CN113942254B - Accurate control method for molded surface of honeycomb sandwich composite material part encapsulation area - Google Patents
Accurate control method for molded surface of honeycomb sandwich composite material part encapsulation area Download PDFInfo
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- CN113942254B CN113942254B CN202111121623.0A CN202111121623A CN113942254B CN 113942254 B CN113942254 B CN 113942254B CN 202111121623 A CN202111121623 A CN 202111121623A CN 113942254 B CN113942254 B CN 113942254B
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- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
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- 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
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- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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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
The invention discloses a method for accurately controlling the molding surface of a honeycomb sandwich composite material part encapsulation area, which belongs to the technical field of composite material processing.
Description
Technical Field
The invention relates to the field of composite material processing, in particular to a method for accurately controlling a molded surface of a honeycomb sandwich composite material part encapsulation area.
Background
The carbon composite material honeycomb sandwich structure has the excellent characteristics of light weight, high specific strength, good bending rigidity, corrosion resistance, integral forming and the like, and is more and more widely applied to the structures of wall plates, control surfaces and the like of modern aircrafts. The commonly used composite material honeycomb sandwich structure is composed of an upper skin, a lower skin, a honeycomb core and an adhesive, in order to ensure the overall mechanical property of the composite material honeycomb sandwich structure, the structural form that the honeycomb core is wrapped by the upper skin and the lower skin is often adopted, the composition structure can be divided into a plate-plate area and a plate-core area, and the typical structure is shown in figure 1. In practical use, the composite material honeycomb sandwich wall panel is connected with the framework of the aircraft in the panel-panel area through a connecting piece, and the composite material honeycomb sandwich control surface structure is usually connected with the framework of the aircraft in a mode of installing a metal connector on the end face.
With the requirements of more and more complex structure and higher performance requirements of modern aircrafts, the connection mode of the honeycomb sandwich structure and the aircraft framework by installing connecting pieces in a plate-plate area or installing metal joints on end faces cannot meet the actual requirements in some areas, so that the development of the connection mode between the plate-core area of the honeycomb sandwich structure and the aircraft framework is more and more urgent. Due to the particularity of the structure and performance of the honeycomb core, if the connecting piece is directly installed in the plate-core area hole, the problems of damage to the structure around the connecting piece, instability of the connecting piece and the like can be caused in the process of fastening the connecting piece. Therefore, the use of the potting adhesive to pre-fill and encapsulate the honeycomb core in the region of the connector to be installed in the honeycomb sandwich structure is an effective way to improve the problems in the board-core region hole-making installation of the connector. The main process of filling and encapsulating the honeycomb core grids comprises the following steps: preparing pouring sealant according to requirements, protecting the honeycomb core in a non-pouring area, filling the pouring sealant into the core grid to be poured in a glue solution active period, and solidifying the pouring sealant at a certain temperature according to the solidifying requirement of the pouring sealant.
However, when the honeycomb core is filled and encapsulated by adopting the above process, the problem that the surface of the encapsulation area of the honeycomb core is not flat often occurs after the encapsulation adhesive is cured, and in order to avoid influencing the product quality of the honeycomb sandwich structure, the encapsulation area needs to be polished and modified in advance, and the problem of excessive polishing or insufficient polishing often occurs in the polishing and modifying process. Excessive polishing can cause the whole encapsulated honeycomb core to be scrapped; insufficient polishing and excessive pouring sealant residue can cause the problems of poor surface quality of the honeycomb sandwich structure part and unqualified nondestructive testing after cementing.
Disclosure of Invention
The invention aims to solve the problem of product quality caused by the fact that the surface of a honeycomb core of a composite material honeycomb sandwich structure is uneven after being filled and sealed and needs to be polished in the prior art, and provides a method for accurately controlling the molded surface of a filling and sealing area of a honeycomb sandwich composite material part.
