Assembly tool and assembly process for large aspect ratio unmanned aerial vehicle wing assembly

Abstract

The application provides an assembly tool and an assembly process for a large-aspect-ratio unmanned aerial vehicle wing assembly, comprising an assembly structure; the assembly structure can be modified and / or extended according to the characteristics of the large-aspect-ratio unmanned aerial vehicle wing; the assembly structure is configured with a plurality of assembly structures according to the length of the large-aspect-ratio unmanned aerial vehicle wing; and the assembly structure can adjust its own horizontal height, so that the horizontal heights of the assembly tools combined by the plurality of assembly structures are consistent with each other. Through the assembly tool, the wing shape precision of the large-aspect-ratio unmanned aerial vehicle wing assembly can be ensured, the assembly process of the assembly tool can greatly improve the assembly efficiency, reduce the cost and save the time, the distance between the wing ribs can be accurately controlled, and the pitch angle of the wing can be accurately controlled.

Description

Technical Field

[0001] This invention relates to the field of assembly tooling for the wings of high aspect ratio unmanned aerial vehicles (UAVs), specifically, to an assembly tooling and assembly process for the wing assembly of high aspect ratio UAVs. Background Technology

[0002] In the development and manufacturing of high aspect ratio UAVs, the overall wing assembly involves connecting the load section, fuselage section, transition section, and dihedral section to form the wing according to design requirements. The typical assembly method involves assembling individual components first. The assembly cost of a component depends on the assembly method, which in turn affects assembly time and quality. In component manufacturing, traditional assembly sequence planning relies on the experience and intuition of assembly personnel, resulting in significant subjectivity and uncertainty, making it difficult to guarantee assembly quality, and leading to long assembly cycles and high costs. Therefore, a reasonable assembly process plan can significantly reduce the product development lifecycle and manufacturing costs. On the other hand, high aspect ratio UAV wings have many components, are long, and are prone to deformation, making overall shape control after assembly difficult. Furthermore, attitude control products have high requirements for airfoil accuracy and stability. Assembly tooling directly affects the final quality of the high aspect ratio UAV wing, thus placing high demands on assembly. Summary of the Invention

[0003] In view of the deficiencies in the prior art, the purpose of this invention is to provide an assembly fixture and assembly process for the final assembly of wings of high aspect ratio UAVs. This fixture can be used to complete the assembly from parts to wings, realizing the one-time final assembly of wings of high aspect ratio UAVs. It can not only meet the design accuracy requirements of the airfoil, but also greatly reduce the dependence on the work experience and subjective judgment of assembly personnel.

[0004] An assembly fixture for assembling the wings of a high aspect ratio unmanned aerial vehicle (UAV) according to the present invention includes assembly structural components;

[0005] The assembly structure can be modified / extended according to the characteristics of a high aspect ratio UAV wing;

[0006] The assembly structure can be adjusted in horizontal height to ensure the airfoil accuracy of the high aspect ratio UAV wing assembly.

[0007] Preferably, the assembly structural components include supports, crossbeams, longitudinal beams, and adjusting bolts;

[0008] The crossbeam is connected to the support;

[0009] The longitudinal beams are connected to the transverse beams;

[0010] The adjusting bolt is installed at the bottom of the bracket; the adjusting bolt enables the horizontal height adjustment of the assembly tooling.

[0011] Preferably, the crossbeam is provided with a first screw hole and a mating groove for connecting with the longitudinal beam, a first countersunk hole for connecting with the support, and a support groove for supporting the main / sub-beams of the high aspect ratio UAV.

[0012] Preferably, the longitudinal beam is provided with a wing rib groove that connects to the wing of a high aspect ratio UAV and a second countersunk hole that connects to the crossbeam.

[0013] Preferably, the support groove is a semi-cylindrical support groove.

[0014] Preferably, the support groove on the crossbeam can be modified / expanded according to the change in the outer diameter of the main / sub-beam supporting the large aspect ratio UAV.

[0015] Preferably, the position of the rib slot can change with the assembly position between the ribs, and the profile of the rib slot is the same as the profile of the rib support position.

[0016] Preferably, the rib slot can be modified / expanded according to the changes in the shape of the ribs of the high aspect ratio UAV wing and the changes in the spacing between the ribs of the high aspect ratio UAV wing.

