CN109605762B - Composite material unmanned aerial vehicle bonding structure and bonding method thereof - Google Patents
Composite material unmanned aerial vehicle bonding structure and bonding method thereof Download PDFInfo
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- CN109605762B CN109605762B CN201811405754.XA CN201811405754A CN109605762B CN 109605762 B CN109605762 B CN 109605762B CN 201811405754 A CN201811405754 A CN 201811405754A CN 109605762 B CN109605762 B CN 109605762B
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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
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- 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
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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
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a bonding structure of a composite material unmanned aerial vehicle and a bonding method thereof, wherein the bonding structure of the composite material unmanned aerial vehicle comprises bonding parts respectively formed on two mutually bonded components, and the bonding parts are respectively provided with butt joint surfaces; the inner surfaces of the bonding parts are respectively provided with inner inclined planes extending to the butt joint surfaces; the outer surfaces of the bonding parts are respectively provided with outer inclined planes extending to the butt joint surfaces; the butt joint surfaces are bonded through structural adhesive; and a plurality of fiber reinforced composite material layers are respectively bonded in the grooves formed between the inner inclined planes and the grooves formed between the outer inclined planes. The bonding structure and the bonding method of the composite material unmanned aerial vehicle solve the problems that the surface of a machine body is rough due to the inward flange caused by the existing bonding structure and the bonding method, the machine body cannot be polished or cut, the installation and the use of other equipment are influenced when the internal space of the unmanned aerial vehicle is smaller than the design space, and the like, so that the product strength is ensured, and the surface attractiveness is ensured.
Description
Technical Field
The invention relates to the field of composite material unmanned aerial vehicle manufacturing, in particular to a composite material unmanned aerial vehicle bonding structure and a bonding method thereof.
Background
Unmanned aerial vehicle is more and more extensive in the application on the market to the function is more and more, and the molding of unmanned aerial vehicle casing is also more and more complicated. The spare part preparation such as many rotor unmanned aerial vehicle and fixed wing unmanned aerial vehicle combined material fuselage, wing in the existing market is mostly the method of split mould preparation recombination shaping again, and present bonding mode is mostly the mode of preparation turn-ups flange to enlarge bonding area, bond fuselage, wing etc.. However, the unmanned aerial vehicle manufactured by the method has the problems that the unmanned aerial vehicle is not attractive, and the inner space of the unmanned aerial vehicle body is smaller than the design space, more importantly, the bonding strength of the method is low, and once the bonding glue falls off and the mold closing seam is opened due to the strength problem in flight, great danger is generated.
Disclosure of Invention
In view of the above disadvantages of the prior art, an object of the present invention is to provide a bonding structure of a composite material unmanned aerial vehicle and a bonding method thereof, which are used to solve the problems of low strength, weak structural performance, etc. of the composite material unmanned aerial vehicle caused by the existing bonding structure and bonding method.
In order to achieve the above objects and other related objects, the present invention provides a bonding structure of a composite material unmanned aerial vehicle, including bonding portions respectively formed on two mutually bonded components, the bonding portions being respectively provided with butt surfaces; the inner surfaces of the bonding parts are respectively provided with inner inclined planes extending to the butt joint surfaces; the outer surfaces of the bonding parts are respectively provided with outer inclined planes extending to the butt joint surfaces; the butt joint surfaces are bonded through structural adhesive; and a plurality of fiber reinforced composite material layers are respectively bonded in the grooves formed between the inner inclined planes and the grooves formed between the outer inclined planes.
Optionally, the maximum thickness of the inner bevel and/or the outer bevel accounts for 1/5-1/3 of the thickness of the part.
Preferably, the structural adhesive is a double-component structural adhesive, so that the strength, the stripping resistance and the impact resistance are improved, and the construction is simple and convenient.
Preferably, the fiber reinforced composite material layer is a fiber cloth layer.
Preferably, the structural adhesive is prepared by mixing resin and a curing agent according to a weight ratio of 100: 20.
The fiber cloth has the advantages of high specific rigidity, high wall rigidity, economic wear resistance, high internal temperature, internal complex and the like, and the fiber reinforced composite material layer is made of the carbon fiber cloth.
Another aspect of the present invention provides a bonding method for a composite material unmanned aerial vehicle, including the following steps:
1. cleaning the bonding part;
2. relatively fixing the two mutually bonded components;
3. coating structural adhesive between the butt joint surfaces and filling gaps;
4. bonding a plurality of carbon fiber reinforced composite material layers in a groove formed between the inner inclined surfaces through an adhesive until the carbon fiber reinforced composite material layers are flush with the inner surfaces of the two mutually bonded components;
5. and bonding a plurality of carbon fiber reinforced composite material layers in a groove formed between the outer inclined surfaces through an adhesive until the carbon fiber reinforced composite material layers are flush with the outer surfaces of the two mutually bonded components.
Preferably, after the plurality of carbon fiber reinforced composite material layers are cured, the surface of the bonding part is polished and cleaned.
