Assembly tool and assembly process flow of unmanned aerial vehicle flat tail

Abstract

The application provides an unmanned aerial vehicle flat tail assembly tool and assembly process flow, which comprises a support, two cross beams and two longitudinal beams, the cross beams and the longitudinal beams are horizontally arranged and tightly installed on the support, each cross beam is provided with a support groove, the main beam of the unmanned aerial vehicle flat tail is placed on the support groove, each longitudinal beam is provided with a plurality of wing rib clamping grooves, and the plurality of wing ribs of the unmanned aerial vehicle flat tail are respectively placed on the wing rib clamping grooves; and the bottom of the support is provided with a height adjusting device. The cross beam is provided with the support groove, the main beam of the unmanned aerial vehicle flat tail is placed on the support groove, the longitudinal beam is provided with the plurality of wing rib clamping grooves, the plurality of wing ribs of the unmanned aerial vehicle flat tail are respectively placed on the wing rib clamping grooves, and the bottom of the support is provided with the height adjusting device. By fully considering the characteristics of the flat tail, the wing shape precision requirement of the flat tail of the unmanned aerial vehicle is met, the assembly requirement is high, the demand is met, the assembly efficiency is improved, and the cost is reduced.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to an assembly tooling and assembly process for a UAV horizontal stabilizer. Background Technology

[0002] In the development and manufacturing of unmanned aerial vehicles (UAVs), overall assembly involves assembling various parts, instruments, and components into individual units according to design requirements, followed by the assembly of these units. The assembly cost of a unit depends on the assembly method, which in turn affects assembly time and quality. Traditional assembly sequence planning in component manufacturing 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, reasonable assembly process planning can significantly reduce the product development lifecycle and manufacturing costs. On the other hand, because the horizontal stabilizer in this invention has many components with thin walls, making it prone to deformation, controlling the overall shape after assembly is difficult. Furthermore, attitude control products have high requirements for airfoil accuracy and stability; therefore, assembly tooling and processes directly affect component quality, thus placing high demands on assembly.

[0003] Therefore, the inventors believe that it is necessary to design assembly tooling and assembly process according to the structure and characteristics of the horizontal stabilizer to realize the assembly of the UAV's horizontal stabilizer and achieve the design accuracy requirements of the airfoil. Summary of the Invention

[0004] To address the shortcomings of existing technologies, the purpose of this invention is to provide an assembly tooling and assembly process for a drone horizontal stabilizer.

[0005] An assembly fixture for a drone horizontal stabilizer according to the present invention includes: a support, two crossbeams and two longitudinal beams. The crossbeams and longitudinal beams are horizontally arranged and fastened to the support. Each of the crossbeams is provided with a support groove, and the main beam of the drone horizontal stabilizer is placed on the support groove. Each of the longitudinal beams is provided with multiple wing rib slots, and multiple wing ribs of the drone horizontal stabilizer are respectively placed on the wing rib slots. A height adjustment device is provided at the bottom of the support.

[0006] Preferably, the support is welded from multiple square steel tubes, and the crossbeam includes a first crossbeam and a second crossbeam arranged in parallel. The top of the support is provided with a threaded hole, and both ends of the first crossbeam and the second crossbeam are provided with corresponding countersunk holes. The first crossbeam and the second crossbeam are respectively fastened to the support by bolts.

[0007] Preferably, the longitudinal beam includes a first longitudinal beam and a second longitudinal beam, and the top of each of the crossbeams is provided with two mating grooves, and the two ends of the first longitudinal beam and the second longitudinal beam are respectively fastened to the mating grooves.

[0008] Preferably, the distance between the first longitudinal beam and the second longitudinal beam is less than the distance between the inner edge of the leading edge of the UAV horizontal tail and the C-shaped beam.

[0009] Preferably, the support groove is semi-cylindrical.

[0010] Preferably, the height adjustment device includes adjustment bolts, and a plurality of the adjustment bolts are symmetrically distributed at the bottom of the support.

[0011] According to the assembly process of a drone horizontal stabilizer provided by the present invention, using the above-mentioned assembly tooling for the drone horizontal stabilizer, the process includes the following steps:

[0012] Step 1: Install the assembly fixture for the drone's horizontal stabilizer, adjust the height using the height adjustment device, and measure the horizontal level using a level measuring instrument;

[0013] Step 2: The ribs include a first rib, a second rib, a third rib, a fourth rib, a fifth rib, a sixth rib, and a seventh rib. The first rib, the second rib, the third rib, the fourth rib, the fifth rib, the sixth rib, and the seventh rib are sequentially threaded onto the main beam, and the two ends of the main beam are placed on the support grooves respectively.

