CN104724277A - Light airplane composite material skin integral rapid connecting structure and manufacturing method thereof - Google Patents
Light airplane composite material skin integral rapid connecting structure and manufacturing method thereof Download PDFInfo
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- CN104724277A CN104724277A CN201510053729.XA CN201510053729A CN104724277A CN 104724277 A CN104724277 A CN 104724277A CN 201510053729 A CN201510053729 A CN 201510053729A CN 104724277 A CN104724277 A CN 104724277A
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- composite material
- thin skin
- material thin
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- mushroom head
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Abstract
The invention discloses a light airplane composite material skin integral rapid connecting structure. An airplane truss and a composite material thin skin are rapidly connected by an industrial buckling band which is a mushroom hairstyle buckling band comprising a first mushroom hairstyle and a second mushroom hairstyle which are meshed with each other. The manufacturing method comprises the following steps: selecting required components; cleaning and treating the selected components; firstly, bonding the second mushroom hairstyle to a composite material thin skin, then fitting the first mushroom hairstyle to an airplane truss, and finally laying the composite material thin skin to the airplane truss structure in parallel; and finally, fixing the composite material thin skin. By the mode, the material integrity of the material can be ensured, cracks due to machinery or stress can be prevented, so that the service life of the composite material thin skin is prolonged; during installation, the composite material thin skin can be rapidly installed and positioned so as to improve the assembling efficiency; the light airplane composite material skin integral rapid connecting structure is convenient to dismount, and the industrial buckling band can be opened and closed repeatedly for thousands of times.
Description
Technical field
The present invention relates to technical field of aerospace, particularly relate to overall fast joint structure of a kind of aviette composite material thin skin and preparation method thereof.
Background technology
Composite material is little with its thermal expansion coefficient, antifatigue and the feature such as vibration resistance is strong, anticorrosive, significantly can reduce part, fastener quantity improves integrally-built Combination property, become one of large main material of aircraft body structure four of new generation.Compared with metal construction, the weakness such as composite material interlayer intensity is low, impact resistance is poor, the assembly connection difficulty determining its structure is large, technical requirements is high.
Rationally and neatly use type of attachment and the method for composite material, be improve composite material structural member intensity, alleviate structural weight, one of the essential condition giving full play to composite material excellent specific property.Assembly connection between composite material parts or between composite material and metal parts, has mechanical connection, splicing and Hybrid connections 3 kinds of methods usually.In composite material Joining Technology technology, select which kind of method of attachment, mainly fixed according to actual operation requirements.In general, when carrying is comparatively large, reliability requirement is higher, mechanical connection should be adopted; When carrying is less, component is thinner, environmental conditions is very not severe, should adopts and glued joint connection; At some in particular cases, during for improving the fail safety characteristic of structure, Hybrid connections can be adopted.
It is more complicated that the features such as the anisotropy of composite thin plate, breaking strain are little make composite material connect, composite material is comparatively difficult when machining hole, the distribution of cut fibres around-the-hole stress is comparatively complicated, stress concentration degree height very easily cracks and causes its intensity degradation, therefore be the weak link of structure in composite material connection, be badly in need of the connection structure that a kind of not attacking material structure of research accurately can be located again, be assembled, the problem such as material crack and rapid disassembling maintenance can be produced because riveted joint produces internal stress by actv. solution aviette composite material thin skin.
Summary of the invention
The technical matters that the present invention mainly solves is to provide a kind of composite material thin skin that can effectively solve because being mechanically connected the material crack and maintenance for convenience detach that produce, overall fast joint structure of aviette composite material thin skin improving efficiency of assembling problem and preparation method thereof.
For solving the problems of the technologies described above, the technical scheme that the present invention adopts is: provide a kind of aviette composite material thin skin overall fast joint structure, comprise, aircraft truss and composite material thin skin, described aircraft truss is connected by industrial cingulum fast with between composite material thin skin, described industrial cingulum adopts mushroom head cingulum, described mushroom head cingulum comprises the first engaged mushroom head and the second mushroom head, and the back side of the first mushroom head and the second mushroom head is equipped with glue-line, first mushroom head is fixed on aircraft truss by glue-line, described second mushroom head is fixed on composite material thin skin by glue-line.
