CN110103483A - A kind of honeycomb core joining method - Google Patents
A kind of honeycomb core joining method Download PDFInfo
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- CN110103483A CN110103483A CN201910310995.4A CN201910310995A CN110103483A CN 110103483 A CN110103483 A CN 110103483A CN 201910310995 A CN201910310995 A CN 201910310995A CN 110103483 A CN110103483 A CN 110103483A
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- Prior art keywords
- cement
- honeycomb
- thermal expansion
- joining method
- component
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Classifications
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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
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The present invention provides a kind of honeycomb core joining method, including whole joining method and cement trapezoidal profile；Whole joining method is on the composite, places all composite materials to be spliced together and cellular component between lower panel, and insertion cement in centre disposably completes hot-press solidifying into tank；Trapezoidal density cement refers to the thermal expansion coefficient and interface temperature distribution situation according to both sides material, sets corresponding trapezoidal profile for cement density, alleviates honeycomb cracking or problem on deformation caused by splicing interfacial thermal stress.The present invention is spliced to form period length, the thermal expansion stress problem etc. occurred when honeycomb sandwich structure for big quantity, multiple types honeycomb and composite material, the problems such as manufacturing cycle of big quantity, multiple types honeycomb sandwich structure can be shortened, and alleviate deformation caused by thermal expansion coefficient mismatches and honeycomb cracking.
Description
Technical field
The present invention relates to field of compound material, and in particular to a kind of honeycomb core joining method.
Background technique
Honeycomb and composite material all have higher specific strength, are existed by the honeycomb sandwich structure that honeycomb and composite material are formed
Aerospace field is widely used.As aerospace field proposes honeycomb sandwich structure functional diversity demand
Height, honeycomb sandwich construction is more towards honeycomb and composite material assembly, and the more directions of type are developed.
Currently, honeycomb core joining method is predominantly centered on honeycomb, with cement by composite material, honeycomb and the honeycomb
Spliced, then hot setting is at a new entirety.Centered on the entirety, then pass through cement and composite material structure
Part, honeycomb are spliced, and form a new entirety, so circulation to complete the splicing of honeycomb and composite material.This method
Mainly has the following two problems: 1) it is directed to the honeycomb sandwich construction formed by a fairly large number of honeycomb and composite material assembly,
It needs repeatedly to be spliced, increases cure cycle.And be heating and curing repeatedly will affect honeycomb and composite material splicing performance and
Service life.2) honeycomb sandwich construction formed for multiple types honeycomb and composite material assembly, different materials are in splicing
It is middle honeycomb to be caused to crack because thermal expansion coefficient mismatches, lead to whole scrap.
The relevant technologies and document discovery are consulted, patent (patent No. CN103589349) discloses a kind of honeycomb core splicing side
Method.This method main contents are as follows: insertion meets and wants between the honeycomb core assembly or honeycomb core and peripheral frame skeleton of honeycomb sandwich board
The foaming bar glue asked then completes splicing under hot pressing making sheet high temperature.This method can not solve big quantity and multiple types honeycomb
Sandwich period length, honeycomb core problem of Cracking.
Summary of the invention
The purpose of the present invention is the period occurred when splicing for big quantity and multiple types honeycomb and composite material is long and
Because of the problems such as thermal expansion coefficient mismatches the honeycomb cracking generated, unsticking between different materials, a kind of honeycomb core spelling is proposed
Method is connect, molding cycle is shortened and reduces the problems such as bring honeycomb cracking is mismatched due to thermal expansion.
A kind of honeycomb core joining method proposed by the present invention, comprising the following steps:
Step 1: placing lower panel in tooling, and successively places non-porous release film and porous release film on plate below；
Step 2: all honeycombs and composite material assembly are placed on plate below；
Step 3: cement is inserted between honeycomb or between honeycomb and composite material assembly；
1/2 of the cement thickness no more than component splicing gap is 2 layers in the splicing interface setting cement number of plies；In heat
The high component side cement of the coefficient of expansion carries out full laying, and the high length component of thermal expansion coefficient is L, low in thermal expansion coefficient
Components side cement length are as follows:
(1)
Wherein,、Respectively temperature value of the component of high thermal expansion coefficient and low thermal coefficient of expansion when cement solidifies；
WithThe respectively thermal expansion coefficient of high thermal expansion coefficient and low thermal coefficient of expansion component；
Step 4: anti-be collapsed auxiliary mould is placed around, and places porous release film, non-porous release film and top panel；
Step 5: vacuum bag encapsulation is carried out by whole, hot-press equipment is sent into according to adhesive technology parameter and carries out hot-press solidifying.
