A method of manufacturing a housing, a housing, a fuselage, and an unmanned aerial vehicle

Abstract

The embodiment of the present application relates to the technical field of unmanned aerial vehicle manufacturing, and discloses a shell manufacturing method, a shell, a fuselage and an unmanned aerial vehicle, the shell manufacturing method comprises the following steps: providing a preform, an air bag, a mold and a curing furnace, wherein the air bag is in the shape of an inner cavity of the shell, the air bag is provided with an inflation port, the preform is attached to the surface of the air bag, the air bag with the attached preform is placed in the mold, the preform is compacted by inflating the air bag through the inflation port, the inflation of the air bag is stopped and the inflation port is closed, and the mold with the preform and the air bag is placed in the curing furnace to be heated and cured to obtain the shell. Through the above method, the shell is integrally manufactured, the shell is lightweight and high-strength, and the shell is prevented from being broken.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) manufacturing technology, and in particular to a method for manufacturing a shell, a shell, a fuselage, and an UAV. Background Technology

[0002] With the technological advancements in unmanned aerial vehicles (UAVs), their applications are becoming increasingly widespread, including aerial photography, surveillance, and cargo transport. UAVs used for cargo transport typically consist of an airframe, flight control system, drive module, antenna module, and battery module.

[0003] However, in the process of implementing the embodiments of the present invention, the inventors discovered that: the body includes an upper cover, a lower frame, a shell, and a fixing plate, the upper cover is connected to the lower frame, the shell covers the lower frame, and the fixing plate is disposed on the shell. Currently, the shell is obtained by segmented molding and then gluing them together as a whole, but the strength of the glued joints of the shell is insufficient, and the glued joints of the shell may break. Summary of the Invention

[0004] The main technical problem solved by the embodiments of the present invention is to provide a method for manufacturing a shell, which integrally manufactures the shell, ensuring the strength of the shell and preventing the shell from breaking.

[0005] To solve the above-mentioned technical problems, one technical solution adopted by the present invention is: to provide a method for manufacturing a shell, comprising: providing a preform, an air bladder, a mold, and a curing oven, wherein the air bladder is shaped like the inner cavity of the shell, the air bladder is provided with an inflation port, the preform is laid on the surface of the air bladder, the air bladder with the preform laid on it is placed in the mold, and the air bladder is inflated and the preform is compacted through the inflation port, inflation of the air bladder is stopped and the inflation port is closed, and the mold with the preform and the air bladder is placed in the curing oven and heated to cure to obtain the shell.

[0006] Optionally, the preform includes an outer layer, a first reinforcing member, a second reinforcing member, a third reinforcing member, a fourth reinforcing member, and an inner layer; The step of applying the preform to the surface of the airbag further includes: The inner layer is laid on the surface of the airbag; The first reinforcing member, the second reinforcing member, the third reinforcing member, and the fourth reinforcing member are respectively laid in the preset first area, the preset second area, the preset third area, and the preset fourth area; The outer layer is laid on the surface of the inner layer. The first reinforcing member is sandwiched between the inner layer and the outer layer in a predetermined first region. The second reinforcing member is sandwiched between the inner layer and the outer layer in a predetermined second region. The third reinforcing member is sandwiched between the inner layer and the outer layer in a predetermined third region. The fourth reinforcing member is sandwiched between the inner layer and the outer layer in a predetermined fourth region.

[0007] Optionally, the preset first region, preset second region, preset third region and preset fourth region are the main stress-bearing regions of the shell, and the inner layer region other than the preset first region, preset second region, preset third region and preset fourth region is the preset fifth region, which is the secondary stress-bearing region of the shell.

[0008] Optionally, the secondary stress-bearing region includes an outer layer and an inner layer from the outside to the inside.

[0009] Optionally, stopping the inflation of the airbag and sealing the inflation port, and placing the mold containing the preform and the airbag in the curing oven for heating and curing to obtain the shell further includes: The temperature of the curing oven is controlled to be increased in a stepped manner to cure the preform; After curing is complete, open the inflation port to deflate the airbag; After deflation is complete, the airbag is removed from the mold; Remove the housing from the mold.

[0010] Optionally, the stepwise temperature increase of the curing oven to cure the preform further includes: The temperature of the curing oven is raised to 110°C-130°C, and the curing oven is kept at this temperature for two hours for the first stage of curing. After the first stage of curing is completed, raise the temperature of the curing oven to 130°C-160°C and keep the curing oven at that temperature for three hours to carry out the second stage of curing. After the second stage of curing is completed, raise the temperature of the curing oven to 160°C-180°C and keep the oven at that temperature for three hours to carry out the third stage of curing.

[0011] The present invention also provides a housing embodiment, wherein the housing is prepared by means of the method described in any of the above embodiments.

