阅读说明：本技术 一种复合材料无人机粘接结构及其粘接方法 (Composite material unmanned aerial vehicle bonding structure and bonding method thereof ) 是由 徐忠海 蔡朝灿 赫晓东 王荣国 杨帆 刘文博 于 2021-09-24 设计创作，主要内容包括：一种复合材料无人机粘接结构及其粘接方法,涉及一种粘接结构及其粘接方法。本发明解决了现有的无人机机身与机翼的连接处由于受力复杂,存在胶接处易断裂的问题。本发明的机身和机翼相对布置,机翼与机身之间插接,且通过结构胶胶接固定。方法：步骤一：对机身的连接部和机翼的连接部进行清洗；步骤二：先在机翼的连接部上涂覆有一层结构胶,将碳纤维增强复合层粘贴在结构胶上,再在碳纤维增强复合层上涂覆一层结构胶,静置20秒-40秒；步骤三：将机翼插装在机身上；步骤四：待机身与机翼的胶接处连接牢固后,在漏斗形的大端和倒漏斗形的大端贴附有纤维增强复合层,至此,完成了机身与机翼的连接。本发明用于无人机粘接。(A composite material unmanned aerial vehicle bonding structure and a bonding method thereof relate to a bonding structure and a bonding method thereof. The invention solves the problem that the joint of the fuselage and the wing of the existing unmanned aerial vehicle is easy to break due to complex stress. The fuselage and the wings of the aircraft are oppositely arranged, and the wings are inserted into the fuselage and are fixed by structural adhesive. The method comprises the following steps: the method comprises the following steps: cleaning the connecting part of the fuselage and the connecting part of the wing; step two: coating a layer of structural adhesive on a connecting part of the wing, pasting the carbon fiber reinforced composite layer on the structural adhesive, coating a layer of structural adhesive on the carbon fiber reinforced composite layer, and standing for 20-40 seconds; step three: inserting the wings on the fuselage; step four: after the glue joint of the fuselage and the wing is firmly connected, fiber reinforced composite layers are attached to the funnel-shaped large end and the inverted funnel-shaped large end, so that the connection of the fuselage and the wing is completed. The invention is used for bonding the unmanned aerial vehicle.)

1. The utility model provides a combined material unmanned aerial vehicle bonding structure, it includes fuselage (1) and wing (2), its characterized in that: the aircraft further comprises a structural adhesive (3), the aircraft body (1) and the wings (2) are oppositely arranged, the wings (2) and the aircraft body (1) are spliced, and are fixedly connected through the structural adhesive (3) with the carbon fiber reinforced composite layer;

an upper transition boss (1-1), a first splicing lug (1-2), a second splicing lug (1-3), a machine body connecting piece (1-4) and a lower transition boss (1-5) are sequentially arranged on a connecting part of the machine body (1) from top to bottom, and a machine body splicing groove (1-6) is arranged between the first splicing lug (1-2) and the second splicing lug (1-3); an upper floating abdicating boss (2-1), a wing connecting piece (2-2), a third splicing lug (2-3) and a lower floating abdicating boss (2-4) are sequentially arranged at the connecting part of the wing (2) from top to bottom, and a wing splicing groove (2-5) is arranged between the third splicing lug (2-3) and the lower floating abdicating boss (2-4); the aircraft body connecting piece (1-4) is inserted in the wing inserting groove (2-5), the wing connecting piece (2-2) is inserted in the aircraft body inserting groove (1-6), and the first inserting convex block (1-2) and the second inserting convex block (1-3) on the aircraft body (1) are matched with the third inserting convex block (2-3) and the lower floating abdicating convex block (2-4) on the aircraft wing (2) in a concave-convex inserting manner.

2. The composite material unmanned aerial vehicle bonding structure of claim 1, wherein: the gap between the upper transition boss (1-1) and the upper floating abdication boss (2-1) forms a funnel shape.

3. The composite material unmanned aerial vehicle bonding structure of claim 2, wherein: gaps between the lower transition bosses (1-5) and the lower floating abdicating bosses (2-4) form an inverted funnel shape.

4. The composite material unmanned aerial vehicle bonding structure of claim 3, wherein: the gap between the wing (2) and the fuselage (1) is 2-10 mm.

5. The composite material unmanned aerial vehicle bonding structure of claim 4, wherein: the end parts of the fuselage connecting pieces (1-4) and the wing connecting pieces (2-2) are T-shaped connecting pieces.

6. The composite material unmanned aerial vehicle bonding structure of claim 5, wherein: the novel funnel-shaped composite material is characterized by further comprising a fiber reinforced composite layer (4), wherein the fiber reinforced composite layer (4) is respectively arranged at the funnel-shaped large end and the inverted funnel-shaped large end.

7. The composite material unmanned aerial vehicle bonding structure of claim 6, wherein: the distance between the upper part and the lower part of the connection part of the fuselage (1) and the wing (2) is gradually increased.