Described to be additionally provided with middle layer between 2 layers of cement of splicing interface setting, the cement length of middle layer is
(2)
Wherein, n indicates the cement number of plies, and i is indicated from high thermal expansion coefficient component to the i-th of low thermal coefficient of expansion component direction
Layer.
The cement sectional is placed, in which: the cement length at component both ends is not less than L/8, between each section of cement
Gap is no longer than 0.5mm.
The gap of each section of cement is not overlapped with another layer of gap.
The cement is foamed glue or glue film.
Technical thought of the invention includes two aspects of whole joining method and trapezoidal density cement design method:
Whole joining method refer on the composite, all composite materials to be spliced together and honeycomb group are placed between lower panel
Part, centre insertion cement, disposably completes hot-press solidifying into tank.
Trapezoidal density cement refers to the thermal expansion coefficient and interface temperature distribution situation according to both sides material, by cement
Density is set as corresponding trapezoidal profile, alleviates honeycomb cracking or problem on deformation caused by splicing interfacial thermal stress.
The beneficial effects of the present invention are:
The period occurred when being spliced to form honeycomb sandwich structure for big quantity, multiple types honeycomb and composite material is long, thermally expands
Stress problem etc. proposes the whole method for being glued all honeycombs and composite product in the present invention, and devises a kind of trapezoidal
The cement adhering method of Density Distribution.Present design can shorten the manufacture week of big quantity, multiple types honeycomb sandwich structure
Phase, and alleviate the problems such as deformation caused by thermal expansion coefficient mismatches is cracked with honeycomb.
Detailed description of the invention
Fig. 1 is adhesive bonding of composites assembling schematic diagram.
Fig. 2 is that schematic diagram is placed in adhesive bonding of composites agent.
In figure: 1- vacuum bag, 2- composite material face, 3- non-porous release film, the anti-collapse tooling of 4-, 5- honeycomb, 5a ~ 5b- bee
Nest, 6- have hole isolation film, 7- foamed glue, 8- tooling.
Specific embodiment
The present invention is further illustrated with example with reference to the accompanying drawing:
As shown in Figs. 1-2.
Embodiment 1
A kind of honeycomb core joining method of the invention, comprising the following steps:
Step 1: placing lower panel in tooling, and successively places non-porous release film and porous release film on plate below；
Step 2: all honeycombs and composite material assembly are placed on plate below；
Step 3: cement is inserted between honeycomb or between honeycomb and composite material assembly；
1/2 of the cement thickness no more than component splicing gap is 2 layers in the splicing interface setting cement number of plies；In heat
The high component side cement of the coefficient of expansion carries out full laying, and the high length component of thermal expansion coefficient is L, low in thermal expansion coefficient
Components side cement length are as follows:
(1)
Wherein,、Respectively temperature value of the component of high thermal expansion coefficient and low thermal coefficient of expansion when cement solidifies；
WithThe respectively thermal expansion coefficient of high thermal expansion coefficient and low thermal coefficient of expansion component；
Step 4: anti-be collapsed auxiliary mould is placed around, and places porous release film, non-porous release film and top panel；
Step 5: vacuum bag encapsulation is carried out by whole, hot-press equipment is sent into according to adhesive technology parameter and carries out hot-press solidifying.
Embodiment 2
A kind of honeycomb core joining method, key are that the foamed glue 7 of trapezoidal density is placed between the honeycomb 6 not of the same race of splicing,
Specific embodiment are as follows:
Step 1: placing composite material face 2 in tooling 8, successively places non-porous release film 3 after positioning again and has hole isolation film
6；
Step 2: honeycomb 5 to be spliced together is placed on having hole isolation film 6；
Step 3: in honeycomb 5a with being inserted into foamed glue 7 between 5b.It is three layers that foamed glue 7, which divides, and each slice width degree is splicing relief width
The 1/3 of degree.