[0017] This invention also provides a process flow for assembling a high aspect ratio UAV wing, which uses the assembly tooling described above for the overall assembly of a high aspect ratio UAV wing, and further includes the following steps:

[0018] Step 1: Install the final assembly fixture, rotate the adjusting bolts to adjust the horizontal height of the assembly fixture, and use a level measuring instrument to measure the level.

[0019] Step 2: Assemble the high aspect ratio UAV wing into segments according to its structural characteristics;

[0020] Step 3: Apply adhesive to the connection between the main beam and the rib, and after curing for 12 hours, apply adhesive to any areas where there is insufficient adhesive at the connection.

[0021] Step 4: Apply adhesive to the areas where the front and rear edges are assembled with the ribs, and allow it to cure for 12 hours after assembling the front and rear edges.

[0022] Step 5: Inspect the connection points and apply glue to any areas where it is insufficient.

[0023] Furthermore, in step one, the horizontal tolerance of the horizontal measurement is less than 1 mm.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. This invention employs multiple assembly structural components with adjustable horizontal height. The assembly tooling formed by splicing multiple assembly structural components can control the horizontal height of the assembly work within a certain precision, ensuring the airfoil accuracy of the large aspect ratio UAV wing assembly, improving assembly efficiency, reducing costs and saving time. It can also precisely control the distance between each wing rib, and can precisely control the pitch angle of the wing.

[0026] 2. By strictly controlling the horizontal height of the assembly fixture, and simultaneously completing all sections of the high aspect ratio UAV on the same assembly fixture at one time, this invention can effectively improve assembly accuracy and ensure that the elevation angle of the high aspect ratio UAV is within the allowable error range. Attached Figure Description

[0027] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0028] Figure 1 This is an overall structural diagram of the assembly tooling for the high aspect ratio UAV wing of the present invention;

[0029] Figure 2 This is a structural diagram of the support of the present invention;

[0030] Figure 3 This is a structural diagram of the beam of the present invention;

[0031] Figure 4 This is a structural diagram of the longitudinal beam of the present invention;

[0032] Figure 5 A structural diagram of a high aspect ratio UAV wing;

[0033] Figure 6 This is a structural schematic diagram of an assembly embodiment of a high aspect ratio UAV wing. Detailed Implementation

[0034] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0035] This invention provides an assembly fixture for the final assembly of a high-aspect-ratio UAV wing, comprising assembly structural components. These assembly structural components can be modified and / or expanded according to the characteristics of the high-aspect-ratio UAV wing. Several assembly structural components are configured according to the length of the UAV wing. Each assembly structural component can adjust its own horizontal height, ensuring that the horizontal height of the assembly fixture composed of multiple assembly structural components is consistent with each other. The ability of multiple assembly structural components to independently adjust their horizontal height, combined with the assembly fixture formed by splicing these components, allows for precise control of the assembly horizontal height, ensuring the airfoil accuracy of the high-aspect-ratio UAV wing assembly, improving assembly efficiency, reducing costs, and saving time.

[0036] Specifically, the assembly fixture of the present invention is provided with 9 assembly structural components, each of which includes a support, a crossbeam, a longitudinal beam, a screw, and an adjusting bolt.

[0037] The crossbeam is connected to the support by screws;

[0038] The longitudinal beams are connected to the transverse beams by screws;

[0039] The adjusting bolt is installed at the bottom of the bracket; the adjusting bolt enables the horizontal height adjustment of the assembly tooling.

[0040] The crossbeam is provided with a first screw hole 1 and a mating groove 4 for connecting with the longitudinal beam, a first countersunk hole 3 for connecting with the support, and a support groove 2 for supporting the main / sub-beams of the high aspect ratio UAV; the support groove 2 is a semi-cylindrical support groove; in particular, the support groove 2 on the crossbeam can be modified / expanded according to the change of the outer diameter of the main beam and the sub-beam supporting the main / sub-beams of the high aspect ratio UAV; specifically, the shape and size of the support groove 2 on the crossbeam depend on the shape and size of the main / sub-beams of the high aspect ratio UAV.

[0041] The longitudinal beam is provided with rib groove 5, screw hole, and second countersunk hole 6 connected to the crossbeam;

[0042] The position of the rib slot 5 varies depending on the assembly position between the ribs, and the profile of the rib slot 5 is the same as that of the rib support position. Specifically, the rib slot 5 can be modified / expanded according to changes in the shape and size of the ribs and the spacing between them of the high-aspect-ratio UAV wing; specifically, the modification / expansion can be achieved by changing the shape and spacing of the rib slot 5, as well as the number of rib slots 5. Furthermore, the shape and size of the rib slot 5 on the longitudinal beam, and the spacing between the rib slots 5, depend on the shape and size of the ribs and the spacing between them of the high-aspect-ratio UAV wing; thus, the assembly fixture can not only precisely control the distance between each rib, but also precisely control the wing's pitch angle.