According to the bonding method of the composite material unmanned aerial vehicle, the layer laying surface is covered with the layer of demolding cloth for extruding the layer laying surface to ensure flatness and attractiveness.
As described above, the bonding structure and the bonding method provided by the invention solve the problems that the surface of the machine body is rough due to the inverted flange caused by the existing bonding structure and bonding method, the machine body cannot be polished or cut, the installation and use of other equipment are influenced when the internal space of the unmanned aerial vehicle is smaller than the design space, and the like, so that the strength of the product is ensured, the attractiveness of the surface is ensured, and the size of the internal space of the product cannot be influenced due to the smoothness of the internal surface.
Drawings
FIG. 1 is a schematic illustration of a composite fuselage bonding configuration in accordance with one embodiment of the present invention.
In the figure: 1. fuselage, 2, fuselage, 11, bonding portion, 21, bonding portion, 111, butt-joint face, 112, inner bevel, 113, outer bevel, 211, butt-joint face, 212, inner bevel, 213, outer bevel.
Detailed Description
The structures, proportions, and dimensions shown in the drawings and described in the specification are for understanding and reading the present disclosure, and are not intended to limit the scope of the present disclosure, which is defined in the claims, and are not essential to the skilled in the art. In addition, the terms "upper", "lower", "front", "rear" and "middle" used in the present specification are for clarity of description, and are not intended to limit the scope of the present invention, and the relative relationship between the terms and the relative positions may be changed or adjusted without substantial technical changes.
As shown in fig. 1, the present embodiment provides a composite material unmanned aerial vehicle bonding structure, wherein the mutually bonded components (in the present embodiment, the fuselage 1 and the fuselage 2) each include a station bonding portion 11 and 21, the bonding portions 11 and 21 are respectively provided with the same butt surfaces 111 and 211, the inner surfaces of the bonding portions 11 and 21 are respectively provided with inner inclined surfaces 112 and 212 extending to the butt surfaces, and the outer surfaces of the bonding portions 11 and 21 are respectively provided with outer inclined surfaces 113 and 213 extending to the butt surfaces. Preferably the maximum thickness of each ramp is 1/5-1/3, more preferably 1/3, of the thickness of the fuselage. The bevel may be formed by grinding or die machining. The butting surfaces 111 and 211 are bonded through structural adhesive, and a plurality of fiber reinforced composite material layers are bonded in a groove formed between the inner inclined surfaces 112 and 212 and a groove formed between the outer inclined surfaces 113 and 213 respectively.
The embodiment also provides a bonding method of the composite material unmanned aerial vehicle with the bonding structure. Taking the fuselage bonding of the composite material unmanned aerial vehicle as an example, the bonding method comprises the following steps:
cleaning the bonding part 11 and the bonding part 21 with an ethanol cleaning agent;
the machine body 1 and the machine body 2 are relatively fixed through a tool;
the structural adhesive is applied between the abutting surface 111 and the bonding member 211 to fill the gap.
By means of an adhesive. Such as a mixed resin, bonds the fiber-toughened composite material layers in the grooves formed between the inner bevels 112 and 212. The layering process is repeated until the fiber reinforced composite material layer and the inner surfaces of the machine body 1 and the machine body 2 are cured for 12 hours at normal temperature.
By means of an adhesive. Such as a mixed resin, bonds the fiber-toughened composite material layers in the grooves formed between the outer bevels 113 and 213. And repeating the layering process until the fiber reinforced composite material layer and the outer surfaces of the machine body 1 and the machine body 2 are cured for 12 hours at normal temperature.
And (3) polishing the surfaces of the bonding part 11 and the bonding part 21, preferably 60-mesh and 240-mesh abrasive paper, ensuring that the laying layer is flush with the surface of the machine body, and wiping the surface of the product clean by using a cleaning agent such as alcohol after polishing to finish bonding.
The structural adhesive is preferably a two-component structural adhesive, such as an Elida 2015A/B structural adhesive, so as to improve the strength, the stripping resistance and the impact resistance, and meanwhile, the construction is simple and convenient. The fiber reinforced composite material is preferably fiber cloth, and the fiber cloth has the advantages of high specific strength, high wall rigidity, economic wear resistance, high internal temperature, high internal complex formula and the like, and for example, the carbon fiber cloth plays a role in enhancing the mechanical property of the fiber. The mixed resin as the adhesive is preferably prepared by mixing a resin and a curing agent at a weight ratio of 100:20, for example, M1 epoxy resin and 956 curing agent. Because the surface of the fiber cloth subjected to the layering treatment has the granular protrusions, a layer of demolding cloth can be covered on the surface of the layering after the layering is finished, and the surface of the layering is smooth and attractive under the action of gravity.
In conclusion, the bonding method of the composite material unmanned aerial vehicle is simple and efficient to operate, can effectively solve the problems that the surface of a machine body is rough due to the fact that an inverted flange is caused by an existing bonding structure and the existing bonding method, the machine body cannot be polished or cut, installation and use of other equipment are affected when the internal space of the unmanned aerial vehicle is smaller than the design space, and the like, and can improve the bonding strength.
