Positioning tool for manufacturing aircraft metal parts

Abstract

The utility model discloses a positioning tool for manufacturing aircraft metal parts, and relates to the technical field of aircraft manufacturing, the positioning tool comprises a bottom plate, two sides of the top end of the bottom plate are fixedly connected with two sliding frames, the inner top end faces of the two sliding frames are fixedly connected with electric telescopic rods, and the inner top end faces of the two sliding frames are fixedly connected with the electric telescopic rods. And spring pushing clamps are fixedly connected to the bottom ends of the two electric telescopic rods correspondingly, bottom end fixing bases are fixedly connected to the positions, right opposite to the lower portions of the top ends of the sliding frames, of the two sides of the top end of the bottom plate, and spring pushing clamps are slidably connected to the inner walls of the two sliding frames correspondingly. The positioning tool for manufacturing the metal parts of the airplane has the advantages of being capable of achieving accurate positioning, effectively reducing the rejection rate of the parts caused by positioning deviation and improving the manufacturing quality of the airplane, and has the functions of effectively resisting interference of external force such as vibration and cutting force and ensuring that the parts are always kept stable in the machining process.

Description

Technical Field

[0001] This utility model relates to the field of aircraft manufacturing technology, specifically to a positioning tooling for manufacturing aircraft metal parts. Background Technology

[0002] In the aircraft manufacturing industry, the manufacturing precision of metal components directly affects the overall performance and flight safety of an aircraft. Traditional positioning fixtures for aircraft metal components have many problems:

[0003] Most existing positioning fixtures for aircraft metal parts employ simple mechanical clamps or manual adjustment devices, making it difficult to achieve precise positioning of complex-shaped metal parts. In the drilling, milling, and welding processes of aircraft parts, even minute positioning deviations can cause parts dimensions to fail to meet design requirements, affecting subsequent assembly accuracy and even requiring rework, increasing production costs and manufacturing cycles. Furthermore, they lack flexibility: traditional fixtures have fixed structures and cannot adapt to the positioning needs of aircraft metal parts of different specifications and shapes. When producing parts for different aircraft models, it is often necessary to change the entire set of fixtures, which not only consumes a lot of time and manpower but also increases fixture manufacturing costs, reduces production efficiency, and suffers from poor clamping stability. During processing, parts are prone to displacement due to vibration, cutting forces, and other factors, leading to decreased machining accuracy and even safety accidents. Therefore, a positioning fixture for aircraft metal part manufacturing is proposed. Utility Model Content

[0004] This utility model provides a positioning fixture for manufacturing aircraft metal parts. It has the advantages of achieving precise positioning, effectively reducing the scrap rate of parts caused by positioning deviation, improving the quality of aircraft manufacturing, and effectively resisting external forces such as vibration and cutting forces, ensuring that the parts remain stable during the processing.

[0005] This utility model provides the following technical solution: a positioning fixture for manufacturing aircraft metal parts, including a base plate, two sliding frames are fixedly connected to both sides of the top of the base plate, an electric telescopic rod is fixedly connected to the inner top surface of the two sliding frames, and a spring push clamp is fixedly connected to the bottom end of the two electric telescopic rods.

[0006] Bottom fixing seats are fixedly connected to the top two sides of the base plate, directly below the top of the sliding frame. Spring push clamps are slidably connected to the inner walls of both sliding frames.

[0007] As a preferred embodiment of this utility model, a hydraulic cylinder is rotatably connected to one side of the outer wall of the base plate, a rotating joint is rotatably connected to the output end of the hydraulic cylinder, and a top connecting joint is fixedly connected to the top end of the rotating joint.

[0008] As a preferred embodiment of this utility model, the top end of the top connecting section is fixedly connected to a rotating shaft, the inner wall of the rotating shaft is rotatably connected to a connecting rod, and both ends of the connecting rod are rotatably connected to a pull arm.

[0009] As a preferred embodiment of this utility model, one end of each of the two pulling arms is fixedly connected to a linkage joint, and one side of the outer wall of each of the two linkage joints is rotatably connected to a rotating frame, and one end of each of the two rotating frames is fixedly connected to a fixing plate.

[0010] As a preferred technical solution of this utility model, the outer walls of the two linkages are rotatably connected to a positioning arm on one side of the rotating frame, and the ends of the two positioning arms away from the linkages are fixedly connected to a fixing seat.

[0011] As a preferred embodiment of this utility model, the bottom ends of the two fixed seats are fixedly connected with positioning rods, and both positioning rods have parts passing through them.

[0012] As a preferred technical solution of this utility model, the top of the base plate is fixedly connected to a limiting clamp between two bottom fixing seats. A positioning frame is fixedly connected to one side of the limiting clamp, and a placement frame is fixedly connected to the other side of the limiting clamp. The inner walls of the positioning frame, the placement frame, and the limiting clamp are all provided with parts.

