CN110103483B - Honeycomb core splicing method - Google Patents
Honeycomb core splicing method Download PDFInfo
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- CN110103483B CN110103483B CN201910310995.4A CN201910310995A CN110103483B CN 110103483 B CN110103483 B CN 110103483B CN 201910310995 A CN201910310995 A CN 201910310995A CN 110103483 B CN110103483 B CN 110103483B
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- adhesive
- thermal expansion
- honeycomb
- expansion coefficient
- splicing
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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
- B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
- B29C65/481—Non-reactive adhesives, e.g. physically hardening adhesives
- B29C65/4815—Hot melt adhesives, e.g. thermoplastic adhesives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/60—Multitubular or multicompartmented articles, e.g. honeycomb
- B29L2031/608—Honeycomb structures
Abstract
The invention provides a honeycomb core splicing method, which comprises an integral splicing method and a cement trapezoidal distribution; the integral splicing method is that all composite materials and honeycomb assemblies needing to be spliced are placed between an upper panel and a lower panel of the composite materials, a cementing agent is inserted in the middle of the composite materials, and hot-pressing solidification is completed by one-step tank feeding; the trapezoidal density adhesive is characterized in that the adhesive density is set to be correspondingly distributed in a trapezoidal shape according to the thermal expansion coefficients of materials on two sides and the distribution condition of interface temperature, so that the problem of honeycomb cracking or deformation caused by the thermal stress of a splicing interface is solved. The invention aims at the problems of long period, thermal expansion stress and the like when a large number of various honeycombs and composite materials are spliced to form the honeycomb sandwich structure, can shorten the manufacturing period of the large number of various honeycomb sandwich structures, and relieves the problems of deformation, honeycomb cracking and the like caused by mismatching of thermal expansion coefficients.
Description
Technical Field
The invention relates to the field of composite materials, in particular to a honeycomb core splicing method.
Background
Both the honeycomb and the composite material have higher specific strength, and the honeycomb sandwich structure formed by the honeycomb and the composite material is widely applied to the field of aerospace. With the improvement of the demand of the aerospace field for the functional diversity of the honeycomb sandwich structure, the honeycomb sandwich structure develops towards the direction that the number of honeycomb and composite material components is more and the variety is more.
At present, the honeycomb core splicing method mainly comprises the steps of taking a honeycomb as a center, splicing a composite material, the honeycomb and the honeycomb by using a cementing agent, and then curing at high temperature to form a new whole. And (3) taking the whole as a center, splicing the composite material member and the honeycomb by using the adhesive to form a new whole, and repeating the steps to complete the splicing of the honeycomb and the composite material. The method mainly has the following two problems: 1) for a honeycomb sandwich structure formed by a large number of honeycombs and composite material components, multiple splicing is needed, and the curing period is increased. And the repeated heating and curing can affect the splicing performance and the service life of the honeycomb and the composite material. 2) Aiming at the honeycomb sandwich structure formed by various honeycombs and composite material components, the honeycombs are cracked due to the mismatching of the thermal expansion coefficients of different materials in the splicing process, so that the whole body is scrapped.
Referring to the related art and the literature findings, a patent (patent No. CN 103589349) discloses a honeycomb core splicing method. The method mainly comprises the following steps: strip-shaped foaming glue meeting the requirements is inserted between the honeycomb core assembly of the honeycomb sandwich board or the honeycomb core and the frame framework, and then the splicing is finished at the high temperature of the hot-pressed board. The method can not solve the problems of long period and honeycomb core cracking of a large number of and various honeycomb sandwich structures.
Disclosure of Invention
The invention aims to provide a honeycomb core splicing method aiming at the problems of long cycle when a large number of and various honeycombs and composite materials are spliced, honeycomb cracking and debonding caused by mismatching of thermal expansion coefficients among different materials and the like, so that the forming cycle is shortened, and the problems of honeycomb cracking and the like caused by mismatching of thermal expansion coefficients are reduced.
