CN116714265A - Edge processing method suitable for large-scale film structure in space - Google Patents
Edge processing method suitable for large-scale film structure in space Download PDFInfo
- Publication number
- CN116714265A CN116714265A CN202311006913.XA CN202311006913A CN116714265A CN 116714265 A CN116714265 A CN 116714265A CN 202311006913 A CN202311006913 A CN 202311006913A CN 116714265 A CN116714265 A CN 116714265A
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- Prior art keywords
- film
- transition
- layer
- edge
- metal layer
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- Pending
Links
- 238000003672 processing method Methods 0.000 title claims description 8
- 230000007704 transition Effects 0.000 claims abstract description 56
- 229910052751 metal Inorganic materials 0.000 claims abstract description 37
- 239000002184 metal Substances 0.000 claims abstract description 37
- 238000000034 method Methods 0.000 claims abstract description 16
- 238000005520 cutting process Methods 0.000 claims abstract description 15
- 238000004080 punching Methods 0.000 claims abstract description 8
- 238000012545 processing Methods 0.000 claims abstract description 7
- 238000005452 bending Methods 0.000 claims description 8
- 239000002313 adhesive film Substances 0.000 claims description 7
- 238000013461 design Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 abstract description 23
- 239000010410 layer Substances 0.000 description 62
- 239000010408 film Substances 0.000 description 58
- 239000002356 single layer Substances 0.000 description 6
- 239000003292 glue Substances 0.000 description 5
- 238000009958 sewing Methods 0.000 description 5
- 239000010409 thin film Substances 0.000 description 5
- 239000004642 Polyimide Substances 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 229920001721 polyimide Polymers 0.000 description 4
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 239000004579 marble Substances 0.000 description 2
- 238000010345 tape casting Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 238000003491 array Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 238000003698 laser cutting Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
- B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
- B29C65/60—Riveting or staking
Abstract
The invention provides a method for processing the edge of a large-scale film structure, which comprises the following steps: s1, cutting a film; s2, paving a transition layer; s3, setting a metal layer; s4, bonding the metal layer; s5, punching and riveting. According to the invention, the adaptability of the flexible material and the rigid material is increased through the transition layer paving, the generation of cracks of a large-scale film structure caused by the film edge cutting process is eliminated, the edge strength is improved, and the uniform stress of the whole molded surface is ensured.
Description
Technical Field
The invention belongs to the field of aerospace, and particularly relates to an edge processing method suitable for a large-scale film structure in space.
Background
With the demands of space remote sensing, high resolution and high precision of communication, the demands of large and light weight are increasing for spacecraft, and more large thin film expandable structures, such as thin film light shields, thin film antennas, thin film solar cell arrays and the like, are applied. The film material is easy to be damaged in the manufacturing process, and particularly, the edge part connected with the rigid mechanism is damaged under the stress condition, so that the manufacturing of the film material is difficult. There is therefore a strong need for edge processing methods for thin film structures.
Disclosure of Invention
In view of the above, the invention aims to provide a method for processing the edges of a large-scale film structure in space, which is used for increasing the adaptability of flexible materials and rigid materials through the laying of a transition layer, eliminating the generation of cracks of the large-scale film structure caused by the cutting process of the edges of the film, improving the edge strength and ensuring the uniform stress of the whole molded surface.
In order to achieve the above purpose, the technical scheme of the invention is realized as follows:
an edge processing method suitable for a large-scale film structure in space comprises the following steps:
s1, cutting a film; drawing and cutting the large film according to a design configuration, and adopting a fillet transition treatment at the bending part;
s2, paving a transition layer; according to the shape of the edge area, paving a transition layer at the edge of the film, wherein the paving process is carried out on a marble table top; the transition layer is a double-sided adhesive film; the transition layer is connected with the edge of the film in a sewing way;
the transition layer is connected with nonmetallic materials of the film by glue, the size of the transition region is different from 10mm to 50mm in width according to the configuration and the material characteristics, for example, when the polyimide single-layer film is drawn, the transition layer with the width of 25mm is paved at the edge. The edge area overbending part of the flexible material is a stress concentration part, double-layer wire adhesive manual sewing in the vertical direction is adopted along the edge of the overbending part, straight line running flat seams are adopted, and all materials are purchased from the market;
s3, setting a metal layer; arranging a metal layer along the outline according to the interface position of the edge area;
the metal layers are arranged along the outline with the width of 10mm-30mm, and the structural rigidity and the interface precision of the metal layers with the width can be well ensured. In order to keep the flexibility of the film structure and the rigidity of the interface, the metal layer adopts aluminum, copper and other alloys with good toughness, and the thickness is generally not more than 2mm;
s4, bonding the metal layer; bonding a metal layer with the transition layer on the upper surface of the film, and bonding a metal layer with the transition layer on the lower surface of the film;
s5, punching and riveting; and fixing and forming the metal layer, the transition layer and the film in a punching and riveting mode.
