CN109605762A - A kind of composite material unmanned plane bonded structure and its adhering method - Google Patents
A kind of composite material unmanned plane bonded structure and its adhering method Download PDFInfo
- Publication number
- CN109605762A CN109605762A CN201811405754.XA CN201811405754A CN109605762A CN 109605762 A CN109605762 A CN 109605762A CN 201811405754 A CN201811405754 A CN 201811405754A CN 109605762 A CN109605762 A CN 109605762A
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- China
- Prior art keywords
- plane
- composite material
- bonded
- unmanned plane
- outer inclined
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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
- B29C65/52—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 way of applying the adhesive
- B29C65/54—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 way of applying the adhesive between pre-assembled parts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- 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
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
Abstract
The present invention provides the bonded structure and its adhering method of a kind of composite material unmanned plane, and the bonded structure of composite material unmanned plane includes the adhesive portion being respectively formed on the component that two are mutually bonded, and adhesive portion is respectively equipped with interface；The inner surface of adhesive portion is respectively equipped with the outer inclined-plane for extending to interface；The outer surface of adhesive portion is respectively equipped with the outer inclined-plane for extending to interface；Interface passes through structure glue sticking；Multi-layer fiber enhancing composite layer is bonded in the groove formed in the groove formed between outer inclined-plane and between outer inclined-plane respectively.It is coarse that composite material unmanned plane bonded structure and adhering method provided by the invention solve body surface caused by varus flange caused by existing bonded structure and adhering method, and polishing or cutting process cannot be carried out to it, unmanned plane inner space is less than the problems such as design space will affect the installation and use of other equipment, both guarantee product strength, ensure that the aesthetics on surface.
Description
Technical field
The present invention relates to composite material unmanned plane production field, especially a kind of composite material unmanned plane bonded structure and its
Adhering method.
Background technique
Unmanned plane is applied more and more extensive in the market, and function is more and more, and the moulding of unmanned plane shell is also got over
Come more complicated.The components such as multi-rotor unmanned aerial vehicle and fixed-wing unmanned plane composite material fuselage, wing production currently on the market is more
Make the molding method of recombinant for a point molding, and bonding way is mostly to make the mode of Flange at present, to expand bonding plane
Product, is bonded fuselage, wing etc..But the method production unmanned plane exist unsightly, fuselage interior space be less than design
The problem of space, it is often more important that the adhesive strength of the method is lower, once in-flight since strength problem causes bonded adhesives de-
It falls molding seam to open, then can generate biggish risk.
Summary of the invention
In view of the foregoing deficiencies of prior art, the purpose of the present invention is to provide a kind of the viscous of composite material unmanned plane
Binding structure and its adhering method, for solve composite material unmanned plane intensity caused by existing bonded structure and adhering method it is low,
The problems such as structural behaviour is weak.
In order to achieve the above objects and other related objects, the present invention provides a kind of bonded structure packet of composite material unmanned plane
The adhesive portion being respectively formed on the component that two are mutually bonded is included, the adhesive portion is respectively equipped with interface；The adhesive portion
Inner surface is respectively equipped with the outer inclined-plane for extending to interface；The outer surface of the adhesive portion, which is respectively equipped with, extends to the outer of interface
Inclined-plane；The interface passes through structure glue sticking；Shape in the groove that is formed between the outer inclined-plane and between the outer inclined-plane
At groove in be bonded with respectively multi-layer fiber enhancing composite layer.
Optionally, the maximum gauge on the outer inclined-plane and/or the outer inclined-plane accounts for the 1/5~1/3 of the component thickness.
Preferably, the structure glue is bicomponent structure glue, to improve intensity, antistripping, impact resistance while construct
It is easy.
Preferably, the fibre reinforced composites layer is scrim cloth.
Preferably, the bonding agent is mixed with by resin and curing agent according to weight ratio 100:20.
Due to fiber cloth it is with higher than stiffness, wall rigidity with economic wearability, interior high temperature and it is interior compound the advantages that, institute
State fibre reinforced composites layer choosing carbon cloth.
Another aspect of the present invention is to provide a kind of adhering method of composite material unmanned plane, including the following steps:
1, the adhering part is cleaned；
2, the component being mutually bonded described two is relatively fixed；
3, structure glue is applied between the interface and fills up gap；
4, it is bonded multilayer carbon-fiber-reinforcomposite composite material layer in the groove formed between the outer inclined-plane by bonding agent,
Until the inner surface for the component that fibre reinforced composites layer is mutually bonded with described two flushes；
5, it is bonded multilayer carbon-fiber-reinforcomposite composite material layer in the groove formed between the outer inclined-plane by bonding agent,
Until the outer surface for the component that fibre reinforced composites layer is mutually bonded with described two flushes.
Preferably, it after multilayer carbon-fiber-reinforcomposite composite material layer solidification, polishes the adhesive portion surface
And cleaning.
