Fixed-wing aircraft assembly fixture structure

Abstract

The utility model discloses a fixed wing aircraft assembly fixture structure, which relates to the technical field of aviation engineering, and comprises an assembly base, the assembly base comprises a wing fixing mechanism, an empennage fixing mechanism and a fixing seat, the wing fixing mechanism and the empennage fixing mechanism comprise a vertical seat and a fixing column, and the vertical seat and the fixing column are connected through a connecting rod. A motor is arranged on one side of the fixing column, the output end of the motor is connected with a first bevel gear, the first bevel gear is in meshed connection with a second bevel gear, the inner ring of the second bevel gear is connected with a lead screw, the outer ring of the lead screw is sleeved with a first sliding seat, and one side of the first sliding seat is connected with an upper cover plate. A first sliding groove is formed in one side of the fixing column. The fixing mechanism has the effect of being high in position clamping stability, can ensure that the airplane structural part is kept at the correct position and posture in the assembling process, and reduces assembling errors caused by displacement or deformation.

Description

Technical Field

[0001] This utility model relates to the field of aerospace engineering technology, specifically to a fixed-wing aircraft assembly frame structure. Background Technology

[0002] Currently, small general-purpose fixed-wing aircraft are developing rapidly in the field of aerospace engineering, characterized by low cost, high efficiency, and convenient and flexible use. While ensuring the assembly accuracy meets design requirements, how to quickly and effectively complete the aircraft assembly work has a significant impact on reducing aircraft manufacturing costs, increasing the speed of aircraft delivery to customers, and thus increasing enterprise profits. Therefore, developing an assembly jig suitable for small general-purpose fixed-wing aircraft can effectively meet the current production needs of enterprises. Existing fixed-wing aircraft assembly jigs suffer from unstable clamping, requiring workers to spend more time and effort adjusting and fixing the positions of parts during assembly operations, thus increasing the assembly difficulty. Therefore, this application proposes a fixed-wing aircraft assembly jig structure. Utility Model Content

[0003] This utility model provides a fixed-wing aircraft assembly jig structure with strong stability through multi-position clamping. This fixing mechanism can ensure that the aircraft structural components maintain the correct position and attitude during the assembly process, reduce assembly errors caused by displacement or deformation, and solve the problem that existing fixed-wing aircraft assembly requires workers to spend more time and effort to adjust and fix the position of parts during assembly operations due to unstable clamping, thus increasing the assembly difficulty.

[0004] To improve the stability of multi-position clamping, this utility model provides the following technical solution: a fixed-wing aircraft assembly frame structure, including an assembly base, the assembly base including a wing fixing mechanism, a tail fixing mechanism and a fixing seat, the wing fixing mechanism and the tail fixing mechanism including a stand and a fixing column, a motor is provided on one side of the fixing column, the output end of the motor is connected to a bevel gear one, the bevel gear one is meshed with a bevel gear two, the inner ring of the bevel gear two is connected to a lead screw, the outer ring of the lead screw is fitted with a sliding seat one, and a top cover plate is connected to one side of the sliding seat one.

[0005] As a preferred technical solution of this utility model, a sliding groove is provided on one side of the fixed column, a slider is connected inside the sliding groove, a lower cover plate is connected to one side of the slider, and an airbag is embedded on one side of both the upper cover plate and the lower cover plate.

[0006] As a preferred technical solution of this utility model, a second sliding groove is provided on one side of another fixed column, and a second slider and a fourth slider are connected inside the second sliding groove. The second slider is connected to the upper cover plate, and the fourth slider is connected to the lower cover plate. A first cylinder is embedded in the top of the stand, and the first cylinder is connected to the lower cover plate.

[0007] As a preferred technical solution of this utility model, the wing fixing mechanism further includes a groove, a threaded rod connected inside the groove, a slider three sleeved on the outer ring of the threaded rod, the slider three being connected to the stand, a turntable connected to one end of the threaded rod, and a handle connected to one side of the turntable.

[0008] As a preferred technical solution of this utility model, the tail fin fixing mechanism includes a second groove, a bidirectional lead screw is connected inside the second groove, and a second sliding seat is sleeved on the outer ring of the bidirectional lead screw.

[0009] As a preferred embodiment of this utility model, a fixing plate is connected to one side of the fixing column, an air pump is provided on the top of the fixing plate, an air pipe is connected to the output end of the air pump, a pipe head is connected to one end of the air pipe, an air delivery pipe is connected to the side wall of the pipe head, and the air delivery pipe is connected to the airbag.

[0010] As a preferred technical solution of this utility model, a cylinder two is embedded in the top of the fixed base, a top ring is connected to the top of the cylinder two, and a self-locking universal wheel is provided at the bottom of the assembly base.

[0011] Compared with the prior art, this utility model provides a fixed-wing aircraft assembly jig structure, which has the following beneficial effects:

[0012] 1. The fixed-wing aircraft assembly frame structure, by setting a fixing mechanism, can make the structural components of the wing and tail more tightly and accurately connected during assembly by the stable clamping of the fixing mechanism, ensuring the integrity and strength of the structure. The precise clamping of the assembled tail can ensure the installation accuracy and mobility of its control surfaces.