[0012] Optionally, the housing is provided with an inner cavity, a first arm mounting port, a second arm mounting port, a third arm mounting port, a fourth arm mounting port, a battery heat dissipation port, an opening, a through hole, a connecting wire opening, and a gimbal mounting groove. The inner cavity is respectively connected to the first arm mounting port, the second arm mounting port, the third arm mounting port, the fourth arm mounting port, the battery heat dissipation port, the opening, the through hole, and the connecting wire opening.

[0013] Optionally, the length of the inner cavity is greater than or equal to 5 cm and less than or equal to 150 cm; The width of the inner cavity is greater than or equal to 3 cm and less than or equal to 40 cm; The height of the inner cavity is greater than or equal to 2 cm and less than or equal to 30 cm.

[0014] The present invention also provides a fuselage embodiment, the fuselage including an upper cover, a lower frame, a fixing plate and the aforementioned housing; The upper cover is connected to the lower frame, the shell partially encloses the lower frame, and the fixing plate is disposed on the shell.

[0015] The present invention also provides an embodiment of an unmanned aerial vehicle, the unmanned aerial vehicle including a flight control system, a first drive module, a first antenna module, a second drive module, a second antenna module, a third drive module, a third antenna module, a fourth drive module, a fourth antenna module, a gimbal module, a battery module, and the aforementioned fuselage; The flight control system is housed within the fuselage and is electrically connected to the first, second, third, and fourth drive modules. The flight control system controls these modules. The first drive module is located at one end of the first sidewall of the fuselage, near the top of the fuselage. The first antenna module is located at the end of the first drive module furthest from the fuselage. The second drive module is located at one end of the second sidewall of the fuselage, near the top of the fuselage. The second antenna module is located at the end of the second drive module furthest from the fuselage. The third drive module is located at one end of the fuselage, near the bottom of the fuselage, on the other end of the first sidewall of the fuselage. The third antenna module is located at the end of the third drive module away from the fuselage. The fourth drive module is located at the other end of the second sidewall of the fuselage, near the bottom of the fuselage. The fourth antenna module is located at the end of the fourth drive module away from the fuselage. The first sidewall is opposite to the second sidewall. The gimbal module is located in the gimbal mounting slot of the fuselage shell. The battery module is located inside the fuselage and is electrically connected to the flight control system and the gimbal module.

[0016] Optionally, the first drive module includes a first arm, a first drive assembly, and a first electronic speed controller (ESC) assembly. One end of the first arm is located at one end of the first sidewall of the fuselage near the top of the fuselage. A first arm lock is provided at one end of the first arm, which can lock or unlock the first arm. The first drive assembly is located at the other end of the first arm. The first ESC assembly is located in the middle of the first arm. The first ESC assembly is electrically connected to the first drive assembly and the flight control system. The first antenna module is disposed at the other end of the first arm and is located above the first drive assembly. The first antenna module is used to radiate the position signal of the unmanned aerial vehicle and transmit images.

[0017] Optionally, the second drive module includes a second arm, a second drive assembly, and a second electronic speed controller assembly. One end of the second arm is located at one end of the second sidewall of the fuselage near the top of the fuselage. The second drive assembly is located at the other end of the second arm. The second electronic speed controller assembly is located in the middle of the second arm. The second electronic speed controller assembly is electrically connected to the second drive assembly and the flight control system. The second antenna module is disposed at the other end of the second arm and is located above the second drive assembly. The second antenna module is used to radiate the position signal of the unmanned aerial vehicle and transmit images.

[0018] Optionally, the third drive module includes a third arm, a third drive assembly, and a third electronic speed controller assembly. One end of the third arm is located at the other end of the first sidewall of the fuselage near the bottom of the fuselage. The third drive assembly is located at the other end of the third arm. The third electronic speed controller assembly is located in the middle of the third arm. The third electronic speed controller assembly is electrically connected to the third drive assembly and the flight control system. The third antenna module is located inside the third arm and is used to radiate the position signal of the unmanned aerial vehicle and transmit images.

[0019] Optionally, the fourth drive module includes a fourth arm, a fourth drive assembly, and a fourth electronic speed controller assembly. One end of the fourth arm is located at the other end of the second sidewall of the fuselage near the bottom of the fuselage. The fourth drive assembly is located at the other end of the fourth arm. The fourth electronic speed controller assembly is located in the middle of the fourth arm. The fourth electronic speed controller assembly is electrically connected to the fourth drive assembly and the flight control system. The fourth antenna module is located inside the fourth arm and is used to radiate the position signal of the unmanned aerial vehicle and transmit images.

