A method for molding an integrated carbon fiber composite UAV and the UAV obtained by the method

Abstract

This invention relates to the field of unmanned aerial vehicles (UAVs), specifically to a method for molding an integrated UAV using carbon fiber composite materials and the UAV obtained by this method. The UAV is constructed with two layers: an additional reinforcing layer at the motor mount and the UAV's hatch; two additional reinforcing layers at the outer sides of the legs and the connection points between the arms and fuselage; three additional reinforcing layers on the inner sides of the legs and the lower side of the fuselage; and ten additional reinforcing layers in the central area of ​​the motor mount. Through this layered design, a weight reduction of over 50% is achieved while meeting load-bearing requirements, effectively reducing energy consumption. Simultaneously, the superior properties of carbon fiber are utilized to achieve high strength, corrosion resistance, low coefficient of thermal expansion, fatigue resistance, and electromagnetic properties. Integrated molding reduces the number of parts and fasteners, streamlines the assembly process, and avoids errors caused by assembly. Compared to traditional processes, manufacturing reduces transfer steps, eliminates related tooling and jigs, and lowers manufacturing costs.

Description

Technical Field

[0001] This invention relates to the field of integrated carbon fiber composite material unmanned aerial vehicle (UAV) molding, specifically to a method for integrated carbon fiber composite material UAV molding and the UAV obtained by the method. Background Technology

[0002] Currently, in the field of drones, the connection points and weight of various components significantly reduce the flight performance of drones; the high density and weight of metal materials mean limited endurance and flight speed, which limits the performance of tasks such as long-distance reconnaissance, cargo transportation, and environmental monitoring; traditional drones usually require the assembly of multiple parts, resulting in a cumbersome manufacturing process; traditional drones often use traditional metal materials, which have poor corrosion resistance in harsh environments, which may lead to structural damage and affect the service life of the drone.

[0003] To address the aforementioned issues, existing technologies disclose methods for molding drone components using carbon fiber composite materials. For example, patent CN118306030A discloses a method for manufacturing a reinforced wall panel of a carbon fiber composite amphibious drone; patent CN113211823B discloses a method for molding a carbon fiber composite drone wing; patent CN212709933U discloses a multi-walled wing of a carbon fiber composite drone; patent CN110843234A discloses a molding process for a carbon fiber composite main beam of a drone; and patent CN117382217A discloses an integral molding method for a drone, etc. In particular, patent CN117382217A discloses an integral molding method for a drone, which is also based on integral molding using carbon fiber composite materials. This method includes: S1, tooling preparation, inspecting the equipment to be used; S2, preheating the mold; and S3, layup processing, laying the fibers according to the layup information table, with unidirectional tape along the fiber... Directional splicing; overlapping of fabrics in non-fitting areas is permitted; slits are permitted in areas prone to bridging, sharp turning areas, and areas where components meet on three sides; S4, bag making process, the bag making process includes: S41, laying a peel-off layer on the machine body area, first laying a layer of release film on the parts, placing the irregularly shaped air bag coated with release agent on the tooling, folding the corresponding position of the irregularly shaped air bag, and completely wrapping the irregularly shaped air bag with the folded prepreg material. After wrapping, check the wrapping condition of all folded areas. For those not wrapped, cut the corresponding material pieces. S42. Extend and cover the edge; S43. Mold closing process; S44. Wrap and protect the tooling, fill the tooling sealing groove with sealing strips, and then make a mother-daughter bag; S45. Check the airtightness, and perform a vacuum leak check on the molding mold; S6. Curing process, and perform a second system vacuum on the molding mold; S7. Demolding process, remove the vacuum bag on the tooling, remove the corresponding bolts and nuts, and take out the workpiece; S8. Demolding inspection process; S9. Manual processing, manually remove edge burrs and excess glue at the mold closing seam, and do not process other holes. However, the patent only discloses the carbon fiber laying process in detail, stating that the laying work should be carried out according to the layup information table, and defects such as inclusions and bridging are not allowed during the laying process; unidirectional tapes should be butt-jointed along the fiber direction with a gap of ≤1mm; non-cooperative areas of the fabric are allowed to overlap, with an overlap width of 12mm to 25mm; slits are allowed in areas prone to bridging, areas with sharp turns, and areas where three sides of the components meet; the size range of the slit gap is -1mm to 0mm, and the seams of the same 4 layers should be staggered by at least 25mm; in reality, how the carbon fiber layers of each component of the drone are laid directly affects the load-bearing capacity and quality of the drone. Summary of the Invention

[0004] In order to provide a drone that can meet the requirements of load-bearing performance and quality, this invention discloses an integrated carbon fiber composite material drone molding method. By designing the carbon fiber layup of different components of the drone, it can meet certain load-bearing performance and quality requirements.