In a preferred embodiment of the present invention, be provided with T-slot in the middle part of described aircraft truss, described T-slot both sides are the locating surface installing composite material thin skin.
In a preferred embodiment of the present invention, described composite material thin skin is that benchmark is connected fast with aircraft truss with locating surface.
In a preferred embodiment of the present invention, the aluminum alloy pressing plate of fixing composite material thin skin is installed in described T-slot.
In a preferred embodiment of the present invention, the peel strength of described mushroom head cingulum is less than or equal to 6N ~ 7N, mushroom head cingulum width 23cm-28cm.
For solving the problems of the technologies described above, another technical solution used in the present invention is: the method for making providing the overall fast joint structure of a kind of aviette composite material thin skin, comprises the following steps:
Step one: choose industrial cingulum, the heating-up temperature when sectional dimension of the peel strength determination composite material thin skin be stripped when being fastened by industrial cingulum, the thickness of composite material thin skin, industrial cingulum glue-line are bondd for the first time and type of heating;
Step 2: the parts that step one is determined are cleared up and processed;
Step 3: the bonding completing the laying of composite material thin skin, industrial cingulum;
First the glue-line of the second mushroom head in mushroom head cingulum is bonded on composite material thin skin by the mode of heating, then by the first mushroom head glue-line by heating mode fit on aircraft truss, finally by composite material thin skin parallel laid on aircraft truss structure;
Step 4: complete the fixing of composite material thin skin;
Aluminum alloy pressing plate for compressing composite material thin skin being assemblied in aircraft truss structure, being fixed on aircraft truss structure by flathead screw;
Step 5: after said structure installation, carries out the debugging of integral composite light-skinned structure.
The sectional dimension of composite material thin skin is 900mm ~ 1100mm × 400 ~ 600mm, the thickness 0.5mm ~ 1mm of composite material thin skin.
In a preferred embodiment of the present invention, type of heating when industrial cingulum glue-line bonds for the first time is heating rod heating.
The invention has the beneficial effects as follows:
(1) composite material thin skin need not use machine drilling, adopts industrial cingulum glue-line to bond, and ensures material integrity, avoids causing crackle because of machinery or stress thus improving composite material thin skin service life.
(2) its Joint strenght requirement can be met when adopting the surface of industrial hasp mushroom head moulding engaged, during installation, efficiency of assembling can be improved in composite material thin skin Fast Installation, location.
(3) when aviette maintenance maintenance, composite material thin skin is convenient to dismounting, and industrial cingulum can repeat folding more than hundreds of times.
(4) adopt industrial cingulum be no matter resetting or structure-reinforced etc. functionally, glue is more average on distribution of stress, the single point pressure that machinery is fixing can be got rid of, the material telescopic shape change brought because of the temperature difference can be cushioned simultaneously, under dynamic and static state, all keep stable adhesive force between different structure.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme in the embodiment of the present invention, below the accompanying drawing used required in describing embodiment is briefly described, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings, wherein:
Fig. 1 is the structural representation of a preferred embodiment of mushroom head cingulum in the overall fast joint structure of aviette composite material thin skin of the present invention;
Fig. 2 is the structural representation of a preferred embodiment of aircraft truss in the overall fast joint structure of aviette composite material thin skin of the present invention;
Fig. 3 is the structural representation of a preferred embodiment of composite material thin skin in the overall fast joint structure of aviette composite material thin skin of the present invention;
Fig. 4 is the structural representation for a preferred embodiment of the aircraft truss of composite material thin skin location in the overall fast joint structure of aviette composite material thin skin of the present invention;
Fig. 5 is the structural representation of the preferred embodiment after the overall fast joint structure of aviette composite material thin skin of the present invention has assembled;
In accompanying drawing, the mark of each parts is as follows: 101-glue-line, 102-first mushroom head, 103-parting paper, 104-second mushroom head, 201-aircraft truss, 202-composite material thin skin, 401-T type groove, 402-locating surface, 501-aluminum alloy pressing plate.