Furthermore, in the step S1, the radius is transited, the diameter of the radius is not less than 1mm, so that the film is torn due to stress concentration, and the transition radius is cut out by using a sharp cutting tool when the transition radius passes through a bending area.
Further, the width dimension of the transition layer ranges from 10mm to 50mm.
Compared with the prior art, the edge processing method suitable for the large-scale film structure in space has the following advantages:
(1) The invention provides a method for processing the edge of a large-scale film structure, which is suitable for space, and aims to solve the problems that the large-scale film structure is cracked, the edge strength is improved and the stress uniformity of the whole molded surface is ensured due to the fact that the film edge is cut by paving a transition layer to increase the adaptability of flexible materials and rigid materials and ensuring the rigidity of the film structure and the dimensional accuracy of an interface.
(2) The edge treatment method suitable for the large-scale film structure in space, disclosed by the invention, has the advantages that the fillet transition treatment with the diameter not smaller than 1mm is adopted at the large-scale film bending part, the generation of crack sources can be effectively reduced, and the tearing damage of film materials in the manufacturing process is avoided.
(3) According to the edge treatment method suitable for the large-scale film structure in space, the transition layer is paved at the edge, so that the strength and the tearing damage resistance of the flexible material are improved, and the stress of the film structure is homogenized through proper width design of the transition region, so that the formation of buckling is reduced; the transition layer is paved by glue and nonmetallic materials with proper thickness, so that the transition layer has better friction force with the rigid layer in the manufacturing process, is convenient to lay and position and has good adaptability with the rigid material; the double-layer wire tape glue stitching in the vertical direction is adopted on the local stress concentration path with larger stress, and the whole treatment can resist 100N force.
(4) The method is suitable for processing the edge of the large-scale film structure in space, the metal layer is made of aluminum alloy with good toughness, the thickness is not more than 2mm, the method can adapt to plastic deformation of the film configuration process, reliable connection with the transition layer is realized through riveting, the rigidity of the film structure is ensured, and the precision of an external interface is ensured.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a schematic view of a film structure according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a rounded transition according to an embodiment of the present invention;
fig. 3 is a schematic view of sheet metal mounting according to an embodiment of the present invention.
Reference numerals illustrate:
1. a film; 2. a transition layer; 3. a metal layer; 4. and (5) a rivet.
Detailed Description
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art in a specific case.
The invention will be described in detail below with reference to the drawings in connection with embodiments.
The metal layer is a plurality of pairs of metal sheets arranged at the edges of the film and is in a positional relationship with the flexible material as shown in fig. 1 and 2. The transition layer is a reserved part width between the edge of the flexible material and the metal sheet, and the part can be folded to cover the metal sheet and be adhered to the flexible material on the inner side of the metal sheet, and the form is shown in figure 3.
An edge processing method suitable for a large-scale film structure in space comprises the following steps:
s1, cutting a film; drawing and cutting the large film according to a design configuration, and adopting a fillet transition treatment at the bending part;
s2, paving a transition layer; according to the shape of the edge area, paving a transition layer at the edge of the film, wherein the paving process is carried out on a marble table top; the transition layer is a double-sided adhesive film; the transition layer is connected with the edge of the film in a sewing way;
the transition layer is connected with nonmetallic materials of the film by glue, the size of the transition region is different from 10mm to 50mm in width according to the configuration and the material characteristics, for example, when the polyimide single-layer film is drawn, the transition layer with the width of 25mm is paved at the edge. The edge area overbending part of the flexible material is a stress concentration part, double-layer wire adhesive manual sewing in the vertical direction is adopted along the edge of the overbending part, straight line running flat seams are adopted, and all materials are purchased from the market;
s3, setting a metal layer; arranging a metal layer along the outline according to the interface position of the edge area;
the metal layers are arranged along the outline with the width of 10mm-30mm, and the structural rigidity and the interface precision of the metal layers with the width can be well ensured. In order to keep the flexibility of the film structure and the rigidity of the interface, the metal layer adopts aluminum, copper and other alloys with good toughness, and the thickness is generally not more than 2mm;
s4, bonding the metal layer; bonding the metal layer with the transition layer on the upper surface of the film according to the layout, and bonding the metal layer with the transition layer on the lower surface of the film according to the layout;
s5, punching and riveting; and fixing and forming the metal layer, the transition layer and the film in a punching and riveting mode.
Furthermore, in the step S1, the radius is transited, the diameter of the radius is not less than 1mm, so that the film is torn due to stress concentration, and the transition radius is cut out by using a sharp cutting tool when the transition radius passes through a bending area.
The film structure is divided into a single-layer film structure and a multi-layer film structure, and the construction modes of the single-layer film structure and the multi-layer film structure are described as two examples;
example 1: single layer film structure
Step one: drawing the polyimide single-layer film according to a design configuration, wherein the film is easy to tear due to cutting by scissors, cutting by laser is adopted, and a fillet transition with the diameter of 2.5mm is adopted at the bending part.