[0005] The technical solution adopted in this invention is as follows:

[0006] In a first aspect, the present invention provides a method for molding an integrated unmanned aerial vehicle (UAV) using carbon fiber composite materials, including carbon fiber layup; wherein the UAV is laid up with two layers in total, with an additional reinforcing layer at the motor mount and the UAV mouth cover; two additional reinforcing layers at the connection between the outer sides of the legs and the fuselage of the arms; three additional reinforcing layers at the inner sides of the legs and the underside of the fuselage; and ten additional reinforcing layers in the central area of ​​the motor mount.

[0007] The drone is constructed with two layers: the first layer is a 0° carbon fiber layup, and the second layer is a 90° carbon fiber layup. The 0° direction is along the drone's flight path.

[0008] The motor mount and the reinforcing layer at the mouth cover of the drone are made of carbon fiber 0° layup.

[0009] The two reinforcing layers at the connection between the outer side of the leg and the arm and body are, from the inside out, a 90° carbon fiber layup and a 0° carbon fiber layup.

[0010] The three reinforcing layers on the inner side of the legs and the lower side of the fuselage are, from the inside out, carbon fiber 45° layup, carbon fiber 90° layup and carbon fiber 0° layup.

[0011] The ten reinforcing layers in the central region of the motor base are, from the inside out, carbon fiber 45° layup, carbon fiber 90° layup, carbon fiber 0° layup, carbon fiber 45° layup, carbon fiber -45° layup, carbon fiber 0° layup, carbon fiber 90° layup, carbon fiber 45° layup, carbon fiber 90° layup, and carbon fiber 0° layup.

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

[0013] As a further technical solution, the addition of a reinforcing layer at the motor mount and drone mouth cover of the drone is to lay another reinforcing layer on the mold corresponding to the motor mount and drone mouth cover of the drone after the overall drone is laid out.

[0014] As a further technical solution, the addition of two reinforcing layers at the connection between the outer side of the legs and the arm and fuselage is to lay two reinforcing layers on the mold corresponding to the connection between the outer side of the legs and the arm and fuselage after the overall drone is laid out.

[0015] As a further technical solution, the addition of three reinforcing layers on the inner side of the legs and the lower side of the fuselage involves laying three reinforcing layers on the corresponding molds on the inner side of the legs and the lower side of the fuselage after the overall installation of the UAV is completed.

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

[0017] As a further technical solution, after the carbon fiber layup of all components 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 curing, it is demolded.

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

[0019] (1) Heat from room temperature to 82℃ at a rate of 3℃ / min and hold for 30 minutes;

[0020] (2) Heat from 82℃ to 125℃ at a rate of 3℃ / min and hold for 120min;

[0021] (3) Natural cooling.

[0022] Secondly, the present invention also provides a drone, which is obtained by the integrated drone molding method of carbon fiber composite material.

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

[0024] This invention proposes an integrated carbon fiber composite material unmanned aerial vehicle (UAV) molding method and UAV. By designing the number of carbon fiber layers and the angle of carbon fiber laying at different locations on the UAV, the UAV can meet the requirements of low weight and high load-bearing capacity after molding. Integrated molding is achieved through the cooperation of the mold itself and the core mold, reducing the number of parts and fasteners, simplifying the assembly process, and avoiding errors caused by assembly. Compared with traditional processes, manufacturing reduces transfer steps, eliminates related tooling and jigs, and reduces manufacturing costs. Attached Figure Description

[0025] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an improper limitation of the invention.

[0026] Figure 1 This is a three-dimensional simulation diagram of the UAV proposed in this invention;

[0027] Figure 2 This is the molding process diagram proposed in this invention;

[0028] Figure 3 , Figure 4 A three-dimensional simulation diagram illustrating the deformation of the UAV after adding a payload, as proposed in this invention;

[0029] Figure 5 This is a schematic diagram illustrating the increased payload of the UAV proposed in this invention;

[0030] Figure 6 This is a schematic diagram of the mold used in the molding of this invention;

[0031] In the diagram: 1-lower mold; 2-top cover; 3-first fixing block; 4-second fixing block; 5-third fixing block; 6-fourth fixing block; 7-first movable block; 8-second movable block; 9-third movable block; 10-fourth movable block; 11-base; 12-drone. Detailed Implementation

[0032] It should be noted that the following detailed description is illustrative and intended to provide further explanation of the invention. Unless otherwise specified, all technical and scientific terms used in this invention have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains.

