Aircraft fuselage horizontal positioning tool

Abstract

The utility model relates to the technical field of horizontal positioning tools, and discloses an aircraft fuselage horizontal positioning tool which comprises a tool base, the front side and the rear side of the tool base are fixedly connected with supporting bases, and the left side and the right side of the bottom of each supporting base are in threaded connection with height adjusters. A plurality of flat plates are fixedly connected to the outer portion of the tool base, a right portal frame is fixedly connected to the right sides of two of the flat plates, a left portal frame is fixedly connected to the left sides of the two of the flat plates, a front fixing pipe is fixedly connected to the front side of the right portal frame, and a rear fixing pipe is fixedly connected to the rear side of the top of the left portal frame. The tops of the sides, close to each other, of the right portal frame and the left portal frame are each fixedly connected with two fixing plates. The positioning tool provided by the utility model has the advantages of reliable performance, proper safety protection, simple structure, low cost, safety, firmness and accurate displacement, can be used under a loading working condition, and cannot cause damage to an experimental structure.

Description

Technical Field

[0001] The utility model relates to the technical field of horizontal positioning tools, in particular to a horizontal positioning tool for an aircraft fuselage. Background Technique

[0002] A horizontal positioning tool for an aircraft fuselage is a process tool used to ensure the correct alignment and installation of various components and parts during the aircraft assembly process. This kind of tool plays a crucial role in aircraft manufacturing. Through precise positioning and support, it ensures the accuracy and quality of aircraft assembly. When conducting a static test on the aircraft fuselage, a horizontal positioning tool is needed to ensure the stability and reliability of the aircraft fuselage during the test, thereby ensuring the accuracy of the test.

[0003] However, some existing horizontal positioning tools for aircraft fuselages are relatively complex in design, require higher technical requirements and more processing procedures during manufacturing, resulting in higher processing costs. Moreover, the horizontal positioning tool cannot achieve stable and reliable positioning of the fuselage, leading to errors in the static test. Therefore, in view of the above deficiencies, a horizontal positioning tool for an aircraft fuselage is proposed to solve the above problems. Summary of the Utility Model

[0004] In order to make up for the above deficiencies, the utility model provides a horizontal positioning tool for an aircraft fuselage, aiming to improve the problems that some horizontal positioning tools for aircraft fuselages in the prior art are complex in design, expensive in processing, and cannot effectively ensure the accuracy, reliability, and safety of the fuselage tool in the static test.

[0005] In order to achieve the above purpose, the utility model adopts the following technical scheme:

[0006] A horizontal positioning tool for an aircraft fuselage includes a tooling base. Both the front and rear sides of the tooling base are fixedly connected with support bases. Threaded height adjusters are connected to the left and right sides of the bottoms of the two support bases. A plurality of flat plates are fixedly connected to the outside of the tooling base. A right gantry is fixedly connected to the right sides of two of the flat plates, and a left gantry is fixedly connected to the left sides of two of the flat plates. A front fixed pipe is fixedly connected to the front side of the right gantry, and a rear fixed pipe is fixedly connected to the rear side of the top of the left gantry. Two fixing plates are fixedly connected to the adjacent sides of the top of the right gantry and the left gantry. Pins are fixedly connected to the adjacent sides of the plurality of fixing plates. Right L-shaped plates are fixedly connected to the rear sides of the right gantry, and left L-shaped plates are fixedly connected to the rear sides of the left gantry. Support components for support are arranged on the front and rear sides of the top of the tooling base, and a horizontal component for judging whether it is horizontal is arranged at the bottom of the tooling base;

[0007] As a further description of the above technical solution:

[0008] The support assembly includes a fixed limit frame, the bottom of the fixed limit frame is fixedly connected to the rear side of the top of the tooling base, the top of the fixed limit frame is fixedly connected to the rear support frame of the fuselage, the front side of the top of the tooling base is fixedly connected to the front support frame of the fuselage, and the front sides of the outer sides of the other two flat plates are fixedly connected to the front fixing frame of the fuselage;

