Carbon fiber composite material integrated unmanned aerial vehicle forming method and unmanned aerial vehicle obtained through method

Abstract

The invention relates to the field of unmanned aerial vehicles, in particular to a carbon fiber composite integrated unmanned aerial vehicle forming method and an unmanned aerial vehicle obtained through the method, the unmanned aerial vehicle is integrally laid into two layers, and a reinforcing layer is added to a motor base of the unmanned aerial vehicle and a covering cap of the unmanned aerial vehicle; two reinforcing layers are additionally arranged at the joints of the outer sides of the machine legs and the machine arms and the machine body; three reinforcing layers are additionally arranged on the inner sides of the legs and the lower side of the belly; and ten reinforcing layers are added in the central area of the motor base. Through the layer laying design, on the premise that the bearing requirement is met, the weight is reduced by 50% or above, energy consumption is effectively reduced, and meanwhile the excellent performance of carbon fibers is utilized, so that the high strength, corrosion resistance, low thermal expansion coefficient and fatigue resistance are achieved, and meanwhile the electromagnetic effect is considered. And through die integrated forming, the number of parts and fasteners is reduced, the assembling process is reduced, and errors caused by assembling are avoided. And compared with the traditional process, the manufacturing production has the advantages that circulation procedures are reduced, related manufacturing tools and fixtures are omitted, and the manufacturing cost is reduced.

Description

Technical Field

[0001] The invention relates to the field of carbon fiber composite material integrated unmanned aerial vehicle molding, and in particular to a carbon fiber composite material integrated unmanned aerial vehicle molding method and a unmanned aerial vehicle obtained by the method. Background Art

[0002] Currently in the field of drones, the connection points and weight of various drone components have significantly reduced the flight performance of drones; metal materials are dense and heavy, which means limited endurance and flight speed, which is limited for performing long-distance reconnaissance, cargo transportation, environmental monitoring and other tasks; and traditional drones usually require multiple parts to be assembled, which is a cumbersome production process; traditional drones often use traditional metal materials, which have poor corrosion resistance in harsh environments, which may cause damage to the drone structure and affect its service life.

[0003] In order to solve the above problems, the prior art discloses a method of using carbon fiber composite materials to form UAV parts; for example, patent CN118306030A discloses a method for manufacturing a reinforced wall panel of a water UAV made of carbon fiber composite materials; patent CN113211823B discloses a method for forming a wing of a UAV made of carbon fiber composite materials; patent CN212709933U discloses a multi-wall wing of a UAV made of carbon fiber composite materials; patent CN110843234A discloses a process method for forming a main beam of a UAV made of carbon fiber composite materials; patent CN117382217A discloses a method for forming an entire UAV, and so on, especially patent CN117382217A discloses a method for forming an entire UAV, which is also based on one-piece forming of carbon fiber composite materials, and includes, S1, tooling preparation, checking the equipment to be used; S2, preheating the mold; S3, paving treatment, paving according to the ply information table, and the unidirectional belt is laid along the fiber Directional butt splicing; overlapping of fabrics in non-matching areas is allowed; incisions are allowed in areas prone to bridging, sharp turning areas, and areas where components meet on three sides; S4, bag making, the bag making process includes: S41, laying a tear-off layer in the fuselage position area, first laying a layer of isolation film on the parts, placing the special-shaped airbags coated with release agent on the tooling, folding the corresponding positions of the special-shaped airbags, and using the flanged prepreg to completely wrap the special-shaped airbags. After wrapping, check the wrapping conditions of all flanged areas. For those that are not wrapped, cut the corresponding sheets for S42, mold closing process; S43, wrap and protect the tooling, fill the sealing groove of the tooling with sealing strips, and then make mother-and-child bags; S44, check the airtightness, and vacuum the molding mold for leakage inspection; S5, curing process, vacuum the molding mold for the second system; S6, demoulding process, remove the vacuum bag on the tooling, remove the corresponding bolts and nuts on it, and take out the workpiece; S7, demoulding inspection process; S8, manual processing, manually remove the edge burrs and glue overflow at the mold seam, and do not process other holes. However, in the steps of carbon fiber paving, the patent only discloses that paving work should be carried out according to the ply information table, and defects such as inclusions and bridging are not allowed during the paving process; unidirectional tapes are butt-jointed along the fiber direction with a gap of ≤1mm; fabrics in non-matching areas are allowed to overlap with a width of 12mm to 25mm; cuts are allowed in areas prone to bridging, sharp turning areas, and areas where three sides of the component meet; the size range of the cut gap is -1mm to 0mm, and the seams of the same 4 layers are staggered by at least 25mm; in fact, how the carbon fiber layers of each component of the drone are laid directly affects the load-bearing performance and quality of the drone. Summary of the invention