8. A bonding method of a composite material unmanned aerial vehicle bonding structure according to any one of claims 1 to 7, characterized in that: it comprises the following steps:

the method comprises the following steps: cleaning the connecting part of the fuselage (1) and the connecting part of the wing (2);

step two: firstly, coating a layer of structural adhesive (3) on a connecting part of the wing (2), pasting a carbon fiber reinforced composite layer on the structural adhesive (3), then coating a layer of structural adhesive (3) on the carbon fiber reinforced composite layer, and standing for 20-40 seconds;

step three: inserting the wings (2) on the fuselage (1);

in the insertion process, the wings (2) slide in the fuselage (1) in a reciprocating manner, and the structural adhesive (3) is fixed after being viscous;

step four: after the glue joint of the fuselage (1) and the wing (2) is firmly connected, fiber reinforced composite layers (4) are attached to the funnel-shaped large end and the inverted funnel-shaped large end, so that the connection of the fuselage (1) and the wing (2) is completed.

9. The bonding method according to claim 8, characterized in that: the carbon fiber reinforced composite layer is adhered to the structural adhesive (3) in a corrugated form.

Technical Field

The invention relates to a bonding structure and a bonding method thereof, in particular to a bonding structure of a composite material unmanned aerial vehicle and a bonding method thereof, and belongs to the field of composite material unmanned aerial vehicle manufacturing.

Background

Along with the continuous increase of unmanned aerial vehicle application, according to the user to the difference of unmanned aerial vehicle performance demand, directly influenced unmanned aerial vehicle's manufacture craft and unmanned aerial vehicle's structure. And the connected mode between present unmanned aerial vehicle fuselage and the wing also is different because of its different performance demands, for example: some fuselages and wings need to be spliced, some fuselages and wings need to be glued, and some fuselages and wings need to be integrally formed.

When adopting the adhesive bonding mode, prior art makes the toper respectively with the connecting portion of fuselage and wing, then glues, though this mode occupies the problem of fuselage inner space when having avoided bolted connection, nevertheless because unmanned aerial vehicle can produce shake, vibration at the flight in-process, because fuselage and wing junction atress are complicated, have the easy cracked problem of splice.

In conclusion, the problem that the joint of the existing unmanned aerial vehicle body and the existing wing is easy to break due to complex stress at the joint is solved.

Disclosure of Invention

The invention aims to solve the problem that the joint of the fuselage and the wing of the existing unmanned aerial vehicle is easy to break due to complex stress. And further provides a composite material unmanned aerial vehicle bonding structure and a bonding method thereof.

The technical scheme of the invention is that the bonding structure of the composite material unmanned aerial vehicle comprises a fuselage, wings and structural adhesive, wherein the fuselage and the wings are arranged oppositely, and the wings are spliced with the fuselage and are bonded and fixed by the structural adhesive with a carbon fiber reinforced composite layer; the connecting part of the machine body is sequentially provided with an upper transition boss, a first splicing lug, a second splicing lug, a machine body connecting piece and a lower transition boss from top to bottom, and a machine body splicing groove is arranged between the first splicing lug and the second splicing lug; the connecting part of the wing is sequentially provided with an upper floating abdicating boss, a wing connecting piece, a third splicing lug and a lower floating abdicating boss from top to bottom, and a wing splicing groove is arranged between the third splicing lug and the lower floating abdicating boss; the first inserting lug and the second inserting lug on the machine body are in concave-convex inserting fit with the third inserting lug and the lower floating abdicating lug on the wing.

The invention also provides a bonding method, which comprises the following steps:

the method comprises the following steps: cleaning the connecting part of the fuselage and the connecting part of the wing;

step two: coating a layer of structural adhesive on a connecting part of the wing, pasting the carbon fiber reinforced composite layer on the structural adhesive, coating a layer of structural adhesive on the carbon fiber reinforced composite layer, and standing for 20-40 seconds;

step three: inserting wings on the fuselage 1;

in the inserting process, the wings slide in the fuselage in a reciprocating manner, and the wings are fixed after the structural adhesive is sticky;

step four: after the glue joint of the fuselage and the wing is firmly connected, fiber reinforced composite layers are attached to the funnel-shaped large end and the inverted funnel-shaped large end, so that the connection of the fuselage and the wing is completed.

Compared with the prior art, the invention has the following improvement effects:

1. the connection between the fuselage and the wings adopts a mode of combining glue joint and splicing joint, compared with the traditional glue joint, the connection mode can effectively avoid and reduce the problem of wing cracking, because the gap between the wing 2 and the fuselage 1 is 2-10mm, the gap is filled with structural adhesive, the structural adhesive has certain flexibility, and the flexibility can play a role in deformation of the wing during vibration and shaking.

2. The plug-in structure adopted by the invention can prevent the wings and the body from falling off, and ensures the safety performance of the unmanned aerial vehicle in the flying process.

3. The bonding method is simple, and the carbon fiber reinforced composite layer is filled between the structural adhesives and bonded in a wrinkle mode, so that the connection strength can be increased, and the composite layer is clamped in the wing inserting grooves 2-5 and the fuselage inserting grooves 1-6, so that the connection strength between the whole wing and the fuselage is ensured.

Drawings

FIG. 1 is a schematic view of a wing mounted to a fuselage. FIG. 2 is a schematic view of the structure of the connection between the wing and the fuselage.