[0009] As a further description of the above technical solution:

[0010] The horizontal assembly includes a fixed block, the top of the fixed block is fixedly connected to the bottom of the tooling base, an arc-shaped groove is formed inside the fixed block, a sliding shaft is slidably connected inside the arc-shaped groove, limiting disks are fixedly connected to both the left and right ends of the sliding shaft, suspension ropes are fixedly connected to the bottoms of the two limiting disks, plumb bobs are fixedly connected to the bottoms of the two suspension ropes, empty grooves are formed on both the left and right outer sides of the fixed block, a magnetic strip is fixedly connected inside the fixed block, and a body is arranged on the top of the tooling base;

[0011] As a further description of the above technical solution:

[0012] The rear side of the front fixing pipe is fixedly connected to the front side of the left gantry, and the bottom of the rear fixing pipe is fixedly connected to the rear side of the top of the right gantry;

[0013] As a further description of the above technical solution:

[0014] The rear side of the bottom of the body is in contact with the top of the rear support frame of the fuselage, and the front side of the bottom of the body is in contact with the top of the front support frame of the fuselage;

[0015] As a further description of the above technical solution:

[0016] The bottom of the front fixing pipe is in contact with the outside of the body, and the bottom of the rear fixing pipe is in contact with the outside of the body;

[0017] As a further description of the above technical solution:

[0018] The right side of the left L-shaped plate is in contact with the outside of the body, and the left side of the right L-shaped plate is in contact with the outside of the body;

[0019] As a further description of the above technical solution:

[0020] There is a magnetic force and mutual attraction between the sliding shaft and the magnetic strip, and the outside of the sliding shaft is slidably connected inside the fixed block.

[0021] The utility model has the following beneficial effects:

[0022] 1. In this utility model, the tooling base is welded by high-strength I-beams to form a solid square frame structure, ensuring the stability and durability of the overall structure. In addition, the gantry is designed by welding three channel steels together, further enhancing the structural rigidity and load-bearing capacity, making it not easy to deform when bearing the weight of the fuselage and various forces generated during the operation process. The application of bolts and threaded connections ensures the firmness of the connection between components, making it easier to adjust and maintain. At the same time, it can effectively prevent loosening problems caused by long-term use. This positioning tooling has reliable performance, is not easy to loosen, has in-place safety protection, a simple structure, low cost, is safe and firm, is convenient to load, has accurate displacement, meets the use of the loading working conditions, and will not cause damage and injury to the experimental structure.

[0023] 2. In this utility model, when the fuselage is completely horizontal, the sliding shaft remains in the middle of the arc-shaped groove under the magnetic force of the magnetic strip; once it tilts, the offset of the plumb bob will immediately cause the sliding shaft to break away from the magnetic attraction and slide, accurately and quickly indicating the horizontal state of the fuselage. This not only simplifies the complex process of traditional multiple measurements and adjustments but also reduces errors introduced by improper human operations, improving work efficiency and accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a three-dimensional view of an aircraft fuselage horizontal positioning tooling proposed by this utility model;

[0025] Figure 2 is a schematic structural diagram of the support base of an aircraft fuselage horizontal positioning tooling proposed by this utility model;

[0026] Figure 3 is a schematic structural diagram of the flat plate of an aircraft fuselage horizontal positioning tooling proposed by this utility model;

[0027] Figure 4 is a schematic structural diagram of the plumb bob of an aircraft fuselage horizontal positioning tooling proposed by this utility model;

[0028] Figure 5 is a schematic structural diagram of the magnetic strip of an aircraft fuselage horizontal positioning tooling proposed by this utility model.