[0020] Optionally, the housing is provided with a receiving slot, and the battery module is received in the receiving slot; the side wall of the receiving slot is provided with a plug-in slot; The battery module includes a handle and a battery lock. The handle is rotatably connected to one end of the battery lock. The battery lock is provided with a pin, which is inserted into the insertion slot, so that the battery module is locked to the body. When the handle is rotated under external force, the handle drives the pin to disengage from the insertion slot, thereby unlocking the battery module from the body.

[0021] The beneficial effects of the embodiments of the present invention are as follows: Unlike the prior art, the embodiments of the present invention provide a method for manufacturing a shell. By inflating an airbag and combining it with a mold to compact a preform, and then placing the mold containing the preform and airbag in a curing oven to heat and cure, the shell is obtained. This achieves the integrated manufacturing of the shell, changing the traditional processing method of segmented manufacturing of the shell and then bonding it together. This achieves lightweight and high strength of the shell, and can disperse stress, avoiding stress concentration in the shell that could lead to breakage. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments of this application will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on the drawings without creative effort.

[0023] Figure 1 This is a flowchart of a method for manufacturing a housing provided in an embodiment of the present invention; Figure 2 yes Figure 1 A detailed flowchart of step 02 in the process; Figure 3 yes Figure 1 Detailed flowchart of step 04 in the process; Figure 4 yes Figure 3 A detailed flowchart of an embodiment of step 041 in the process; Figure 5 yes Figure 3 A detailed flowchart of another embodiment of step 041 in the diagram; Figure 6 yes Figure 3 A detailed flowchart of another embodiment of step 041 in the process; Figure 7 This is a schematic diagram of the fuselage structure of the unmanned aerial vehicle provided in the embodiment of the present invention; Figure 8This is another schematic diagram of the fuselage structure of the unmanned aerial vehicle provided in the embodiment of the present invention; Figure 9 This is a schematic diagram of the structure of the shell in the fuselage of the unmanned aerial vehicle provided in the embodiment; Figure 10 This is a schematic diagram of the structure of the unmanned aerial vehicle provided in an embodiment of the present invention; Figure 11 This is a schematic diagram of the structure of the battery module in the unmanned aerial vehicle provided in an embodiment of the present invention.

[0024] Explanation of reference numerals in the attached figures: 1. Unmanned Aerial Vehicle; 10. Fuselage; 101. Top Cover; 102. Lower Frame; 103. Shell; 1031. Inner Cavity; 1032. First Arm Mounting Port; 1033. Second Arm Mounting Port; 1034. Third Arm Mounting Port; 105. Fourth Arm Mounting Port; 1036. Battery Heat Dissipation Vent; 1037. Opening; 1038. Through Hole; 1039. Connecting Cable Opening; 103a. Gimbal Mounting Slot; 104. Fixing Plate; 105. Reception Slot; 106. Plug-in Slot; 11. First Drive Module; 111. First Arm; 1111. First Arm Lock; 112. First Drive Assembly; 113. First Electronic Speed ​​Controller Assembly; 2. First antenna module; 13. Second drive module; 131. Second arm; 1311. Second arm lock; 132. Second drive assembly; 133. Second electronic speed control assembly; 14. Second antenna module; 15. Third drive module; 151. Third arm; 1511. Third arm lock; 152. Third drive assembly; 153. Third electronic speed control assembly; 16. Fourth drive module; 161. Fourth arm; 1611. Fourth arm lock; 162. Fourth drive assembly; 163. Fourth electronic speed control assembly; 17. Battery module; 171. Battery; 1711. Placement slot; 172. Handle; 173. Battery lock; 1731. Pin. Detailed Implementation

[0025] To facilitate understanding of the present invention, a more detailed description is provided below with reference to the accompanying drawings and specific embodiments. It should be noted that when an element is described as being "fixed to" another element, it can be directly on the other element, or one or more intermediate elements may exist between them. When an element is described as being "connected to" another element, it can be directly connected to the other element, or one or more intermediate elements may exist between them. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this specification are for illustrative purposes only.

[0026] Unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the invention. The term "and / or" as used in this specification includes any and all combinations of one or more of the associated listed items.

[0027] Please see Figure 1 , Figure 1 This is a flowchart of a method for manufacturing the housing 103 according to the present invention, the method comprising: Step 01: Provide the preform, airbag, mold and curing oven.

[0028] The airbag is shaped like the inner cavity of the shell 103 and has an inflation port.

[0029] In some embodiments, the airbag includes a shell and a filler. The shell encloses the filler, which is shaped like the inner cavity of the shell 103, such that the airbag is shaped like the inner cavity 1031 of the shell 103. The filler is made of polystyrene foam, which shrinks when heated. During the manufacture of the filler, an engraving device is used to engrave the outer surface of the filler into the shape of the inner cavity 1031 of the shell 103.

[0030] It is understood that in some embodiments, the surface of the housing is provided with a release cloth, which is used to facilitate the separation of the housing 103.

