An assembly process for reinforcing a target drone

Abstract

The application provides an assembly process for reinforcing a target machine, relates to the technical field of composite material target machine body assembly, and comprises the following steps: the assembly process is used for assembling the reinforcing target machine through an assembly tool, the assembly tool comprises a lower fixing device, an upper fixing device, a mold closing device, a wing positioning device, a horizontal tail positioning device and a fuselage limiting device, and the assembly process comprises the following steps: pretreating the upper fuselage skin and the lower fuselage skin after demolding; positioning the lower fixing device and the fuselage limiting device through positioning pins, connecting them through bolts and reserving a 5mm clamping gap, and placing the pretreated lower fuselage skin into the lower fixing device. The application provides an assembly process for reinforcing a target machine, effectively reduces the total artificial consumption in the assembly process, has high overall strength and high use reliability, and does not need subsequent secondary grinding.

Description

Technical Field

[0001] This application relates to the field of composite material target assembly technology, and in particular to an assembly process for reinforcing target machines. Background Technology

[0002] Currently, there are generally two methods for assembling the body of traditional composite material target machines, i.e., reinforced target machines. One method is to use a molding die for positioning and assembly. The other method is to assemble the body in a free state after demolding.

[0003] The molding die positioning and assembly method uses the die body as the base of the assembly fixture to fix the target drone body. Then, calipers and measuring tapes are used to mark and position the internal partition frames. Afterwards, the upper and lower fuselage molding dies are used for guiding and positioning, and the upper and lower fuselage bodies are closed using their own weight. Because this type of fuselage molding die is usually made of steel and typically weighs over 1 ton, the current traditional assembly method for fuselage assembly poses safety hazards during closure and results in a large workload and high cost. Furthermore, the positioning accuracy using tools such as steel rulers and calipers during fuselage closure is inaccurate. When subsequently adapting the fuselage to other target drone body components such as wings and tail fins, dimensional deviations may prevent successful assembly on the first attempt. Moreover, the fuselage components require grinding, which may lead to the risk of scrapping them. Furthermore, the upper and lower bodies are molded together in one go. During the mold-closing process, the partition frames, which are marked and positioned, are placed freely. When the molding mold is closed, the weight of the mold may cause the reinforcing partition frames to move, resulting in a decrease in the overall strength of the reinforced target machine after mold closing.

[0004] The traditional assembly method for assembling composite target drone bodies involves assembling the fuselage in its free state after demolding. This is typically done by positioning the upper and lower fuselage sections in a free state using pre-defined positioning spaces. The upper and lower fuselage sections are pressurized using F-clamps, C-clamps, and other clamps. Multiple internal partitions are positioned using calipers or tape measures, and then pre-positioned and bonded with super-drying adhesive. This assembly method results in inaccurate positioning of the partitions using tools like steel rulers and calipers. This can lead to difficulties in assembling other target drone components such as wings and tail fins in a single assembly, requiring reworking and potentially even scrapping the entire drone. Furthermore, using super-drying adhesive to fix the partitions can cause displacement due to external pressure during the mold-closing process, reducing the overall strength of the reinforced target drone after mold closing. Summary of the Invention

[0005] The purpose of this application is to address the above problems by providing an assembly process for strengthening a target machine. The multiple devices of the assembly fixture are accurately positioned and stably connected. The strengthened target machine can be detached from the forming mold and assembled. The assembled strengthened target machine has high overall strength and high reliability, and does not require subsequent secondary grinding.

[0006] This application provides an assembly process for reinforcing a target drone. The assembly process uses an assembly fixture to assemble the reinforced target drone. The assembly fixture includes a lower fixing device, an upper fixing device, a mold closing device, a wing positioning device, a horizontal tail positioning device, and a fuselage limiting device. The assembly process includes: pre-treating the upper and lower fuselage skins after demolding; positioning the lower fixing device and the fuselage limiting device with positioning pins, then connecting them with bolts and leaving a 5mm clamping gap; placing the pre-treated lower fuselage skin into the lower fixing device, so that the lower fixing device... The support bracket of the fixing device supports the lower fuselage skin, and then the 5mm clamping gap between the lower fixing device and the fuselage limiting device is locked; multiple first connecting metal parts and multiple first partition frames are pre-treated for bonding, and after the pre-treatment is completed, they are bonded to the inner surface of the lower fuselage skin. Multiple positioning frames of the upper fixing device are respectively positioned with positioning pins and then bolted to the lower fixing device and the tailstock positioning device, thereby bonding multiple first connecting metal parts and multiple first partition frames to the lower fuselage skin. Simultaneously, the fuselage skin is... The body limiting device is bolted to the first first partition frame; the device, which has been positioned by positioning pins and bolted together, is cured at room temperature for a predetermined time, and after curing, the upper fixing device and the flat tail positioning device are removed; adhesive is applied to the inner surface of the upper fuselage skin and then bonded to multiple first connecting metal parts and multiple first partition frames to align with the lower fuselage skin placed on the lower fixing device; the mold closing device is positioned to the lower fixing device using positioning pins and then bolted together; multiple positioning frames are connected from the upper fuselage... The upper part of the skin is connected to the mold-closing device, so that the upper fuselage skin and the lower fuselage skin are molded together. Among the multiple positioning frames, two of the positioning frames are respectively positioned with the horizontal stabilizer positioning device and the wing positioning device using positioning pins and then clamped by bolts. The horizontal stabilizer positioning device is connected to the horizontal stabilizer connecting metal part by positioning pins. After the multiple devices of the assembly fixture are positioned and clamped by bolts, they are cured at room temperature for a predetermined time. After curing, the multiple devices of the assembly fixture are removed so that the reinforced target machine can be taken out of the assembly fixture.

[0007] According to the technical solutions provided in certain embodiments of this application, the step of applying adhesive to the inner surface of the upper fuselage skin and bonding it to a plurality of first connecting metal parts and a plurality of first partition frames to mate with the lower fuselage skin placed on the lower fixing device includes: performing pre-bonding treatment on the plurality of first connecting metal parts, the plurality of first partition frames and the upper fuselage skin.