In order to achieve the above object, the technical solution of the present invention is as follows:
a method for accurately controlling the molded surface of a honeycomb sandwich composite material part encapsulation area comprises the following steps:
placing, positioning and fixing a lower skin on the surface of a part forming tool, and sequentially placing an isolation material and a strippable layer on the contact surface of the lower skin and a honeycomb core;
protecting non-encapsulation areas on the upper side and the lower side of the honeycomb core by using a protective material;
placing, positioning and fixing the honeycomb core with the protective material on the surface of the lower skin on which the isolation material and the strippable layer are laid;
step four, preparing the potting adhesive liquid in an environment place with indexes meeting the requirements, and filling the prepared adhesive liquid into the honeycomb core grids of the area to be potted from top to bottom in the activity validity period of the potting adhesive;
Removing redundant pouring sealant in the pouring areas of the upper surface and the lower surface of the honeycomb core after pouring;
sixthly, after a strippable layer is placed on the surfaces of the pouring sealant filling areas on the upper surface and the lower surface of the honeycomb core, the honeycomb core is installed on the lower skin with the isolation material placed on the lower skin again to complete positioning;
placing an isolation material on the upper surface of the honeycomb core, and placing, positioning and fixing the upper skin above the honeycomb core on which the isolation material is laid;
step eight, placing auxiliary materials, and assembling an envelope;
putting the assembled honeycomb sandwich structure into a heating and pressurizing device capable of being vacuumized along with a tool, and precuring the pouring sealant in a vacuum heating and pressurizing environment;
step ten, after the pouring sealant is cured, removing the bag sealing material, the upper skin, the lower skin and the isolation material on the surface of the honeycomb sandwich structure to obtain a filled and sealed honeycomb core matched with the molded surfaces of the upper panel and the lower panel to be bonded, and directly using the filled and sealed honeycomb core and the upper skin and the lower skin after removing the strippable layer in the filling and sealing area before bonding the subsequent honeycomb core and the upper skin and the lower skin.
Further, the preparation temperature of the encapsulating glue solution is 22 +/-4 ℃, and the humidity is 30-65%.
Further, the protective material is one or more of a contactable paper adhesive tape, a pressure-sensitive adhesive tape or an adhesive release cloth.
Further, the peelable layer should be at least 10mm larger in size than the potting area.
Further, the assembled honeycomb sandwich structure is placed in a heating and pressurizing device capable of being vacuumized along with a tool, vacuumized to be below-0.85 Bar, applied with pressure of 2.0Bar, heated to 120 plus materials at a heating rate of 1.5 ℃/min, kept at a constant temperature for 60-70min, cooled to be below 60 ℃ at a cooling rate of 1.5 ℃/min and then taken out.
In summary, the invention has the following advantages:
1. according to the method, after the honeycomb core is filled and sealed, the pouring sealant is cured under certain vacuum, temperature and pressure environments, glue liquid has certain fluidity in the early stage of curing of the pouring sealant, the honeycomb core is in direct contact with the upper skin and the lower skin to be glued, the profile of the filling and sealing area of the honeycomb core and the to-be-glued joint surface of the upper skin and the lower skin generate a conformal effect under the action of vacuum pressure, and after the pouring sealant is cured, the profile of the filling and sealing area is completely matched with the upper skin and the lower skin to be glued, so that the accurate control of the profile of the filling and sealing area of the honeycomb core is realized;
2. according to the method, the strippable layer is used for carrying out surface treatment on the pouring sealant area, the traditional grinding and roughening operation is replaced, and the method is safe and environment-friendly;
3. The invention is also applicable to metal glued parts, namely parts of which the metal skins are glued with the honeycomb core.
