the plate 1, of the heavy pressing block 3 so as to prevent the surface of the plate 1 from being scratched in the rolling process.
In one embodiment, the weight 3 is in rolling engagement with the top surface of the sheet 1. The re-pressing member 3 employs a re-pressing bar in line contact with the sheet material 1, and a nylon layer is attached to the outer peripheral wall of the re-pressing bar to prevent scratching of the surface of the sheet material 1 during the flattening process.
The positioning and flattening processes of the plate 1 are completed on a vacuum adsorption tool 2 outside the milling machine tool, and after the plate 1 is flattened, the whole vacuum adsorption tool 2 is transferred to a workbench of the milling machine tool.
After the vacuum adsorption tool is installed on the workbench, the flattening state can be checked again to ensure that the plate 1 is tightly attached and fixed to the vacuum adsorption tool in the flattening state.
Before milling the plate 1, measuring the flatness of the flattened plate 1, and performing regional processing according to different thicknesses and different radians of each region of the formed plate 1.
When the plate 1 is milled, a conventional milling numerical control device (for example, a conventional 3-axis numerical control machine) is adopted.
In the present embodiment, in the milling process of the plate material 1 in the flattened state, in order to reduce the risk of deformation of the plate material 1 after machining, suitable machining parameters, tools, tool paths, and the like are adopted.
In the milling process of the plate material 1, as shown in fig. 3, the angle of the milling lower cutter is less than 3 degrees, wherein the arrow marks the moving direction of the milling cutter to reduce the cutting force, and the machining parameters (for example, 20000rpm) of the high-speed milling are used in combination to reduce the deformation degree of the plate material 1 after the plate material 1 is processed.
When the plate 1 is milled and sunk, the processing mode adopts a layered processing mode, namely, the region needing sinking processing on the plate 1 is processed to the same thickness by one-time cutting, and then the region is cut layer by layer to the next-stage thickness until the sinking thickness meets the preset value.
Each layer is further cut into rough machining and finish machining. And (3) reserving proper thickness allowance on the plate 1 during rough machining, verifying the actual thickness, and then performing finish machining until the subsided thickness meets a preset value.
In step 300, the obtained skin slab will recover to a curved state after being detached from the vacuum adsorption tool, and at this time, some difference exists between the radian and the preset radian. And (4) performing roll bending on the skin slab again to obtain a skin finished product according with the preset radian.
When the second roll bending is carried out, the roll bending equipment (such as a four-roll bending machine) used for the first roll bending can be used, so that the requirement on the equipment is reduced, and the roll bending can be corrected by adopting other roll bending equipment (such as a three-roll bending machine) with smaller action and flexible operation method.
As shown in fig. 4, the skin slab is corrected using a three roll bending machine. In the roll bending process, two lower rollers 4 with the same radius are arranged on the bottom surface of the skin plate blank, one lower roller 4 with the smaller radius is arranged on the top surface of the skin plate blank, the radian convex surface of the skin plate blank faces the lower roller 4, and the concave surface faces the upper roller 5. In the figure, arrows indicate the moving direction of each upper roller and each lower roller, the positions of the two lower rollers 4 are moved along the horizontal and vertical directions of the axes of the lower rollers 4, so that the gap between the two lower rollers 4 corresponds to the position of the skin slab to be corrected, and the upper roller 5 arranged on the top surface moves up and down corresponding to the gap to act on the skin slab with small force, so that the radian of the skin slab at the position is corrected until the radian is in accordance with the preset radian.
Considering the problem that the outer surface of the plate 1 is scratched in the process of roll bending and milling of the plate 1, a plastic protective film with the thickness of not less than 0.3mm and the viscosity of not less than 150cps is attached to the outer surface of the plate 1 so as to ensure the protective effect of the plate 1 in the processes of transportation, roll bending forming and milling. The protective film is removed during the second roll bending.
The manufacturing process of the single-curve aircraft skin is simple and practical in process, and each process does not need to adopt special equipment, so that the equipment requirement is reduced. The method adopts a plurality of milling processes to replace a green manufacturing process of chemical milling, and solves the problem of environmental pollution of skin chemical milling processing. Compared with chemical milling and numerical control mirror milling used in the traditional skin manufacturing scheme, the manufacturing process reduces the fixed investment cost of skin manufacturing (investment of VS chemical milling lines of a conventional 3-axis numerical control machine tool or mirror milling equipment). And no special equipment is invested, so that the equipment requirement for skin processing is reduced.
When the skin is milled, the thickness of the skin and the edge cutting are milled at one time, so that secondary clamping and positioning are avoided, and the high-precision skin edge line profile can be ensured. The machining assembly is relatively simple and easy to manufacture and maintain. The 3-shaft high-speed milling (20000+ rpm) is used for reducing the deformation of the skin workpiece in the processing process, and meanwhile, the numerical control milling has high processing efficiency and is beneficial to mass production.
