Horizontal tail fixing structure
By designing a flat-tail fixing structure including fuselage bosses, carbon plates, butt blocks, docking grooves, connectors and fixing parts, the problems of cumbersome assembly of traditional flat-tail fixing structures and unstable bonding methods are solved, and the effect of rapid fixing and time-saving cost is achieved.
Patent Information
- Application Number
- CN202421838517.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-31
- Publication Date
- 2025-06-24
- Estimated Expiration
- 2034-07-31
AI Technical Summary
The traditional flat-tail fixed structure has problems such as cumbersome, time-consuming and labor-intensive and difficult to adjust during the assembly process, and the strength of the bonding method is greatly affected by environmental factors and is difficult to replace and maintain.
A flat tail fixing structure including a fuselage boss, carbon plate, docking block, docking groove, connecting piece and fixing piece is designed. The fast fixing of the flat tail is achieved through the cooperation of the docking block and the limiting groove.
This structure greatly shortens the installation time, avoids the unappearance problems caused by hole glue fixation, saves time and costs, and improves assembly efficiency.
Smart Images
Figure CN223014889U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aviation component assembly, and particularly relates to a horizontal tail fixing structure. Background Art
[0002] In the fields of model airplanes and unmanned aerial vehicles, the horizontal tail (abbreviation: horizontal tail) is an important part of the airplane, and the design of its fixing structure is directly related to the flight stability and safety of the airplane. Traditional horizontal tail fixing methods often have problems such as cumbersome assembly, time-consuming and laborious, and difficult adjustment. These problems not only increase the production cost but also reduce the production efficiency.
[0003] Currently, most of the horizontal tail fixing structures on the market are fixed by means of bolt connection, bonding or welding. Although the bolt connection method is firm and reliable, precise alignment is required during the assembly process, and the bolts need to be tightened multiple times, which is cumbersome. The bonding method is simple and fast, but the bonding strength is greatly affected by environmental factors, and it is not easy to replace and maintain. At the same time, the bonding method is also prone to phenomena such as glue overflow, directly affecting the overall aesthetic degree.
[0004] In view of this, a horizontal tail fixing structure is provided to overcome the above defects. Content of the Utility Model
[0005] The purpose of the utility model is to provide a horizontal tail fixing structure to solve the problems put forward in the above background art.
[0006] To solve the above technical problems, a horizontal tail fixing structure provided by the utility model includes a fuselage boss and a horizontal tail. A carbon plate is installed on the top surface of the fuselage boss, a docking block is integrally formed on the top surface of the carbon plate, a docking groove is penetrated and opened on the outer wall of the horizontal tail, a limiting groove is opened on the bottom surface of the horizontal tail, a connecting piece is threadedly connected inside the docking groove, a fixing piece is arranged above the connecting piece, and the limiting groove is adapted to the docking block.
[0007] Furthermore, a cavity is opened inside the docking block, a large round hole and a small round hole are penetrated between the cavity and the top surface of the docking block, and the large round hole and the small round hole are also penetrated.
[0008] Furthermore, a sliding rod is fixedly installed on the top surface of the connecting piece, a threaded sleeve rod is arranged above the sliding rod, and a threaded groove is opened inside the threaded sleeve rod.
[0009] Furthermore, the threaded sleeve rod is adapted to the docking groove, the connecting piece is adapted to the large round hole, and the sliding rod is adapted to the small round hole.
[0010] Further, a rotating handle is integrally formed at the top end of the fixing member, and a threaded rod is fixedly connected to the bottom end of the fixing member, and the threaded rod is adapted to the threaded groove.
[0011] Further, a plurality of fixing bolts are fixedly installed on the top surface of the docking block, and the carbon plate and the docking block are fixedly installed on the top surface of the fuselage boss through the plurality of fixing bolts.
[0012] Further, the length of the limiting groove is longer than the length of the docking block, and rounded corners are provided at the edge positions of the docking block and the limiting groove.
[0013] Compared with the prior art, the beneficial effects of the present utility model are as follows:
[0014] By providing a docking block and a limiting groove, and opening a docking groove on the top surface of the horizontal tail, installing a connecting member inside the docking groove, and connecting a fixing member inside the connecting member, the horizontal tail can be quickly fixed above the fuselage boss, greatly shortening the installation time, better avoiding the ugliness caused by fixing with hole drilling and gluing, shortening the assembly time, and saving time costs. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 is a schematic structural diagram of the whole of the present utility model;
[0016] Figure 2 is a schematic bottom surface structure diagram of the horizontal tail of the present utility model;
[0017] Figure 3 is a schematic structural diagram of the carbon plate of the present utility model;
[0018] Figure 4 is a schematic structural diagram of the fixing member of the present utility model;
[0019] Figure 5 is a schematic structural diagram of the connecting member of the present utility model.