[0008] According to the technical solutions provided in certain embodiments of this application, the step of positioning the mold closing device and the lower fixing device with positioning pins and then clamping them together with bolts includes: positioning both mating plates of the mold closing device and the lower fixing device with positioning pins and then clamping them together with bolts.

[0009] According to the technical solutions provided in certain embodiments of this application, the flat-tail positioning device is connected to the flat-tail connecting metal part by a positioning pin, including: positioning the flat-tail positioning device and the lower fixing device by a positioning pin; positioning the flat-tail positioning device, which is positioned with the lower fixing device by a positioning pin, and the flat-tail connecting metal part by a positioning pin and clamping them with bolts.

[0010] According to the technical solutions provided in certain embodiments of this application, the predetermined time for room temperature curing is at least 12 hours.

[0011] According to the technical solutions provided in certain embodiments of this application, the pretreatment involves trimming the rough edges or burrs of the demolded upper body skin and the lower body skin, and polishing the bonding surfaces of the upper body skin and the lower body skin.

[0012] According to the technical solutions provided in certain embodiments of this application, the connection gaps between the multiple devices of the assembly fixture are all no greater than 0.1 mm.

[0013] Compared with the prior art, the beneficial effects of this application are as follows: The lower fixing device and the upper fixing device are positioned by locating pins and then clamped together with bolts. This ensures that after the upper fixing device is assembled with the upper fuselage skin, and the lower fixing device is assembled with the lower fuselage skin, the positions of the upper and lower fuselage skins automatically correspond after the upper and lower fixing devices are connected, guaranteeing a stable connection without dimensional deviations. After connecting the mold-closing device to the lower fixing device, the mold-closing device can mold the upper and lower fuselage skins, ensuring high mold-closing accuracy and positional correspondence. This avoids secondary rework caused by misalignment of the upper and lower fuselage skins, reducing losses and costs. Furthermore, the manual operation is simple, and the resulting reinforced target machine body has high strength, reducing overall costs by more than 30%. This application is suitable for the assembly and manufacturing of target machine bodies for this type of reinforced target machine. Furthermore, the assembly process for reinforcing the target drone in this application involves bonding and positioning the upper and lower fuselage skins to the first bulkhead in stages. Specifically, after bonding and positioning the lower fuselage skin to the first bulkhead, the upper and lower fuselage skins are then pressurized and molded together. This assembly method ensures the compressive force and positioning accuracy during the molding of the reinforced target drone's body. This strengthens the bonding strength of the adhesive surfaces of the upper and lower fuselage skins and the positioning layout of the corresponding bulkhead, achieving a unified positioning assembly effect. This increases product reliability and enhances the overall strength of the product. Moreover, the wings and horizontal stabilizer are positioned using dedicated positioning devices, further ensuring the accuracy of subsequent installation interfaces after connection. This reduces the risk of extensive grinding or scrapping during subsequent adaptation. Furthermore, with the multi-positioning and staged bonding and pressurization, the entire assembly process does not require mold transfer, simplifying the process and facilitating demolding, effectively reducing labor and material costs. The main body of the reinforced target drone requires high dimensional accuracy and precision control.

[0014] It should be understood that the descriptions of technical features, technical solutions, beneficial effects, or similar language in this application do not imply that all features and advantages can be achieved in any single embodiment. Rather, it is understood that the description of a feature or beneficial effect means that a specific technical feature, technical solution, or beneficial effect is included in at least one embodiment. Therefore, the descriptions of technical features, technical solutions, or beneficial effects in this specification do not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions, and beneficial effects described in this embodiment can be combined in any suitable manner. Those skilled in the art will understand that embodiments can be implemented without one or more specific technical features, technical solutions, or beneficial effects of a particular embodiment. In other embodiments, additional technical features and beneficial effects may be identified in specific embodiments that do not embody all embodiments. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A three-dimensional structural schematic diagram of an assembly fixture for reinforcing a target machine provided in an embodiment of this application;

[0017] Figure 2 A three-dimensional structural schematic diagram of an assembly fixture for reinforcing a target machine, provided as an embodiment of this application;

[0018] Figure 3 A partial three-dimensional structural schematic diagram of an assembly fixture for reinforcing a target machine provided in an embodiment of this application;

[0019] Figure 4 A partial top view of an assembly fixture for reinforcing a target machine provided in an embodiment of this application;

[0020] Figure 5 A partial three-dimensional structural schematic diagram of an assembly fixture for reinforcing a target machine provided in an embodiment of this application;

[0021] Figure 6 A three-dimensional structural diagram of an assembly fixture for reinforcing a target drone and the upper and lower fuselage skins of the target drone provided in this application;

[0022] Figure 7 for Figure 6 Enlarged view of a portion of point A in the middle;

[0023] Figure 8 A flowchart illustrating an assembly process for reinforcing a target machine, provided as an embodiment of this application;

[0024] Figure 9 A step-by-step flowchart of step S9 in the assembly process for strengthening a target machine, provided in an embodiment of this application;

[0025] Figure 10 This is a step-by-step flowchart of step S7 in the assembly process for strengthening a target machine, provided in an embodiment of this application.

[0026] The text labels in the image represent:

[0027] 100. Assembly tooling;

[0028] 110. Lower fixing device; 111. Support frame; 112. Mating plate; 120. Upper fixing device; 121. Positioning frame;

[0029] 130. Mold closing device; 140. Wing positioning device;

[0030] 150. Horizontal stabilizer positioning device; 160. Fuselage limiting device;

[0031] 170. Bolts;

[0032] 200. Enhance the target drone;

[0033] 210. Upper fuselage skin; 220. Lower fuselage skin. Detailed Implementation

[0034] To enable those skilled in the art to better understand the technical solutions of this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. The descriptions in this section are merely illustrative and explanatory, and should not be construed as limiting the scope of protection of this application. Specifically, the described embodiments are only some embodiments of this application, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort should fall within the scope of protection of this application.