The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Many modifications may be made to the present invention without departing from the spirit or scope of the general inventive concept, and it will be apparent to those skilled in the art that changes and modifications may be made to the above-described embodiments without departing from the spirit or scope of the invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (8)
1. The utility model provides a bonding structure of combined material unmanned aerial vehicle, includes the bonding portion that forms respectively on two mutual components that bond, its characterized in that:
the bonding parts are respectively provided with butt joint surfaces;
the inner surfaces of the bonding parts are respectively provided with inner inclined planes extending to the butt joint surfaces;
the outer surfaces of the bonding parts are respectively provided with outer inclined planes extending to the butt joint surfaces;
the butt joint surfaces are bonded through structural adhesive;
and a plurality of fiber reinforced composite material layers are respectively bonded in the grooves formed between the inner inclined planes and the grooves formed between the outer inclined planes.
2. The bonding structure of composite material unmanned aerial vehicle of claim 1, characterized in that:
the maximum thickness of the inner inclined plane and/or the outer inclined plane accounts for 1/5-1/3 of the thickness of the part.
3. The bonding structure of composite material unmanned aerial vehicle of claim 1, characterized in that:
the structural adhesive is a bi-component structural adhesive.
4. The bonding structure of composite material unmanned aerial vehicle of claim 1, characterized in that:
the fiber reinforced composite material layer is a fiber cloth layer.
5. The bonding structure of composite material unmanned aerial vehicle of claim 1, characterized in that:
the structural adhesive is prepared by mixing resin and a curing agent according to a weight ratio of 100: 20.
6. A method of bonding a composite drone using the bonded structure of claim 1, characterized by the steps of:
cleaning the bonding part;
relatively fixing the two mutually bonded components;
coating structural adhesive between the butt joint surfaces and filling gaps;
bonding a plurality of carbon fiber reinforced composite material layers in a groove formed between the inner inclined surfaces through an adhesive until the carbon fiber reinforced composite material layers are flush with the inner surfaces of the two mutually bonded components;
and bonding a plurality of carbon fiber reinforced composite material layers in a groove formed between the outer inclined surfaces through an adhesive until the carbon fiber reinforced composite material layers are flush with the outer surfaces of the two mutually bonded components.
7. The bonding method according to claim 6, characterized in that:
the multilayer carbon fiber reinforced composite material layer is covered with demolding cloth.
8. The bonding method according to claim 6, characterized in that:
and after the plurality of layers of carbon fiber reinforced composite material layers are cured, polishing and cleaning the surface of the bonding part.
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| CN201811405754.XA CN109605762B (en) | 2018-11-23 | 2018-11-23 | Composite material unmanned aerial vehicle bonding structure and bonding method thereof |
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| CN201811405754.XA CN109605762B (en) | 2018-11-23 | 2018-11-23 | Composite material unmanned aerial vehicle bonding structure and bonding method thereof |
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| CN109605762A CN109605762A (en) | 2019-04-12 |
| CN109605762B true CN109605762B (en) | 2021-04-30 |
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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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| CN101730618A (en) * | 2007-01-17 | 2010-06-09 | Airbusoperations有限公司 | The joint method of thermoplastic and fibrous composite |
| CN101898422A (en) * | 2009-05-27 | 2010-12-01 | 阿海珐输配电股份公司 | Assembly and method for assembling two tubes, fuse keeping device and its application |
| CN202685322U (en) * | 2012-06-20 | 2013-01-23 | 张万虎 | Connecting device for carbon fiber reinforced thermoplastic resin composite materials |
| CN102317054B (en) * | 2009-02-16 | 2013-11-27 | 积水化学工业株式会社 | Method for bonding cylindrical members, method for manufacturing composite cylindrical body, method for molding fiber-reinforced resin molded object and molded object |
| CN104371488A (en) * | 2014-11-05 | 2015-02-25 | 赵培仲 | Quick bonding repair method of ultraviolet-curing composite material |
| DE102013222970A1 (en) * | 2013-11-12 | 2015-05-13 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method for connecting two components, connecting portion of a component and composite component |
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2018
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Patent Citations (6)
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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 |
| CN102317054B (en) * | 2009-02-16 | 2013-11-27 | 积水化学工业株式会社 | Method for bonding cylindrical members, method for manufacturing composite cylindrical body, method for molding fiber-reinforced resin molded object and molded object |
| CN101898422A (en) * | 2009-05-27 | 2010-12-01 | 阿海珐输配电股份公司 | Assembly and method for assembling two tubes, fuse keeping device and its application |
| CN202685322U (en) * | 2012-06-20 | 2013-01-23 | 张万虎 | Connecting device for carbon fiber reinforced thermoplastic resin composite materials |
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| CN104371488A (en) * | 2014-11-05 | 2015-02-25 | 赵培仲 | Quick bonding repair method of ultraviolet-curing composite material |
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