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

Abstract

The application provides an unmanned aerial vehicle vertical tail assembly tool and an 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, the two cross beams are oppositely provided with positioning pins and rear beam support grooves, the two ends of a main beam of the unmanned aerial vehicle vertical tail are respectively installed on the positioning pins and the rear beam support grooves, a plurality of wing rib clamping grooves are arranged on any longitudinal beam, a plurality of wing ribs of the unmanned aerial vehicle vertical tail are respectively placed on the wing rib clamping grooves, and a height adjusting device is arranged at the bottom of the support. The two ends of the main beam of the unmanned aerial vehicle vertical tail are respectively installed on the positioning pins and the rear beam support grooves, the plurality of wing ribs of the unmanned aerial vehicle vertical tail are respectively placed on the wing rib clamping grooves, and the height adjusting device is arranged at the bottom of the support, the characteristics of the vertical tail are fully considered, the demand of high wing shape precision and high assembly requirement of the unmanned aerial vehicle vertical tail 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 vertical tail. Background Technology

[0002] 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 accuracy. 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 accuracy, 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 vertical tail 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 vertical tail to realize the assembly of the UAV vertical tail 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's vertical tail.

[0005] An assembly fixture for a UAV vertical tail 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. Positioning pins and rear beam support grooves are arranged opposite each other on the two crossbeams. The two ends of the main beam of the UAV vertical tail are respectively installed on the positioning pins and the rear beam support grooves. Multiple wing rib slots are provided on each of the longitudinal beams. Multiple wing ribs of the UAV vertical tail 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, a horizontal positioning pin hole is provided in the middle of the first crossbeam, and the positioning pin is horizontally installed on the first crossbeam through the positioning pin hole.

[0008] Preferably, the positioning pin comprises three cylinders with different outer diameters, the outer diameter of which gradually decreases from the first crossbeam to the second crossbeam.

[0009] Preferably, the second crossbeam is provided with the rear beam support groove, which is semi-cylindrical.

[0010] Preferably, the longitudinal beam includes a first longitudinal beam and a second longitudinal beam, the two ends of the first longitudinal beam being fastened to the ends of the first crossbeam and the second crossbeam respectively by angle iron; the two ends of the second longitudinal beam being fastened to the ends of the first crossbeam and the second crossbeam respectively by angle iron.

[0011] Preferably, the height adjustment device includes adjustment bolts, and a plurality of the adjustment bolts are symmetrically distributed at the bottom of the support.

[0012] According to the assembly process of a UAV vertical tail provided by the present invention, using the above-mentioned assembly fixture for the UAV vertical tail, the process includes the following steps:

[0013] Step 1: Install the assembly fixture for the UAV's vertical tail, adjust the height adjustment device to adjust the height, and measure the level with a level measuring instrument;

[0014] Step 2: The ribs include a first rib, a second rib, a third rib, and a fourth rib. The first rib, the second rib, the third rib, and the fourth rib are sequentially threaded onto the main beam. The end of the main beam near the first rib is inserted into the positioning pin, and the end of the main beam near the fourth rib is placed on the rear beam support groove.

[0015] Step 3: Secure the C-shaped beam to one side of both the second wing rib and the third wing rib;

[0016] Step 4: Secure one end of the C-shaped beam to the first wing rib;

[0017] Step 5: Secure one end of the control surface assembly to the first wing rib;

[0018] Step 6: Secure the other end of the C-beam to the fourth wing rib, and secure the other end of the rudder assembly to the fourth wing rib;

[0019] Step 7: Rotate the main beam, adjust the position of the rib and the main beam, and insert the rib into the rib slot;

[0020] Step 8: Rotate the main beam and move it axially. Apply adhesive to the connection point of the main beam at the right end of the rib. Rotate the main beam to return it to its original position.

[0021] Preferably, the method further includes the following steps:

[0022] Step 9: Secure one end of the rib with masking tape, and apply adhesive after curing;

[0023] Step 10: Apply adhesive to the position where the head of the rib is assembled with the leading edge, then attach the leading edge and wrap masking tape around the corresponding position to secure it;

[0024] Step 11: Remove the masking tape and cut the main beam to obtain the tail assembly.

