CN116818446A - Aviation filler compression test piece preparation method, defoaming and sinking die tool - Google Patents
Aviation filler compression test piece preparation method, defoaming and sinking die tool Download PDFInfo
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- CN116818446A CN116818446A CN202310437231.8A CN202310437231A CN116818446A CN 116818446 A CN116818446 A CN 116818446A CN 202310437231 A CN202310437231 A CN 202310437231A CN 116818446 A CN116818446 A CN 116818446A
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- tool
- test piece
- aviation
- defoaming
- filler
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- 239000000945 filler Substances 0.000 title claims abstract description 56
- 238000012669 compression test Methods 0.000 title claims abstract description 32
- 238000002360 preparation method Methods 0.000 title claims abstract description 13
- 238000000034 method Methods 0.000 claims abstract description 33
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 27
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 27
- 239000000203 mixture Substances 0.000 claims abstract description 25
- 238000012360 testing method Methods 0.000 claims abstract description 22
- 239000000853 adhesive Substances 0.000 claims abstract description 17
- 230000001070 adhesive effect Effects 0.000 claims abstract description 17
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 16
- 239000004005 microsphere Substances 0.000 claims abstract description 16
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims abstract description 16
- 238000012856 packing Methods 0.000 claims abstract description 10
- 238000002156 mixing Methods 0.000 claims abstract description 9
- 238000005303 weighing Methods 0.000 claims abstract description 7
- 238000004519 manufacturing process Methods 0.000 claims abstract description 5
- 238000005498 polishing Methods 0.000 claims abstract description 5
- 239000004744 fabric Substances 0.000 claims description 4
- 239000006082 mold release agent Substances 0.000 claims description 4
- 238000003756 stirring Methods 0.000 claims description 4
- 238000005516 engineering process Methods 0.000 abstract description 4
- 239000002131 composite material Substances 0.000 abstract description 3
- 238000005266 casting Methods 0.000 description 4
- 238000003754 machining Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000008034 disappearance Effects 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Abstract
The invention belongs to the manufacturing technology of aviation composite materials, and relates to a preparation method of an aviation filler compression test piece, a defoaming and sinking die tool, wherein the method comprises the following steps: 1) Weighing the adhesive, the curing agent and the hollow phenolic microspheres according to a certain proportion, and mixing and preparing in a container; 2) Pouring the prepared filler into a defoaming tool, and placing the tool into a vacuum oven for vacuum defoaming; 3) Pouring the mixture subjected to vacuum defoamation into a sinking die tool; 4) Putting the aluminum tubular mould treated by the release agent into a sinking mould tool, so that the aluminum tubular mould slowly sinks into the mixture, and the mixture completely penetrates through the aluminum tubular mould; 5) Placing the sinking die tool which is sunk into the aluminum tubular die into room temperature for curing or curing in an oven to obtain an aviation filler compression test piece; 6) Ejecting the aviation packing compression test piece from the die, and polishing the top of the test piece until the top of the test piece is flat.
Description
Technical Field
The invention belongs to the manufacturing technology of aviation composite materials, and relates to a preparation method of an aviation filler compression test piece, a defoaming and sinking die tool.
Background
The aviation No. 16 and No. 17 fillers are prepared by blending a normal-temperature curing adhesive and hollow phenolic microspheres according to a certain proportion, are mainly applied to edge sealing and splicing of a composite honeycomb sandwich structure and peripheral filling of an inlay piece, and have obvious weight reduction benefit compared with the use of a pure adhesive. Aviation fillers (adhesives and hollow phenolic microspheres) adopted by the current helicopter model are all imported. In model batches, the quality of the filler is generally ensured by controlling the compressive strength of the mixed filler after curing. The current type of filler compression strength test piece is generally prepared by the following 2 methods: 1) After the adhesive and the hollow phenolic microspheres are mixed according to the proportion, the bubbles are punctured by metal needles, and after the surface is free of bubbles, the adhesive and the hollow phenolic microspheres are integrally cured in a tool, and after the adhesive and the hollow phenolic microspheres are cured, machining is performed according to the size of a test piece; 2) And (3) after the adhesive and the hollow phenolic microspheres are mixed according to the proportion, the air bubbles are punctured by metal needles, after no air bubbles exist on the surface, the air bubbles are cast into a test piece tool with a determined size, and after solidification, demoulding is carried out.