[0035] It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such process, method, product, or apparatus.

[0036] As mentioned in the background section, there are currently two common methods for assembling the body of traditional composite material target machines, i.e., reinforced target machines. One method is to use a molding die for positioning and assembly. The other method is to assemble the body in a free state after demolding.

[0037] The molding die positioning and assembly method uses the die body as the base of the assembly fixture to fix the target drone body. Then, calipers and measuring tapes are used to mark and position the internal partition frames. Afterwards, the upper and lower fuselage molding dies are used for guiding and positioning, and the upper and lower fuselage bodies are closed using their own weight. Because this type of fuselage molding die is usually made of steel and typically weighs over 1 ton, the current traditional assembly method for fuselage assembly poses safety hazards during closure and results in a large workload and high cost. Furthermore, the positioning accuracy using tools such as steel rulers and calipers during fuselage closure is inaccurate. When subsequently adapting the fuselage to other target drone body components such as wings and tail fins, dimensional deviations may prevent successful assembly on the first attempt. Moreover, the fuselage components require grinding, which may lead to the risk of scrapping them. Furthermore, the upper and lower bodies are molded together in one go. During the mold-closing process, the partition frames, which are marked and positioned, are placed freely. When the molding mold is closed, the weight of the mold may cause the reinforcing partition frames to move, resulting in a decrease in the overall strength of the reinforced target machine after mold closing.

[0038] The traditional assembly method for assembling composite target drone bodies involves assembling the fuselage in its free state after demolding. This is typically done by positioning the upper and lower fuselage sections in a free state using pre-defined positioning spaces. The upper and lower fuselage sections are pressurized using F-clamps, C-clamps, and other clamps. Multiple internal partitions are positioned using calipers or tape measures, and then pre-positioned and bonded with super-drying adhesive. This assembly method results in inaccurate positioning of the partitions using tools like steel rulers and calipers. This can lead to difficulties in assembling other target drone components such as wings and tail fins in a single assembly, requiring reworking and potentially even scrapping the entire drone. Furthermore, using super-drying adhesive to fix the partitions can cause displacement due to external pressure during the mold-closing process, reducing the overall strength of the reinforced target drone after mold closing.

[0039] In other words, most domestically produced reinforced target drones currently use molded molds for positioning and assembly. The body components, as the core main parts of the target drone body, need to connect other components and are the primary force-bearing core. Therefore, the body structure involves multiple positioning connections and multiple reinforced frames. Because the target drone body requires precise connections at multiple points, and the molded mold cannot achieve complete positioning connections, some structures and interfaces with other components cannot be accurately connected during assembly. This necessitates secondary repairs in subsequent overall fitting processes, resulting in longer processing times, higher costs, and greater difficulty in refinishing. Furthermore, because the spacers in the target drone body cannot be accurately positioned within the mold during positioning and assembly, the supporting spacers may shift, reducing the overall strength of the target drone body. This also leads to unstable pressure during the closure of the upper and lower bodies, creating obvious interfaces between the adhesive joints and increasing the risk of breakage. Products manufactured using these processes exhibit poor stability and reliability, and have low breaking loads. At the same time, the above manufacturing process will significantly increase the labor and material manufacturing costs of control panel products, making it unsuitable for mass production.

[0040] To address the problems in the prior art, this embodiment provides an assembly process for reinforcing a target machine. The reinforced target machine can be detached from the molding die and assembled. The assembled reinforced target machine has high overall strength and high reliability, and does not require subsequent secondary grinding.

[0041] Before describing the assembly process for reinforcing the target machine in this application, please refer to the appendix to the specification. Figures 1-7 Briefly describe the assembly tooling 100 used in the assembly process for reinforcing the target machine according to this application.

[0042] like Figure 1 As shown, the assembly fixture 100 used in the assembly process of the target drone for strengthening the target drone in this application includes a lower fixing device 110, an upper fixing device 120, a mold closing device 130, a wing positioning device 140, a horizontal tail positioning device 150, and a fuselage limiting device 160. The lower fixing device 110 includes a support frame 111 and two mating plates 112. The support frame 111 includes multiple support plates spaced apart along the length of the assembly fixture 100. The upper ends of the multiple support plates are provided with arc-shaped grooves that conform to the surface of the lower fuselage skin 220. The two mating plates 112 are spaced apart along the length of the assembly fixture 100. Both mating plates 112 are connected to the upper part of the support frame 111, and both mating plates 112 correspond to the position of the mold closing device 130, while avoiding the arc-shaped grooves.

[0043] The following is in conjunction with the instruction manual appendix. Figures 8-10The assembly process for strengthening the target machine described in this application is described in detail.

[0044] According to an assembly process for reinforcing a target machine according to this application, the assembly process is used to assemble the reinforcing target machine 200 using the assembly fixture 100 described above, such as... Figure 8 As shown, the assembly process includes:

[0045] Step S1: After demolding the upper body skin 210 and the lower body skin 220, perform pretreatment;

[0046] Specifically, in this step, after the upper fuselage skin 210 and the lower fuselage skin 220 are demolded, pre-processing is required to facilitate subsequent mold closing and assembly. This ensures high precision after subsequent mold closing and assembly of the target machine 200's fuselage with other structural components, and eliminates the need for secondary grinding, thereby reducing rework and material waste.

[0047] Step S2: After positioning the lower fixing device 110 and the fuselage limiting device 160 with positioning pins, connect them with bolts 170 and leave a 5mm clamping gap. Place the pre-treated lower fuselage skin 220 into the lower fixing device 110 so that the lower fuselage skin 220 is supported by the support bracket 111 of the lower fixing device 110. Then lock the 5mm clamping gap between the lower fixing device 110 and the fuselage limiting device 160.