[0031] Step 02: Apply the preform to the surface of the airbag.

[0032] The preform comprises an outer layer, a first reinforcing member, a second reinforcing member, a third reinforcing member, a fourth reinforcing member, and an inner layer. Both the outer and inner layers are made of aramid epoxy prepreg, which possesses excellent mechanical properties: a strength of 3.6 GPa, an elongation modulus of 131 GPa, and an elongation at break of 2.8%. It also exhibits excellent thermal properties, with a long-term service temperature of 180℃, an axial thermal expansion coefficient of -2 × 10⁻⁶ / K, and a thermal conductivity of 0.048 W / (m·K). The first, second, third, and fourth reinforcing members are all made of PVC foam. PVC foam provides lightweight rigid support and exhibits good durability and compressive strength. The first, second, third, and fourth reinforcing members serve to increase strength and distribute stress. Optionally, the first, second, third, and fourth reinforcing members can also be made of different materials, such as one or more of EVA foam, polyurethane foam, PE foam, PP foam, and PVC foam. The material of the corresponding reinforcing member can be selected and set according to the stress borne by each area.

[0033] In some embodiments, the aramid epoxy prepreg is a semi-solid, viscous epoxy resin.

[0034] In some embodiments, please refer to Figure 2 Step 02 further includes: Step 021: Lay the inner layer on the surface of the airbag.

[0035] Step 022: Lay the first reinforcing member, the second reinforcing member, the third reinforcing member and the fourth reinforcing member in the preset first area a, the preset second area b, the preset third area c and the preset fourth area d respectively.

[0036] Please refer to Figure 9 Preset first region a is the peripheral region where the housing 103 connects to the first arm 111. Preset second region b is the peripheral region where the housing 103 connects to the second arm 131. Preset third region c is the peripheral region where the housing 103 connects to the third arm 151. Preset fourth region d is the peripheral region where the housing 103 connects to the fourth arm 161. Preset first region a, preset second region b, preset third region c, and preset fourth region d are the main stress-bearing regions of the housing 103. The remaining regions of the housing 103 other than preset first region a, preset second region b, preset third region c, and preset fourth region d are preset fifth regions, and preset fifth region e is the secondary stress-bearing region of the housing 103.

[0037] Step 023: Lay the outer layer on the surface of the inner layer, and sandwich the inner and outer layers of the first region a with a first reinforcing member, sandwich the inner and outer layers of the second region b with a second reinforcing member, sandwich the inner and outer layers of the third region c with a third reinforcing member, and sandwich the inner and outer layers of the fourth region d with a fourth reinforcing member.

[0038] The pre-defined fifth region's secondary stress-bearing area includes an inner layer and an outer layer, both of which are two layers of aramid epoxy prepreg.

[0039] Step 03: Place the airbag with the preform on it into the mold, and inflate the airbag through the air inlet to compact the preform.

[0040] Step 04: Stop inflating the airbag and seal the inflation port, then place the mold with the preform and airbag in a curing oven to heat and cure, thus obtaining the shell.

[0041] In some embodiments, please refer to Figure 3 Step 04 includes: Step 041: Control the temperature of the curing oven to increase in a stepwise manner to cure the preform.

[0042] Step 042: After curing, open the inflation port to deflate the airbag.

[0043] Step 043: After deflation is complete, remove the airbag from the mold.

[0044] Step 044: Remove the housing 103 from the mold.

[0045] In some embodiments, please refer to Figure 4 Step 041 includes: Step 0411: Raise the temperature of the curing oven to 110°C-130°C and keep the curing oven at that temperature for two hours to carry out the first stage of curing; Step 0412: After the first stage of curing is completed, raise the temperature of the curing oven to 130°C-160°C and keep the curing oven at that temperature for three hours to carry out the second stage of curing; Step 0413: After the second stage of curing is completed, raise the temperature of the curing oven to 160°C-180°C and keep the curing oven at that temperature for three hours to carry out the third stage of curing.

[0046] It should be noted that step 041 can also be implemented in other ways, for example: please refer to Figure 5 Step 04 includes: Step 0411': Raise the temperature of the curing oven to 110°C-130°C and keep the curing oven at that temperature for two hours to carry out the first stage of curing.

[0047] Step 0412': After the first stage of curing is completed, raise the temperature of the curing oven to 130°C-160°C and keep the curing oven at that temperature for four hours to carry out the second stage of curing.

[0048] Step 0413': After the second stage of curing is completed, raise the temperature of the curing oven to 160°C-180°C and keep the curing oven at that temperature for six hours to carry out the third stage of curing.

[0049] It should be noted that step 041 can also be implemented in other ways, for example: please refer to Figure 6 Step 041 includes: Step 0411: Raise the temperature of the curing oven to 110°C-130°C and keep the curing oven at that temperature for four hours to carry out the first stage of curing.