[0004] In order to propose a UAV that can meet the requirements of load-bearing performance and quality, the present invention discloses a carbon fiber composite material integrated UAV molding method, and the carbon fiber ply design of different parts of the UAV is made to meet certain load-bearing performance and quality requirements.

[0005] The technical solution adopted by the present invention is as follows:

[0006] In a first aspect, the present invention provides a carbon fiber composite integrated drone molding method, including carbon fiber laying; wherein two layers are laid on the entire drone, and a reinforcement layer is added at the motor seat of the drone and the position of the drone cover; two reinforcement layers are added at the outer side of the legs and the connection between the arms and the fuselage; three reinforcement layers are added on the inner side of the legs and the lower side of the belly; and ten reinforcement layers are added in the central area of ​​the motor seat;

[0007] The drone is laid with two layers as a whole, the first layer is a carbon fiber 0° layer; the second layer is a carbon fiber 90° layer; wherein the 0° direction is along the heading of the drone;

[0008] The reinforcement layers at the motor seat and the mouth cover of the drone are carbon fiber 0° plies;

[0009] The two reinforcement layers at the connection between the outer side of the machine leg and the machine arm fuselage are carbon fiber 90° ply and carbon fiber 0° ply from inside to outside.

[0010] The three reinforcement layers on the inner side of the machine leg and the lower side of the machine belly are, from inside to outside, carbon fiber 45° ply, carbon fiber 90° ply and carbon fiber 0° ply.

[0011] The ten reinforcement layers in the central area of ​​the motor base are, from inside to outside, carbon fiber 45° ply, carbon fiber 90° ply, carbon fiber 0° ply, carbon fiber 45° ply, carbon fiber -45° ply, carbon fiber 0° ply, carbon fiber 90° ply, carbon fiber 45° ply, carbon fiber 90° ply and carbon fiber 0° ply.

[0012] As a further technical solution, the overall laying of the UAV is to first lay a first layer of carbon fiber on the corresponding mold, and then lay a second layer of carbon fiber on the corresponding mold.

[0013] As a further technical solution, the method of adding a reinforcement layer at the position of the motor seat and the mouth cover of the drone is to lay another reinforcement layer on the mold corresponding to the motor seat and the mouth cover of the drone after the entire drone is laid.

[0014] As a further technical solution, the two reinforcement layers are added at the connection between the outer side of the legs and the arms and fuselage. After the overall laying of the UAV is completed, two reinforcement layers are laid on the mold corresponding to the connection between the outer side of the legs and the arms and fuselage.

[0015] As a further technical solution, the three reinforcement layers are added on the inner side of the legs and the lower side of the belly. After the overall laying of the UAV is completed, three reinforcement layers are laid on the corresponding molds on the inner side of the legs and the lower side of the belly.

[0016] As a further technical solution, the addition of ten reinforcement layers in the central area of ​​the motor seat is to lay ten reinforcement layers on the mold corresponding to the central area of ​​the motor seat after the overall laying of the drone is completed.

[0017] As a further technical solution, after the carbon fiber laying of all parts of the drone is completed, a core mold is placed in the mold, and then the core mold is inflated; then it is cured, and after the curing is completed, it is demolded.

[0018] As a further technical solution, the curing process is:

[0019] (1) Heating from room temperature to 82°C at a rate of 3°C / min and keeping warm for 30 minutes;

[0020] (2) Heating from 82°C to 125°C at a rate of 3°C / min and keeping at this temperature for 120 min;

[0021] (3) Natural cooling.

[0022] In a second aspect, the present invention further provides a UAV, which is obtained by the carbon fiber composite material integrated UAV molding method.