The invention provides a honeycomb core splicing method, which comprises the following steps:
the method comprises the following steps: a lower panel is arranged on the tool, and a nonporous isolation film and a porous isolation film are sequentially arranged on the lower panel;
step two: placing all honeycomb and composite components on the lower panel;
step three: inserting a cement between the honeycombs or between the honeycombs and the composite material assembly;
the thickness of the adhesive is not more than 1/2 of the assembly splicing gap, and 2 layers of adhesive are arranged on the splicing interface; the adhesive is fully paved on one side of the component with high thermal expansion coefficient, the length of the component with high thermal expansion coefficient is L, and the adhesive length on the side of the component with low thermal expansion coefficient is:
wherein the content of the first and second substances,
、
the temperature values of the components with high thermal expansion coefficient and low thermal expansion coefficient when the adhesive is cured are respectively set;
and
the thermal expansion coefficients of the high thermal expansion coefficient and the low thermal expansion coefficient components respectively;
step four: placing an anti-collapse auxiliary tool around the upper panel, and placing a porous isolation membrane, a non-porous isolation membrane and an upper panel;
step five: and packaging the whole body by a vacuum bag, and sending the whole body into hot-pressing equipment to carry out hot-pressing solidification according to the gluing process parameters.
An intermediate layer is also arranged between the 2 layers of adhesive arranged on the splicing interface, and the length of the adhesive in the intermediate layer is
Where n represents the number of layers of cement and i represents the ith layer from the high cte assembly to the low cte assembly.
The cement may be placed in sections, wherein: the length of the cementing agent at the two ends of the component is not less than L/8, and the gap between each section of the cementing agent is not more than 0.5 mm.
The gaps of the sections of the adhesive do not coincide with the gaps of the other layer.
The adhesive is foaming adhesive or adhesive film.
The technical idea of the invention comprises an integral splicing method and a trapezoidal density cement design method:
the integral splicing method is that all composite materials and honeycomb assemblies needing to be spliced are placed between an upper panel and a lower panel of the composite materials, a cementing agent is inserted in the middle of the composite materials, and hot-pressing solidification is completed by feeding the composite materials into a tank at one time.
The trapezoidal density adhesive is characterized in that the adhesive density is set to be correspondingly distributed in a trapezoidal shape according to the thermal expansion coefficients of materials on two sides and the distribution condition of interface temperature, so that the problem of honeycomb cracking or deformation caused by the thermal stress of a splicing interface is solved.
The invention has the beneficial effects that:
aiming at the problems of long period, thermal expansion stress and the like when a large number of various honeycombs and composite materials are spliced to form a honeycomb sandwich structure, the invention provides a method for integrally bonding all honeycombs and composite material parts, and designs a glue bonding method with trapezoidal density distribution. The design scheme can shorten the manufacturing period of a large number of honeycomb sandwich structures and various honeycomb sandwich structures, and solves the problems of deformation, honeycomb cracking and the like caused by mismatching of thermal expansion coefficients.
Drawings
Figure 1 is a schematic diagram of a composite material cementing assembly.
Figure 2 is a schematic representation of composite cement placement.
In the figure: the production process comprises the following steps of 1-vacuum bag, 2-composite material panel, 3-nonporous isolation film, 4-collapse prevention tool, 5-honeycomb, 5 a-5 b-honeycomb, 6-porous isolation film, 7-foaming glue and 8-tool.
Detailed Description
The invention is further illustrated by the following figures and examples:
as shown in fig. 1-2.