[0050] Step 0412: After the first stage of curing is completed, raise the temperature of the curing oven to 130°C-160°C and keep the curing oven at this temperature for six hours to carry out the second stage of curing.

[0051] Step 0413: After the second stage of curing is completed, raise the temperature of the curing oven to 160°C-180°C and keep the oven at that temperature for eight hours for the third stage of curing. During the first stage of curing, it is usually necessary to keep the temperature at 110°C-130°C for two to four hours to allow the epoxy resin to begin the curing reaction and form a certain cross-linked structure. This also helps to remove moisture and volatiles from the preform, reduce air bubbles, and ensure the quality of the finished shell.

[0052] During the second stage of curing, it is usually necessary to keep the temperature at 130°C-160°C for three to six hours to increase the cross-linked structure and gradually increase the strength and hardness of the shell during the fabrication process.

[0053] During the third stage of curing, the through-channel needs to be kept at a temperature of 160°C-180°C for three to eight hours to ensure that the epoxy resin is completely cured. Complete curing can improve the strength, rigidity, heat resistance and corrosion resistance of the manufactured shell, and improve the performance of the manufactured shell in practical applications.

[0054] In this embodiment of the invention, the preform is formed by inflating the airbag and compacting it with a mold. The mold containing the preform and the airbag is then placed in a curing oven and heated to cure, resulting in the shell 103. This achieves the integral manufacturing of the shell 103, changing the traditional processing method of segmented manufacturing of the shell 103 and bonding it together. This achieves lightweight and high strength of the shell 103, and can disperse stress, avoiding stress concentration and breakage of the shell 103. The integrally manufactured shell 103 has advantages such as bending resistance, impact resistance, good toughness, light weight, and good environmental adaptability.

[0055] The present invention also provides an embodiment of housing 103, wherein housing 103 is prepared by the method described above.

[0056] For the aforementioned housing, please refer to Figure 9 The housing 103 is provided with an inner cavity 1031, a first arm mounting port 1032, a second arm mounting port 1033, a third arm mounting port 1034, a fourth arm mounting port 1035, a battery heat dissipation port 1036, an opening 1037, a through hole 1038, a connecting wire opening 1039, and a gimbal mounting slot 1039. The inner cavity 1031 is connected to the first arm mounting port 1032, the second arm mounting port 1033, the third arm mounting port 1034, the fourth arm mounting port 1035, the battery heat dissipation port 1036, the opening 1037, the through hole 1038, and the connecting wire opening 1039. The through hole 1038 is used for the radar to pass through.

[0057] The length of the inner cavity 1031 is greater than or equal to 5 cm and less than or equal to 150 cm, the width of the inner cavity 1031 is greater than or equal to 3 cm and less than or equal to 40 cm, and the height of the inner cavity 1031 is greater than or equal to 2 cm and less than or equal to 30 cm.

[0058] The present invention also provides 10 embodiments of the fuselage, please refer to [link / reference]. Figures 7-8 The fuselage 10 includes an upper cover 101, a lower frame 102, a fixing plate 104, and the aforementioned housing 103. The upper cover 101 and the lower frame 102 are connected. The housing 103 partially covers the lower frame 102. The fixing plate 104 is fixed to the opening 1037 of the housing 1031. The fuselage 10 is provided with a receiving groove 105, and the side wall of the receiving groove 105 is provided with a insertion groove 106.

[0059] This invention also provides an embodiment of an unmanned aerial vehicle, please refer to [link / reference]. Figure 10 The unmanned aerial vehicle 1 includes a flight control system (not shown), a first drive module 11, a first antenna module 12, a second drive module 13, a second antenna module 14, a third drive module 15, a third antenna module (not shown), a fourth drive module 16, a fourth antenna module (not shown), a gimbal module (not shown), a battery module 17, and the aforementioned fuselage 10. For the specific structure and function of the fuselage 10, please refer to the above embodiments, which will not be repeated here.

[0060] The flight control system is located inside the fuselage 10 and is electrically connected to the first drive module 11, the second drive module 13, the third drive module 15, and the fourth drive module 16. The flight control system controls the first drive module 11, the second drive module 13, the third drive module 15, and the fourth drive module 16. The first drive module 11 is located on the first sidewall of the fuselage 10 near the top of the fuselage 10. The first antenna module 12 is located at the end of the first drive module 11 away from the fuselage 10. The second drive module 13 is located on the second sidewall of the fuselage 10 near the top of the fuselage 10. The second antenna module 14 is located on the second sidewall of the fuselage 10 near the top of the fuselage 10. The second drive module 13 is located at the end furthest from the fuselage 10. The third drive module 15 is located on the first side wall of the fuselage 10 near the bottom of the fuselage 10. The third antenna module is located at the end of the third drive module 15 furthest from the fuselage 10. The fourth drive module 16 is located on the second side wall of the fuselage 10 near the bottom of the fuselage 10. The fourth antenna module is located at the end of the fourth drive module 16 furthest from the fuselage 10. The first side wall and the second side wall are opposite each other. The gimbal module is located in the gimbal mounting slot 103a of the housing 103 of the fuselage 10. The battery module 17 is located inside the fuselage 10 and is electrically connected to the flight control system and the gimbal module.