Detailed description of the invention
Be clearly and completely described to the technical scheme in the embodiment of the present invention below, obviously, described embodiment is only a part of embodiment of the present invention, instead of whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art, not making other embodiments all obtained under creative work prerequisite, belong to the scope of protection of the invention.
The embodiment of the present invention comprises:
The overall fast joint structure of a kind of aviette composite material thin skin, comprise, aircraft truss 201 and composite material thin skin 202, described aircraft truss 201 is connected by industrial cingulum fast with between composite material thin skin 202.
Due to hole machined can not be carried out to composite material thin skin 202, in order to ensure its bulk strength, composite material thin skin 202 stressing conditions can be improved by applicable industry cingulum, being convenient to dismounting simultaneously and safeguarding, thus expanding its application, improving its field of application.
Described industrial cingulum adopts the mushroom head cingulum having sufficiently high peel strength, and composite material skin adopts T300 unidirectional cloth, and laying is 90/45/0/-45/-90, one-body molded through autoclave.
As shown in Figure 1, described mushroom head cingulum comprises the first engaged mushroom head 102 and the second mushroom head 104, and the back side of the first mushroom head 102 and the second mushroom head 104 is equipped with glue-line 101, glue-line 101 before not using above with parting paper 103, during use, parting paper 103 is opened.Glue-line 101 can be applied certain pressure by the mode of heating is pasted on composite material thin skin 202 and aircraft truss 201, and stable adhesive force can be kept between industrial cingulum and parts to there is not single-point by force phenomenon.
In preferred enforcement of the present invention, the first mushroom head 102 is fixed on aircraft truss 201 by glue-line 101, and described second mushroom head 104 is fixed on composite material thin skin 202 by glue-line 101, as shown in Figures 2 and 3.
Affiliated aircraft truss 201 meets light-weight design, ensures sufficient intensity requirement, should be designed with locating surface 402 and required mounting and positioning device in junction, ensures to connect Fast Installation to locate.
Therefore, as shown in Figure 4, be provided with T-slot 401 in the middle part of described aircraft truss 201, described T-slot 401 both sides are the locating surface 402 installing composite material thin skin 202.Described composite material thin skin 202 is connected with aircraft truss 201 for benchmark fast with locating surface 402.The effect of locating surface 402 is the installation sites can determining composite material thin skin 202 quickly and accurately.
The aluminum alloy pressing plate 501 of fixing composite material thin skin 202 is installed in described T-slot 401, and is fixed in aircraft truss 201 structure with flathead screw.As shown in Figure 5, this structure can resist the situations such as the vibrations that aviette produces awing, can ensure installation strength requirement simultaneously.
In addition, the method for making of the overall fast joint structure of aviette composite material thin skin 202, comprises the following steps:
Step one: according to the different application scope of sticking belt, choose industrial cingulum, the sectional dimension of the peel strength determination composite material thin skin 202 be stripped when being fastened by industrial cingulum, the thickness of composite material thin skin 202, industrial cingulum glue-line 101 for the first time bonding time heating-up temperature and type of heating;
Step 2: the parts that step one is determined are cleared up and processed; Comprise composite material thin skin 202 section burr and the cleaning of aircraft truss 201 bearing surface, composite material thin skin 202 and aircraft truss 201 bearing surface should clean, drying;
Step 3: the bonding completing the laying of composite material thin skin 202, industrial cingulum;
First the glue-line 101 of the second mushroom head 104 in mushroom head cingulum is bonded on composite material thin skin 202 by the mode of heating, then by the first mushroom head 102 glue-line 101 by heating mode fit on aircraft truss 201, finally by composite material thin skin 202 parallel laid in aircraft truss 201 structure;
Step 4: complete the fixing of composite material thin skin 202;
Aluminum alloy pressing plate 501 for compressing composite material thin skin 202 being assemblied in aircraft truss 201 structure, being fixed in aircraft truss 201 structure by flathead screw;
Step 5: after said structure installation, carries out integral composite thin skin 202 structural adjustment.