[0043] Based on the structural characteristics of high aspect ratio UAV wings, the wings can be divided into several segments. For example, for a high aspect ratio UAV wing with a bilaterally symmetrical structure, it can be divided into a load-bearing segment, a fuselage segment, a transition segment, and anhedral segment. Figure 5 As shown.

[0044] This invention also provides a process flow for assembling the wings of a high aspect ratio unmanned aerial vehicle (UAV), comprising the following steps:

[0045] Step 1: Install the assembly fixture, rotate the adjusting bolts to adjust the horizontal height of the assembly fixture, and use a level measuring instrument to measure the level. The assembly fixture is 19m long and the horizontal tolerance is less than 1mm.

[0046] Step 2: Assemble the high aspect ratio UAV wing in sections according to its structural characteristics. Specifically, based on the structural design of the high aspect ratio UAV wing, place the parts of each section (i.e., load section, fuselage section, transition section, and dihedral section) in their respective positions according to the design requirements, and assemble each section on the assembly fixture. During assembly, thread the wing ribs onto the main and secondary beams in one go according to the design requirements.

[0047] Step 3: According to the design requirements, the connection between the wing rib and the main beam and sub-beam is made by adhesive bonding. Therefore, apply adhesive to the areas that need to be bonded, and after curing for 12 hours, apply adhesive to the areas where there is insufficient adhesive at the connection. At this time, the purpose of the assembly tooling is to ensure that the relative positions between the wing rib and the main and sub-beams remain unchanged.

[0048] Step 4: Apply adhesive to the positions where the leading and trailing edges of the wing are assembled with the ribs, and allow it to cure for 12 hours after assembly. The assembly fixture ensures the assembly of the rib airfoil, connecting the leading and trailing edges of the wing with the ribs, so that the assembly shape of the leading and trailing edges is consistent with the design, thus ensuring aerodynamic characteristics.

[0049] Step 5: Apply glue to the areas where the leading and trailing edges of the wing meet the wing ribs where glue is insufficient. Double-checking and applying glue ensures a secure connection between parts.

[0050] The working principle of this invention is as follows:

[0051] The high aspect ratio UAV wing assembly tooling of the present invention is as follows: Figure 1 As shown, it mainly consists of 9 sections. Each section includes a support, a crossbeam, a longitudinal beam, screws, and adjusting bolts. The crossbeams are connected to the supports by screws, and the longitudinal beams are connected to the crossbeams by screws. The final assembly fixture includes 10 crossbeams, 14 longitudinal beams, 10 supports, and adjusting bolts under the supports. The supports come in two sizes, the crossbeams are available in 5 types, and the longitudinal beams in 14 types.

[0052] Supports for the assembly tooling of high aspect ratio UAV wings, such as Figure 2As shown in (a,b). Support (a) and support (b) are of the same type but different in size.

[0053] 5 types of beams Figure 3 As shown in (a,b,c,d,e), the common features of the crossbeams are the first screw hole 1 and the mating groove 4 that connect with the longitudinal beam, the first countersunk hole 3 that connects with the support, and the semi-cylindrical support groove 2 that supports the main and secondary beams of the UAV with a large aspect ratio.

[0054] 14 types of longitudinal beams, such as Figure 4 As shown in (a,b,c,d,e,f,g,h,i,j,k,l,m,n), the common features of the longitudinal beams are the rib slots 5 and screw holes. The position of each rib slot 5 changes with the assembly position between the ribs. The profile of each rib slot 5 is the same as the profile of the rib support position. The longitudinal beams have countersunk holes and are connected to the crossbeams by screws.

[0055] The assembly fixture has a height and level adjustment function, which is achieved by adjusting bolts.

[0056] Figure 5 The UAV wing of the assembly embodiment is a high aspect ratio UAV wing with a left-right symmetrical structure, including a load section, a fuselage section, a transition section and an anti-reverse section.