[0025] Preferably, the C-shaped beam has two assembly holes in the middle, and the ends of the second rib and the third rib are respectively glued to the C-shaped beam through the assembly holes.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] This invention features two crossbeams with locating pins and rear beam support grooves positioned opposite each other. The two ends of the main beam of the UAV's vertical tail are respectively mounted on the locating pins and rear beam support grooves. Each longitudinal beam has multiple wing rib slots, and the multiple wing ribs of the UAV's vertical tail are placed in the wing rib slots. A height adjustment device is provided at the bottom of the support. By fully considering the characteristics of the vertical tail, this invention can meet the high requirements of the UAV's vertical tail for airfoil accuracy and high assembly requirements, which helps to improve assembly efficiency, reduce costs, and precisely control the distance between each wing rib, thus accurately controlling the overall shape of the vertical tail. This effectively ensures assembly quality and shortens the assembly cycle. Attached Figure Description

[0028] 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:

[0029] Figure 1 This is a schematic diagram illustrating the structure of the assembly tooling for the vertical tail of an unmanned aerial vehicle (UAV) in this invention.

[0030] Figure 2 This is a schematic diagram illustrating the structure of the support, which is the main feature of this invention.

[0031] Figure 3 This is a schematic diagram illustrating the structure of the first crossbeam, which is the main feature of this invention.

[0032] Figure 4 This is a schematic diagram illustrating the structure of the second crossbeam, which is the main feature of this invention.

[0033] Figure 5This is a schematic diagram illustrating the structure of the first longitudinal beam, which is the main feature of this invention.

[0034] Figure 6 This is a schematic diagram illustrating the structure of the second longitudinal beam, which is the main feature of this invention.

[0035] Figure 7 This is a schematic diagram illustrating the structure of the positioning pin, which is the main feature of this invention.

[0036] Figure 8 This is a schematic diagram illustrating the structure of the vertical tail of an unmanned aerial vehicle (UAV) as the main feature of this invention.

[0037] Figure 9 This is a schematic diagram illustrating the assembly process of the UAV's vertical tail, which is the main feature of this invention.

[0038] Figure 10 This is a schematic diagram illustrating the assembly process of the UAV's vertical tail, which is the main feature of this invention.

[0039] Figure 11 This is a schematic diagram illustrating the assembly process of the UAV's vertical tail, which is the main feature of this invention.

[0040] Figure 12 This is a schematic diagram illustrating the assembly process of the UAV's vertical tail, which is the main feature of this invention.

[0041] Figure 13 This is a schematic diagram illustrating the assembly process of the UAV's vertical tail, which is the main feature of this invention.

[0042] Figure 14 This is a schematic diagram illustrating the assembly process of the UAV's vertical tail, which is the main feature of this invention.

[0043] As shown in the figure:

[0044] Support 1 First horizontal beam 2 First longitudinal beam 3

[0045] Second longitudinal beam 4; Second transverse beam 5; Angle iron 6

[0046] 7 Adjusting bolt, 8 Locating pin, 11 First wing rib

[0047] Second wing rib 12, Third wing rib 13, Fourth wing rib 14

[0048] Main beam 15, C-beam 16, Rudder assembly 17 Detailed Implementation

[0049] 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.

[0050] Example 1

[0051] like Figure 1-7 As shown, an assembly fixture for a UAV vertical tail 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. Positioning pins 8 and rear beam support grooves are arranged opposite each other on the two crossbeams. The two ends of the main beam 15 of the UAV vertical tail are respectively installed on the positioning pins 8 and the rear beam support grooves. Multiple wing rib slots are provided on each longitudinal beam. Multiple wing ribs of the UAV vertical tail are respectively placed on the wing rib slots. A height adjustment device is provided at the bottom of the support 1.

[0052] 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 the assembly time and quality. The vertical tail 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.

[0053] 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.

[0054] A horizontal positioning pin hole is provided in the middle of the first crossbeam 2, and the positioning pin 8 is horizontally installed on the first crossbeam 2 through the positioning pin hole.

[0055] The positioning pin 8 consists of three cylinders with different outer diameters. The outer diameter of the cylinders gradually decreases from the first crossbeam 2 to the second crossbeam 5. The different outer diameters form a shoulder, which serves as a positioning element.