Wherein, type of heating when the preferred industrial cingulum glue-line 101 of the present invention bonds for the first time is heating rod heating.By heating rod heating glue-line 101, industrial cingulum is pasted on aircraft truss 201 and composite material thin skin 202.
The preferred embodiments of the present invention 1: based on above-mentioned fast joint structure, wherein, the peel strength of described mushroom head cingulum is less than or equal to 6N, mushroom head cingulum width 23cm.
The sectional dimension of composite material thin skin 202 is 900mm × 400, the thickness 0.8mm of composite material thin skin 202.
Preferred enforcement 2 of the present invention: based on above-mentioned fast joint structure, the maximum peeling strength of described mushroom head cingulum is less than or equal to 6.66N, mushroom head cingulum width 25cm.
The sectional dimension of composite material thin skin 202 is 1000mm × 500mm, the thickness 0.5mm of composite material thin skin 202.
Preferred enforcement 3 of the present invention: based on above-mentioned fast joint structure, the peel strength of described mushroom head cingulum is less than or equal to 7N, mushroom head cingulum width 28cm.
The sectional dimension of composite material thin skin 202 is 1100mm × 600mm, the thickness 1mm of composite material thin skin 202.
The present invention includes following advantage:
Composite material thin skin 202 need not use machine drilling, adopts industrial cingulum glue-line 101 to bond, and ensures material integrity, avoids causing crackle because of machinery or stress thus improving composite material thin skin 202 service life.
Its Joint strenght requirement can be met when adopting the surface of industrial hasp mushroom head moulding engaged, during installation, efficiency of assembling can be improved in composite material thin skin 202 Fast Installation, location.
When aviette maintenance maintenance, composite material thin skin 202 is convenient to dismounting, and industrial cingulum can repeat folding more than hundreds of times.
Adopt industrial cingulum be no matter resetting or structure-reinforced etc. functionally, glue is more average on distribution of stress, the single point pressure that machinery is fixing can be got rid of, the material telescopic shape change brought because of the temperature difference can be cushioned simultaneously, under dynamic and static state, all keep stable adhesive force between different structure.
The foregoing is only embodiments of the invention; not thereby the scope of the claims of the present invention is limited; every utilize description of the present invention to do equivalent structure or equivalent flow process conversion; or be directly or indirectly used in other relevant technical field, be all in like manner included in scope of patent protection of the present invention.
Claims (8)
1. the overall fast joint structure of aviette composite material thin skin, comprise, aircraft truss and composite material thin skin, described aircraft truss is connected by industrial cingulum fast with between composite material thin skin, it is characterized in that, described industrial cingulum adopts mushroom head cingulum, described mushroom head cingulum comprises the first engaged mushroom head and the second mushroom head, and the back side of the first mushroom head and the second mushroom head is equipped with glue-line, first mushroom head is fixed on aircraft truss by glue-line, and described second mushroom head is fixed on composite material thin skin by glue-line.
2. the overall fast joint structure of aviette composite material thin skin according to claim 1, is characterized in that, be provided with T-slot in the middle part of described aircraft truss, and described T-slot both sides are the locating surface installing composite material thin skin.
3. the overall fast joint structure of aviette composite material thin skin according to claim 2, it is characterized in that, described composite material thin skin is that benchmark is connected fast with aircraft truss with locating surface.
4. the overall fast joint structure of aviette composite material thin skin according to claim 2, is characterized in that, be provided with the aluminum alloy pressing plate of fixing composite material thin skin in described T-slot.
5. the overall fast joint structure of aviette composite material thin skin according to claim 1, it is characterized in that, the peel strength of described mushroom head cingulum is less than or equal to 6N ~ 7N, mushroom head cingulum width 23cm-28cm.