[0013] 2. This fixed-wing aircraft assembly jig structure has a compact overall structure, is easy to operate, and can adjust the clamping width, thereby improving the assembly clamping of aircraft of different widths. In addition, the structure is equipped with an auxiliary airbag clamping structure, which can reduce clamping damage to the aircraft wings and improve their service life. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of a fixed-wing aircraft assembly frame structure according to the present invention;

[0015] Figure 2This is a schematic diagram of the tail fin mechanism of a fixed-wing aircraft assembly frame structure according to the present invention;

[0016] Figure 3 This is a schematic diagram of the internal connection structure of the fixed column of a fixed-wing aircraft assembly frame structure according to the present invention;

[0017] Figure 4 for Figure 1 A magnified structural diagram of point A.

[0018] In the diagram: 1. Assembly base; 2. Wing fixing mechanism; 21. Fixing column; 22. Motor; 23. Bevel gear one; 24. Bevel gear two; 25. Lead screw; 26. Slide groove one; 27. Slider one; 28. Stand; 29. ​​Cylinder one; 210. Lower cover plate; 211. Slide groove two; 212. Slider two; 213. Upper cover plate; 214. Groove one; 215. Threaded rod; 216. Slider three; 217. Slider four; 218. Sliding seat one; 3. Tail wing fixing mechanism; 31. Groove two; 32. Double-acting lead screw; 33. Sliding seat two; 4. Fixing plate; 5. Air pump; 6. Airbag; 7. Air pipe; 8. Pipe head; 9. Air supply pipe; 10. Turntable; 11. Handle; 12. Self-locking caster wheel; 13. Fixing seat; 14. Cylinder two; 15. Top ring. Detailed Implementation

[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0020] Please see Figures 1-4 This utility model discloses a fixed-wing aircraft assembly frame structure, including an assembly base 1. The assembly base 1 includes a wing fixing mechanism 2, a tail fixing mechanism 3, and a fixing seat 13. The wing fixing mechanism 2 and the tail fixing mechanism 3 include a stand 28 and a fixing column 21. A motor 22 is provided on one side of the fixing column 21. The output end of the motor 22 is connected to a bevel gear 23. The bevel gear 23 is meshed with a bevel gear 24. The inner ring of the bevel gear 24 is connected to a lead screw 25. The outer ring of the lead screw 25 is fitted with a sliding seat 218. One side of the sliding seat 218 is connected to an upper cover plate 213.

[0021] Specifically, the support 28 and the fixed column 21 are fixedly installed by bolts. The motor 22 drives the bevel gear 23 to rotate, and through the meshing principle, it drives the bevel gear 24 and the lead screw 25 to rotate. The sliding seat 218 is screwed to the outer ring of the lead screw 25. The upper cover plate 213 and the sliding seat 218 are welded together and used to adjust the up and down movement of the upper cover plate 213.

[0022] In this embodiment, a groove 26 is provided on one side of the fixed column 21, a slider 27 is connected inside the groove 26, a lower cover plate 210 is connected to one side of the slider 27, and an airbag 6 is embedded on one side of both the upper cover plate 213 and the lower cover plate 210.

[0023] Specifically, slider 27 is slidably connected inside the groove 26, slider 27 is welded to the lower cover plate 210, and airbag 6 is embedded on the surface of the upper cover plate 213 and the lower cover plate 210 to limit the upper cover plate 213 and the lower cover plate 210 and to assist in clamping the aircraft wing.

[0024] In this embodiment, a sliding groove 211 is provided on one side of another fixed column 21. Sliding slider 212 and sliding slider 4 217 are connected inside the sliding groove 211. Sliding slider 212 is connected to the upper cover plate 213, and sliding slider 4 217 is connected to the lower cover plate 210. A cylinder 1 29 is embedded in the top of the stand 28 and is connected to the lower cover plate 210.

[0025] Specifically, slider 212 and slider 4 217 are slidably connected inside slide groove 211 and are welded to upper cover plate 213 and lower cover plate 210 respectively for limiting movement. Cylinder 1 29 is fixedly connected to lower cover plate 210 by bolts for adjusting the height of lower cover plate 210.

[0026] In this embodiment, the wing fixing mechanism 2 also includes a groove 214, a threaded rod 215 is connected inside the groove 214, a slider 216 is sleeved on the outer ring of the threaded rod 215, the slider 216 is connected to the stand 28, one end of the threaded rod 215 is connected to a turntable 10, and one side of the turntable 10 is connected to a handle 11.

[0027] Specifically, the threaded rod 215 is rotatably connected inside the groove 214, the slider 216 is screwed onto the outer ring of the threaded rod 215 and welded to the stand 28, the turntable 10 is keyed to the threaded rod 215, and the handle 11 is welded to the turntable 10 for rotating the threaded rod 215 to adjust the width between the stands 28.

[0028] In this embodiment, the tail wing fixing mechanism 3 includes a second groove 31, a bidirectional lead screw 32 is connected inside the second groove 31, and a sliding seat 33 is sleeved on the outer ring of the bidirectional lead screw 32.