Both methods have certain problems; 1) After the adhesive and the hollow phenolic microspheres are blended according to a certain proportion, the effect of puncturing the surface bubbles by the metal needle-shaped objects is poor, and time and labor are wasted; 2) Machining after the whole solidification, wherein extra defects possibly are introduced in the machining process due to factors such as vibration, machining precision and the like, and the performance of the material cannot be accurately represented; 3) The quality of the test piece is influenced by the fact that bubbles are easily wrapped in the process of casting the prepared mixture into the tool.
Disclosure of Invention
Object of the Invention
The invention provides a preparation method of an aviation filler compression test piece, a defoaming and sinking die tool, wherein the vacuum defoaming is adopted to greatly reduce the internal bubbles of the blended filler, and the die is adopted to sink into the blended filler, so that the bubbles possibly wrapped in the casting process are avoided. The application of the preparation method greatly improves the quality and the production efficiency of the packing compression test piece, and has a larger practical application value.
Technical proposal
The preparation method of the aviation filler compression test piece comprises the following steps:
1) Weighing the adhesive, the curing agent and the hollow phenolic microspheres according to a certain proportion, and mixing and preparing in a container;
2) Pouring the prepared filler into a defoaming tool, and placing the tool into a vacuum oven for vacuum defoaming;
3) Pouring the mixture subjected to vacuum defoamation into a sinking die tool;
4) Putting the aluminum tubular mould treated by the release agent into a sinking mould tool, so that the aluminum tubular mould slowly sinks into the mixture, and the mixture completely penetrates through the aluminum tubular mould;
5) Placing the sinking die tool which is sunk into the aluminum tubular die into room temperature for curing or curing in an oven to obtain an aviation filler compression test piece;
6) Ejecting the aviation packing compression test piece from the die, and polishing the top of the test piece until the top of the test piece is flat.
Further, in the step 1), the weight ratio of the adhesive, the curing agent and the hollow phenolic microspheres is 10:3:3.5 or 10:3:1.5, stirring in the same direction until the mixture is uniformly mixed, and the viscosity reaches 7-10Pa.s.
Further, in step 2), the height of the filler in the defoaming tool is not more than 5mm.
In the step 2), the vacuum box is vacuumized for 25+/-5 min at the temperature of 35-45 ℃ under the pressure of-0.085 to-0.1 MPa.
Further, the mold release agent treatment of the aluminum tubular mold is specifically to uniformly coat a layer of mold release agent on the surface of the aluminum tubular mold.
Further, in step 5), the room temperature curing process is to cure for more than 5 days at the temperature of 23+/-2 ℃; the oven curing process was 3 hours curing at a temperature of 65 ℃ ± 3 ℃.
Further, before the step 2), sticking a release cloth at the outlet of the defoaming tool.
The defoaming tool comprises a defoaming tool body with an opening at the top, an outlet is formed in the bottom of the defoaming tool body, and an included angle is formed between the inner bottom surface of the defoaming tool body and the horizontal plane.
The sinking die tool applied to the method is a container with an opening at the top.
Advantageous effects
(1) According to the invention, a vacuum defoaming process is innovatively introduced into the preparation process of the packing compression test piece, so that the exhaust efficiency is remarkably improved, and the internal pores of the test piece are reduced;
(2) The method establishes the technological parameters suitable for vacuum defoamation of aviation fillers, and forms a set of mature and stable technological process and tooling design method;
(3) The sinking die technology is adopted to replace the original casting technology, so that the air bubbles introduced in the casting process are greatly reduced, and the quality of the test piece is improved.
The invention has the following specific technical effects:
(1) The quality of aviation packing compression test pieces is improved, and the compactness is improved by about 14%;
(2) The preparation time of the packing compression test piece is greatly shortened, the preparation efficiency is improved, and the preparation time is reduced to 1/3 of that of the original process;
(3) The qualification rate of the compression test piece is improved to more than 90% from the original 20%.
Drawings
FIG. 1 is a flow chart of the method of the present invention;
FIG. 2 is a flow chart of the method of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
One embodiment of the present invention is shown in fig. 1 as: the preparation method of the aviation filler compression test piece comprises the following steps:
1) Weighing the adhesive, the curing agent and the hollow phenolic microspheres according to the following proportion, and mixing and blending in a container; weighing the adhesive, the curing agent and the hollow phenolic microspheres according to the weight ratio of 10:3:3.5 or 10:3:1.5, stirring the materials in the same direction in the blending process until the materials are uniformly mixed.