[0029] LEGEND DESCRIPTION:

[0030] 1. Tooling base; 2. Support base; 3. Height adjuster; 4. Flat plate; 5. Right gantry; 6. Left gantry; 7. Front fixing pipe; 8. Rear fixing pipe; 9. Fixing plate; 10. Pin shaft; 11. Left L-shaped plate; 12. Right L-shaped plate; 13. Fixed limit frame; 14. Rear support frame of fuselage; 15. Front support frame of fuselage; 16. Front fixing frame of fuselage; 17. Fixed block; 18. Arc groove; 19. Sliding shaft; 20. Limit disc; 21. Suspension rope; 22. Plumb bob; 23. Empty groove; 24. Magnetic strip; 25. Machine body. Detailed implementation mode

[0031] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present invention.

[0032] Refer to Figures 1 to 2 , an embodiment provided by the present invention: An aircraft fuselage horizontal positioning tooling, including a tooling base 1, which is formed into a square structure by welding I-beams and has high strength and stability. Both the front and rear sides of the tooling base 1 are fixedly connected with support bases 2. Threaded height adjusters 3 are connected to the left and right sides of the bottoms of the two support bases 2. The height adjusters 3 are connected to the support bases 2 by threads and have the function of precisely adjusting the height. In actual operation, the height of the support base 2 can be changed by rotating the height adjuster 3, thereby adjusting the levelness of the tooling base 1. The design of the height adjuster 3 enables the operator to easily perform fine-tuning to ensure that the tooling base 1 reaches an accurate horizontal state and provides a stable foundation for the positioning of the fuselage. Multiple flat plates 4 are fixedly connected to the outside of the tooling base 1. The flat plates 4 are welded to the sides and front of the tooling base 1 to provide an installation plane for installing other components. A right gantry 5 is fixedly connected to the right sides of two of the flat plates 4, and a left gantry 6 is fixedly connected to the left sides of two of the flat plates 4. The right gantry 5 and the left gantry 6 are composed of three channel steels welded together and have high strength and rigidity. The selection of the channel steels ensures that the gantry will not deform when bearing the weight of the fuselage and the forces generated during the positioning process.

[0033] Refer to Figures 1 to 3, a front fixing pipe 7 is fixedly connected to the front side of the right gantry 5, the rear side of the front fixing pipe 7 is fixedly connected to the front side of the left gantry 6, the bottom of the front fixing pipe 7 is in contact with the outside of the machine body 25, a rear fixing pipe 8 is fixedly connected to the rear side of the top of the left gantry 6, the bottom of the rear fixing pipe 8 is fixedly connected to the rear side of the top of the right gantry 5, the bottom of the rear fixing pipe 8 is in contact with the outside of the machine body 25, two fixing plates 9 are fixedly connected to the top of the adjacent sides of the right gantry 5 and the left gantry 6, a pin shaft 10 is fixedly connected to the adjacent sides of the plurality of fixing plates 9, and the fixing plate 9 is fixed to the gantry by bolts, providing a stable support for the installation of the pin shaft 10. The function of the pin shaft 10 is to be inserted into the hole on the side of the fuselage to support and position the fuselage. The rear sides of the right gantry 5 are all fixedly connected with right L-shaped plates 12, the left side of the right L-shaped plates 12 is in contact with the outside of the machine body 25, the rear side of the left gantry 6 is fixedly connected with left L-shaped plates 11, and the right side of the left L-shaped plates 11 is in contact with the outside of the machine body 25. The left L-shaped plate and the right L-shaped plate just contact the side of the fuselage, which can ensure that the fuselage is centered relative to the tooling.