Example 1
The invention discloses a honeycomb core splicing method, which comprises the following steps:
the method comprises the following steps: a lower panel is arranged on the tool, and a nonporous isolation film and a porous isolation film are sequentially arranged on the lower panel;
step two: placing all honeycomb and composite components on the lower panel;
step three: inserting a cement between the honeycombs or between the honeycombs and the composite material assembly;
the thickness of the adhesive is not more than 1/2 of the assembly splicing gap, and 2 layers of adhesive are arranged on the splicing interface; the adhesive is fully paved on one side of the component with high thermal expansion coefficient, the length of the component with high thermal expansion coefficient is L, and the adhesive length on the side of the component with low thermal expansion coefficient is:
wherein the content of the first and second substances,
、
the temperature values of the components with high thermal expansion coefficient and low thermal expansion coefficient when the adhesive is cured are respectively set;
and
the thermal expansion coefficients of the high thermal expansion coefficient and the low thermal expansion coefficient components respectively;
step four: placing an anti-collapse auxiliary tool around the upper panel, and placing a porous isolation membrane, a non-porous isolation membrane and an upper panel;
step five: and packaging the whole body by a vacuum bag, and sending the whole body into hot-pressing equipment to carry out hot-pressing solidification according to the gluing process parameters.
Example 2
A honeycomb core splicing method is characterized in that trapezoidal-density foaming glue 7 is placed among different types of spliced honeycombs 6, and the specific implementation mode is as follows:
the method comprises the following steps: placing a composite material panel 2 on a tool 8, and placing a nonporous isolation membrane 3 and a porous isolation membrane 6 in sequence after positioning;
step two: placing honeycombs 5 to be spliced on the porous isolating membrane 6;
step three: a foam 7 is interposed between the honeycomb 5a and the honeycomb 5 b. The foam 7 is divided into three layers, each layer having a width of 1/3 of the width of the splicing gap.
Wherein the gluing interface of the honeycomb 6a is completely laid with a layer of foaming glue 7,
the section of the foaming adhesive 7 laid on the bonding interface of the honeycomb 5b is shown in fig. 2, the foaming adhesive is divided into three sections which are symmetrically arranged, and the length of the section of the foaming adhesive 7 at the upper section is as follows:
(wherein, among others,
、
respectively the temperature values of the honeycombs 6a and 6b during solidification;
and
respectively, the thermal expansion coefficients of the honeycomb 5a and the honeycomb 5b, and
＞
and L is the section length of the foaming adhesive 7 on the honeycomb 5 a. ) The section length of the middle section foaming adhesive 7 is as follows:
. The middle layer foaming glue 7 is divided into two sections, and the section length of each section of the foaming glue 7 is
。
Gaps among all the sections of the foaming glue 7 are smaller than 0.5mm, and the honeycombs of each section are in lap joint with the front layer and the rear layer of the foaming glue.
Step four: placing an anti-collapse auxiliary tool 4 around the composite material panel, and placing a porous isolation membrane 6, a non-porous isolation membrane 3 and the composite material panel 2;
step five: and packaging the vacuum bag 1, and sending the vacuum bag into hot-pressing equipment to carry out hot-pressing solidification according to the gluing process parameters. When the temperature is raised and the foaming glue 7 is solidified, the foaming glue 7 expands, gaps among the sections of the foaming glue 7 are filled, and the foaming glue 7 forms a trapezoidal density distribution according to the gap distribution.
The above is only a specific application example of the present invention, and the protection scope of the present invention is not limited in any way. All technical solutions formed by equivalent transformation or equivalent replacement fall within the protection scope of the present invention.
Claims (5)
1. A honeycomb core splicing method is characterized by comprising the following steps:
the method comprises the following steps: a lower panel is arranged on the tool, and a nonporous isolation film and a porous isolation film are sequentially arranged on the lower panel;
step two: placing all honeycomb and composite material components on the nonporous isolation film and the porous isolation film of the lower panel;
step three: inserting a cement between the honeycombs or between the honeycombs and the composite material assembly;
the thickness of the adhesive is not more than 1/2 of the assembly splicing gap, and 2 layers of adhesive are arranged on the splicing interface; the adhesive is fully paved on one side of the component with high thermal expansion coefficient, the length of the component with high thermal expansion coefficient is L, and the adhesive length on the side of the component with low thermal expansion coefficient is:
wherein the content of the first and second substances,
、
the temperature values of the components with high thermal expansion coefficient and low thermal expansion coefficient when the adhesive is cured are respectively set;
and
the thermal expansion coefficients of the high thermal expansion coefficient and the low thermal expansion coefficient components respectively;
step four: placing an anti-collapse auxiliary tool around the upper panel, and placing a porous isolation membrane, a non-porous isolation membrane and an upper panel;
step five: and packaging the whole body by a vacuum bag, and sending the whole body into hot-pressing equipment to carry out hot-pressing solidification according to the gluing process parameters.