[0023] The beneficial effects of the present invention are as follows:

[0024] The carbon fiber composite integrated UAV molding method and UAV proposed in the present invention can meet the requirements of low quality and high load after the UAV is formed by designing the number of layers of carbon fiber laid at different positions of the UAV and the angle of carbon fiber laying; the integrated molding is achieved through the cooperation between the mold itself and the core mold, the number of parts and fasteners is reduced, the assembly process is reduced, and errors caused by assembly are avoided. Compared with traditional processes, the manufacturing production reduces the circulation process, omits the related production tools and jigs, and reduces the manufacturing cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The accompanying drawings in the specification, which constitute a part of the present invention, are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0026] Figure 1 It is a schematic diagram of the three-dimensional simulation of the UAV proposed by the present invention;

[0027] Figure 2 It is a molding flow chart proposed by the present invention;

[0028] Figure 3 , Figure 4 A schematic diagram of the three-dimensional simulation deformation of the UAV proposed by the present invention after adding load;

[0029] Figure 5 It is a schematic diagram of increasing the load of the UAV proposed by the present invention;

[0030] Figure 6 It is a schematic diagram of the mold used for molding of the present invention;

[0031] In the figure: 1-lower mold; 2-top cover; 3-first fixed block; 4-second fixed block; 5-third fixed block; 6-fourth fixed block; 7-first movable block; 8-second movable block; 9-third movable block; 10-fourth movable block, 11 base; 12 drone. DETAILED DESCRIPTION

[0032] It should be noted that the following detailed descriptions are illustrative and intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used in the present invention have the same meanings as those commonly understood by those skilled in the art to which the present invention belongs.

[0033] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present invention. As used herein, unless otherwise explicitly stated in the present invention, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "include" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof;

[0034] For the convenience of description, if the words "up", "down", "left" and "right" appear in the present invention, they only indicate that they are consistent with the up, down, left and right directions of the drawings themselves, and do not limit the structure. They are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation on the present invention.

[0035] As introduced in the background technology, in order to solve the deficiencies existing in the prior art and the above technical problems, the present invention proposes a carbon fiber composite material integrated UAV molding method and a UAV obtained by the method.

[0036] In a typical embodiment of the present invention, Figure 1 As shown in the figure, a carbon fiber composite integrated UAV molding method is proposed, including mainly using carbon fiber for plying, which is mainly composed of T300 carbon fiber fabric prepreg and T300 unidirectional prepreg; the specific laying process requirements are: two layers are laid on the entire UAV, and a reinforcement layer is added at the motor seat and the UAV cover of the UAV; two reinforcement layers are added on the outside of the leg and the connection between the arm and the fuselage; three reinforcement layers are added on the inside of the leg and the lower side of the belly; ten reinforcement layers are added in the central area of ​​the motor seat; the specific laying information is shown in Table 1 below:

[0037] Table 1. Layer requirements for UAVs;

[0038]

[0039] The drone is laid with two layers as a whole, the first layer is a carbon fiber 0° layer; the second layer is a carbon fiber 90° layer; wherein the 0° direction is along the heading of the drone;

[0040] The reinforcement layer of the motor seat and the cover of the drone is a carbon fiber 0° ply. Figure 1 The red part in

[0041] The two reinforcement layers at the connection between the outer side of the leg and the arm fuselage are carbon fiber 90° ply and carbon fiber 0° ply from inside to outside; Figure 1 The orange part;

[0042] The three reinforcement layers on the inner side of the leg and the lower side of the belly are carbon fiber 45° ply, carbon fiber 90° ply and carbon fiber 0° ply from the inside to the outside, corresponding to the attached Figure 1 The green part;

[0043] The ten reinforcing layers in the central area of ​​the motor seat are, from inside to outside, carbon fiber 45° ply, carbon fiber 90° ply, carbon fiber 0° ply, carbon fiber 45° ply, carbon fiber -45° ply, carbon fiber 0° ply, carbon fiber 90° ply, carbon fiber 45° ply, carbon fiber 90° ply and carbon fiber 0° ply; corresponding to the attached Figure 1 The purple part.

[0044] As a further technical solution, in this embodiment, the overall laying of the above-mentioned drone is to first lay a first layer of carbon fiber on the corresponding mold, and then lay a second layer of carbon fiber on the corresponding mold.