Wherein one layer of foamed glue 7 of the complete laying in the splicing interface of honeycomb 6a,
Honeycomb 5b is glued 7 section of foamed glue of interface laying as shown in Fig. 2, being divided into three sections, symmetry arrangement, upper section foamed glue 7
Cross-sectional length are as follows:(wherein, wherein 、Respectively temperature value of the honeycomb 6a with 6b when solidifying；WithRespectively honeycomb 5a with 5b thermal expansion coefficient, and>, L is 7 cross-sectional length of foamed glue on honeycomb 5a.) interlude hair
Steep 7 cross-sectional length of glue are as follows:.It is two sections that middle layer foamed glue 7, which is divided to, and every section of 7 cross-sectional length of foamed glue is。
Gap is less than 0.5mm between all segmentations of foamed glue 7, and each section of honeycomb is intended to guarantee to take with two layers of front and back foamed glue
It connects.
Step 4: placing anti-be collapsed auxiliary mould 4 around, and is placed with hole isolation film 6, non-porous release film 3 and compound
Material panel 2；
Step 5: carrying out vacuum bag 1 and encapsulate, and is sent into hot-press equipment according to adhesive technology parameter and carries out hot-press solidifying.When heating is solid
When change, foamed glue 7 expands, and the gap between each section of foamed glue 7 is filled, and foamed glue 7 forms trapezoidal density according to gap distribution
Distribution.
The above is only specific application examples of the invention, are not limited in any way to protection scope of the present invention.All uses
Equivalents or equivalence replacement and the technical solution formed, all fall within rights protection scope of the present invention.
Claims (5)
1. a kind of honeycomb core joining method, which comprises the following steps:
Step 1: placing lower panel in tooling, and successively places non-porous release film and porous release film on plate below；
Step 2: all honeycombs and composite material assembly are placed on plate below；
Step 3: cement is inserted between honeycomb or between honeycomb and composite material assembly；
1/2 of the cement thickness no more than component splicing gap is 2 layers in the splicing interface setting cement number of plies；In heat
The high component side cement of the coefficient of expansion carries out full laying, and the high length component of thermal expansion coefficient is L, low in thermal expansion coefficient
Components side cement length are as follows:
Wherein,、Respectively temperature value of the component of high thermal expansion coefficient and low thermal coefficient of expansion when cement solidifies；WithThe respectively thermal expansion coefficient of high thermal expansion coefficient and low thermal coefficient of expansion component；
Step 4: anti-be collapsed auxiliary mould is placed around, and places porous release film, non-porous release film and top panel；
Step 5: vacuum bag encapsulation is carried out by whole, hot-press equipment is sent into according to adhesive technology parameter and carries out hot-press solidifying.
2. a kind of honeycomb core joining method according to claim 1, which is characterized in that 2 layers in the setting of splicing interface
Middle layer is additionally provided between cement, the cement length of middle layer is
Wherein, n indicates the cement number of plies, and i is indicated from high thermal expansion coefficient component to the i-th of low thermal coefficient of expansion component direction
Layer.
3. a kind of honeycomb core joining method according to claim 1 or claim 2, which is characterized in that the cement sectional is placed,
Wherein: the cement length at component both ends is not less than L/8, and each section of cement gap is no longer than 0.5mm.
4. a kind of honeycomb core joining method according to claim 2, which is characterized in that the gap of each section of cement and another
One layer of gap is not overlapped.
5. a kind of honeycomb core joining method according to claim 2, which is characterized in that the cement is foamed glue or glue
Film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910310995.4A CN110103483B (en) | 2019-04-18 | 2019-04-18 | Honeycomb core splicing method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910310995.4A CN110103483B (en) | 2019-04-18 | 2019-04-18 | Honeycomb core splicing method |
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| CN110103483A true CN110103483A (en) | 2019-08-09 |
| CN110103483B CN110103483B (en) | 2021-08-03 |
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| CN201910310995.4A Active CN110103483B (en) | 2019-04-18 | 2019-04-18 | Honeycomb core splicing method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN112743880A (en) * | 2020-12-11 | 2021-05-04 | 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 |
| CN112829161A (en) * | 2021-01-07 | 2021-05-25 | 中国航空制造技术研究院 | Foaming glue filling method for composite material honeycomb sandwich structure |
| CN117565406A (en) * | 2024-01-16 | 2024-02-20 | 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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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| 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 |
| CN112829161A (en) * | 2021-01-07 | 2021-05-25 | 中国航空制造技术研究院 | Foaming glue filling method for composite material honeycomb sandwich structure |
| CN117565406A (en) * | 2024-01-16 | 2024-02-20 | 成都飞机工业（集团）有限责任公司 | Aluminum alloy skin and honeycomb core gluing method |
| 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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| Publication number | Publication date |
|---|---|
| CN110103483B (en) | 2021-08-03 |
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