Detailed Description

The first embodiment is as follows: the embodiment is described with reference to fig. 1 to 2, and the bonding structure of the composite material unmanned aerial vehicle of the embodiment comprises a fuselage 1, wings 2 and a structural adhesive 3, wherein the fuselage 1 and the wings 2 are arranged oppositely, and the wings 2 are inserted into the fuselage 1 and are bonded and fixed by the structural adhesive 3 with a carbon fiber reinforced composite layer; the connecting part of the machine body 1 is sequentially provided with an upper transition lug boss 1-1, a first splicing lug boss 1-2, a second splicing lug boss 1-3, a machine body connecting piece 1-4 and a lower transition lug boss 1-5 from top to bottom, and a machine body splicing groove 1-6 is arranged between the first splicing lug boss 1-2 and the second splicing lug boss 1-3; an upper floating abdicating boss 2-1, a wing connecting piece 2-2, a third splicing lug 2-3 and a lower floating abdicating boss 2-4 are sequentially arranged at the connecting part of the wing 2 from top to bottom, and a wing splicing groove 2-5 is arranged between the third splicing lug 2-3 and the lower floating abdicating boss 2-4; the aircraft body connecting piece 1-4 is inserted in the wing inserting groove 2-5, the wing connecting piece 2-2 is inserted in the aircraft body inserting groove 1-6, and the first inserting convex block 1-2 and the second inserting convex block 1-3 on the aircraft body 1 are in concave-convex inserting fit with the third inserting convex block 2-3 and the lower floating abdicating convex block 2-4 on the aircraft wing 2.

The second embodiment is as follows: referring to fig. 2, the gap between the upper transition boss 1-1 and the upper floating abdicating boss 2-1 of the present embodiment is funnel-shaped. So set up, the funnel main aspects of being convenient for can provide sufficient flexible force when receiving the wing shake or vibration from top to bottom. Other components and connections are the same as in the first embodiment.

The third concrete implementation mode: referring to fig. 2, the gap between the lower transition boss 1-5 and the lower floating abdicating boss 2-4 of the present embodiment is formed in an inverted funnel shape. So set up, the funnel main aspects of being convenient for can provide sufficient flexible force when receiving the wing shake or vibration from top to bottom. Other compositions and connections are the same as in the first or second embodiments.

The fourth concrete implementation mode: referring to fig. 2, the gap between the wing 2 and the fuselage 1 of the present embodiment is 2-10 mm. So set up, be convenient for provide sufficient flexible power, can fuse into carbon fiber reinforced composite bed simultaneously. Other compositions and connection relationships are the same as in the first, second or third embodiment.

The fifth concrete implementation mode: referring to fig. 2, the end parts of the fuselage connection piece 1-4 and the wing connection piece 2-2 of the present embodiment are both T-shaped connection pieces. Due to the arrangement, the connection strength is convenient to improve, and the falling off between the fuselage and the wings can be prevented; other compositions and connection relationships are the same as those in the first, second, third or fourth embodiment.

The sixth specific implementation mode: the present embodiment is described with reference to fig. 2, and the present embodiment further includes a fiber-reinforced composite layer 4, and the fiber-reinforced composite layer 4 is attached to the funnel-shaped large end and the inverted funnel-shaped large end, respectively. So set up, prevent that the structural layer from using the back for a long time, causing ageing and joint strength low problem. Other compositions and connection relationships are the same as in the first, second, third, fourth or fifth embodiment.

The seventh embodiment: the present embodiment is described with reference to fig. 2, in which the distance between the upper and lower portions of the connection portion between the fuselage 1 and the wing 2 is increased. So set up, provide sufficient bending deformation space for the wing during vibration and shake. Other components and connection relations are the same as those of any one of the first to sixth embodiments.

The specific implementation mode is eight: the present embodiment will be described with reference to fig. 2, and the bonding method of the present embodiment includes the steps of:

the method comprises the following steps: cleaning the connecting part of the fuselage 1 and the connecting part of the wing 2;

step two: firstly, coating a layer of structural adhesive 3 on a connecting part of the wing 2, pasting a carbon fiber reinforced composite layer on the structural adhesive 3, coating a layer of structural adhesive 3 on the carbon fiber reinforced composite layer, and standing for 20-40 seconds;

step three: inserting the wings 2 on the fuselage 1;

in the inserting process, the wings 2 slide in the fuselage 1 in a reciprocating manner, and the structural adhesive 3 is fixed after being viscous;

step four: after the glue joint of the fuselage 1 and the wing 2 is firmly connected, the large funnel-shaped end and the large inverted funnel-shaped end are attached with the fiber reinforced composite layer 4, so that the connection of the fuselage 1 and the wing 2 is completed.

The specific implementation method nine: the present embodiment will be described with reference to fig. 2, in which the carbon fiber reinforced composite layer of the present embodiment is attached to the structural adhesive 3 in the form of wrinkles. So set up, be convenient for improve joint strength. Other compositions and connection relations are the same as those of any one of the first to eighth embodiments.

The carbon fiber reinforced composite material used in the present embodiment is a fiber cloth layer, and can play a role in enhancing mechanical properties by fibers.

The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.