[0013] Compared with the prior art, this utility model provides a positioning fixture for manufacturing aircraft metal parts, which has the following advantages:

[0014] 1. This positioning fixture for manufacturing aircraft metal parts utilizes high-precision control via an electric telescopic rod and hydraulic cylinder, combined with the precise fit between the positioning rod and the positioning holes on the parts, to improve positioning accuracy and meet the high-precision requirements of aircraft metal part manufacturing. Whether for complex curved surface parts or structural components with precision positioning holes, accurate positioning can be achieved, effectively reducing the scrap rate of parts due to positioning deviations and improving aircraft manufacturing quality.

[0015] 2. The positioning fixture for manufacturing aircraft metal parts utilizes a spring-loaded clamp with elastic gripping and anti-slip design, combined with auxiliary positioning from limit clamps, positioning frames, and placement frames, forming a comprehensive, multi-layered stable clamping system. During parts processing, it effectively resists external forces such as vibration and cutting forces, ensuring the parts remain stable throughout the process and preventing decreased machining accuracy and safety accidents caused by parts displacement, thus improving the reliability and safety of the fixture. Attached Figure Description

[0016] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0017] Figure 2 This is a multi-angle three-dimensional structural diagram of the present invention;

[0018] Figure 3 This is a schematic diagram of the positioning arm connection structure of this utility model;

[0019] Figure 4 This is a schematic diagram of the positioning frame connection structure of this utility model.

[0020] In the diagram: 1. Base plate; 2. Sliding frame; 3. Electric telescopic rod; 4. Spring push clamp; 5. Bottom fixed seat; 6. Hydraulic cylinder; 7. Rotating joint; 8. Top connecting joint; 9. Rotating shaft; 10. Connecting rod; 11. Pulling arm; 12. Linkage joint; 13. Rotating frame; 14. Fixed plate; 15. Positioning arm; 16. Positioning rod; 17. Fixed seat; 18. Part; 19. Limit clamp; 20. Positioning frame; 21. Placement frame. Detailed Implementation

[0021] 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.

[0022] Please see Figures 1-4 This utility model discloses a positioning fixture for manufacturing aircraft metal parts, including a base plate 1, two sliding frames 2 are fixedly connected to both sides of the top of the base plate 1, an electric telescopic rod 3 is fixedly connected to the inner top surface of the two sliding frames 2, and a spring push clamp 4 is fixedly connected to the bottom end of the two electric telescopic rods 3.

[0023] Bottom fixing seats 5 are fixedly connected to the top two sides of the base plate 1, directly below the top of the sliding frame 2. Spring push clamps 4 are slidably connected to the inner walls of both sliding frames 2.

[0024] Specifically, this positioning fixture uses a base plate 1 as its basic support platform. A vertical rapid clamping and positioning system is formed by sliding frames 2, electric telescopic rods 3, and spring-driven clamps 4. A linkage mechanism consisting of hydraulic cylinders 6, rotating joints 7, top connecting joints 8, and rotating shafts 9 enables precise horizontal positioning and adjustment of the positioning arm 15 and positioning rod 16. Simultaneously, limit clamps 19, positioning frames 20, and placement frames 21 work together to assist in the positioning and support of components. Two sliding frames 2, symmetrically arranged on either side of the top of the base plate 1, are made of high-strength aluminum alloy. Electric telescopic rods 3 are fixedly connected to their internal top surfaces, allowing for automatic extension and retraction and rapid adjustment of the clamping height to accommodate aircraft metal components of varying thicknesses. Spring-driven clamps 4, fixedly connected to the bottom ends of the two electric telescopic rods 3, contain high-strength compression springs, providing stable and adjustable clamping force. The clamping surface of the spring-driven clamp 4 is made of anti-slip rubber with a finely textured surface, increasing friction with the component surface to prevent slippage during clamping and avoiding damage to the component surface. In addition, the inner wall of the sliding frame 2 is also slidably connected with a spring-driven clamp 4, which can assist in clamping the parts in the horizontal direction and further enhance the clamping stability.

[0025] In this embodiment, a hydraulic cylinder 6 is rotatably connected to one side of the outer wall of the base plate 1, a rotating joint 7 is rotatably connected to the output end of the hydraulic cylinder 6, and a top connecting joint 8 is fixedly connected to the top end of the rotating joint 7.

[0026] Specifically, the output end of the hydraulic cylinder 6, rotatably connected to one side of the outer wall of the base plate 1, is rotatably connected to the rotating joint 7. The rotating joint 7 rotates freely, converting the linear thrust of the hydraulic cylinder 6 into multi-directional rotational power. The top connecting joint 8, fixedly connected to the top of the rotating joint 7, is rotatably connected to the connecting rod 10 via the rotating shaft 9. The pull arms 11, rotatably connected to both ends of the connecting rod 10, are fixedly connected to the linkage joint 12. When the hydraulic cylinder 6 works, it pushes the rotating joint 7 to rotate, transmitting power through the top connecting joint 8, rotating shaft 9, and connecting rod 10, driving the pull arms 11 and the linkage joint 12 to move. The rotating frame 13, rotatably connected to one side of the outer wall of the linkage joint 12, is fixed to the fixed plate 14, and the positioning arm 15, rotatably connected to the other side, has a positioning rod 16 fixed at its end that can pass through the positioning hole on the aircraft metal parts to achieve precise horizontal positioning. By adjusting the extension and rotation angle of the hydraulic cylinder 6, the position of the positioning rod 16 can be flexibly adjusted to adapt to the positioning requirements of parts with different shapes.