[0057] An embodiment of the assembly process for the wings of a high aspect ratio UAV of the present invention includes the following steps:

[0058] Step 1: Install the final assembly fixture, adjust the height by rotating the adjusting bolts, and measure the level with a level measuring instrument. The final assembly fixture is 19m long and the level tolerance is less than 1mm.

[0059] Step 2: Place the parts of each segment into their respective positions according to the design requirements, and assemble each segment on the final assembly fixture. The assembly process of each segment will not be described in detail.

[0060] Step 3: Apply adhesive to the areas that need bonding, allow it to cure for 12 hours, and then apply adhesive to any areas that are lacking it.

[0061] Step 4: Apply adhesive to the assembly points of the front and rear edges and ribs, and allow the front and rear edges to cure for 12 hours.

[0062] Step 5: Apply glue to the areas where glue is missing.

[0063] This invention is not limited to the foregoing embodiments. Based on the characteristics of high aspect ratio UAV wings, the assembly tooling and assembly process of high aspect ratio UAV wings provided by this invention can be modified or extended to meet assembly requirements. Modifications or extensions include, but are not limited to, changes in the outer diameter of the main beam and sub-beam, changes in the shape and spacing of the ribs, and changes in the number of ribs.

[0064] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0065] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. An assembly fixture for the final assembly of a high aspect ratio unmanned aerial vehicle (UAV) wing, characterized in that, Including assembled structural components; The assembly structure can be modified and / or expanded according to the characteristics of the high aspect ratio UAV wing; The assembly structural components are configured in several quantities according to the length of the wing of the high aspect ratio UAV. The assembly structure can adjust its own horizontal height so that the horizontal height of the assembly tooling composed of multiple assembly structure components is consistent with each other. The assembly structural components include supports, crossbeams, longitudinal beams, and adjusting bolts; The crossbeam is connected to the support; The longitudinal beams are connected to the transverse beams; The adjusting bolt is installed at the bottom of the bracket; The adjusting bolt enables the horizontal height adjustment of the assembly tooling; The crossbeam is provided with a first screw hole (1) and a mating groove (4) for connecting with the longitudinal beam, a first countersunk hole (3) for connecting with the support, and a support groove (2) for supporting the main / sub-beams of the large aspect ratio UAV.

2. The assembly fixture for the overall assembly of a high aspect ratio UAV wing according to claim 1, characterized in that, The longitudinal beam is provided with a wing rib groove (5) that connects to the wing of a high aspect ratio UAV and a second countersunk hole (6) that connects to the crossbeam.

3. The assembly fixture for the overall assembly of a high aspect ratio UAV wing according to claim 1, characterized in that, The support groove (2) is a semi-cylindrical support groove.

4. The assembly fixture for the overall assembly of a high aspect ratio UAV wing according to claim 1, characterized in that, The support groove (2) on the crossbeam can be modified and / or expanded according to the change in the outer diameter of the main / sub-beam supporting the large aspect ratio UAV.

5. The assembly fixture for the final assembly of a high aspect ratio UAV wing according to claim 2, characterized in that, The position of the rib slot (5) can change with the assembly position between the ribs, and the profile of the rib slot (5) is the same as the profile of the rib support position.

6. The assembly fixture for the final assembly of a high aspect ratio UAV wing according to claim 2, characterized in that, The rib slot (5) can be modified / expanded according to the changes in the shape of the ribs of the high aspect ratio UAV wing and the changes in the spacing between the ribs of the high aspect ratio UAV wing.

7. A process flow for assembling the wings of a high aspect ratio unmanned aerial vehicle (UAV), characterized in that, The assembly tooling for assembling the wings of a high aspect ratio unmanned aerial vehicle (UAV) as described in any one of claims 1-6 further includes the following steps: Step 1: Install the final assembly fixture, rotate the adjusting bolts to adjust the horizontal height of the assembly fixture, and use a level measuring instrument to measure the level. Step 2: Assemble the high aspect ratio UAV wing into segments according to its structural characteristics; Step 3: Apply adhesive to the connection between the main beam and the rib, and after curing for 12 hours, apply adhesive to any areas where there is insufficient adhesive at the connection. Step 4: Apply adhesive to the areas where the leading and trailing edges of the wing are assembled with the wing ribs, and allow it to cure for 12 hours after assembly. Step 5: Inspect the connection points and apply glue to any areas where it is insufficient.

8. The assembly process for a high aspect ratio UAV wing according to claim 7, characterized in that, In step one, the horizontal tolerance of the horizontal measurement is less than 1 mm.

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