The adhering method of above-mentioned composite material unmanned plane, the laying surface covers one layer of release cloth, for squeezing laying
Surface is smooth and beautiful to guarantee.
As described above, bonded structure provided by the invention and adhering method solve existing bonded structure and adhering method is led
Body surface caused by the varus flange of cause is coarse, and it cannot be carried out polishing or cutting process, unmanned plane inner space it is small
In design space will affect the installation and use of other equipment the problems such as, both guarantees product strength, ensure that the beauty on surface
Property, and due to inner surface planarization, it will not influence the size of the inner space of product.
Detailed description of the invention
Fig. 1 is the composite material fuselage bonded structure schematic diagram in one implementation of the present invention.
In figure: 1, fuselage, 2, fuselage, 11, adhesive portion, 21, adhesive portion, 111, interface, 112, outer inclined-plane, 113, it is outer tiltedly
Face, 211, interface, 212, outer inclined-plane, 213, outer inclined-plane.
Specific embodiment
Structure depicted in Figure of description, ratio, size etc., only to cooperate the revealed content of specification, with
Understand for those skilled in the art and read, be not intended to limit the invention enforceable qualifications, therefore does not have technically
Essential meaning, the modification of any structure, the change of proportionate relationship or the adjustment of size can be generated not influencing the present invention
Under effect and the purpose that can reach, should all still it fall in the range of disclosed technology contents can cover.Meanwhile
Cited such as "upper", "lower", "front", "rear", " centre " term in this specification are merely convenient to being illustrated for narration, and
It is non-that to limit the scope of the invention, relativeness is altered or modified, under the content of no substantial changes in technology, when
Also it is considered as the enforceable scope of the present invention.
As shown in Figure 1, the present embodiment provides a kind of composite material unmanned plane bonded structure, component (this reality for being mutually bonded
Apply in example as fuselage 1 and fuselage 2) it include station adhesive portion 11 and 21, adhesive portion 11 and 21 is respectively equipped with identical interface 111
With 211, the inner surface of adhesive portion 11 and 21 is all provided with the outer inclined-plane 112 and 212 for extending to interface, the appearance of adhesive portion 11 and 21
Face is all provided with the outer inclined-plane 113 and 213 for extending to interface.It is preferred that the maximum gauge on each inclined-plane accounts for the 1/5-1/3 of fuselage thickness,
More preferably 1/3.Inclined-plane can be formed by the modes such as polishing or mold processing.Pass through structure glue between interface 111 and 211
It is bonded, is glued respectively in the groove formed in the groove of the formation between outer inclined-plane 112 and 212 and between outer inclined-plane 113 and 213
It is connected to multi-layer fiber enhancing composite layer.
The present embodiment also provides a kind of adhering method of composite material unmanned plane with above-mentioned bonded structure.With composite wood
For expecting for the fuselage bonding of unmanned plane, adhering method includes the following steps:
Adhesive portion 11 and adhesive portion 21 are cleaned using ethyl alcohol cleaning agent；
It is by tooling that fuselage 1 and fuselage 2 is relatively fixed；
Structure glue is applied between interface 111 and adhering part 211 and fills up gap.
Pass through bonding agent.Such as hybrid resin, bondable fibers toughening in the groove formed between outer inclined-plane 112 and 212
Composite layer.The above laying process is repeated, until the inner surface of fibre reinforced composites layer and fuselage 1 and fuselage 2, room temperature
Solidification 12 hours.
Pass through bonding agent.Such as hybrid resin, bondable fibers toughening in the groove formed between outer inclined-plane 113 and 213
Composite layer.The above laying process is repeated, until the outer surface of fibre reinforced composites layer and fuselage 1 and fuselage 2, room temperature
Solidification 12 hours.
It polishes adhesive portion 11 and 21 surface of adhesive portion, is preferably polished with 60 mesh and 240 mesh sand paper, it is ensured that paving
Layer is concordant with fuselage surface, is wiped clean product surface using cleaning agents such as alcohol after polishing, completes bonding.
The preferred bicomponent structure glue of structure glue, such as love jail reach 2015A/B structure glue, to improve intensity, antistripping, resistance to punching
Hit performance, while easy construction.The preferred fiber cloth of fibre reinforced composites, fiber cloth specific strength with higher, wall rigidity
With economic wearability, interior high temperature and it is interior compound the advantages that, such as carbon cloth plays the role of fiber reinforcement mechanical property.Make
Preferably be mixed with by resin and curing agent according to weight ratio 100:20 for the hybrid resin of bonding agent, for example, M1 epoxy resin and
956 curing agent are mixed with.It can be since the fiber cloth surface that handles through laying is there are graininess protrusion, after the completion of laying
Laying surface, which covers one layer of release cloth, makes laying surfacing and beauty by gravity.