[0045] As a further technical solution, in this embodiment, the above-mentioned addition of a reinforcement layer at the position of the motor seat and the drone cover of the drone is to lay another reinforcement layer on the mold corresponding to the motor seat and the drone cover of the drone after the entire drone is laid;

[0046] As a further technical solution, in this embodiment, two reinforcement layers are added at the connection between the outer side of the legs and the arm and fuselage. After the overall laying of the drone is completed, two reinforcement layers are laid on the mold corresponding to the connection between the outer side of the legs and the arm and fuselage.

[0047] As a further technical solution, in this embodiment, the three reinforcement layers are added on the inner side of the legs and the lower side of the belly. After the overall laying of the UAV is completed, three reinforcement layers are laid on the corresponding molds on the inner side of the legs and the lower side of the belly.

[0048] As a further technical solution, in this embodiment, the above-mentioned ten reinforcement layers are added in the central area of ​​the motor seat. After the overall laying of the drone is completed, ten reinforcement layers are laid on the mold corresponding to the central area of ​​the motor seat.

[0049] Specifically, the mold corresponding to this molding process can refer to the mold disclosed in patent CN202410786942.0, and the molding mold includes: a base 11, a top cover 2, a first fixed block 3, a second fixed block 4, a third fixed block 5, a fourth fixed block 6, a first movable block 7, a second movable block 8, a third movable block 9 and a fourth movable block 10.

[0050] The first fixed block 3, the second fixed block 4, the third fixed block 5, and the fourth fixed block 6 are fixed on the base in a rectangular shape (located at the four corner points of the rectangle), the first movable block 5 is located between the first fixed block 3 and the second fixed block 4 and is movably connected to the base, the second movable block 6 is located between the second fixed block 4 and the third fixed block 5 and is movably connected to the base, the third movable block 7 is located between the third fixed block 5 and the fourth fixed block 6 and is movably connected to the base, and the fourth movable block 8 is located between the fourth fixed block 6 and the first fixed block 3 and is movably connected to the base;

[0051] The top cover 2 is detachably fixedly connected to the top of the first fixed block 3, the second fixed block 4, the third fixed block 5, the fourth fixed block 6, the first movable block 7, the second movable block 8, the third movable block 9 and the fourth movable block 10 respectively. After the first movable block 7, the second movable block 8, the third movable block 9 and the fourth movable block 10 move inward by a set distance, they cooperate with the first fixed block 3, the second fixed block 4, the third fixed block 5, the fourth fixed block 6, the base 11 and the top cover 2 to form an inner cavity for molding. And the lower mold 1 is fixed on the base 11. Based on this mold, the preparation process of the above-mentioned integrated drone finishing is as follows Figure 2 As shown, the details are as follows:

[0052] Step 1: First clean the mold and apply the release agent to the entire area of ​​the mold body and the parting mold;

[0053] Step 2: Moisture absorption treatment of air bags: Before use, absorb moisture first, put the air bags into a moisture absorption room, moisture absorption cabinet or moisture absorption barrel, and fully expose them to moisture for more than 24 hours at a temperature of 25±5℃ and a relative humidity of 60-80%. Avoid the air bags from touching water.

[0054] Step 3 After the moisture is absorbed, first conduct the airbag pressure test, close the mold, and inflate without laying prepreg. Before closing the mold, simulate the prepreg laying to prevent the airbag from being punctured by the sharp edge of the mold. After the protection is completed, gradually increase the air pressure until the required layer protects the mold seams of each mold (important), with a maximum pressure of 13bar.

[0055] Step 4: Carbon fiber laying. The specific laying angle and number of layers refer to the previous description. The specific laying process is as follows:

[0056] Step 4.1 Lay the first layer of carbon fiber on the mold base at an angle of 0°

[0057] The part that is laid on the lower mold of the base for molding the drone is left with a 10-12mm flange, the excess is cut off, and the corners are notched to make the prepreg fully fit the lower mold, and no air or other impurities are allowed to fill it.