[0020] In the figure: 1, fuselage boss; 2, carbon plate;
[0021] 3, docking block; 31, cavity; 32, large round hole; 33, small round hole; 34, fixing bolt;
[0022] 4, horizontal tail; 5, docking groove;
[0023] 6, fixing member; 61, rotating handle; 62, threaded rod;
[0024] 7, connecting member; 71, threaded sleeve rod; 72, threaded groove; 73, sliding rod;
[0025] 8, limiting groove. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0026] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.
[0027] Embodiment 1
[0028] Refer to Figures 1-5 , a fixed structure for a horizontal tail 4, including a fuselage boss 1 and a horizontal tail 4. A carbon plate 2 is installed on the top surface of the fuselage boss 1. A docking block 3 is integrally formed on the top surface of the carbon plate 2. A docking groove 5 is penetrated and opened on the outer wall of the horizontal tail 4. A limiting groove 8 is opened on the bottom surface of the horizontal tail 4. A connecting piece 7 is threadedly connected inside the docking groove 5. A fixing piece 6 is arranged above the connecting piece 7. The limiting groove 8 is adapted to the docking block 3.
[0029] Further, refer to Figures 1-5 , a cavity 31 is opened inside the docking block 3. A large round hole 32 and a small round hole 33 are penetrated and opened between the cavity 31 and the top surface of the docking block 3. The large round hole 32 and the small round hole 33 are also penetrated. By providing the cavity 31, the connecting piece 7 can be accommodated inside the cavity 31. A sliding rod 73 is fixedly installed on the top surface of the connecting piece 7. A threaded sleeve rod 71 is arranged above the sliding rod 73. A threaded groove 72 is opened inside the threaded sleeve rod 71. The threaded sleeve rod 71 is adapted to the docking groove 5. The connecting piece 7 is adapted to the large round hole 32. The sliding rod 73 is adapted to the small round hole 33. By providing the large round hole 32 and the small round hole 33, and setting that the large round hole 32 and the small round hole 33 are also penetrated, and finally setting that the connecting piece 7 is adapted to the large round hole 32 and the sliding rod 73 is adapted to the small round hole 33, the connecting piece 7 can enter the inside of the cavity 31 through the large round hole 32. After the connecting piece 7 enters the inside of the cavity 31, the sliding rod 73 is directly flush with the height of the large round hole 32. At this time, moving the sliding rod 73 into the small round hole 33 can complete the limitation of the connecting piece 7, so that the connecting piece 7 cannot move longitudinally without horizontal movement.
[0030] Even further, refer to Figures 4-5 , a threaded sleeve rod 71 is arranged above the sliding rod 73. A threaded groove 72 is opened inside the threaded sleeve rod 71. A rotating handle 61 is integrally formed at the top end of the fixing piece 6. A threaded rod 62 is fixedly connected to the bottom end of the fixing piece 6. The threaded rod 62 is adapted to the threaded groove 72. By providing the threaded sleeve rod 71, the connecting piece 7 can be threadedly connected inside the docking groove 5. By providing that the threaded rod 62 is adapted to the threaded groove 72, the fixing piece 6 can be connected to the connecting piece 7 through the threaded rod 62. By providing the rotating handle 61, the rotation of the fixing piece 6 is made simpler.
[0031] In addition, a plurality of fixing bolts 34 are fixedly installed on the top surface of the docking block 3. The carbon plate 2 and the docking block 3 are fixedly installed on the top surface of the fuselage boss 1 through the plurality of fixing bolts 34. The length of the limiting groove 8 is longer than the length of the docking block 3. Rounding corners are provided at the edge positions of the docking block 3 and the limiting groove 8. By setting the length of the limiting groove 8 to be longer than the length of the docking block 3, after the connecting piece 7 is aligned and covered with the large circular hole 32, the user can still drive the docking block 3 to move inside the limiting groove 8 by pushing the horizontal tail 4, so that the connecting piece 7 can move inside the large circular hole 32, forming a limit on the connecting piece 7. By setting rounding corners at the edge positions of the docking block 3 and the limiting groove 8, the alignment and covering of the docking block 3 and the limiting groove 8 are made simpler.
[0032] During specific implementation, the user needs to thread the connecting piece 7 into the docking groove 5 through the threaded sleeve rod 71. After the fixing of the connecting piece 7 is completed, the user can align the limiting groove 8 opened at the bottom of the horizontal tail 4 with the docking block 3 installed on the top of the fuselage boss 1. At the same time, the connecting piece 7 needs to be aligned with the large circular hole 32. After alignment, directly cover the horizontal tail 4 above the carbon plate 2 and push the horizontal tail 4 forward. At this time, the connecting piece 7 is located below the small circular hole 33 and cannot easily break out of the cavity 31. In order to make the device more stable in connection, at this time, the threaded rod 62 provided below the fixing piece 6 can be threadedly connected to the threaded groove 72, and the fixing piece 6 and the threaded rod 62 are tightened through the rotating handle 61. After tightening, the top surface of the connecting piece 7 closely fits the inner wall top surface of the cavity 31, and the fixing piece 6 also fits to the bottom surface of the horizontal tail 4. At this time, the horizontal tail 4 will not easily fall off without manual force.