In conclusion operation is easy and efficient for the adhering method of composite material unmanned plane of the present invention, can effectively solve the problem that existing
Body surface caused by varus flange caused by bonded structure and adhering method is coarse, and polishing or cut place cannot be carried out to it
Reason, unmanned plane inner space is less than the problems such as design space will affect the installation and use of other equipment, while can be improved viscous
Connect intensity.
The principle of the present invention and its effect is only illustrated in above embodiment, and is not intended to limit the present invention.This hair
It is bright to be improved under the premise of without prejudice to overall thought there are many more aspect, it all can be for those skilled in the art
Without prejudice under spirit and scope of the invention, can carry out modifications and changes to above-described embodiment.Therefore, technical field such as
Middle all equivalent modifications for being completed without departing from the spirit and technical ideas disclosed in the present invention of tool usually intellectual or
Change, should be covered by the claims of the present invention.
Claims (8)
1. a kind of bonded structure of composite material unmanned plane, including the adhesive portion being respectively formed on the component that two are mutually bonded,
It is characterized by:
The adhesive portion is respectively equipped with interface；
The inner surface of the adhesive portion is respectively equipped with the outer inclined-plane for extending to interface；
The outer surface of the adhesive portion is respectively equipped with the outer inclined-plane for extending to interface；
The interface passes through structure glue sticking；
Multilayer fibre is bonded in the groove formed in the groove formed between the outer inclined-plane and between the outer inclined-plane respectively
Dimension enhancing composite layer.
2. the bonded structure of composite material unmanned plane according to claim 1, it is characterised in that:
The maximum gauge on the outer inclined-plane and/or the outer inclined-plane accounts for the 1/5~1/3 of the component thickness.
3. the bonded structure of composite material unmanned plane according to claim 1, it is characterised in that:
The structure glue is bicomponent structure glue.
4. the bonded structure of composite material unmanned plane according to claim 1, it is characterised in that:
The fibre reinforced composites layer is scrim cloth.
5. the bonded structure of composite material unmanned plane according to claim 1, it is characterised in that:
The bonding agent is mixed with by resin and curing agent according to weight ratio 100:20.
6. a kind of adhering method of the composite material unmanned plane using bonded structure described in claim 1, which is characterized in that including
The following steps:
The adhering part is cleaned；
The component that described two are mutually bonded is relatively fixed；
Structure glue is applied between the interface and fills up gap；
Multilayer carbon-fiber-reinforcomposite composite material layer is bonded in the groove formed between the outer inclined-plane by bonding agent, until fine
The inner surface for the component that dimension enhancing composite layer is mutually bonded with described two flushes；
Multilayer carbon-fiber-reinforcomposite composite material layer is bonded in the groove formed between the outer inclined-plane by bonding agent, until fine
The outer surface for the component that dimension enhancing composite layer is mutually bonded with described two flushes.
7. adhering method according to claim 6, it is characterised in that:
The multilayer carbon-fiber-reinforcomposite composite material layer is covered with release cloth.
8. adhering method according to claim 6, it is characterised in that:
After multilayer carbon-fiber-reinforcomposite composite material layer solidification, the surface of the adhesive portion is polished and cleaned.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811405754.XA CN109605762B (en) | 2018-11-23 | 2018-11-23 | Composite material unmanned aerial vehicle bonding structure and bonding method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811405754.XA CN109605762B (en) | 2018-11-23 | 2018-11-23 | Composite material unmanned aerial vehicle bonding structure and bonding method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109605762A true CN109605762A (en) | 2019-04-12 |
| CN109605762B CN109605762B (en) | 2021-04-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811405754.XA Active CN109605762B (en) | 2018-11-23 | 2018-11-23 | Composite material unmanned aerial vehicle bonding structure and bonding method thereof |
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| Country | Link |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110561765A (en) * | 2019-07-26 | 2019-12-13 | 中国航空工业集团公司济南特种结构研究所 | Connecting method for large-size composite material parts |
| CN113665782A (en) * | 2021-09-24 | 2021-11-19 | 肇庆市海特复合材料技术研究院 | Composite material unmanned aerial vehicle bonding structure and bonding method thereof |
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| CN101730618A (en) * | 2007-01-17 | 2010-06-09 | Airbusoperations有限公司 | The joint method of thermoplastic and fibrous composite |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110561765A (en) * | 2019-07-26 | 2019-12-13 | 中国航空工业集团公司济南特种结构研究所 | Connecting method for large-size composite material parts |
| CN113665782A (en) * | 2021-09-24 | 2021-11-19 | 肇庆市海特复合材料技术研究院 | Composite material unmanned aerial vehicle bonding structure and bonding method thereof |
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| Publication number | Publication date |
|---|---|
| CN109605762B (en) | 2021-04-30 |
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