[0014] Step 3: Securely connect the first wing rib, the second wing rib, the third wing rib, the fourth wing rib, the fifth wing rib, and the sixth wing rib to the C-shaped beam respectively;

[0015] Step 4: Secure one end of the elevator to the first wing rib;

[0016] Step 5: Securely connect the seventh wing rib to the C-shaped beam and the elevator respectively;

[0017] Step 6: Rotate the main beam, adjust the position of the rib, and insert the rib into the rib slot;

[0018] Step 7: Rotate the main beam axially away from the assembly position, apply adhesive at the connection between the rib and the main beam, and rotate the main beam to return it to its original position.

[0019] Preferably, the method further includes the following steps:

[0020] Step 8: Use masking tape to wrap around the contact point between the crossbeam and the main beam to fix the main beam, and apply adhesive after curing;

[0021] Step 9: Apply adhesive to the position where the head of the rib is assembled with the leading edge, then attach the leading edge and secure it with masking tape;

[0022] Step 10: Remove the masking tape and cut the main beam to obtain the flat tail assembly.

[0023] Preferably, the C-shaped beam has multiple assembly holes, and the multiple ribs are respectively glued to the C-shaped beam through the assembly holes.

[0024] Preferably, the two ends of the elevator are glued to the first wing rib and the seventh wing rib, respectively.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] This invention features a support groove on the crossbeam, on which the main beam of the UAV's horizontal stabilizer rests. Multiple wing rib slots are provided on the longitudinal beam, and the multiple wing ribs of the UAV's horizontal stabilizer are placed in these slots. A height adjustment device is located at the bottom of the support. By fully considering the characteristics of the horizontal stabilizer, this invention meets the high requirements for airfoil precision and assembly of the UAV's horizontal stabilizer, helping to improve assembly efficiency, reduce costs, and precisely control the distance between each wing rib, thus accurately controlling the overall shape of the horizontal stabilizer. This effectively ensures assembly quality and shortens the assembly cycle. 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 a schematic diagram illustrating the structure of the assembly tooling for the horizontal stabilizer of an unmanned aerial vehicle (UAV) as the main feature of this invention.

[0029] Figure 2 This is a schematic diagram illustrating the structure of the support, which is the main feature of this invention.

[0030] Figure 3 This is a schematic diagram illustrating the structure of the crossbeam, which is the main feature of this invention.

[0031] Figure 4 This is a schematic diagram illustrating the main structure of the longitudinal beam in this invention;

[0032] Figure 5 This is a schematic diagram illustrating the structure of the horizontal stabilizer of an unmanned aerial vehicle (UAV) as the main feature of this invention.

[0033] Figure 6 This is a schematic diagram illustrating the assembly of the horizontal stabilizer of an unmanned aerial vehicle (UAV) on an assembly fixture, which is the main feature of this invention.

[0034] As shown in the figure:

[0035] Support 1 First horizontal beam 2 First longitudinal beam 3

[0036] 4. Second longitudinal beam; 5. Second transverse beam; 6. Adjusting bolt.

[0037] First rib 11, Second rib 12, Third rib 13

[0038] Fourth flank 14, Fifth flank 15, Sixth flank 16

[0039] Seventh wing rib 17 Main beam 18 C-beam 19

[0040] Elevator 20 Detailed Implementation

[0041] 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.

[0042] Example 1

[0043] like Figures 1 to 6 As shown, an assembly fixture for a drone horizontal stabilizer according to the present invention includes: a support 1, two crossbeams and two longitudinal beams. The crossbeams and longitudinal beams are horizontally arranged and fastened to the support 1. Each crossbeam is provided with a support groove. The main beam 18 of the drone horizontal stabilizer is placed on the support groove. Each longitudinal beam is provided with multiple wing rib slots. Multiple wing ribs of the drone horizontal stabilizer are respectively placed on the wing rib slots. A height adjustment device is provided at the bottom of the support 1.

[0044] In the development and manufacturing of unmanned aerial vehicles (UAVs), overall assembly involves assembling various parts, instruments, and components into individual parts according to design requirements, followed by the assembly of these parts. The assembly cost of a component depends on the assembly method, which in turn affects assembly time and quality. The horizontal stabilizer of a UAV requires high airfoil precision and has stringent assembly requirements. The assembly tooling proposed in this application effectively ensures assembly quality while offering a short assembly cycle and low cost.