[0033] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the scope of exemplary embodiments according to the invention. As used herein, unless otherwise expressly indicated by the invention, the singular form is also intended to include the plural form. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0034] For ease of description, the words "up," "down," "left," and "right" appearing in this invention only indicate that they are consistent with the up, down, left, and right directions of the accompanying drawings themselves, and do not limit the structure. They are merely for the purpose of facilitating the description of this invention and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0035] As described in the background section, there are shortcomings in the existing technology. In order to solve the above-mentioned technical problems, this invention proposes a method for molding an integrated carbon fiber composite drone and a drone obtained by the method.

[0036] In a typical embodiment of the present invention, such as Figure 1 As shown, a method for molding an integrated carbon fiber composite UAV is proposed, which mainly uses carbon fiber for layup, primarily composed of T300 carbon fiber prepreg and T300 unidirectional prepreg. The specific layup process requirements are: the UAV is laid with two layers; an additional reinforcing layer is added at the motor mount and the UAV hatch; two reinforcing layers are added at the outer sides of the legs and the connection points of the arms and fuselage; three reinforcing layers are added on the inner sides of the legs and the lower side of the fuselage; and ten reinforcing layers are added in the central area of ​​the motor mount. Specific layup information is shown in Table 1 below.

[0037] Table 1. Layup requirements for UAVs;

[0038]

[0039] The drone is constructed with two layers: the first layer is a 0° carbon fiber layup, and the second layer is a 90° carbon fiber layup. The 0° direction is along the drone's flight path.

[0040] The motor mount and the reinforcement layer at the drone's mouth cover are made of carbon fiber 0° layup, corresponding to the attached... Figure 1 The red part in the image;

[0041] The two reinforcing layers at the connection between the outer side of the leg and the arm / body are, from the inside out, a 90° carbon fiber layup and a 0° carbon fiber layup; corresponding to the attached... Figure 1 The orange part;

[0042] The three reinforcing layers on the inner side of the legs and the lower side of the fuselage, from the inside out, are successively a 45° carbon fiber layup, a 90° carbon fiber layup, and a 0° carbon fiber layup, corresponding to the attached... Figure 1 The green part;

[0043] The ten reinforcing layers in the central region of the motor mount, from the inside out, are: carbon fiber 45° layup, carbon fiber 90° layup, carbon fiber 0° layup, carbon fiber 45° layup, carbon fiber -45° layup, carbon fiber 0° layup, carbon fiber 90° layup, carbon fiber 45° layup, carbon fiber 90° layup, and carbon fiber 0° layup; 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 UAV involves first laying a first layer of carbon fiber on the corresponding mold, and then laying 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 reinforcing layer at the motor mount and drone mouth cover position of the drone is to lay another reinforcing layer on the mold corresponding to the motor mount and drone mouth cover of the drone after the overall drone is laid out.

[0046] As a further technical solution, in this embodiment, the above-mentioned addition of two reinforcing layers at the connection between the outer side of the legs and the connection between the arms and the fuselage is to lay two reinforcing layers on the mold corresponding to the connection between the outer side of the legs and the connection between the arms and the fuselage after the overall drone is laid out.

[0047] As a further technical solution, in this embodiment, the above-mentioned addition of three reinforcing layers on the inner side of the legs and the lower side of the fuselage is to lay three reinforcing layers on the corresponding molds on the inner side of the legs and the lower side of the fuselage after the overall drone is laid out.

[0048] As a further technical solution, in this embodiment, the above-mentioned addition of ten reinforcing layers in the central area of ​​the motor mount is to lay ten reinforcing layers on the mold corresponding to the central area of ​​the motor mount after the overall drone is laid out.

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

[0050] The first fixing block 3, the second fixing block 4, the third fixing block 5, and the fourth fixing block 6 are fixed to the base in a rectangular arrangement (located at the four corner points of the rectangle). The first movable block 7 is located between the first fixing block 3 and the second fixing block 4 and is movably connected to the base. The second movable block 8 is located between the second fixing block 4 and the third fixing block 5 and is movably connected to the base. The third movable block 9 is located between the third fixing block 5 and the fourth fixing block 6 and is movably connected to the base. The fourth movable block 10 is located between the fourth fixing block 6 and the first fixing block 3 and is movably connected to the base.