2. The honeycomb core splicing method according to claim 1, wherein an intermediate layer is further arranged between the 2 layers of the adhesive arranged at the splicing interface, and the length of the adhesive of the intermediate layer is equal to
Where n represents the number of layers of cement and i represents the ith layer from the high cte assembly to the low cte assembly.
3. The honeycomb core splicing method according to claim 1 or 2, wherein the cement is placed in segments, wherein: the length of the cementing agent at the two ends of the component is not less than L/8, and the gap between each section of the cementing agent is not more than 0.5 mm.
4. The method of claim 2, wherein the gaps of the cement segments are not coincident with the gaps of the other layer.
5. The honeycomb core splicing method according to claim 2, wherein the adhesive is a foaming adhesive or an adhesive film.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110815901A (en) * | 2019-10-17 | 2020-02-21 | 成都飞机工业（集团）有限责任公司 | Method for controlling through hole rate of acoustic lining wall plate made of honeycomb sandwich composite material |
| CN112743880B (en) * | 2020-12-11 | 2022-08-09 | 哈尔滨飞机工业集团有限责任公司 | Repairing method for large-area damage of honeycomb sandwich structural member |
| CN112829161B (en) * | 2021-01-07 | 2022-10-21 | 中国航空制造技术研究院 | Foaming glue filling method for composite material honeycomb sandwich structure |
| CN117565406B (en) * | 2024-01-16 | 2024-04-12 | 成都飞机工业（集团）有限责任公司 | Aluminum alloy skin and honeycomb core gluing method |
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| DE10146201A1 (en) * | 2001-09-13 | 2003-04-10 | Deutsch Zentr Luft & Raumfahrt | Production of sandwich type fiber reinforced composite structures has a cellular core with a cover at the open cell ends to prevent resin penetration of cells |
| CN101151142A (en) * | 2005-02-02 | 2008-03-26 | 波音公司 | Low temperature, vacuum cure fabrication process for large, honeycomb core stiffened composite structures |
| WO2013014289A1 (en) * | 2011-07-27 | 2013-01-31 | Airbus Operations Gmbh | A device for the manufacture of a bonded component and also a method |
| CN102917863A (en) * | 2010-05-11 | 2013-02-06 | 洛林航空工程公司 | Process for manufacturing a part made of a composite having a hollow core |
| CN102555302B (en) * | 2011-12-16 | 2014-01-22 | 沈阳飞机工业（集团）有限公司 | Process method of whole cocure shaping of honeycomb sandwich structure of composite material |
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2019
- 2019-04-18 CN CN201910310995.4A patent/CN110103483B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE10146201A1 (en) * | 2001-09-13 | 2003-04-10 | Deutsch Zentr Luft & Raumfahrt | Production of sandwich type fiber reinforced composite structures has a cellular core with a cover at the open cell ends to prevent resin penetration of cells |
| CN101151142A (en) * | 2005-02-02 | 2008-03-26 | 波音公司 | Low temperature, vacuum cure fabrication process for large, honeycomb core stiffened composite structures |
| CN102917863A (en) * | 2010-05-11 | 2013-02-06 | 洛林航空工程公司 | Process for manufacturing a part made of a composite having a hollow core |
| WO2013014289A1 (en) * | 2011-07-27 | 2013-01-31 | Airbus Operations Gmbh | A device for the manufacture of a bonded component and also a method |
| CN102555302B (en) * | 2011-12-16 | 2014-01-22 | 沈阳飞机工业（集团）有限公司 | Process method of whole cocure shaping of honeycomb sandwich structure of composite material |
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