[0045] Support 1 is welded from multiple square steel tubes. The crossbeams include a first crossbeam 2 and a second crossbeam 5 arranged in parallel. Threaded holes are provided at the top of support 1, and corresponding countersunk holes are provided at both ends of the first crossbeam 2 and the second crossbeam 5. The first crossbeam 2 and the second crossbeam 5 are respectively fastened to support 1 with bolts. The main beam 18 is generally a circular tube beam. The support grooves on the crossbeams are semi-cylindrical, matching the shape of the main beam 18, facilitating the adjustment of the position of the main beam 18. Furthermore, the shape and size of the support grooves depend on the shape and size of the main beam 18.

[0046] The longitudinal beams include a first longitudinal beam 3 and a second longitudinal beam 4. Each beam has two mating grooves at its top. The two ends of the first longitudinal beam 3 and the second longitudinal beam 4 are respectively fastened into the mating grooves, usually by screws.

[0047] The distance between the first longitudinal beam 3 and the second longitudinal beam 4 is less than the distance between the inner edge of the leading edge of the UAV's horizontal stabilizer and the C-shaped beam 19. The position of the rib slots on the longitudinal beams varies with the assembly position between the ribs, and the profile of the rib slots is the same as the profile of the corresponding support position of the rib.

[0048] The height adjustment device includes adjusting bolts 6, and multiple adjusting bolts 6 are symmetrically distributed at the bottom of the support 1. The height level adjustment function is achieved by rotating the adjusting bolts 6.

[0049] This application fully considers the characteristics of the flat tail and meets the assembly requirements. Reasonable assembly process planning can significantly reduce the product development life cycle and manufacturing costs.

[0050] Example 2

[0051] like Figure 6 As shown, according to the assembly process of a UAV horizontal stabilizer provided by the present invention, the assembly tooling of the UAV horizontal stabilizer of Embodiment 1 is used, including the following steps:

[0052] Step 1: Install the assembly fixture for the drone's horizontal tail, adjust the height by rotating the adjusting bolt 6, and measure the level with a level measuring instrument;

[0053] Step 2: The ribs include the first rib 11, the second rib 12, the third rib 13, the fourth rib 14, the fifth rib 15, the sixth rib 16, and the seventh rib 17. The first rib 11, the second rib 12, the third rib 13, the fourth rib 14, the fifth rib 15, the sixth rib 16, and the seventh rib 17 are sequentially threaded onto the main beam 18, and the two ends of the main beam 18 are placed on the support grooves respectively.

[0054] Step 3: Multiple assembly holes are provided on the C-shaped beam 19. Multiple ribs are glued to the C-shaped beam 19 through the assembly holes. Glue is applied to the end assembly positions of the first rib 11, second rib 12, third rib 13, fourth rib 14, fifth rib 15 and sixth rib 16 respectively, and glue is applied to the assembly holes of the C-shaped beam 19. Three people work together to adjust the positions of the first rib 11, second rib 12, third rib 13, fourth rib 14, fifth rib 15 and sixth rib 16, and then fasten the first rib 11, second rib 12, third rib 13, fourth rib 14, fifth rib 15 and sixth rib 16 to the C-shaped beam 19 respectively. At this time, the seventh rib 17 at the end is hung on the main beam 18.

[0055] Step 4: Apply glue to one end of the elevator 20 and fasten the elevator 20 to the first wing rib 11. At this time, the seventh wing rib 17 at the end is still hanging on the main beam 18.

[0056] Step 5: Apply adhesive to the end of C-beam 19 and the hole for assembly with the seventh wing rib 17, apply adhesive to the hole for assembly with the elevator 20 and the seventh wing rib 17, and glue and fasten the seventh wing rib 17 to C-beam 19 and elevator 20 respectively.

[0057] Step 6: Rotate the main beam 18, adjust the position of each rib, and insert each rib into the rib slot of the longitudinal beam;

[0058] Step 7: Rotate the main beam 18 axially away from the assembly position by 10mm, apply 8mm of adhesive at the connection between the rib and the main beam 18, and rotate the main beam 18 back into place.

[0059] Step 8: Use masking tape to wrap around the contact point between the crossbeam and the main beam 18 to fix the main beam 18. After curing for 12 hours, apply adhesive.