[0061] For the first driving module 11 mentioned above, please refer to Figure 10The first drive module 11 includes a first arm 111, a first drive assembly 112, and a first electronic speed controller (ESC) assembly 113. One end of the first arm 111 is located near the top of the first sidewall of the fuselage 10, and a first arm lock 1111 is provided at one end of the first arm 111 to lock or unlock the first arm 111. The first drive assembly 112 is located at the other end of the first arm 111 and is used to drive the unmanned aerial vehicle (UAV) 1 in flight. The first ESC assembly 113 is located in the middle of the first arm 111 and is electrically connected to the first drive assembly 112 and the flight control system. The flight control system is used to control the first ESC assembly 113, and in turn, to control the start, stop, and speed of the motors in the first drive assembly 112.

[0062] For the first antenna module 12 mentioned above, please refer to Figure 10 The first antenna module 12 is disposed at the other end of the first arm 111 and is located above the first drive assembly 112. The first antenna module 12 is used to radiate the position signal of the unmanned aerial vehicle 1 and transmit images.

[0063] For the second drive module 13 mentioned above, please refer to Figure 10 The second drive module 13 includes a second arm 131, a second drive assembly 132, and a second electronic speed controller (ESC) assembly 133. One end of the second arm 131 is located near the top of the second sidewall of the fuselage 10. A second arm lock 1311 is provided at one end of the second arm 131, which can lock or unlock the second arm 131. The second drive assembly 132 is located at the other end of the second arm 131 and is used to drive the unmanned aerial vehicle 1 to fly. The second ESC assembly 133 is located in the middle of the second arm 131 and is electrically connected to the second drive assembly 132 and the flight control system. The flight control system is used to control the second ESC assembly 133, and in turn, to control the start, stop, and speed of the motors in the second drive assembly 132.

[0064] For the second antenna module 14 mentioned above, please refer to Figure 10 The second antenna module 14 is located at the other end of the second arm 131 and is situated above the second drive assembly 132. The second antenna module 14 is used to radiate the position signal of the unmanned aerial vehicle 1 and transmit images.

[0065] For the third drive module 15 mentioned above, please refer to Figure 10The third drive module 15 includes a third arm 151, a third drive assembly 152, and a third electronic speed controller (ESC) assembly 153. One end of the third arm 151 is located at the other end of the first sidewall of the fuselage 10, near the bottom of the fuselage 10. A third arm lock 1511 is provided at one end of the third arm 151, which can lock or unlock the third arm 151. The third drive assembly 152 is located at the other end of the third arm 151 and is used to drive the unmanned aerial vehicle 1 to fly. The third ESC assembly 153 is located in the middle of the third arm 151 and is electrically connected to the third drive assembly 152 and the flight control system. The flight control system is used to control the third ESC assembly 153, and in turn, to control the start, stop, and speed of the motors in the third drive assembly 152.

[0066] The third antenna module is located inside the third arm 151 and is used to radiate the position signal of the unmanned aerial vehicle 1 and transmit images.

[0067] For the fourth drive module 16 mentioned above, please refer to Figure 10 The fourth drive module 16 includes a fourth arm 161, a fourth drive assembly 162, and a fourth electronic speed controller (ESC) assembly 163. One end of the fourth arm 161 is located at the other end of the second sidewall of the fuselage 10, near the bottom of the fuselage 10. A fourth arm lock 1611 is provided at one end of the fourth arm 161, which can lock or unlock the fourth arm 161. The fourth drive assembly 162 is located at the other end of the fourth arm 161 and is used to drive the unmanned aerial vehicle 1 to fly. The fourth ESC assembly 163 is located in the middle of the fourth arm 161 and is electrically connected to the fourth drive assembly 162 and the flight control system. The flight control system is used to control the fourth ESC assembly 163, and in turn, to control the start, stop, and speed of the motors in the fourth drive assembly 162.

[0068] The fourth antenna module is located inside the fourth arm 161 and is used to radiate the position signal of the unmanned aerial vehicle 1 and transmit images.