[0029] Specifically, the bidirectional lead screw 32 is rotatably connected inside the groove 31, and the sliding seat 33 is screwed onto the outer ring of the bidirectional lead screw 32.

[0030] In this embodiment, a fixing plate 4 is connected to one side of the fixing column 21, an air pump 5 is provided on the top of the fixing plate 4, an air pipe 7 is connected to the output end of the air pump 5, a pipe head 8 is connected to one end of the air pipe 7, an air supply pipe 9 is connected to the side wall of the pipe head 8, and the air supply pipe 9 is connected to the airbag 6.

[0031] Specifically, the fixing plate 4 is welded to the fixing column 21, the air pump 5 is installed on the top of the fixing plate 4 by bolts, the air pipe 7 is used to supply air, and the pipe head 8 and the air delivery pipe 9 are used to divert the air to the interior of the upper cover plate 213 and the lower cover plate 210 for auxiliary clamping.

[0032] In this embodiment, a cylinder 14 is embedded in the top of the fixed base 13, a top ring 15 is connected to the top of the cylinder 14, and a self-locking caster wheel 12 is provided at the bottom of the mounting base 1.

[0033] Specifically, cylinder 14 and top ring 15 are fixedly installed by bolts to adjust the height of top ring 15 so as to support the nose of the aircraft. Self-locking caster wheel 12 is used for movement and locking.

[0034] The working principle and usage process of this utility model are as follows: During assembly, firstly, adjust the position of the assembly base 1 according to the specific assembly position of the aircraft, and lock it after moving it using the self-locking universal wheel 12. Then, when fixing the wing, determine the width of the wing, turn the handle 11 to adjust the width, and then adjust the upper cover plate 213 and the lower cover plate 210 according to the specific height. The lower cover plate 210 and the upper cover plate 213 can be adjusted by the cylinder 29 and the lead screw 25 respectively. During this process, the air pump 5 is started to supply air to the airbag 6 to assist in clamping the wing. When clamping the tail wing, the width is adjusted by the bidirectional lead screw 32, and the clamping method is the same as that of the wing. The nose of the aircraft is supported by the top ring 15.

[0035] It should be noted that, in this document, terms such as "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0036] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A fixed-wing aircraft assembly jig structure comprising an assembly base (1), characterised in that: The mounting base (1) includes a wing fixing mechanism (2), a tail fixing mechanism (3) and a fixing seat (13). The wing fixing mechanism (2) and the tail fixing mechanism (3) include a stand (28) and a fixing column (21). A motor (22) is provided on one side of the fixing column (21). The output end of the motor (22) is connected to a bevel gear (23). The bevel gear (23) is meshed with a bevel gear (24). The inner ring of the bevel gear (24) is connected to a lead screw (25). The outer ring of the lead screw (25) is fitted with a sliding seat (218). One side of the sliding seat (218) is connected to an upper cover plate (213).

2. A fixed-wing aircraft assembly jig structure according to claim 1, wherein: A sliding groove (26) is provided on one side of the fixed column (21), and a slider (27) is connected inside the sliding groove (26). A lower cover plate (210) is connected to one side of the slider (27), and an airbag (6) is embedded on one side of both the upper cover plate (213) and the lower cover plate (210).

3. A fixed-wing aircraft assembly jig structure according to claim 1, wherein: Another fixed column (21) has a sliding groove (211) on one side. The sliding groove (211) is connected to a slider (212) and a slider (217). The slider (212) is connected to the upper cover plate (213), and the slider (217) is connected to the lower cover plate (210). The top of the stand (28) is fitted with a cylinder (29), which is connected to the lower cover plate (210).

4. The fixed-wing aircraft assembly jig structure of claim 1, wherein: The wing fixing mechanism (2) also includes a groove (214), inside which a threaded rod (215) is connected, and a slider (216) is sleeved on the outer ring of the threaded rod (215). The slider (216) is connected to the stand (28), and one end of the threaded rod (215) is connected to a turntable (10). One side of the turntable (10) is connected to a handle (11).

5. A fixed-wing aircraft assembly frame structure according to claim 1, characterized in that: The tail fin fixing mechanism (3) includes a second groove (31), and a two-way lead screw (32) is connected inside the second groove (31). A sliding seat (33) is sleeved on the outer ring of the two-way lead screw (32).

6. A fixed-wing aircraft assembly jig structure according to claim 1, wherein: A fixing plate (4) is connected to one side of the fixing column (21). An air pump (5) is provided on the top of the fixing plate (4). An air pipe (7) is connected to the output end of the air pump (5). A pipe head (8) is connected to one end of the air pipe (7). An air supply pipe (9) is connected to the side wall of the pipe head (8). The air supply pipe (9) is connected to the airbag (6).

7. A fixed-wing aircraft assembly jig structure according to claim 1, wherein: The top of the fixed base (13) is fitted with a cylinder two (14), the top of the cylinder two (14) is connected with a top ring (15), and the bottom of the mounting base (1) is provided with a self-locking universal wheel (12).

Images