[0048] Specifically, in this step, positioning accuracy is ensured by using a positioning pin between the fuselage limiting device 160 and the lower fixing device 110. Simultaneously, the fuselage limiting device 160 and the lower fixing device 110 are clamped together using bolts 170, ensuring a stable connection. A 5mm clamping gap is maintained between the lower fixing device 110 and the fuselage limiting device 160 to facilitate the subsequent placement of the lower fuselage skin 220 into the lower fixing device 110. After placing the lower fuselage skin 220 into the lower fixing device 110, the lower fixing device 110 is locked to the fuselage limiting device 160. This means the fuselage limiting device 160 abuts against the lower fuselage skin 220, effectively limiting its position in the length direction and preventing lateral slippage that could reduce subsequent assembly accuracy. This improves the positional accuracy of the lower fuselage skin 220 and ensures overall assembly precision.

[0049] Step S3: Perform pre-bonding treatment on multiple first connecting metal parts and multiple first partition frames, and after the pre-bonding treatment is completed, bond them to the inner surface of the lower fuselage skin 220. After positioning pins are used to position the multiple positioning frames 121 of the upper fixing device 120 to the lower fixing device 110 and the tail positioning device 150, the multiple first connecting metal parts and multiple first partition frames are bonded to the lower fuselage skin 220. At the same time, the fuselage limiting device 160 is bolted to the first first partition frame.

[0050] Specifically, in this step, multiple first connecting metal parts and multiple first partition frames are first pre-treated for bonding. Then, the pre-treated first connecting metal parts and multiple first partition frames are bonded to the inner surface of the lower fuselage skin 220. Next, multiple positioning frames 121 of the upper fixing device 120 are respectively connected and clamped to the lower fixing device 110 and the horizontal stabilizer positioning device 150 using positioning pins and bolts 170. That is, some positioning frames 121 in the upper fixing device 120 are connected to the lower fixing device 110, and some positioning frames 121 in the upper fixing device 120 are connected to the horizontal stabilizer positioning device 150. Thus, the lower fixing device 110 provides stable support to the lower fuselage skin 220. The multiple positioning frames 121 in the upper fixing device 120 provide stable downward pressure to the multiple first connecting metal parts and multiple first partition frames. This ensures stable bonding between the multiple first connecting metal parts and multiple first partition frames and the lower fuselage skin 220. Furthermore, the relative positions of the upper fuselage skin 210 and the lower fuselage skin 220 can be determined by the connection positions between the multiple positioning frames 121 and the lower fixing device 110. This improves the assembly accuracy of the upper fuselage skin 210 and the lower fuselage skin 220. The first connecting metal part and the first bulkhead can support the lower fuselage skin 220, preventing structural deformation due to excessive speed during the flight of the reinforced target drone 200. Correspondingly, the second connecting metal part and the second bulkhead can support the upper fuselage skin 210.

[0051] Step S4: The device that has been positioned by the positioning pin and connected and clamped by the bolt 170 is cured at room temperature for a predetermined time, and the upper fixing device 120 and the flat tail positioning device 150 are removed after curing is completed.

[0052] Step S6: After applying adhesive to the inner surface of the upper fuselage skin 210, it is bonded to multiple first connecting metal parts and multiple first partition frames to mate with the lower fuselage skin 220 placed on the lower fixing device 110.

[0053] Step S7: After positioning the mold clamping device 130 and the lower fixing device 110 using locating pins, clamp them together using bolts 170. Specifically, in this step, positioning with locating pins before connection can improve the assembly accuracy. Furthermore, the mold clamping device 130 can be connected to the lower fixing device 110 to clamp the connection between the upper fuselage skin 210 and the lower fuselage skin 220. Those skilled in the art will understand that the connection between the upper fuselage skin 210 and the lower fuselage skin 220 both have flanges. After the flanges of the upper fuselage skin 210 and the lower fuselage skin 220 are aligned, the mold clamping device 130 is connected to the lower fixing device 110 to clamp the connection between the flanges of the upper fuselage skin 210 and the lower fuselage skin 220, thereby achieving mold clamping.

[0054] Step S8: Connect multiple positioning frames 121 from above the upper fuselage skin 210 to the mold closing device 130, so that the upper fuselage skin 210 and the lower fuselage skin 220 are molded together. Among them, two positioning frames 121 are respectively positioned with the horizontal tail positioning device 150 and the wing positioning device 140 using positioning pins and then clamped and connected by bolts 170.

[0055] Specifically, when the upper fuselage skin 210 and the lower fuselage skin 220 are molded and fixed, downward pressure is applied by multiple positioning frames 121, which can improve the tightness of the fit between the upper fuselage skin 210 and the lower fuselage skin 220, thereby improving the connection stability of the upper fuselage skin 210 and the lower fuselage skin 220 after mold closing.

[0056] Step S9: The horizontal tail positioning device 150 is connected to the horizontal tail connecting metal part through the positioning pin;

[0057] Step S10: After the multiple devices of the assembly fixture 100 are positioned and clamped by bolts 170, they are cured at room temperature for a predetermined time. After curing, the multiple devices of the assembly fixture 100 are removed so that the reinforced target machine 200 can be taken out of the assembly fixture 100.

[0058] Specifically, in this step, room temperature curing ensures the overall strength stability of the reinforced target 200 after molding.