[0069] For the battery module 17 mentioned above, please refer to Figure 11The battery module 17 includes a battery 171, a handle 172, and a battery lock 173. The battery 171 is housed in a receiving slot 105 and has a placement slot 1711. The battery 171 is electrically connected to the flight control system and the gimbal module. The handle 172 is rotatably housed in the placement slot 1711 and is rotatably connected to the battery 171, facilitating easy handling of the battery 171. The battery lock 173 is fixed to the placement slot 1711, with one end rotatably connected to the handle 172. The battery lock 173 has a pin 1731 that inserts into a insertion slot 106, fixing the battery module 17 to the fuselage 10. The pin 1731 can slide relative to the insertion slot 106. When the handle 172 is rotated under the action of external force, the handle 172 drives the pin 1731 to slide away from the bottom of the insertion slot 106, so that the pin 1731 is disengaged from the insertion slot 106, thereby unlocking the battery module 17 from the body 10, so that the user can take the battery module 17 out of the receiving slot 105.

[0070] It should be noted that while the preferred embodiments of the present invention are given in the specification and accompanying drawings, the present invention can be implemented in many different forms and is not limited to the embodiments described herein. These embodiments are not intended to impose additional limitations on the content of the present invention; their purpose is to provide a more thorough and comprehensive understanding of the disclosure of the present invention. Furthermore, the above-described technical features can be combined with each other to form various embodiments not listed above, all of which are considered to be within the scope of the present invention specification. Moreover, those skilled in the art can make improvements or modifications based on the above description, and all such improvements and modifications should fall within the protection scope of the appended claims.

Claims

1. A method for manufacturing a housing, characterized in that, include: Provided a preform, an airbag, a mold, and a curing oven, wherein the airbag is shaped like the inner cavity of a shell and is provided with an inflation port; The preform is laid on the surface of the airbag; The airbag with the preform is placed in the mold, and air is injected into the airbag through the air inlet to compact the preform; Stop inflating the airbag and seal the inflation port, and place the mold containing the preform and airbag in the curing oven to heat and cure to obtain the shell; The step of stopping inflation of the airbag and sealing the inflation port, and placing the mold containing the preform and the airbag in the curing oven for heating and curing to obtain the shell further includes: The temperature of the curing oven is controlled to be increased in a stepped manner to cure the preform; After curing is complete, open the inflation port to deflate the airbag; After deflation is complete, the airbag is removed from the mold; Remove the housing from the mold.

2. The method for manufacturing a housing according to claim 1, characterized in that, The preform includes an outer layer, a first reinforcing member, a second reinforcing member, a third reinforcing member, a fourth reinforcing member, and an inner layer; The step of applying the preform to the surface of the airbag further includes: The inner layer is laid on the surface of the airbag; The first reinforcing member, the second reinforcing member, the third reinforcing member, and the fourth reinforcing member are respectively laid in the preset first area, the preset second area, the preset third area, and the preset fourth area; The outer layer is laid on the surface of the inner layer. The first reinforcing member is sandwiched between the inner layer and the outer layer in a predetermined first region. The second reinforcing member is sandwiched between the inner layer and the outer layer in a predetermined second region. The third reinforcing member is sandwiched between the inner layer and the outer layer in a predetermined third region. The fourth reinforcing member is sandwiched between the inner layer and the outer layer in a predetermined fourth region.

3. The method for manufacturing the shell according to claim 2, characterized in that, The preset first region, preset second region, preset third region and preset fourth region are the main stress-bearing regions of the shell, and the remaining regions of the inner layer other than the preset first region, preset second region, preset third region and preset fourth region are the preset fifth region, which is the secondary stress-bearing region of the shell.

4. The method for manufacturing the shell according to claim 3, characterized in that, The secondary stress-bearing region includes an outer layer and an inner layer from the outside in.

5. The method for manufacturing a housing according to claim 1, characterized in that, The stepwise temperature increase of the curing oven to cure the preform further includes: The temperature of the curing oven is raised to 110°C-130°C, and the curing oven is kept at this temperature for two hours for the first stage of curing. After the first stage of curing is completed, raise the temperature of the curing oven to 130°C-160°C and keep the curing oven at that temperature for three hours to carry out the second stage of curing. After the second stage of curing is completed, raise the temperature of the curing oven to 160°C-180°C and keep the oven at that temperature for three hours to carry out the third stage of curing.

6. A housing, characterized in that, The shell is prepared by the method described in any one of claims 1-5.

7. The housing according to claim 6, characterized in that, The housing is provided with an inner cavity, a first arm mounting port, a second arm mounting port, a third arm mounting port, a fourth arm mounting port, a battery heat dissipation port, an opening, a through hole, a connecting wire opening, and a gimbal mounting slot. The inner cavity is connected to the first arm mounting port, the second arm mounting port, the third arm mounting port, the fourth arm mounting port, the battery heat dissipation port, the opening, the through hole, and the connecting wire opening, respectively.