2) Judging whether the viscosity of the mixture meets the requirement, if so, executing the subsequent steps downwards, otherwise, re-weighing the weight ratio of the adhesive, the curing agent and the hollow phenolic microspheres, and blending the filler, wherein the viscosity requirement of the mixture is as follows: the viscosity reaches 7-10Pa.s. The viscosity is controlled within 7-10Pa.s, so that the strength of a subsequently prepared test piece can be ensured to meet the requirement, otherwise, the strength of the prepared test piece is low when the viscosity is too low, and the viscosity is too high, so that the mixture of the filler cannot normally flow in a defoaming tool and a sinking tool.
3) Sticking a demolding cloth at the outlet of the defoaming tool, so that the bottom of the defoaming tool is sealed, and leakage from the defoaming tool after pouring the filler mixture is avoided;
4) Pouring the prepared filler into a defoaming tool, and then placing the defoaming tool containing the filler into a vacuum oven for vacuum defoaming; the pressure in the vacuum box is-0.085 to-0.1 MPa, the temperature is 35 to 45 ℃ and the vacuumizing time is 25+/-5 min, because the pressure in the vacuum box adopts negative pressure of-0.085 to-0.1 MPa, the pressure value in the vacuum box is smaller than the pressure value inside bubbles in the filler mixture, the volume of the bubbles in the filler mixture is continuously increased, and the volume of the filler is further continuously increased in the defoaming tool, so that the volume of the filler is ensured not to overflow the defoaming tool in the increasing process, and the height of the filler in the defoaming tool is ensured not to exceed 5mm, so that the volume of the filler is ensured not to overflow the defoaming tool from the top all the time in the increasing process; along with the smaller and smaller vacuum pressure, the buoyancy of bubbles in the filler is larger and larger, the bubbles can quickly float from the inside of the filler to the surface of the filler, and the bubbles continuously disappear, and meanwhile, the disappearance of the bubbles can be accelerated by adopting the environment with the temperature of 35-45 ℃ so as to achieve the purpose of defoaming the filler.
5) And after the filler is defoamed, taking out the filler from the vacuum oven, at the moment, changing the air pressure from vacuum negative pressure to atmospheric pressure at room temperature, shrinking and reducing the volume of the filler mixture again, at the moment, placing the sinking die tool below the defoamed tool, enabling an outlet of the defoamed tool to be aligned with the top of the sinking die tool, tearing off a demolding cloth at the outlet of the defoamed tool, and enabling the filler in the defoamed tool to flow into the sinking die tool from the outlet.
6) Putting the aluminum tubular mould treated by the release agent into a sinking mould tool, so that the aluminum tubular mould slowly sinks into the mixture, and the mixture completely penetrates through the aluminum tubular mould; uniformly coating a layer of release agent on the surface of the aluminum tubular mold, forming a layer of film on the surface of the aluminum tubular mold by the release agent, protecting the surface of the mold, preventing the filler from adhering to the surface of the mold, reducing the friction force between the finally formed test piece and the mold, and facilitating the demolding;
5) Placing the sinking die tool which is sunk into the aluminum tubular die into room temperature for curing or curing in an oven to obtain an aviation filler compression test piece; the room temperature curing process is that the curing is carried out for more than 5 days at the temperature of 23+/-2 ℃; the oven curing process was 3 hours curing at a temperature of 65 ℃ ± 3 ℃.
6) Ejecting the aviation packing compression test piece from the aluminum tubular mold, and polishing the top of the test piece until the top of the test piece is flat.
The defoaming tool used in the method comprises a defoaming tool body with an opening at the top, and an outlet is arranged at the bottom of the defoaming tool body, so that filler can flow out of the defoaming tool to a sinking die tool conveniently, and an included angle is formed between the inner bottom surface of the defoaming tool body and the horizontal plane, so that filler can flow conveniently.
The sinking die tool used in the method is a container with an opening at the top.
Another embodiment of the invention is:
1) The weight ratio of the adhesive to the curing agent to the hollow phenolic microspheres is 10:3: and 3.5, weighing and manufacturing a compression test piece, stirring in the same direction in the blending process until the mixture is uniform, and testing to obtain the viscosity of 8.3Pa.s.
2) Pouring the prepared filler into a defoaming tool, and placing the tool into a vacuum oven for vacuum defoaming; in the step 2), the height of the filler in the defoaming tool is 4.3mm, the pressure in a vacuum box is-0.1 MPa, the temperature of an oven is 36 ℃ and the vacuumizing time is 25min
3) Pouring the mixture subjected to vacuum defoamation into a sinking die tool;
4) Putting the aluminum tubular mould treated by the release agent into a sinking mould tool, so that the aluminum tubular mould slowly sinks into the mixture, and the mixture completely penetrates through the aluminum tubular mould;
5) And (3) placing the sinking die tool immersed in the aluminum tubular die for curing at room temperature or in an oven to obtain the aviation filler compression test piece, wherein the oven curing process is that the aviation filler compression test piece is cured for 3 hours at the temperature of 65+/-3 ℃.