[0051] The top cover 2 is detachably and fixedly connected to the tops 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. After the first movable block 7, the second movable block 8, the third movable block 9, and the fourth movable block 10 move inward 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 a molding cavity. A lower mold 1 is fixed on the base 11. Based on this mold, the manufacturing process of the aforementioned integrated UAV assembly is as follows: Figure 2 As shown, the details are as follows:

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

[0053] Step 2: Moisture Absorption Treatment of the Air Bag: Before use, absorb moisture by placing the air bag in a moisture-absorbing room, moisture-absorbing cabinet, or moisture-absorbing bucket, and exposing it to moisture for at least 24 hours under conditions of 25±5℃ and 60-80% relative humidity. Avoid contact between the air bag and water.

[0054] Step 3: After the moisture absorption process is complete, first conduct an airbag pressure test. Close the mold and inflate it without laying prepreg. Before closing the mold, simulate prepreg laying to prevent the airbag from being punctured by the sharp edges of the mold. After the protection is in place, gradually increase the air pressure until the required layer is used to protect the mold joints (important), with a maximum pressure of 13 bar.

[0055] Step 4: Carbon fiber layup. Refer to the previous description for specific layup angles and number of layers. The layup process is as follows:

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

[0057] The part to be molded on the base mold for the drone is to be laid with a 10-12mm flange. Cut off the excess and make a notch at the corners to ensure that the prepreg fully fits the lower mold. Do not allow air or other impurities to be filled in.

[0058] The part of the base body used to mold the drone is then laid out.

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

[0060] Step 4.2: Lay the first layer on the split surface at a 0° angle.

[0061] Lay out the part of the top cover used to shape the drone;

[0062] Lay out the parts of the first movable block, second movable block, third movable block, and fourth movable block used to form the drone;

[0063] Step 4.3 Apply the second layer of carbon fiber to the base at a 90° angle.

[0064] The part to be molded on the base mold for the drone is to be laid with a 10-12mm flange. Cut off the excess and make a notch at the corners to ensure that the prepreg fully fits the lower mold. Do not allow air or other impurities to be filled in.

[0065] The part of the base body used to mold the drone is then laid out.

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

[0067] Step 4.4 Apply the second layer of carbon fiber to the split body at a 90° angle.

[0068] Lay out the part of the top cover used to shape the drone;

[0069] Lay out the parts of the first movable block, second movable block, third movable block, and fourth movable block used to form the drone;

[0070] Step 4.5: Apply the reinforcement layer corresponding to the center area of ​​the drone motor mount, applying ten reinforcement layers sequentially from the inside out.

[0071] Reinforcing layers corresponding to the central areas of the four motor mounts are applied to the first, second, third, and fourth fixing blocks; all four motor mounts require reinforcement.

[0072] Step 4.6 Apply the corresponding reinforcement layer to the drone motor mount and drone port cover.

[0073] A reinforcing layer corresponding to the motor base is laid on the first fixing block, the second fixing block, the third fixing block, and the fourth fixing block;

[0074] Apply a reinforcing layer corresponding to the drone's port onto the top cover;

[0075] Step 4.7 Apply the two reinforcing layers to the outer sides of the drone's legs and the corresponding joints between the arms and fuselage.

[0076] The corresponding reinforcement layers on the outer side of the machine legs are laid on the first movable block, the second movable block, the third movable block, and the fourth movable block;

[0077] Reinforcing layers corresponding to the connection points of the machine arm and body are laid on the lower mold of the base and the first movable block, the second movable block, the third movable block, and the fourth movable block;

[0078] Step 4.8 Apply the three-layer reinforcement layer to the inner side of the drone's legs and the lower side of its belly.

[0079] Apply the corresponding reinforcing layer to the inner side of the machine leg on the lower mold of the base;

[0080] The corresponding reinforcing layer on the lower side of the machine belly is laid on the lower mold of the base;

[0081] Step 5: Place the core mold. In this embodiment, an air bag is used as the core mold. After the 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 air bag inflation port is cut horizontally, inflated, and then sealed with tape and the prepared air nozzle.

[0082] Step 6 Curing process

[0083] (1) Heat from room temperature to 82℃ at a rate of 3℃ / min and hold for 30 minutes;

[0084] (2) Heat from 82℃ to 125℃ at a rate of 3℃ / min and hold for 120min;

[0085] (3) Natural cooling.

[0086] Step 7 Demolding

[0087] (1) Product demolding: Remove the drone from the mold. During the demolding 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 aforementioned integrated carbon fiber composite drone molding method. By designing the number of carbon fiber layers and angles at different locations on the drone, the drone can meet the requirements of low mass and high load-bearing capacity. Specific simulation results are as follows... Figure 3 , Figure 4 As shown; the total weight of the drone is 1kg. Under this design layup, the simulated 8kg load shows that the maximum deformation of the drone is 5.8mm, which is less than 10mm, meeting the design requirements. Test results (as shown) Figure 6 As shown): After the drone is equipped with the legs and bears a load of 8KG, the actual deformation is 7mm, and the deformation at the bottom of the two legs is ≤10mm.