[0059] According to the assembly process for strengthening the target machine 200 in the second aspect of this application, the lower fixing device 110 and the upper fixing device 120 are positioned by a locating pin and then clamped together by bolts 170. This ensures that after the upper fixing device 120 is assembled with the upper fuselage skin 210 and the lower fixing device 110 is assembled with the lower fuselage skin 220, the positions of the upper fuselage skin 210 and the lower fuselage skin 220 automatically correspond after the upper fixing device 120 and the lower fixing device 110 are connected. This ensures a stable connection without dimensional deviation. After connecting the mold closing device 130 to the lower fixing device 110, the mold closing device 130 can close the upper fuselage skin 210 and the lower fuselage skin 220, and ensure that the mold closing accuracy of the upper fuselage skin 210 and the lower fuselage skin 220 is high and the positions correspond, avoiding secondary rework caused by the mismatch of the positions of the upper fuselage skin 210 and the lower fuselage skin 220. At the same time, it reduces losses and costs, and the manual operation difficulty is low. The reinforced target machine 200 body formed after mold closing has high strength, which can reduce the overall cost by more than 30%, and is suitable for the assembly and manufacturing of the target machine body of this type of reinforced target machine 200. Furthermore, the assembly process for reinforcing the target drone 200 in this application involves bonding and positioning the upper fuselage skin 210 and lower fuselage skin 220 to the first bulkhead in stages. Specifically, after bonding and positioning the lower fuselage skin 220 to the first bulkhead, the upper fuselage skin 210 and lower fuselage skin 220 are then pressurized and molded together. This assembly method ensures the compressive force and positioning accuracy of the target drone 200's fuselage during mold closing, thereby strengthening the adhesive strength of the bonding surfaces of the upper fuselage skin 210 and lower fuselage skin 220 and the corresponding positioning layout of the bulkhead, achieving a one-piece positioning assembly effect. This increases product reliability and improves the overall strength of the product. Moreover, the wings and horizontal stabilizer are positioned using dedicated positioning devices, further ensuring the accuracy of subsequent installation interfaces after connection. This reduces the risk of extensive grinding or scrapping during subsequent adaptation. Furthermore, with the above-mentioned multi-positioning and staged bonding and pressurization, the entire assembly process does not require mold transfer, simplifying the process and facilitating demolding, effectively reducing labor and material costs. The main body of the enhanced target drone has high dimensional accuracy requirements and requires high precision control.

[0060] In some embodiments of this application, such as Figure 9 As shown, step S9: The horizontal tail positioning device 150 is connected to the horizontal tail connecting metal part through a positioning pin, including:

[0061] Step S901: Position the flat-tail positioning device 150 and the lower fixing device 110 using positioning pins;

[0062] Specifically, the flat-tail positioning device 150 and the lower fixing device 110 are positioned by positioning pins to ensure the subsequent interface dimensions, overall positioning accuracy and layout strength. Furthermore, the connection gaps between the multiple devices of the assembly tooling 100 are all no greater than 0.1mm, and the positioning accuracy between the overall assemblies can be determined by the connection gaps.

[0063] Step S902: Position the flat tail positioning device 150, which is positioned with the lower fixing device 110 by positioning pins, and the flat tail connecting metal part by positioning pins and bolts 170 to connect and clamp them.

[0064] Specifically, this ensures the accuracy of subsequent interface dimensions, overall positioning accuracy, and layout strength. The positioning pin holes of the horizontal tail metal parts and the horizontal tail positioning device 150 ensure that the overall installation dimensional deviation of the metal parts is no greater than 0.1mm, guaranteeing the installation dimensional accuracy of the subsequent reinforcement target machine 200's body and horizontal tail.

[0065] In some embodiments of this application, such as Figure 8 As shown, step S6: After applying adhesive to the inner surface of the upper fuselage skin 210, it is bonded to multiple first connecting metal parts and multiple first partitions to mate with the lower fuselage skin 220 placed on the lower fixing device 110. Prior to this, the following steps are included:

[0066] Step S5: Perform pre-bonding treatment on multiple first connecting metal parts, multiple first partition frames and upper fuselage skin 210.

[0067] Specifically, through pre-bonding treatment, the bonding of the upper fuselage skin 210 to the multiple first connecting metal parts, as well as the bonding of the upper fuselage skin 210 to the multiple first partition frames, can be made stable and firm. Pre-bonding treatment can involve increasing the surface roughness of the bonding area between the upper fuselage skin 210 and the first connecting metal parts through grinding, and also increasing the surface roughness of the bonding area between the upper fuselage skin 210 and the first partition frames through grinding.

[0068] In some embodiments of this application, such as Figure 10 As shown, step S7: After positioning the mold clamping device 130 and the lower fixing device 110 using locating pins, they are clamped together using bolts 170, including:

[0069] Step S701: Position the mold clamping device 130 and the two mating plates 112 of the lower fixing device 110 simultaneously with the positioning pins and then clamp them together with bolts 170.

[0070] Specifically, by clamping and connecting the two mating plates 112 of the mold closing device 130 and the lower fixing device 110, it can be clamped at the flange joint of the upper fuselage skin 210 and the lower fuselage skin 220, thereby ensuring the mold closing stability of the upper fuselage skin 210 and the lower fuselage skin 220, and enabling the reinforced target machine 200 after mold closing to have high overall strength and strong stability.

[0071] In some embodiments of this application, the predetermined time for room temperature curing is at least 12 hours. Specifically, by curing at room temperature for at least 12 hours, sufficient time can be ensured for mold assembly between the upper fuselage skin 210 and the lower fuselage skin 220, thus ensuring the overall structural stability of the reinforced target machine 200 after molding.

[0072] In some embodiments of this application, the pretreatment involves trimming the rough edges or burrs on the demolded upper fuselage skin 210 and lower fuselage skin 220, and polishing the bonding surfaces of the upper fuselage skin 210 and lower fuselage skin 220. Specifically, the polishing during pretreatment can smooth the mating surfaces of the upper fuselage skin 210 and lower fuselage skin 220, resulting in a smooth and neat mating surface when the two are molded together. This leads to high precision after mold assembly and makes the target machine 200 less prone to detachment, thereby improving the overall structural strength of the target machine 200.

[0073] In addition, 80# sandpaper can be used for sanding the upper fuselage skin 210 and the lower fuselage skin 220.