[0058] Lay the part of the base body used to shape the drone;

[0059] Laying the first fixing block, the second fixing block, the third fixing block, and the fourth fixing block for forming the parts of the drone;

[0060] Step 4.2: Lay the first layer on the split body at an angle of 0°

[0061] Lay out the top cover for the part that will be used to shape the drone;

[0062] Laying the first movable block, the second movable block, the third movable block, and the fourth movable block for forming the drone;

[0063] Step 4.3 Lay the second layer of carbon fiber on the base at an angle of 90°

[0064] The part that is laid on the lower mold of the base for molding the drone is left with a 10-12mm flange, the excess is cut off, and the corners are notched to make the prepreg fully fit the lower mold, and no air or other impurities are allowed to fill it.

[0065] Lay the part of the base body used to shape the drone;

[0066] Laying the first fixing block, the second fixing block, the third fixing block, and the fourth fixing block for forming the parts of the drone;

[0067] Step 4.4 Lay the second layer of carbon fiber on the split body at an angle of 90°

[0068] Lay out the top cover for the part that will be used to shape the drone;

[0069] Laying the first movable block, the second movable block, the third movable block, and the fourth movable block for forming the drone;

[0070] Step 4.5: Lay the reinforcement layer corresponding to the center area of ​​the drone motor seat. Lay the ten reinforcement layers from the inside to the outside.

[0071] Lay the reinforcement layers corresponding to the central areas of the four motor seats on the first fixing block, the second fixing block, the third fixing block, and the fourth fixing block; all four motor seats need to be reinforced;

[0072] Step 4.6: Lay a reinforcement layer corresponding to the drone motor base and the drone mouth cover

[0073] Laying a reinforcement layer corresponding to the motor seat on the first fixing block, the second fixing block, the third fixing block and the fourth fixing block;

[0074] Lay a reinforcement layer corresponding to the UAV mouth on the top cover;

[0075] Step 4.7: Lay two layers of reinforcement corresponding to the outer side of the drone legs and the connection between the arms and the fuselage

[0076] Laying the corresponding reinforcement layers on the outer sides of the machine legs on the first movable block, the second movable block, the third movable block and the fourth movable block;

[0077] Lay the reinforcement layer corresponding to the connection between the arm and the fuselage on the base lower mold and the first movable block, the second movable block, the third movable block and the fourth movable block;

[0078] Step 4.8: Lay the three reinforcement layers corresponding to the inner side of the drone legs and the lower side of the belly

[0079] Lay the corresponding reinforcement layer on the inner side of the machine leg on the lower mold of the base;

[0080] Lay the reinforcement layer corresponding to the lower side of the machine belly on the lower mold of the base;

[0081] Step 5 places the core mold. In this embodiment, an air bag is used as the core mold. After the above-mentioned carbon fiber material is laid, the air bag is straightened into an M shape and placed on the surface of the prepreg that has been laid on the base; the inflation port of the air bag is cut horizontally, inflated, and then sealed with tape and the prepared air nozzle.

[0082] Step 6 Curing process

[0083] (1) Heating from room temperature to 82°C at a rate of 3°C / min and keeping warm for 30 minutes;

[0084] (2) Heating from 82°C to 125°C at a rate of 3°C / min and keeping at this temperature for 120 min;

[0085] (3) Natural cooling.

[0086] Step 7: Demolding

[0087] (1) Product demoulding: Remove the drone from the mold. During the demoulding process, pay attention to the safety of the drone and personnel to avoid injury.

[0088] (2) After demolding, write the corresponding product drawing number, product name, and product number on the surface of the drone with a marker.

[0089] This embodiment also provides a drone, which is obtained by the above-mentioned drone molding method of carbon fiber composite material integration. The drone can meet the requirements of low mass and high load by designing the number and angle of carbon fiber laying layers at different positions of the drone. The specific simulation results are as follows: Figure 3 , Figure 4 As shown in the figure, the total weight of the drone is 1kg. Under this design layer, the maximum deformation of the drone under the simulated 8KG load is 5.8mm, which is less than 10mm and meets the design requirements. Figure 6 As shown in the figure): After the drone is equipped with the foot parts and bears a weight of 8KG, the actual deformation is 7mm, and the deformation of the bottom of the two legs is ≤10mm.