[0056] The second crossbeam 5 is provided with a rear beam support groove, which is semi-cylindrical and matches the shape of the main beam 15, making it convenient to adjust the position of the main beam 15. Furthermore, the shape and size of the rear beam support groove depend on the shape and size of the main beam 15.

[0057] The longitudinal beams include a first longitudinal beam 3 and a second longitudinal beam 4. The two ends of the first longitudinal beam 3 are fastened to the ends of the first crossbeam 2 and the second crossbeam 5 respectively by angle iron 6. The two ends of the second longitudinal beam 4 are fastened to the ends of the first crossbeam 2 and the second crossbeam 5 respectively by angle iron 6.

[0058] The height adjustment device includes adjusting bolts 7, and multiple adjusting bolts 7 are symmetrically distributed at the bottom of the support 1. The height level adjustment function is achieved by rotating the adjusting bolts 6.

[0059] This application fully considers the characteristics of the vertical tail and meets the assembly requirements. A reasonable assembly process plan can significantly reduce the product development life cycle and manufacturing costs.

[0060] Example 2

[0061] like Figure 8-14 As shown, according to the assembly process of a UAV vertical tail provided by the present invention, the assembly tooling of the UAV vertical tail of Embodiment 1 is used, and the process includes the following steps:

[0062] Step 1: Install the assembly fixture for the drone's vertical tail, adjust the height by rotating the adjusting bolt 7, and measure the level with a level measuring instrument;

[0063] Step 2: The ribs include the first rib 11, the second rib 12, the third rib 13 and the fourth rib 14. The first rib 11, the second rib 12, the third rib 13 and the fourth rib 14 are sequentially threaded onto the main beam 15. The end of the main beam 15 near the first rib 11 is inserted into the positioning pin 8, and the end of the main beam 15 near the fourth rib 14 is placed on the rear beam support groove.

[0064] Step 3: Two assembly holes are provided in the middle of the C-shaped beam 16. Apply glue to the two assembly holes and apply glue to the ends of the second rib 12 and the third rib 13. The ends of the second rib 12 and the third rib 13 are respectively glued to the C-shaped beam 16 through the assembly holes. Secure the C-shaped beam 16 to one side of the second rib 12 and the third rib 13. At this time, the first rib 11 and the fourth rib 14 are hung on the main beam 15.

[0065] Step 4: Apply adhesive to the end of the C-beam 16 and the assembly point with the first wing rib 11, and fasten one end of the C-beam 16 to the first wing rib 11. At this time, the fourth wing rib 14 is hung on the main beam 15.

[0066] Step 5: Apply adhesive to the end of the control surface assembly 17 and the hole for assembly with the first wing rib 11, and fasten one end of the control surface assembly 17 to the first wing rib 11. At this time, the fourth wing rib 14 is hung on the main beam 15.

[0067] Step 6: Apply adhesive to the other end of the control surface assembly 17, the C-beam 16 and the hole of the fourth wing rib 14 to which they are assembled, and fasten the other end of the C-beam 16 to the fourth wing rib 14, and fasten the other end of the control surface assembly 17 to the fourth wing rib 14.

[0068] Step 7: Rotate the main beam 15, adjust the position of the end of the wing rib to locate the position of the fourth wing rib 14 and the main beam 15, and insert the wing rib into the wing rib slot;

[0069] Step 8: Rotate the main beam 15 and move it 10mm along the axis. Apply glue 10mm wide at the connection point on the main beam 15 at the right end of the rib. Rotate the main beam 15 to return it to its original position.

[0070] Step 9: Secure one end of the rib with masking tape. Note that you should measure the dimensions before securing it. Apply glue after 12 hours of curing.

[0071] Step 10: Apply adhesive to the position where the wing rib is assembled with the leading edge, then attach the leading edge and wrap masking tape around the corresponding position to secure it;

[0072] Step 11: After 24 hours, the masking tape can be removed, and the excess part of the main beam 15 can be cut off to obtain the tail assembly.