[0074] In some embodiments of this application, the connection gaps between the multiple devices of the assembly fixture 100 are all no greater than 0.1 mm. Specifically, ensuring that the connection gaps between the multiple devices are no greater than 0.1 mm ensures stable clamping of the bolts 170 between each device, stable force distribution, and high overall structural connection strength of the assembled reinforced target machine 200. Furthermore, the connection gaps between the multiple devices of the assembly fixture 100 are all no greater than 0.1 mm, which helps determine the positioning accuracy of the overall assembly. And when the mold closing gap between the various devices of the assembly fixture 100 is no greater than 0.1 mm, the two sides of the wing positioning device 140 conform to the profiles of the other devices of the assembly fixture 100, ensuring that the wing assembly surface is horizontal. The accuracy of the positioning connection can also be ensured by ensuring that the mold closing gap is no greater than 0.1 mm. Furthermore, by using the wing simulation airfoil fixture, the overall profile is flattened, ensuring the horizontality of the wing installation.

[0075] Next, refer to the instruction manual appendix. Figures 1-7 The assembly tooling 100 used for reinforcing the target machine in the assembly process of this application is described in detail.

[0076] like Figure 1 and Figure 2As shown, the assembly fixture 100 for reinforcing the target machine 200 includes a lower fixing device 110, an upper fixing device 120, and a mold closing device 130. The lower fixing device 110 can fix the lower fuselage skin 220 of the target machine 200. Furthermore, the stable placement of the lower fixing device 110 ensures accurate bonding position and improved precision when bonding the first partition frame and the first connecting metal part of the lower fuselage skin 220 to it. Correspondingly, the upper fixing device 120 includes multiple positioning frames 121, which are spaced apart along the length of the assembly fixture 100. Each positioning frame 121 is connected to the mold closing device 130 via positioning pins and bolts 170. Thus, the multiple positioning frames 121 of the upper fixing device 120 can be positioned and connected to the lower fixing device 110 to form multiple corresponding positioning points. The accuracy and precision of multi-point positioning improve the assembly accuracy after the upper fuselage skin 210 and the lower fuselage skin 220 are molded together. After the upper fixing device 120 is assembled with the body skin 210, accurate positioning can be guaranteed. After the lower fixing device 110 is assembled with the lower body skin 220, the positioning point formed on the lower fixing device 110 by the positioning frame 121 can determine the placement position of the lower body skin 220. Therefore, when the upper body skin 210 and the lower body skin 220 are molded, the positional correspondence between the upper body skin 210 and the lower body skin 220 is accurate and precise, thus avoiding rework caused by positioning deviations of the upper body skin 210 and the lower body skin 220. Furthermore, the overall positioning method is convenient and quick, reducing labor costs and material loss costs.

[0077] Furthermore, the overall positioning is achieved through the connection of multiple positioning frames 121 with the lower fixing device 110, ensuring accurate positioning. This prevents inaccurate connection to other structures due to positioning deviations in the target machine 200 during subsequent assembly, i.e., the assembly of the target machine 200's body with other structures. It also eliminates the need for secondary grinding, reduces manual operation difficulty, and improves operational safety. Improved assembly precision also enhances the overall strength and stability of the target machine 200.

[0078] like Figure 1As shown, the mold-closing device 130 and the lower fixing device 110 are positioned by positioning pins and then connected by bolts 170, ensuring the connection between the upper fuselage skin 210 and the lower fuselage skin 220. Thus, the mold-closing device 130 can stably connect the upper fuselage skin 210 and the lower fuselage skin 220. After mold closing, the bolts 170 clamping ensures stable pressure strength and avoids uneven pressure distribution caused by manual operation. Simultaneously, in the mold-closing step of strengthening the target machine 200, room temperature curing for more than 12 hours is required. The bolts 170 clamping ensures stable connection between the upper fuselage skin 210 and the lower fuselage skin 220 during mold closing. Furthermore, during room temperature curing, the mold-closing device 130 enhances the overall structural strength of the strengthened target machine 200 formed after the upper fuselage skin 210 and the lower fuselage skin 220 are molded together.

[0079] In addition, the upper fixing device 120, the lower fixing device 110 and the mold closing device 130 of the assembly fixture 100 are all connected to each other by positioning pins, which can ensure the assembly accuracy. At the same time, they are clamped together by bolts 170, which can ensure the clamping strength after assembly and ensure the stability of clamping pressure.

[0080] According to the assembly fixture 100 for reinforcing the target machine 200 according to the first aspect of this application, after the lower fixing device 110 and the upper fixing device 120 are positioned by the positioning pin and then clamped by the bolt 170, it can be ensured that after the upper fixing device 120 is assembled with the upper fuselage skin 210 and the lower fixing device 110 is assembled with the lower fuselage skin 220, the positions of the upper fuselage skin 210 and the lower fuselage skin 220 automatically correspond after the upper fixing device 120 and the lower fixing device 110 are connected, which can ensure stable connection and no dimensional deviation. Multiple positioning frames 121 of the upper fixing device 120 can be positioned with the lower fixing device 110 through positioning pins, forming positioning points on the lower fixing device 110. Thus, after connecting the mold closing device 130 to the lower fixing device 110, the mold closing device 130 can close the upper fuselage skin 210 and the lower fuselage skin 220, ensuring high mold closing accuracy and corresponding positions of the upper fuselage skin 210 and the lower fuselage skin 220. This avoids secondary rework caused by mismatched positions of the upper fuselage skin 210 and the lower fuselage skin 220, reducing losses and costs. At the same time, the manual operation is easy, and the reinforced target machine 200 body formed after mold closing has high strength, which can reduce the overall cost by more than 30%. It is also suitable for the assembly and manufacturing of the target machine body of this type of reinforced target machine 200.