8. The housing according to claim 7, characterized in that, The length of the inner cavity is greater than or equal to 5 cm and less than or equal to 150 cm; The width of the inner cavity is greater than or equal to 3 cm and less than or equal to 40 cm; The height of the inner cavity is greater than or equal to 2 cm and less than or equal to 30 cm.

9. A fuselage, characterized in that, Includes an upper cover, a lower frame, a fixing plate, and a housing as described in any one of claims 6-8; The upper cover is connected to the lower frame, the shell partially encloses the lower frame, and the fixing plate is disposed on the shell.

10. An unmanned aerial vehicle, characterized in that, It includes a flight control system, a first drive module, a first antenna module, a second drive module, a second antenna module, a third drive module, a third antenna module, a fourth drive module, a fourth antenna module, a gimbal module, a battery module, and the fuselage as described in claim 9; The flight control system is housed within the fuselage and is electrically connected to the first, second, third, and fourth drive modules. The flight control system controls these modules. The first drive module is located at one end of the first sidewall of the fuselage, near the top of the fuselage. The first antenna module is located at the end of the first drive module furthest from the fuselage. The second drive module is located at one end of the second sidewall of the fuselage, near the top of the fuselage. The second antenna module is located at the end of the second drive module furthest from the fuselage. The third drive module is located at one end of the fuselage, near the bottom of the fuselage, on the other end of the first sidewall of the fuselage. The third antenna module is located at the end of the third drive module away from the fuselage. The fourth drive module is located at the other end of the second sidewall of the fuselage, near the bottom of the fuselage. The fourth antenna module is located at the end of the fourth drive module away from the fuselage. The first sidewall is opposite to the second sidewall. The gimbal module is located in the gimbal mounting slot of the fuselage shell. The battery module is located inside the fuselage and is electrically connected to the flight control system and the gimbal module.

11. The unmanned aerial vehicle according to claim 10, characterized in that... The first drive module includes a first arm, a first drive assembly, and a first electronic speed controller (ESC) assembly. One end of the first arm is located at one end of the first sidewall of the fuselage near the top of the fuselage. A first arm lock is provided at one end of the first arm, which can lock or unlock the first arm. The first drive assembly is located at the other end of the first arm. The first ESC assembly is located in the middle of the first arm. The first ESC assembly is electrically connected to the first drive assembly and the flight control system. The first antenna module is disposed at the other end of the first arm and is located above the first drive assembly. The first antenna module is used to radiate the position signal of the unmanned aerial vehicle and transmit images.

12. The unmanned aerial vehicle according to claim 10, characterized in that, The second drive module includes a second arm, a second drive assembly, and a second electronic speed controller (ESC) assembly. One end of the second arm is located at one end of the second sidewall of the fuselage near the top of the fuselage. The second drive assembly is located at the other end of the second arm. The second ESC assembly is located in the middle of the second arm. The second ESC assembly is electrically connected to the second drive assembly and the flight control system. The second antenna module is disposed at the other end of the second arm and is located above the second drive assembly. The second antenna module is used to radiate the position signal of the unmanned aerial vehicle and transmit images.

13. The unmanned aerial vehicle according to claim 10, characterized in that, The third drive module includes a third arm, a third drive assembly, and a third electronic speed controller assembly. One end of the third arm is located at the other end of the first sidewall of the fuselage near the bottom of the fuselage. The third drive assembly is located at the other end of the third arm. The third electronic speed controller assembly is located in the middle of the third arm. The third electronic speed controller assembly is electrically connected to the third drive assembly and the flight control system. The third antenna module is located inside the third arm and is used to radiate the position signal of the unmanned aerial vehicle and transmit images.

14. The unmanned aerial vehicle according to claim 10, characterized in that, The fourth drive module includes a fourth arm, a fourth drive assembly, and a fourth electronic speed controller assembly. One end of the fourth arm is located at the other end of the second side wall of the fuselage near the bottom of the fuselage. The fourth drive assembly is located at the other end of the fourth arm. The fourth electronic speed controller assembly is located in the middle of the fourth arm. The fourth electronic speed controller assembly is electrically connected to the fourth drive assembly and the flight control system. The fourth antenna module is located inside the fourth arm and is used to radiate the position signal of the unmanned aerial vehicle and transmit images.

15. The unmanned aerial vehicle according to claim 10, characterized in that, The fuselage is provided with a receiving slot, the battery module is received in the receiving slot, and the side wall of the receiving slot is provided with a plug-in slot. The battery module includes a handle and a battery lock. The handle is rotatably connected to one end of the battery lock. The battery lock is provided with a pin, which is inserted into the insertion slot, so that the battery module is locked to the body. When the handle is rotated under external force, the handle drives the pin to disengage from the insertion slot, thereby unlocking the battery module from the body.

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