[0034] Refer to Figures 2 to 4 , support components for support are arranged on the front and rear sides of the top of the tooling base 1. The support components include a fixed limit frame 13, the bottom of the fixed limit frame 13 is fixedly connected to the rear side of the top of the tooling base 1, the top of the fixed limit frame 13 is fixedly connected with a rear fuselage support frame 14, the bottom rear side of the machine body 25 is in contact with the top of the rear fuselage support frame 14, a front fuselage support frame 15 is fixedly connected to the front side of the top of the tooling base 1, and the curved surfaces of the front fuselage support frame 15 and the rear fuselage support frame 14 are conformally attached to the fuselage curved surface, which can ensure the stability of the fuselage during the positioning process. The bottom front side of the machine body 25 is in contact with the top of the front fuselage support frame 15. In addition, a front fuselage fixing frame 16 is fixedly connected to the front side of the outside of the other two flat plates 4. The function of the front fuselage fixing frame 16 is to be bolted to the front end of the fuselage to lock the fuselage in a horizontal state. A level component for judging whether it is level is arranged at the bottom of the tooling base 1.

[0035] Refer to Figures 3 to 5, the horizontal component includes a fixed block 17. The top of the fixed block 17 is fixedly connected to the bottom of the tooling base 1. An arc-shaped groove 18 is formed inside the fixed block 17. A sliding shaft 19 is slidably connected inside the arc-shaped groove 18. The outer part of the sliding shaft 19 is slidably connected inside the fixed block 17. Limit disks 20 are fixedly connected to both the left and right ends of the sliding shaft 19. Suspension ropes 21 are fixedly connected to the bottoms of the two limit disks 20. Plumb bobs 22 are fixedly connected to the bottoms of the two suspension ropes 21. Empty grooves 23 are formed on both the left and right sides of the outer part of the fixed block 17. A magnetic strip 24 is fixedly connected inside the fixed block 17. There is a magnetic force and mutual attraction between the sliding shaft 19 and the magnetic strip 24. When the fuselage is in a horizontal state, the sliding shaft 19 is horizontally located in the middle of the arc-shaped groove 18 under the action of the magnetic force of the magnetic strip 24. When the fuselage is not level enough, the plumb bob 22 deflects, causing the sliding shaft 19 to slide out of the influence of the magnetic force of the magnetic strip 24, thereby determining that the fuselage is not in a horizontal state. The top of the tooling base 1 is provided with a fuselage 25.

[0036] Working principle: First, the tooling base 1 is welded by I-beams to form a square, and flat plates 4 are welded to the sides and the front to install other components. The support base 2 is connected to the tooling base 1 by bolts, and a height adjuster 3 is connected by threads below, so that the tooling base 1 can be adjusted to be horizontal as needed. The front fixed frame 16 of the fuselage is fixed on the front flat plate 4 of the tooling base 1 by bolts. The front support frame 15 of the fuselage is placed on the upper surface of the front part of the tooling base 1. A fixed limit frame 13 is fixed on the upper surface of the rear part of the tooling base 1 by bolts, and the rear support frame 14 of the fuselage is placed inside the fixed limit frame 13. The curved surfaces of the rear support frame 14 and the front support frame 15 of the fuselage conform to the curved surface of the fuselage, so as to ensure the stability of the fuselage during the positioning process. The left gantry 6 and the right gantry 5 are welded by three channel steels and fixed on the flat plate 4 by bolts. A front fixed pipe 7 and a rear fixed pipe 8 are fixed between the left gantry 6 and the right gantry 5 by bolts. A fixing plate 9 is fixed on the gantry by bolts. A pin shaft 10 is fixed on the fixing plate 9 by bolts. The left L-shaped plate 11 and the right L-shaped plate 12 are fixed on the gantry by bolts and just touch the side of the fuselage, so as to ensure that the fuselage is centered relative to the tooling. The pin shaft 10 can be inserted into the side hole of the fuselage through the through hole in the middle of the fixing plate 9 to support and position the fuselage. The front end of the fuselage is connected to the front fixed frame 16 of the fuselage by bolts. At this time, the fuselage is locked to a horizontal state. When the fuselage is not level enough, the plumb bob 22 will deflect at this time, and then the sliding shaft 19 will slide out of the influence of the magnetic force of the magnetic strip 24. At this time, it can be judged that the fuselage is not in a horizontal state. Only when it is in a horizontal state, the sliding shaft 19 can be horizontally in the middle of the arc-shaped groove 18 under the action of the magnetic force of the magnetic strip 24.