[0081] In some embodiments of this application, such as Figure 1 and Figure 6As shown, the lower fixing device 110 includes a support frame 111 and two mating plates 112. The support frame 111 includes multiple support plates spaced apart along the length of the assembly fixture 100. The upper ends of the multiple support plates are provided with arc-shaped grooves that fit against the surface of the lower fuselage skin 220. The two mating plates 112 are spaced apart along the length of the assembly fixture 100. The two mating plates 112 are connected to the upper part of the support frame 111 and correspond to the position of the mold closing device 130, while avoiding the arc-shaped grooves. Specifically, the lower fixing device 110 may have a bottom support base, on the upper surface of which the support frame 111 is provided. The support frame 111 is composed of multiple support plates spaced apart along the length of the assembly fixture 100. Furthermore, multiple support plates have arc-shaped grooves to fit against the lower surface of the lower fuselage skin 220, thereby stably supporting the lower fuselage skin 220 and providing upward support force when the upper fuselage skin 210 and the lower fuselage skin 220 are subsequently molded together. In addition, the lower fixing device 110 may also include two mating plates 112. The mating plates 112 are elongated plates, both of which are arranged along the length of the assembly fixture 100. The lower surface of the mating plates 112 is connected to the upper surface of the support plates; that is, the support plates are plates with arc-shaped grooves, and the top surfaces on both sides of the arc-shaped grooves are connected to the lower surface of the mating plates 112, thus forming a... Figure 6 The support frame shown has a support platform on both sides, which can be connected to the mold closing device 130, so that the mating plate 112 and the mold closing device 130 form a clamping fit. In this way, when the upper fuselage skin 210 and the lower fuselage skin 220 are molded, it can be clamped at the flange connection of the upper fuselage skin 210 and the lower fuselage skin 220, forming a clamping force to ensure the stability of the upper fuselage skin 210 and the lower fuselage skin 220 in mold closing, and to ensure the connection strength after mold closing.

[0082] The positions of the multiple support plates correspond to the positions of the multiple first connecting metal parts and the first partition frames in the fuselage skin, and also correspond one-to-one with the positions of the multiple positioning frames 121 of the upper fixing device 120. Therefore, when the mold is closed, the support plates, by corresponding one-to-one with the positions of the first connecting metal parts, can provide support from below. When the upper fuselage skin 210 is subjected to downward pressure by the multiple positioning frames 121 of the upper fixing device 120, the upper fuselage skin 210 and the lower fuselage skin 220 can be tightly fitted together. Furthermore, the surfaces of the mold closing device 130 and the mating plate 112 can be provided with scale lines, thereby allowing the bonding positions between the metal parts and partition frames and the skin to be further determined by the scale positions.

[0083] Furthermore, such as Figure 7As shown, a mating recess can also be provided at the mating plate 112 corresponding to the wing positioning device 140. The two ends of the wing positioning device 140 are located at the mating recess, which facilitates the subsequent assembly of the wing and ensures that the wing assembly surface is horizontal.

[0084] In some embodiments of this application, such as Figure 1 , Figure 6 and Figure 7 As shown, the assembly fixture 100 also includes a wing positioning device 140, which is disposed between the mold closing device 130 and the lower fixing device 110. The wing positioning device 140 is connected to the mold closing device 130 and the lower fixing device 110 by positioning pins and bolts 170.

[0085] Specifically, after multiple positioning frames 121 are positioned and connected to the lower fixing device 110, multiple positioning points are formed. Thus, when the wing positioning device 140 is connected to the lower fixing device 110, the position of the wing positioning device 140 can be determined by the positioning points. After the wing positioning device 140 is connected to the lower fixing device 110 and the mold closing device 130, the position positioning can be accurate during the subsequent assembly of the wing and the fuselage, the overall assembly precision is high, and secondary grinding and rework are avoided.

[0086] In some embodiments of this application, such as Figure 1 , Figure 4 , Figure 5 and Figure 6 As shown, the assembly fixture 100 also includes a flat-tail positioning device 150, which is disposed between the positioning frame 121 and the mold closing device 130. The flat-tail positioning device 150 and the positioning frame 121 are connected by positioning pins and bolts 170.

[0087] Specifically, after the multiple positioning frames 121 are positioned and connected to the lower fixing device 110, multiple positioning points are formed. Therefore, when the horizontal tail positioning device 150 is connected to the mold closing device 130, the assembly position of the horizontal tail positioning device 150 can be determined through these positioning points. This ensures the accuracy of the connection between the horizontal tail positioning device 150 and the fuselage. Consequently, the assembly accuracy of the fuselage and horizontal tail of the reinforced target drone 200 is improved.

[0088] In some embodiments of this application, such as Figure 1 , Figure 2 , Figure 3 and Figure 6 As shown, the assembly fixture 100 also includes a fuselage limiting device 160, which is disposed at the end of the lower fixing device 110 and covers at least part of the accommodating space of the lower fixing device 110 supporting the lower fuselage skin 220.

[0089] Specifically, such as Figure 1 , Figure 2 , Figure 3 and Figure 6 As shown, along the length of the assembly fixture 100, the lower fixing device 110 supports the lower fuselage skin 220. An accommodating space for the lower fuselage skin 220 is provided at the upper part of the lower fixing device 110. After the lower fuselage skin 220 is placed in this accommodating space, the lower fixing device 110 provides stable support for the lower fuselage skin 220 in the height direction, facilitating subsequent mold closing between the lower fuselage skin 220 and the upper fuselage skin 210. In the length direction, to improve the subsequent mold closing accuracy and prevent the lower fuselage skin 220 from shifting position when placed on the lower fixing device 110, thus reducing the mold closing accuracy, further measures are taken. Therefore, a fuselage limiting device 160 is provided at the end of the lower fixing device 110. The fuselage limiting device 160 covers the space of the lower fixing device 110 used to support the lower fuselage skin 220. Thus, the fuselage limiting device 160 can abut against the end of the lower fuselage skin 220, thereby limiting the lower fuselage skin 220 in the length direction of the assembly fixture 100 and preventing inaccurate positioning of the target machine 200 in the length direction. This also prevents the lower fuselage skin 220 from sliding or shifting, which could lead to a reduction in subsequent processing accuracy.