6., according to the method for making of the overall fast joint structure of the arbitrary described aviette composite material thin skin of claim 1-5, it is characterized in that, comprise the following steps:
Step one: choose industrial cingulum, the heating-up temperature when sectional dimension of the peel strength determination composite material thin skin be stripped when being fastened by industrial cingulum, the thickness of composite material thin skin, industrial cingulum glue-line are bondd for the first time and type of heating;
Step 2: the parts that step one is determined are cleared up and processed;
Step 3: the bonding completing the laying of composite material thin skin, industrial cingulum;
First the glue-line of the second mushroom head in mushroom head cingulum is bonded on composite material thin skin by the mode of heating, then by the first mushroom head glue-line by heating mode fit on aircraft truss, finally by composite material thin skin parallel laid on aircraft truss structure;
Step 4: complete the fixing of composite material thin skin;
Aluminum alloy pressing plate for compressing composite material thin skin being assemblied in aircraft truss structure, being fixed on aircraft truss structure by flathead screw;
Step 5: after said structure installation, carries out the debugging of integral composite light-skinned structure.
7. the overall fast joint structure of aviette composite material thin skin according to claim 6, it is characterized in that, the sectional dimension of composite material thin skin is 900mm ~ 1100mm × 400 ~ 600mm, the thickness 0.5mm ~ 1mm of composite material thin skin.
8. the overall fast joint structure of aviette composite material thin skin according to claim 6, is characterized in that, type of heating when industrial cingulum glue-line bonds for the first time is heating rod heating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510053729.XA CN104724277B (en) | 2015-02-03 | 2015-02-03 | Light aerocraft composite thin skin entirety fast joint structure and preparation method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510053729.XA CN104724277B (en) | 2015-02-03 | 2015-02-03 | Light aerocraft composite thin skin entirety fast joint structure and preparation method thereof |
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| CN104724277A true CN104724277A (en) | 2015-06-24 |
| CN104724277B CN104724277B (en) | 2017-11-24 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114915A (en) * | 2016-08-26 | 2016-11-16 | 西安融智航空科技有限公司 | A kind of safeguard structure of interconnected carrying heat-insulation integrative |
| CN106394860A (en) * | 2016-11-25 | 2017-02-15 | 中国工程物理研究院总体工程研究所 | Skin connecting structure capable of being disconnected after being stressed |
| CN107302135A (en) * | 2017-05-19 | 2017-10-27 | 哈尔滨哈玻拓普复合材料有限公司 | Metal frames radome triangular element block and its manufacture method |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU209465U1 (en) * | 2021-09-28 | 2022-03-16 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Composite vehicle compartment shell |
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| WO1988009289A1 (en) * | 1987-05-22 | 1988-12-01 | Grumman Aerospace Corporation | Structural members connected by interdigitating portions |
| US4909659A (en) * | 1989-02-06 | 1990-03-20 | Grumman Aerospace Corporation | Interlocking structural members employing transverse locking means |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114915A (en) * | 2016-08-26 | 2016-11-16 | 西安融智航空科技有限公司 | A kind of safeguard structure of interconnected carrying heat-insulation integrative |
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| CN107302135A (en) * | 2017-05-19 | 2017-10-27 | 哈尔滨哈玻拓普复合材料有限公司 | Metal frames radome triangular element block and its manufacture method |
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| Publication number | Publication date |
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| CN104724277B (en) | 2017-11-24 |
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Effective date of registration: 20190221 Address after: 213000 No. 199 Fenglin South Road, Wujin High-tech Industrial Development Zone, Changzhou City, Jiangsu Province Co-patentee after: Xinyu Defense Technology Co., Ltd. Patentee after: New United Group Co., Ltd. Address before: 213164 Fenglin Road 68, hi tech Industrial Development Zone, Wujin District, Changzhou, Jiangsu Patentee before: New United Group Co., Ltd. |