Drawings
FIG. 1 is a schematic view of a typical honeycomb sandwich composite part structure;
FIG. 2 is a schematic view of a completed honeycomb core to be encapsulated according to the present invention;
FIG. 3 is a schematic view of a honeycomb core of the present invention with a portion of the area filled with potting compound;
FIG. 4 is a schematic view of an exemplary assembled envelope of the present invention;
in the figure:
1. the manufacturing method comprises the following steps of composite material upper covering, 2 honeycomb core, 3 composite material lower covering, 4 protective adhesive tape, 5 filling and sealing area, 6 pouring sealant, 7 vacuum bag, 8 breathable felt, 9 nonporous isolation film, 10 peelable layer, 11 tooling, 12 putty strip.
Detailed Description
The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.
Example 1
The invention provides a method for accurately controlling the molded surface of a honeycomb sandwich composite material part encapsulation area, which comprises the following steps:
placing, positioning and fixing a lower skin 3 on the surface of a part forming tool 11, and sequentially placing an isolation material and a peelable layer 10 on the contact surface of the lower skin 3 and a honeycomb core 2;
step two, protecting non-encapsulation areas 5 on the upper side and the lower side of the honeycomb core 2 by using a protective material;
Thirdly, placing, positioning and fixing the honeycomb core 2 with the protective material on the surface of the lower skin 3 on which the isolation material and the strippable layer 10 are laid;
step four, preparing a pouring sealant 6 liquid in an environment place with indexes meeting requirements, and filling the prepared glue liquid into the honeycomb core 2 lattice of the area to be filled and sealed 5 from top to bottom in the activity validity period of the pouring sealant 6;
removing the redundant pouring sealant 6 in the upper surface pouring area 5 and the lower surface pouring area 5 of the honeycomb core 2 after pouring;
sixthly, after a strippable layer 10 is placed on the surfaces of the filling areas of the pouring sealant 6 on the upper surface and the lower surface of the honeycomb core 2, the honeycomb core 2 is installed on the lower skin 3 with the isolation material placed thereon again to complete positioning;
seventhly, placing an isolation material on the upper surface of the honeycomb core 2, and placing, positioning and fixing the upper skin 1 above the honeycomb core 2 on which the isolation material is laid;
step eight, placing auxiliary materials, and assembling an envelope;
step nine, putting the assembled honeycomb sandwich structure into a heating and pressurizing device capable of being vacuumized along with the tool 11, and pre-curing the pouring sealant 6 in a vacuum heating and pressurizing environment;
step ten, after the curing of the pouring sealant 6 is completed, removing the bag sealing material, the upper skin 3, the lower skin 3 and the isolation material on the surface of the honeycomb sandwich structure to obtain the honeycomb core 2 which is matched with the molded surfaces of the upper panel and the lower panel to be bonded and is subjected to the filling and sealing completion, and directly using the honeycomb core 2 and the upper skin 3 after removing the peelable layer 10 in the filling and sealing area 5 before the bonding.
Example 2
The embodiment provides a method for accurately controlling the molded surface of a honeycomb sandwich composite material part encapsulation area, which comprises the following steps:
step one, according to the use requirement of a certain pouring sealant 6 material, preparing a pouring sealant 6 liquid in an environment place with the temperature of 22 +/-4 ℃ and the humidity of 30-65%;
step two, using a contactable paper tape, a pressure-sensitive tape or a tape release cloth protective material to protect non-encapsulation areas 5 on the upper side and the lower side of the honeycomb core 2, as shown in fig. 2;
placing the lower skin 3 on the surface of the part forming tool 11, determining the position relation between the lower skin 3 and the tool 11 by virtue of positioning holes on a panel or laser projection, and sequentially placing the non-porous isolating membrane 9 on the contact surface of the lower skin 3 and the honeycomb core 2;
step four, using laser projection to place, position and fix the protected honeycomb core 2 on the surface of the lower panel on which the isolation material is laid;
step five, filling the prepared glue solution into the core grids of the honeycomb core 2 to-be-encapsulated area 5 within the activity validity period of the pouring sealant 6, as shown in fig. 3;
taking down the honeycomb core 2, checking that the core lattices in the thickness direction of the potting area 5 of the honeycomb core 2 are completely filled with the potting adhesive 6, removing redundant adhesive liquid on the surface of the honeycomb core 2 by using a scraper or a similar tool, removing the protective adhesive tape 4 in the non-potting area 5 of the honeycomb core 2, laying a strippable layer 10 on the upper surface and the lower surface of the potting area 6 of the honeycomb core 2 respectively, wherein the size of the strippable layer 10 is at least 10mm larger than that of the potting area 5;