[0033] By providing the docking block 3 and the limiting groove 8, opening the docking groove 5 on the top surface of the horizontal tail 4, installing the connecting piece 7 inside the docking groove 5, and connecting the fixing piece 6 inside the connecting piece 7, the horizontal tail 4 can be quickly fixed above the fuselage boss 1, greatly shortening the installation time, better avoiding the unsightliness caused by fixing with hole drilling and gluing, shortening the assembly time, and saving time costs.
[0034] Working principle: The user needs to thread the connecting piece 7 into the inside of the docking groove 5 through the threaded sleeve rod 71. After fixing the connecting piece 7, the user can align the limiting groove 8 opened at the bottom of the horizontal tail 4 with the docking block 3 installed on the top of the fuselage boss 1. At the same time, it is necessary to align the connecting piece 7 with the large round hole 32. After alignment, directly cover the horizontal tail 4 above the carbon plate 2 and push the horizontal tail 4 forward. At this time, the connecting piece 7 is located below the small round hole 33 and cannot easily break away from the cavity 31. In order to make the device more stable, at this time, the threaded rod 62 provided below the fixing piece 6 can be threadedly connected to the threaded groove 72, and the fixing piece 6 and the threaded rod 62 can be tightened through the turning handle 61. After tightening, the top surface of the connecting piece 7 closely fits the inner wall top surface of the cavity 31, and the fixing piece 6 also fits to the bottom surface of the horizontal tail 4. At this time, the horizontal tail 4 will not easily fall off without human force.
[0035] By providing the docking block 3 and the limiting groove 8 and opening the docking groove 5 on the top surface of the horizontal tail 4, installing the connecting piece 7 inside the docking groove 5, and connecting the fixing piece 6 inside the connecting piece 7, the horizontal tail 4 can be quickly fixed above the fuselage boss 1, greatly shortening the installation time, better avoiding the unsightliness caused by fixing with holes and glue, shortening the assembly time, and saving time costs.
Claims
1. A horizontal tail (4) fixing structure, comprising a fuselage boss (1) and a horizontal tail (4), characterized in that: A carbon plate (2) is installed on the top surface of the fuselage boss (1), a docking block (3) is integrally formed on the top surface of the carbon plate (2), a docking groove (5) is penetrated through the outer wall of the horizontal tail (4), a limiting groove (8) is provided on the bottom surface of the horizontal tail (4), a connecting piece (7) is connected to the internal thread of the docking groove (5), a fixing piece (6) is arranged above the connecting piece (7), and the limiting groove (8) is adapted to the docking block (3).
2. A horizontal tail (4) fixing structure as claimed in claim 1, characterized in that: A cavity (31) is provided inside the docking block (3), a large circular hole (32) and a small circular hole (33) are provided between the cavity (31) and the top surface of the docking block (3), and the large circular hole (32) and the small circular hole (33) are also provided in a through-going manner.
3. A horizontal tail (4) fixing structure as claimed in claim 2, characterized in that: A sliding rod (73) is fixedly mounted on the top surface of the connecting member (7), a threaded sleeve rod (71) is arranged above the sliding rod (73), and a threaded groove (72) is arranged inside the threaded sleeve rod (71).
4. A horizontal tail (4) fixing structure as claimed in claim 3, characterized in that: The threaded sleeve rod (71) is matched with the docking groove (5), the connecting piece (7) is matched with the large circular hole (32), and the sliding rod (73) is matched with the small circular hole (33).
5. A horizontal tail (4) fixing structure as claimed in claim 3, characterized in that: The top end of the fixing member (6) is integrally formed with a rotating handle (61), and the bottom end of the fixing member (6) is fixedly connected with a threaded rod (62), and the threaded rod (62) is adapted to the threaded groove (72).
6. A horizontal tail (4) fixing structure as claimed in claim 5, characterized in that: A plurality of fixing bolts (34) are fixedly mounted on the top surface of the docking block (3), and the carbon plate (2) and the docking block (3) are fixedly mounted on the top surface of the fuselage boss (1) via the plurality of fixing bolts (34).
7. A horizontal tail (4) fixing structure as claimed in claim 6, characterized in that: The length of the limiting groove (8) is longer than the length of the docking block (3), and the edges of the docking block (3) and the limiting groove (8) are both provided with rounded corners.