[0090] Furthermore, this invention relates to a lightweight, high-strength, one-piece molded carbon fiber composite UAV, primarily composed of T300 carbon fiber prepreg and T300 unidirectional prepreg. Through a layup design, it achieves a weight reduction of over 50% while meeting load-bearing requirements, effectively reducing energy consumption. Simultaneously, it utilizes the excellent properties of carbon fiber to achieve high strength, corrosion resistance, low coefficient of thermal expansion, fatigue resistance, and also ensures electromagnetic performance. One-piece molding reduces the number of parts and fasteners, streamlines the assembly process, and avoids errors caused by assembly. Compared to traditional processes, manufacturing reduces transfer steps, eliminates related tooling and jigs, and lowers manufacturing costs.

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

[0092] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for molding an integrated carbon fiber composite unmanned aerial vehicle (UAV), comprising carbon fiber layup; characterized in that, The drone is constructed with two layers: an additional reinforcement layer at the motor mount and mouthpiece; two additional reinforcement layers at the outer sides of the legs and the connection points of the arms and fuselage; three additional reinforcement layers at the inner sides of the legs and the underside of the fuselage; and ten additional reinforcement layers in the central area of ​​the motor mount. The first layer is a 0° carbon fiber layup; the second layer is a 90° carbon fiber layup. The reinforcement layers at the motor mount and mouthpiece are 0° carbon fiber layups. The two reinforcement layers at the outer sides of the legs and the connection points of the arms and fuselage are, from the inside out, carbon fiber... The structure consists of 90° fiber layups and 0° carbon fiber layups; the three reinforcing layers on the inner side of the legs and the lower side of the fuselage are, from the inside out, carbon fiber 45° layups, carbon fiber 90° layups, and carbon fiber 0° layups; the ten reinforcing layers in the central region of the motor mount are, from the inside out, carbon fiber 45° layups, carbon fiber 90° layups, carbon fiber 0° layups, carbon fiber 45° layups, carbon fiber -45° layups, carbon fiber 0° layups, carbon fiber 90° layups, carbon fiber 45° layups, carbon fiber 90° layups, and carbon fiber 0° layups; the 0° direction is along the UAV's heading.

2. The method for molding an integrated carbon fiber composite UAV as described in claim 1, characterized in that, The overall deployment of the drone involves first laying a first layer of carbon fiber on the corresponding mold, and then laying a second layer of carbon fiber on the corresponding mold.

3. The method for molding an integrated carbon fiber composite UAV as described in claim 1, characterized in that, The addition of a reinforcing layer to the motor mount and drone mouth cover of the drone refers to laying another reinforcing layer on the mold corresponding to the motor mount and drone mouth cover after the overall drone installation is completed.

4. The method for molding an integrated carbon fiber composite UAV as described in claim 1, characterized in that, The addition of two reinforcing layers at the connection between the outer side of the legs and the fuselage of the drone refers to laying two additional reinforcing layers on the mold corresponding to the connection between the outer side of the legs and the fuselage of the drone after the overall drone installation is completed.

5. The method for molding an integrated carbon fiber composite UAV as described in claim 1, characterized in that, The addition of three reinforcing layers to the inner side of the legs and the lower side of the fuselage refers to laying three reinforcing layers on the corresponding molds on the inner side of the legs and the lower side of the fuselage after the overall drone is laid out.

6. The method for molding an integrated carbon fiber composite UAV as described in claim 1, characterized in that, The aforementioned addition of ten reinforcing layers in the central area of ​​the motor mount refers to laying ten reinforcing layers on the mold corresponding to the central area of ​​the motor mount after the overall drone installation is completed.

7. The method for molding an integrated carbon fiber composite UAV as described in claim 1, characterized in that, After the carbon fiber layup of all components 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 curing, it is demolded.

8. The method for molding an integrated carbon fiber composite UAV as described in claim 7, characterized in that, The curing process is as follows: (1) Heat from room temperature to 82℃ at a rate of 3℃ / min and hold for 30 minutes; (2) Heat from 82℃ to 125℃ at a rate of 3℃ / min and hold for 120min; (3) Natural cooling.

9. A drone, characterized in that, Obtained by the integrated UAV molding method of carbon fiber composite material as described in any one of claims 1-8.

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