[0060] Step 9: Apply adhesive to the area where the wing rib is assembled with the leading edge, then attach the leading edge and secure it with masking tape around key areas;

[0061] Step 10: After 24 hours, the masking tape can be removed, and the excess part of the main beam 18 can be cut off to obtain the flat tail component.

[0062] This application can effectively ensure the airfoil accuracy of horizontal stabilizer assembly, improve assembly efficiency, reduce costs, and precisely control the distance between each rib, thereby precisely controlling the overall shape of the horizontal stabilizer.

[0063] 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.

[0064] 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 a horizontal stabilizer of an unmanned aerial vehicle (UAV), characterized in that, include: Support (1), two crossbeams and two longitudinal beams, the crossbeams and the longitudinal beams are horizontally set and fastened on the support (1), each of the crossbeams is provided with a support groove, the main beam (18) of the drone's horizontal tail is placed on the support groove, each of the longitudinal beams is provided with multiple wing rib slots, the multiple wing ribs of the drone's horizontal tail are respectively placed on the wing rib slots, and the bottom of the support (1) is provided with a height adjustment device; The longitudinal beams include a first longitudinal beam (3) and a second longitudinal beam (4). The top of each of the longitudinal beams is provided with two mating grooves. The two ends of the first longitudinal beam (3) and the second longitudinal beam (4) are respectively fastened in the mating grooves. The distance between the first longitudinal beam (3) and the second longitudinal beam (4) is less than the distance between the inner edge of the leading edge of the UAV horizontal tail and the C-shaped beam (19); The support groove is semi-cylindrical; The height adjustment device includes adjusting bolts (6), and a plurality of adjusting bolts (6) are symmetrically distributed at the bottom of the support (1).

2. The assembly fixture for the horizontal stabilizer of a UAV as described in claim 1, characterized in that, The support (1) is welded from multiple square steel tubes. The crossbeam includes a first crossbeam (2) and a second crossbeam (5) arranged in parallel. The top of the support (1) is provided with a threaded hole. The two ends of the first crossbeam (2) and the second crossbeam (5) are provided with corresponding countersunk holes. The first crossbeam (2) and the second crossbeam (5) are respectively fastened to the support (1) by bolts.

3. An assembly process for a horizontal stabilizer of an unmanned aerial vehicle (UAV), characterized in that, The assembly fixture for the horizontal stabilizer of the UAV as described in any one of claims 1-2 includes the following steps: Step 1: Install the assembly fixture for the drone's horizontal stabilizer, adjust the height using the height adjustment device, and measure the horizontal level using a level measuring instrument; Step 2: The wing ribs include a first wing rib (11), a second wing rib (12), a third wing rib (13), a fourth wing rib (14), a fifth wing rib (15), a sixth wing rib (16), and a seventh wing rib (17). The first wing rib (11), the second wing rib (12), the third wing rib (13), the fourth wing rib (14), the fifth wing rib (15), the sixth wing rib (16), and the seventh wing rib (17) are sequentially threaded onto the main beam (18), and the two ends of the main beam (18) are placed on the support grooves respectively. Step 3: Securely connect the first wing rib (11), the second wing rib (12), the third wing rib (13), the fourth wing rib (14), the fifth wing rib (15), and the sixth wing rib (16) to the C-shaped beam (19) respectively; Step 4: Secure one end of the elevator (20) to the first wing rib (11); Step 5: Securely connect the seventh wing rib (17) to the C-shaped beam (19) and the elevator (20) respectively; Step 6: Rotate the main beam (18), adjust the position of the rib, and insert the rib into the rib slot; Step 7: Rotate the main beam (18) axially away from the assembly position, apply glue to the connection between the rib and the main beam (18), and rotate the main beam (18) to return it to its original position.

4. The assembly process of the UAV horizontal stabilizer as described in claim 3, characterized in that, It also includes the following steps: Step 8: Use masking tape to wrap around the contact point between the crossbeam and the main beam (18) to fix the main beam (18), and apply glue after curing; Step 9: Apply adhesive to the position where the head of the rib is assembled with the leading edge, then attach the leading edge and secure it with masking tape; Step 10: Remove the masking tape and cut the main beam (18) to obtain the flat tail assembly.

5. The assembly process of the UAV horizontal stabilizer as described in claim 4, characterized in that, The C-beam (19) has multiple assembly holes, and the multiple ribs are respectively glued to the C-beam (19) through the assembly holes.

6. The assembly process of the UAV horizontal stabilizer as described in claim 4, characterized in that, The elevator (20) is glued to the first wing rib (11) and the seventh wing rib (17) at both ends.

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