Seventhly, placing the encapsulated honeycomb core 2 on the lower skin 3 on which the nonporous isolation film 9 is placed again to complete positioning, laying a layer of nonporous isolation film 9 above the honeycomb core 2, placing an upper panel above the encapsulated honeycomb core 2 on which the isolation material is laid to complete positioning, and determining the position relationship between the panel and the tool 11 by virtue of positioning holes or laser projection on the panel;
step eight, placing a non-porous isolating membrane 9, an air-permeable felt 8 and a vacuum bag 7 on the surface of the upper panel, and assembling and sealing the bag by using a putty strip 12, as shown in fig. 4;
step nine, placing the assembled honeycomb sandwich structure in a heating and pressurizing device capable of being vacuumized along with a tool 11, vacuumizing to be below-0.85 Bar, applying pressure of 2.0Bar, heating to 120 and 125 ℃ at the heating rate of 1.5 ℃/min, keeping the temperature for 60-70min, cooling to be below 60 ℃ at the cooling rate of 1.5 ℃/min, and taking out;
step ten, after the solidification is finished, removing the auxiliary material, the upper skin 3, the lower skin 3 and the isolation material on the surface of the honeycomb sandwich structure to obtain the honeycomb core 2 with the molded surface of the encapsulation area 5 matched with the molded surfaces of the upper panel and the lower panel to be bonded, wherein the encapsulated honeycomb core 2 can be directly used for manufacturing the honeycomb sandwich structure, and before the bonding, the encapsulation area 5 is torn off and the layer 10 can be peeled.
The scheme of the invention is applied to the production of ARJ project actual parts at present, the problems of no damage and assembly caused by the mismatching of the molded surface of the original part encapsulation area and the skin are solved, the method only uses the manufactured skin without additionally increasing molds such as an encapsulation area pressing plate and the like, and the self-matching effect is achieved by curing the molded surface of the skin and the encapsulated honeycomb core together, so that the method is very suitable for the composite sandwich component with complex molded surface and has good effect.
The foregoing is illustrative of the preferred embodiments of this invention, and it is to be understood that the invention is not limited to the precise form disclosed herein and that various other combinations, modifications, and environments may be resorted to, falling within the scope of the concept as disclosed herein, either as described above or as apparent to those skilled in the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (5)
1. The method for accurately controlling the molded surface of the encapsulation area of the honeycomb sandwich composite material part is characterized by comprising the following steps of:
placing, positioning and fixing a lower skin (3) on the surface of a part forming tool (11), and sequentially placing an isolation material and a strippable layer (10) on the contact surface of the lower skin (3) and a honeycomb core (2);
Step two, using a protective material to protect non-encapsulation areas (5) at the upper side and the lower side of the honeycomb core (2);
thirdly, placing, positioning and fixing the honeycomb core (2) with the protective material on the surface of the lower skin (3) on which the isolation material and the strippable layer (10) are laid;
step four, preparing a pouring sealant (6) liquid in an environment place with indexes meeting requirements, and filling the prepared liquid sealant into the honeycomb core (2) lattice of the area to be filled and sealed (5) from top to bottom in the activity validity period of the pouring sealant (6);
taking down the honeycomb core (2), and removing redundant pouring sealant (6) in the upper surface pouring area and the lower surface pouring area (5) of the honeycomb core (2) after pouring and sealing;
sixthly, after a layer of strippable layer (10) is placed on the surfaces of the filling areas of the pouring sealant (6) on the upper surface and the lower surface of the honeycomb core (2), the honeycomb core (2) is installed on the lower skin (3) with the placed isolation material again to complete positioning;
seventhly, placing an isolation material on the upper surface of the honeycomb core (2), and placing, positioning and fixing the upper skin (1) above the honeycomb core (2) on which the isolation material is laid;
step eight, placing auxiliary materials, and assembling an envelope;
putting the assembled honeycomb sandwich structure into a heating and pressurizing device capable of being vacuumized along with a tool (11), and pre-curing the pouring sealant (6) in a vacuum heating and pressurizing environment;
Step ten, after the curing of the pouring sealant (6) is completed, removing the bag sealing material, the upper skin (3) and the lower skin (3) and the isolation material on the surface of the honeycomb sandwich structure to obtain a honeycomb core (2) which is matched with the molded surfaces of the upper panel and the lower panel to be glued, and removing the strippable layer (10) in the region of the pouring region (5) before gluing the subsequent honeycomb core (2) and the upper skin (3) so as to directly manufacture the honeycomb sandwich structure.