6) Ejecting the aviation packing compression test piece from the die, and polishing the top of the test piece until the top of the test piece is flat.
The surface of the manufactured test piece is smooth and bubble-free, and the experimental results of the specific compression test are shown in the following table, so that the test piece meets the index requirements.
| Sequence number | Intensity (MPa) | Density (g/cm 3) |
| 1. | 27.2 | 0.557 |
| 2. | 26.7 | 0.556 |
| 3. | 25.5 | 0.554 |
| 4. | 27.3 | 0.55 |
| 5. | 26.9 | 0.548 |
| 6. | 27 | 0.554 |
| Index (I) | ＞23.6 | 0.58±0.06 |
The foregoing is merely a detailed description of the invention, which is not a matter of routine skill in the art. However, the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily contemplated by those skilled in the art within the scope of the present invention should be included in the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. The preparation method of the aviation filler compression test piece is characterized by comprising the following steps of:
1) Weighing the adhesive, the curing agent and the hollow phenolic microspheres according to a certain proportion, and mixing and preparing in a container;
2) Pouring the prepared filler into a defoaming tool, and placing the tool into a vacuum oven for vacuum defoaming;
3) Pouring the mixture subjected to vacuum defoamation into a sinking die tool;
4) Putting the aluminum tubular mould treated by the release agent into a sinking mould tool, so that the aluminum tubular mould slowly sinks into the mixture, and the mixture completely penetrates through the aluminum tubular mould;
5) Placing the sinking die tool which is sunk into the aluminum tubular die into room temperature for curing or curing in an oven to obtain an aviation filler compression test piece;
6) Ejecting the aviation packing compression test piece from the die, and polishing the top of the test piece until the top of the test piece is flat.
2. The method for preparing the aviation filler compression test piece according to claim 1, wherein in the step 1), the weight ratio of the adhesive, the curing agent and the hollow phenolic microspheres is 10:3:3.5 or 10:3:1.5, stirring in the same direction until the mixture is uniformly mixed, and the viscosity reaches 7-10Pa.s.
3. The method for preparing an aviation filler compression test piece according to claim 1, wherein in the step 2), the height of the filler in the defoaming tool is not more than 5mm.
4. The method for preparing an aviation filler compression test piece according to claim 1, wherein in the step 2), the pressure in a vacuum box is-0.085 to-0.1 MPa, the temperature is 35-45 ℃, and the vacuumizing time is 25+/-5 min.
5. The method for preparing an aviation packing compression test element according to claim 1, wherein in the step 4), the mold release agent treatment of the aluminum tubular mold is specifically to uniformly coat a layer of mold release agent on the surface of the aluminum tubular mold.
6. The method for preparing an aviation filler compression test piece according to claim 1, wherein in the step 5), the room temperature curing process is performed at a temperature of 23 ℃ +/-2 ℃ for more than 5 days; the oven curing process was 3 hours curing at a temperature of 65 ℃ ± 3 ℃.
7. The method for manufacturing an aviation filler compression test piece according to claim 1, wherein before the step 2), a release cloth is adhered to an outlet of the defoaming tool.
8. A defoaming tool for applying the method of any one of claims 1 to 7, wherein the defoaming tool comprises a defoaming tool body with an opening at the top, an outlet is arranged at the bottom of the defoaming tool body, and an included angle is formed between the inner bottom surface of the defoaming tool body and a horizontal plane.
9. A sinking mould tool for use in the method of any one of claims 1 to 7, wherein the sinking mould tool is a container with an opening at the top.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310437231.8A CN116818446A (en) | 2023-04-21 | 2023-04-21 | Aviation filler compression test piece preparation method, defoaming and sinking die tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310437231.8A CN116818446A (en) | 2023-04-21 | 2023-04-21 | Aviation filler compression test piece preparation method, defoaming and sinking die tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116818446A true CN116818446A (en) | 2023-09-29 |
Family
ID=88123027
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310437231.8A Pending CN116818446A (en) | 2023-04-21 | 2023-04-21 | Aviation filler compression test piece preparation method, defoaming and sinking die tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116818446A (en) |
-
2023
- 2023-04-21 CN CN202310437231.8A patent/CN116818446A/en active Pending
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