Step two: according to the shape of the edge area, a transition layer with the width of 25mm is paved at the edge. The transition layer is a double-sided adhesive film, and the width of the adhesive film on the adhesive side of the transition layer is 25mm; the width of the adhesive film on the side bonded with the metal layer is 20mm.
Step three: according to the interface position of the edge area, an aluminum strip with the width of 20mm is adhered to an adhesive film with the width of 20mm along the outline, the whole is formed by hot pressing, and the stress part of the end part is riveted by local punching.
Example 2: multilayer film structure
Step one: drawing the polyimide multilayer film according to the design configuration, cutting by sharp scissors, bending or cutting joint by a punch with the diameter of 4mm, and rounding transition and crack arrest treatment to avoid uneven heating of each layer of film caused by laser cutting.
Step two: according to the shape of the edge area, a transition layer is paved at the edge after double-layer wires in the vertical direction are adopted on the stress concentration path for tape sewing, the transition layer is coated with silica gel in a doctor-blading thickness of 0.1-0.2mm, the doctor-blading width is 30mm, and a glue plate with the width of 30mm is bonded.
Step three: according to the interface position of the edge area, an aluminum strip with the width of 30mm is adhered to a rubber plate with the width of 30mm along the outline, and the metal strip is integrally punched and riveted with the interval of 100 mm.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Claims (4)
1. The edge processing method suitable for the large-scale film structure in space is characterized by comprising the following steps of:
s1, cutting a film; drawing and cutting the large film according to a design configuration, and adopting a fillet transition treatment at the bending part;
s2, paving a transition layer; according to the shape of the edge area, paving transition layers on the upper surface and the lower surface of the edge of the film; the transition layer is a double-sided adhesive film; the transition layer is bonded with the edge of the film;
s3, setting a metal layer; according to the interface position of the edge area, the metal layer is laid out along the outline;
s4, bonding the metal layer; bonding the metal layer and the transition layer on the surface of the film;
s5, punching and riveting; and fixing and forming the metal layer, the transition layer and the film in a punching and riveting mode.
2. The method for processing the edges of the large-scale film structure in space according to claim 1, wherein the method comprises the following steps: and S1, carrying out transition treatment on a round corner, wherein the diameter of the round corner is not less than 1mm.
3. The method for processing the edges of the large-scale film structure in space according to claim 1, wherein the method comprises the following steps: the width dimension of the transition layer ranges from 10mm to 50mm.
4. The method for processing the edges of the large-scale film structure in space according to claim 1, wherein the method comprises the following steps: the width of the metal layer is 10mm-30mm, and the thickness of the metal layer is not more than 2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311006913.XA CN116714265A (en) | 2023-08-11 | 2023-08-11 | Edge processing method suitable for large-scale film structure in space |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311006913.XA CN116714265A (en) | 2023-08-11 | 2023-08-11 | Edge processing method suitable for large-scale film structure in space |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116714265A true CN116714265A (en) | 2023-09-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311006913.XA Pending CN116714265A (en) | 2023-08-11 | 2023-08-11 | Edge processing method suitable for large-scale film structure in space |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9964131B1 (en) * | 2017-04-28 | 2018-05-08 | The Boeing Company | Methods and apparatuses for providing corrosion protection to joined surfaces |
| CN112411999A (en) * | 2020-12-12 | 2021-02-26 | 宝冶(郑州)建筑工程有限公司 | Structure for protecting traditional wood formwork corners and construction method |
| CN214220009U (en) * | 2020-12-31 | 2021-09-17 | 深圳市天盛膜结构有限公司 | Multilayer pressure-resistant ETFE film body |
| CN114290757A (en) * | 2021-12-03 | 2022-04-08 | 夏春燕 | Processing technology of aluminum plastic packaging bag |
| CN114474924A (en) * | 2021-12-20 | 2022-05-13 | 深圳市瑞昌星科技有限公司 | High-temperature-resistant polymer-coated release film and manufacturing method thereof |
-
2023
- 2023-08-11 CN CN202311006913.XA patent/CN116714265A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9964131B1 (en) * | 2017-04-28 | 2018-05-08 | The Boeing Company | Methods and apparatuses for providing corrosion protection to joined surfaces |
| CN112411999A (en) * | 2020-12-12 | 2021-02-26 | 宝冶(郑州)建筑工程有限公司 | Structure for protecting traditional wood formwork corners and construction method |
| CN214220009U (en) * | 2020-12-31 | 2021-09-17 | 深圳市天盛膜结构有限公司 | Multilayer pressure-resistant ETFE film body |
| CN114290757A (en) * | 2021-12-03 | 2022-04-08 | 夏春燕 | Processing technology of aluminum plastic packaging bag |
| CN114474924A (en) * | 2021-12-20 | 2022-05-13 | 深圳市瑞昌星科技有限公司 | High-temperature-resistant polymer-coated release film and manufacturing method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 双元制培训机械专业理论教材编委会: "《机械工人专业工艺---工模具制造工分册》", 机械工业出版社, pages: 6 * |
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