[0037] Finally, it should be noted that the above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A horizontal positioning tool for an aircraft fuselage, comprising a tool base (1), characterized in that: The front and rear sides of the tooling base (1) are fixedly connected to a support base (2); the left and right sides of the bottoms of the two support bases (2) are threadedly connected to height adjusters (3); the outside of the tooling base (1) is fixedly connected to a plurality of flat plates (4); the right sides of two of the flat plates (4) are fixedly connected to a right gantry (5); the left sides of two of the flat plates (4) are fixedly connected to a left gantry (6); the front side of the right gantry (5) is fixedly connected to a front fixing tube (7); the top rear side of the left gantry (6) is fixedly connected to a rear fixing tube (8); A fixing pipe (8), two fixing plates (9) are fixedly connected to the top of the adjacent sides of the right gantry (5) and the left gantry (6), a pin shaft (10) is fixedly connected to the adjacent sides of the plurality of fixing plates (9), a right L-plate (12) is fixedly connected to the rear side of the right gantry (5), a left L-plate (11) is fixedly connected to the rear side of the left gantry (6), support components for support are arranged on both the front and rear sides of the top of the tooling base (1), and a leveling component for judging whether it is horizontal is arranged at the bottom of the tooling base (1).

2. The aircraft fuselage horizontal positioning tool according to claim 1, characterized in that: The support assembly comprises a fixed limit frame (13), the bottom of the fixed limit frame (13) is fixedly connected to the top rear side of the tooling base (1), the top of the fixed limit frame (13) is fixedly connected to the fuselage tail support frame (14), the top front side of the tooling base (1) is fixedly connected to the fuselage front support frame (15), and the outer front sides of the other two flat plates (4) are fixedly connected to the fuselage front fixing frame (16).

3. The aircraft fuselage horizontal positioning tool according to claim 2, characterized in that: The horizontal component comprises a fixed block (17), the top of the fixed block (17) is fixedly connected to the bottom of the tooling base (1), an arc-shaped groove (18) is provided inside the fixed block (17), a sliding shaft (19) is slidably connected inside the arc-shaped groove (18), the left and right ends of the sliding shaft (19) are fixedly connected to limit plates (20), the bottoms of the two limit plates (20) are fixedly connected to hanging ropes (21), the bottoms of the two hanging ropes (21) are fixedly connected to lead sinkers (22), the left and right sides of the outside of the fixed block (17) are provided with empty grooves (23), the inside of the fixed block (17) is fixedly connected to a magnetic strip (24), and an organic body (25) is provided on the top of the tooling base (1).

4. The aircraft fuselage horizontal positioning tool according to claim 1, characterized in that: The rear side of the front fixed tube (7) is fixedly connected to the front side of the left gantry (6), and the bottom of the rear fixed tube (8) is fixedly connected to the top rear side of the right gantry (5).

5. The aircraft fuselage horizontal positioning tool according to claim 3, characterized in that: The rear side of the bottom of the fuselage (25) contacts the top of the fuselage tail support frame (14), and the front side of the bottom of the fuselage (25) contacts the top of the fuselage front support frame (15).

6. The aircraft fuselage horizontal positioning tool according to claim 3, characterized in that: The bottom of the front fixed tube (7) is in contact with the outside of the machine body (25), and the bottom of the rear fixed tube (8) is in contact with the outside of the machine body (25).

7. The aircraft fuselage horizontal positioning tool according to claim 3, characterized in that: The right side of the left L-plate (11) contacts the outside of the machine body (25), and the left side of the right L-plate (12) contacts the outside of the machine body (25).

8. The aircraft fuselage horizontal positioning tool according to claim 3, characterized in that: There is a magnetic force between the sliding shaft (19) and the magnetic strip (24), and they attract each other, and the outside of the sliding shaft (19) is slidably connected to the inside of the fixed block (17).

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