[0090] Furthermore, the present invention relates to a lightweight, high-strength, integrated carbon fiber composite material UAV mainly composed of T300 carbon fiber fabric prepreg and T300 unidirectional prepreg. Through layer design, while meeting the load-bearing requirements, the weight reduction can be achieved by more than 50%, effectively reducing energy consumption, and at the same time utilizing the excellent performance of carbon fiber to achieve high strength, corrosion resistance, low thermal expansion coefficient, and fatigue resistance, while taking into account the electromagnetic effect. Through mold integrated molding, the number of parts and fasteners is reduced, the assembly process is reduced, and errors caused by assembly are avoided. Compared with traditional processes, manufacturing production reduces the circulation process, omits related production tooling and jigs, and reduces manufacturing costs.

[0091] Finally, it should be noted that relational terms such as first and second are merely used to distinguish one entity or operation from another entity or operation, but do not necessarily require or imply any actual relationship or order between these entities or operations.

[0092] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A carbon fiber composite material integrated UAV molding method, comprising carbon fiber laying; characterized in that: The entire drone is paved with two layers, with one reinforcement layer added to the motor mount and the drone cover; two reinforcement layers are added to the outside of the legs and the connection between the arms and the fuselage; three reinforcement layers are added to the inside of the legs and the lower side of the belly; and ten reinforcement layers are added to the center area of ​​the motor mount.

2. The carbon fiber composite material integrated UAV molding method according to claim 1, characterized in that: The drone is laid with two layers as a whole, the first layer is a carbon fiber 0° layer; the second layer is a carbon fiber 90° layer; the reinforcement layers at the motor seat and the cover of the drone are carbon fiber 0° layers; the two reinforcement layers at the connection between the outer side of the leg and the arm fuselage are carbon fiber 90° layers and carbon fiber 0° layers from the inside to the outside; the three reinforcement layers on the inner side of the leg and the lower side of the belly are carbon fiber 45° layers, carbon fiber 90° layers and carbon fiber 0° layers from the inside to the outside; the ten reinforcement layers in the central area of ​​the motor seat are carbon fiber 45° layers, carbon fiber 90° layers, carbon fiber 0° layers, carbon fiber 45° layers, carbon fiber -45° layers, carbon fiber 0° layers, carbon fiber 90° layers, carbon fiber 45° layers, carbon fiber 90° layers and carbon fiber 0° layers from the inside to the outside; the 0° direction is along the heading of the drone.

3. The carbon fiber composite material integrated UAV molding method according to claim 1, characterized in that: The overall laying of the UAV is to first lay a first layer of carbon fiber on a corresponding mold, and then lay a second layer of carbon fiber on the corresponding mold.

4. The carbon fiber composite material integrated UAV molding method according to claim 1, characterized in that: The method of adding a reinforcement layer at the motor seat and the mouth cover of the drone is to lay another reinforcement layer on the molds corresponding to the motor seat and the mouth cover of the drone after the entire drone is laid.

5. The carbon fiber composite material integrated UAV molding method according to claim 1, characterized in that: The adding of two reinforcement layers at the connection between the outer side of the legs and the arms and the fuselage is that after the overall laying of the UAV is completed, two reinforcement layers are laid on the mold corresponding to the connection between the outer side of the legs and the arms and the fuselage.

6. The carbon fiber composite material integrated UAV molding method according to claim 1, characterized in that: The adding of three reinforcement layers on the inner side of the legs and the lower side of the belly means that after the overall laying of the UAV is completed, three reinforcement layers are laid on the corresponding molds on the inner side of the legs and the lower side of the belly.

7. The carbon fiber composite material integrated UAV molding method according to claim 1, characterized in that: The adding of ten reinforcement layers in the central area of ​​the motor seat means that after the overall laying of the UAV is completed, ten reinforcement layers are laid on the mold corresponding to the central area of ​​the motor seat.

8. The carbon fiber composite material integrated UAV molding method according to claim 1, characterized in that: After the carbon fiber layup of all parts of the drone is completed, a core mold is placed in the mold, and then the core mold is inflated; then it is cured, and after the curing is completed, it is demolded.

9. The carbon fiber composite material integrated UAV molding method according to claim 8, characterized in that: The curing process is: (1) Heating from room temperature to 82°C at a rate of 3°C / min and keeping warm for 30 minutes; (2) Heating from 82°C to 125°C at a rate of 3°C / min and keeping at this temperature for 120 min; (3) Natural cooling.

10. A drone, characterized in that: The method for forming an integrated UAV of carbon fiber composite materials is obtained by any one of claims 1 to 9.

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