The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (10)
1. The manufacturing process of the single-curve aircraft skin is characterized by comprising the following steps:
the plate is rolled to a preset radian which is consistent with the shape of the skin finished product;
flattening the rolled plate, and milling in a flattened state to obtain a skin plate blank;
and roll-bending the skin slab to a preset radian to obtain a skin finished product.
2. The process of manufacturing a single curved aircraft skin according to claim 1, wherein flattening the sheet comprises:
fixing the first side edge of the plate on the supporting surface;
and gradually pushing and grinding the plate towards the second side edge direction of the plate, so that the plate is flattened on the supporting surface.
3. The process for manufacturing a single-curve aircraft skin according to claim 2, wherein the first side of the sheet material is fixed to the supporting surface, and the convex side of the sheet material is used as a bottom surface and faces the supporting surface.
4. The process for manufacturing a single-curve aircraft skin according to claim 2, wherein the rolled sheet material is curled about a spatial axis, the first side edge and the second side edge being respectively located at a leading side and a trailing side of the curl.
5. The process for manufacturing a single-curved aircraft skin according to claim 2,
when the plate is pushed and rolled, the side edge of the flattened part is fixed on the supporting surface by using a clamp.
6. The process for manufacturing a single-curved aircraft skin according to claim 2,
when the plate is pushed and rolled, the flattened part is immediately adsorbed and fixed on the supporting surface in a vacuum adsorption mode.
7. The process for manufacturing a single-curved aircraft skin according to claim 2,
and after the plate is completely flattened, the plate is adsorbed and fixed on the supporting surface in a vacuum adsorption mode.
8. The process for manufacturing a single curved aircraft skin according to claim 2, wherein the panel is pushed and rolled using a ram which is a sliding or rolling fit relative to the panel.
9. The process for manufacturing a single curved aircraft skin according to claim 8, wherein a protective layer is provided at a contact portion of the doubler and the plate.
10. The manufacturing process of the single-curved aircraft skin as claimed in claim 2, wherein a vacuum adsorption tool is used for providing the supporting surface, and the plate and the vacuum adsorption tool are installed to milling equipment together during milling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010440798.7A CN111673377A (en) | 2020-05-22 | 2020-05-22 | Manufacturing process of single-curve aircraft skin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010440798.7A CN111673377A (en) | 2020-05-22 | 2020-05-22 | Manufacturing process of single-curve aircraft skin |
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| Publication Number | Publication Date |
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| CN111673377A true CN111673377A (en) | 2020-09-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010440798.7A Withdrawn CN111673377A (en) | 2020-05-22 | 2020-05-22 | Manufacturing process of single-curve aircraft skin |
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| CN (1) | CN111673377A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112792173A (en) * | 2020-12-22 | 2021-05-14 | 江苏博林机械制造有限公司 | Curved surface forming process for aluminum alloy high-strength plate |
| CN115091129A (en) * | 2022-06-22 | 2022-09-23 | 四川航天长征装备制造有限公司 | Roll bending and shape correcting process method for aluminum alloy wall plate |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US5640767A (en) * | 1995-01-03 | 1997-06-24 | Gen Electric | Method for making a double-wall airfoil |
| WO2004039670A2 (en) * | 2002-08-23 | 2004-05-13 | The Boeing Company | Integrally stiffened axial load carrying skin panel for primary aircraft structure and manufacturing method for making the same |
| CN102107346A (en) * | 2010-12-23 | 2011-06-29 | 成都飞机工业（集团）有限责任公司 | Method for forming integral panel of main body |
| CN103639499A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Numerically-controlled skin machining system and method |
| CN103921068A (en) * | 2014-04-04 | 2014-07-16 | 中航沈飞民用飞机有限责任公司 | Single-curvature cover machining method |
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2020
- 2020-05-22 CN CN202010440798.7A patent/CN111673377A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5640767A (en) * | 1995-01-03 | 1997-06-24 | Gen Electric | Method for making a double-wall airfoil |
| WO2004039670A2 (en) * | 2002-08-23 | 2004-05-13 | The Boeing Company | Integrally stiffened axial load carrying skin panel for primary aircraft structure and manufacturing method for making the same |
| CN102107346A (en) * | 2010-12-23 | 2011-06-29 | 成都飞机工业（集团）有限责任公司 | Method for forming integral panel of main body |
| CN103639499A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Numerically-controlled skin machining system and method |
| CN103921068A (en) * | 2014-04-04 | 2014-07-16 | 中航沈飞民用飞机有限责任公司 | Single-curvature cover machining method |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112792173A (en) * | 2020-12-22 | 2021-05-14 | 江苏博林机械制造有限公司 | Curved surface forming process for aluminum alloy high-strength plate |
| CN112792173B (en) * | 2020-12-22 | 2022-10-04 | 江苏博林机械制造有限公司 | Curved surface forming process for aluminum alloy high-strength plate |
| CN115091129A (en) * | 2022-06-22 | 2022-09-23 | 四川航天长征装备制造有限公司 | Roll bending and shape correcting process method for aluminum alloy wall plate |
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Application publication date: 20200918 |