[0073] After the components of the vertical tail are assembled and cured, the vertical tail can also rotate around the pin to achieve the purpose of flipping, which makes it easy to cover the skin and install photovoltaic panels on the upper and lower sides of the vertical tail.

[0074] This application can effectively ensure the airfoil accuracy of the vertical tail assembly, improve assembly efficiency, reduce costs, and accurately control the distance between each rib, thereby accurately controlling the overall shape of the vertical tail.

[0075] 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.

[0076] 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 UAV vertical tail, characterized in that, include: Support (1), two crossbeams and two longitudinal beams, the crossbeams and the longitudinal beams are horizontally arranged and fastened on the support (1), the two crossbeams are provided with positioning pins (8) and rear beam support grooves respectively, the two ends of the main beam (15) of the UAV tail are respectively installed on the positioning pins (8) and the rear beam support grooves, each of the longitudinal beams is provided with multiple wing rib slots, the multiple wing ribs of the UAV tail are respectively placed on the wing rib slots, and the bottom of the support (1) is provided with a height adjustment device; 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. A horizontal positioning pin hole is provided in the middle of the first crossbeam (2), and the positioning pin (8) is horizontally installed on the first crossbeam (2) through the positioning pin hole; The positioning pin (8) includes three cylinders with different outer diameters, and the outer diameter of the cylinders gradually decreases from the first crossbeam (2) to the second crossbeam (5).

2. The assembly fixture for the UAV vertical tail as described in claim 1, characterized in that, The second crossbeam (5) is provided with the rear beam support groove, which is semi-cylindrical.

3. The assembly fixture for the UAV vertical tail as described in claim 1, characterized in that, The longitudinal beam includes a first longitudinal beam (3) and a second longitudinal beam (4). The two ends of the first longitudinal beam (3) are fastened to the ends of the first crossbeam (2) and the second crossbeam (5) respectively by angle iron (6). The two ends of the second longitudinal beam (4) are fastened to the ends of the first crossbeam (2) and the second crossbeam (5) respectively by angle iron (6).

4. The assembly fixture for the UAV vertical tail as described in claim 1, characterized in that, The height adjustment device includes adjusting bolts (7), and a plurality of adjusting bolts (7) are symmetrically distributed at the bottom of the support (1).

5. An assembly process for a UAV vertical tail, characterized in that, The assembly fixture for the UAV vertical tail according to any one of claims 1-4 includes the following steps: Step 1: Install the assembly fixture for the UAV's vertical tail, adjust the height adjustment device to adjust the height, and measure the level with 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), and a fourth wing rib (14). The first wing rib (11), the second wing rib (12), the third wing rib (13), and the fourth wing rib (14) are sequentially threaded onto the main beam (15). The end of the main beam (15) near the first wing rib (11) is inserted into the positioning pin (8), and the end of the main beam (15) near the fourth wing rib (14) is placed on the rear beam support groove. Step 3: Secure the C-beam (16) to one side of both the second wing rib (12) and the third wing rib (13); Step 4: Secure one end of the C-shaped beam (16) to the first wing rib (11); Step 5: Secure one end of the control surface assembly (17) to the first wing rib (11); Step 6: Secure the other end of the C-beam (16) to the fourth wing rib (14), and secure the other end of the rudder assembly (17) to the fourth wing rib (14); Step 7: Rotate the main beam (15), adjust the position of the rib and the main beam (15), and insert the rib into the rib slot; Step 8: Rotate the main beam (15) and move it axially. Apply glue to the connection point of the main beam (15) at the right end of the wing rib. Rotate the main beam (15) to return it to its original position.

6. The assembly process of the UAV vertical tail as described in claim 5, characterized in that, It also includes the following steps: Step 9: Secure one end of the rib with masking tape, and apply adhesive after curing; Step 10: Apply adhesive to the position where the head of the rib is assembled with the leading edge, then attach the leading edge and wrap masking tape around the corresponding position to secure it; Step 11: Remove the masking tape and cut the main beam (15) to obtain the tail assembly.

7. The assembly process of the UAV vertical tail as described in claim 5, characterized in that, The C-beam (16) has two assembly holes in the middle, and the ends of the second wing rib (12) and the third wing rib (13) are respectively glued to the C-beam (16) through the assembly holes.

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