2. The method for accurately controlling the molding surface of the honeycomb sandwich composite material part encapsulation area according to claim 1, wherein the preparation temperature of the pouring sealant (6) liquid is 22 +/-4 ℃ and the humidity is 30-65%.
3. The method for accurately controlling the profile of the honeycomb sandwich composite part encapsulation area according to claim 1, wherein the protective material is one or more of a contactable paper tape, a pressure-sensitive adhesive tape or an adhesive release cloth.
4. The method for accurately controlling the profile of the encapsulation area of the honeycomb sandwich composite part according to claim 1, wherein the size of the strippable layer (10) is at least 10mm larger than the area of the encapsulation area (5).
5. The method for accurately controlling the molded surface of the honeycomb sandwich composite part encapsulation area as claimed in claim 1, wherein the assembled honeycomb sandwich structure is placed in a heating and pressurizing device capable of being vacuumized along with a tool (11), vacuumized to be below-0.85 Bar, applied with a pressure of 2.0Bar, heated to 120 plus 125 ℃ at a heating rate of 1.5 ℃/min, kept at a constant temperature for 60-70min, cooled to be below 60 ℃ at a cooling rate of 1.5 ℃/min and then taken out.
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| CN116021798B (en) * | 2023-01-28 | 2023-10-20 | 哈尔滨远驰航空装备有限公司 | Zero-glue-absorption forming method of composite material for air inlet channel |
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| GB885395A (en) * | 1958-10-06 | 1961-12-28 | Bristol Aerojet Ltd | Reinforced skin structures |
| JP2573977B2 (en) * | 1988-01-05 | 1997-01-22 | 富士重工業株式会社 | Forming method of honeycomb core composite |
| JP2001341205A (en) * | 2000-06-05 | 2001-12-11 | Yokohama Rubber Co Ltd:The | Joint structure of honeycomb panel end portion and its jointing method |
| CN102275342B (en) * | 2011-06-08 | 2013-09-18 | 沈阳飞机工业（集团）有限公司 | Honeycomb sandwich piece pre-encapsulation molding tool and process method thereof |
| CN111409221A (en) * | 2020-04-27 | 2020-07-14 | 天津波音复合材料有限责任公司 | One-step filling and sealing forming device and process for curved-surface honeycomb core |
| CN112109255A (en) * | 2020-08-24 | 2020-12-22 | 航天特种材料及工艺技术研究所 | Device for resin potting honeycomb structure and method for resin potting honeycomb structure by using device |
| CN113370594A (en) * | 2021-06-21 | 2021-09-10 | 航天科工火箭技术有限公司 | Method for designing and manufacturing honeycomb sandwich plate |
| CN113386449A (en) * | 2021-07-06 | 2021-09-14 | 成都佳驰电子科技股份有限公司 | Manufacturing process for improving structural strength of wave-absorbing honeycomb sandwich plate |
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