[0090] In other words, a limiting member is provided in the space where the lower fixing device 110 supports the lower fuselage skin 220, so that after the lower fuselage skin 220 is placed in the supporting space of the lower fixing device 110, it can abut against the lower fuselage skin 220 in the front-back direction to prevent the lower fuselage skin 220 from moving along the length direction of the assembly fixture 100.

[0091] In some embodiments of this application, the surface roughness of the mating surfaces of the lower fixing device 110, the mold closing device 130, the upper fixing device 120, the wing positioning device 140, the horizontal tail positioning device 150, and the fuselage limiting device 160 is no greater than 0.8 μm. This ensures smooth connection between the various devices of the assembly fixture 100 and prevents wear. The surface roughness between the contact surfaces of the lower fixing device 110, the mold closing device 130, the upper fixing device 120, the wing positioning device 140, the horizontal tail positioning device 150, and the fuselage limiting device 160 and the reinforced target drone 200 is no greater than 0.8 μm. This ensures smooth contact between the various devices of the assembly fixture 100 and the fuselage of the reinforced target drone 200, preventing wear on the surface of the fuselage. This protects the fuselage of the reinforced target drone 200.

[0092] In some embodiments of this application, the lower fixing device 110, the mold closing device 130, the upper fixing device 120, the wing positioning device 140, the horizontal tail positioning device 150, and the fuselage limiting device 160 are all made of P20 steel. This ensures the structural strength of each device in the assembly fixture 100.

[0093] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. The above are only preferred embodiments of this application. It should be noted that due to the limitations of textual expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the concept and technical solution of the application to other occasions without modification, should all be considered within the scope of protection of this application.

Claims

1. An assembly process for reinforcing a target machine, characterized in that, The assembly process involves assembling the reinforced target drone (200) using an assembly fixture (100). The assembly fixture (100) includes a lower fixing device (110), an upper fixing device (120), a mold closing device (130), a wing positioning device (140), a horizontal tail positioning device (150), and a fuselage limiting device (160). The assembly process includes: After demolding, the upper fuselage skin (210) and lower fuselage skin (220) are pre-treated; After positioning the lower fixing device (110) and the fuselage limiting device (160) with positioning pins, connect them with bolts (170) and leave a 5mm clamping gap. Place the pre-treated lower fuselage skin (220) into the lower fixing device (110) so that the lower fuselage skin (220) is supported by the support bracket (111) of the lower fixing device (110). Then lock the 5mm clamping gap between the lower fixing device (110) and the fuselage limiting device (160). Multiple first connecting metal parts and multiple first partition frames are subjected to bonding pretreatment, and after the bonding pretreatment is completed, they are bonded to the inner surface of the lower fuselage skin (220). Multiple positioning frames (121) of the upper fixing device (120) are respectively connected and clamped to the lower fixing device (110) and the tail positioning device (150) with positioning pins and bolts (170) to bond multiple first connecting metal parts and multiple first partition frames to the lower fuselage skin (220). At the same time, the fuselage limiting device (160) is bolted to the first first partition frame. The device, which has been positioned by the positioning pin and connected and clamped by bolts (170), is cured at room temperature for a predetermined time, and after curing is completed, the upper fixing device (120) and the flat tail positioning device (150) are removed. After applying adhesive to the inner surface of the upper fuselage skin (210), it is bonded to a plurality of first connecting metal parts and a plurality of first partition frames to mate with the lower fuselage skin (220) placed on the lower fixing device (110); The mold clamping device (130) and the lower fixing device (110) are positioned using positioning pins and then clamped together by bolts (170); Multiple positioning frames (121) are connected to the mold-closing device (130) from above the upper fuselage skin (210) so that the upper fuselage skin (210) and the lower fuselage skin (220) are molded together. Among the multiple positioning frames (121), two of the positioning frames (121) are respectively positioned with the horizontal tail positioning device (150) and the wing positioning device (140) using positioning pins and then clamped and connected by bolts (170). The horizontal tail positioning device (150) is connected to the horizontal tail connecting metal part by a positioning pin; After the multiple devices of the assembly fixture (100) are positioned and clamped by bolts (170), they are cured at room temperature for a predetermined time. After curing, the multiple devices of the assembly fixture (100) are removed so that the reinforced target machine (200) can be taken out from the assembly fixture (100).

2. The assembly process according to claim 1, characterized in that, The process of applying adhesive to the inner surface of the upper fuselage skin (210) and bonding it to a plurality of first connecting metal parts and a plurality of first partition frames to mate with the lower fuselage skin (220) placed on the lower fixing device (110) includes the following prior steps: The first connecting metal parts, the first partition frames, and the upper fuselage skin (210) are all subjected to bonding pretreatment.

3. The assembly process according to claim 1, characterized in that, The step of positioning the mold clamping device (130) and the lower fixing device (110) with positioning pins and then clamping them together with bolts (170) includes: The mold clamping device (130) is simultaneously positioned with the two mating plates (112) of the lower fixing device (110) by positioning pins and then clamped together by bolts (170).

4. The assembly process according to claim 1, characterized in that, The horizontal tail positioning device (150) is connected to the horizontal tail connecting metal part via a positioning pin, including: The flat-tail positioning device (150) and the lower fixing device (110) are positioned by positioning pins; The flat-tail positioning device (150), which is positioned with the lower fixing device (110) by a positioning pin, is positioned with the flat-tail connecting metal part by a positioning pin and then connected and clamped by bolts (170).

5. The assembly process according to claim 1, characterized in that, The predetermined time for room temperature curing is at least 12 hours.

6. The assembly process according to claim 1, characterized in that, The pretreatment involves trimming the rough edges or burrs of the demolded upper fuselage skin (210) and lower fuselage skin (220), and polishing the bonding surfaces of the upper fuselage skin (210) and lower fuselage skin (220).

7. The assembly process according to claim 1, characterized in that, The connection gaps between the multiple devices of the assembly fixture (100) are all no greater than 0.1 mm.

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