[0027] In this embodiment, a rotating shaft 9 is fixedly connected to the top of the top connecting section 8, and a connecting rod 10 is rotatably connected to the inner wall of the rotating shaft 9. Both ends of the connecting rod 10 are rotatably connected to a pulling arm 11.

[0028] Specifically, the power is transmitted through the top connecting section 8, the rotating shaft 9, and the connecting rod 10, which can drive the pulling arm 11 and the linkage section 12 to move.

[0029] In this embodiment, one end of each of the two pull arms 11 is fixedly connected to a linkage 12, and one side of the outer wall of each of the two linkages 12 is rotatably connected to a rotating frame 13, and one end of each of the two rotating frames 13 is fixedly connected to a fixing plate 14.

[0030] Specifically, by setting the fixing plate 14, the positioning arm 15 is more securely fixed.

[0031] In this embodiment, the outer walls of the two linkages 12 are rotatably connected to positioning arms 15 on one side of the rotating frame 13, and the ends of the two positioning arms 15 away from the linkages 12 are fixedly connected to fixing seats 17.

[0032] Specifically, by setting the fixed seat 17, the positioning rod 16 can be stably positioned.

[0033] In this embodiment, positioning rods 16 are fixedly connected to the bottom ends of the two fixed seats 17, and the two positioning rods 16 are both through the part 18.

[0034] Specifically, by setting a positioning rod 16 that can penetrate the positioning hole on the aircraft's metal parts, precise horizontal positioning can be achieved.

[0035] In this embodiment, the top of the base plate 1 is fixedly connected to a limiting clamp 19 between two bottom fixing seats 5. A positioning frame 20 is fixedly connected to one side of the limiting clamp 19, and a placement frame 21 is fixedly connected to the other side of the limiting clamp 19. Parts 18 are provided on the inner walls of the positioning frame 20, the placement frame 21 and the limiting clamp 19.

[0036] Specifically, the top of the base plate 1 is fixedly connected to the two bottom fixing seats 5, and is suitable for limiting the position of parts of different sizes. The positioning frame 20 on one side of the positioning frame 19 and the placement frame 21 on the other side are both equipped with buffer rubber pads on their inner walls, which can not only provide positioning support for the parts, but also prevent the surface of the parts from being scratched. The three work together to provide initial positioning in the early stage of part placement, and assist the main positioning structure during the processing to enhance the overall stability of the parts.

[0037] The working principle and usage process of this utility model: When using this positioning fixture, first place the aircraft metal parts on the placement rack 21, and use the limiting clamp 19 and the positioning rack 20 for initial positioning and support.

[0038] Subsequently, the electric telescopic rod 3 is activated, and its extension length is adjusted according to the thickness of the component, causing the spring-driven clamp 4 at the top to descend to the appropriate position. The compression spring inside the spring-driven clamp 4 automatically provides clamping force, clamping the component vertically. At the same time, the spring-driven clamp 4 on the inner wall of the sliding frame 2 can also be finely adjusted horizontally according to the shape of the component, ensuring that the component is stably fixed in the vertical direction.

[0039] For horizontal positioning, the extension, retraction, and rotation of hydraulic cylinder 6 are controlled. Hydraulic cylinder 6 outputs thrust, driving rotating joint 7 to rotate. Power is transmitted through top connecting joint 8, rotating shaft 9, connecting rod 10, and pulling arm 11, causing linkage joint 12 to move. Linkage joint 12 drives positioning arm 15 to rotate, accurately inserting positioning rod 16 into the positioning hole of the component, achieving precise horizontal positioning. During positioning, the extension and retraction of hydraulic cylinder 6 can be precisely adjusted according to the specific shape of the component and positioning requirements to ensure the accurate positioning of positioning rod 16. Throughout the processing, the spring-driven clamp 4 continuously provides stable clamping force, buffering vibrations and impacts generated during processing. Limit clamp 19, positioning frame 20, and placement frame 21 assist the main positioning structure, further enhancing the stability of the component and ensuring that the aircraft metal component maintains a high-precision positioning state throughout the processing until completion.

[0040] 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.

[0041] 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 positioning fixture for manufacturing aircraft metal parts, comprising a base plate (1), characterized in that: Two sliding frames (2) are fixedly connected to both sides of the top of the base plate (1). Electric telescopic rods (3) are fixedly connected to the inner top surfaces of the two sliding frames (2). Spring push clamps (4) are fixedly connected to the bottom ends of the two electric telescopic rods (3). The bottom plate (1) has bottom fixing seats (5) fixedly connected to the two sides of the top of the sliding frame (2) directly below the top of the sliding frame (2), and the inner walls of the two sliding frames (2) are slidably connected with spring push clamps (4).

2. A positioning fixture for manufacturing aircraft metal parts according to claim 1, characterized in that: A hydraulic cylinder (6) is rotatably connected to one side of the outer wall of the base plate (1). A rotating joint (7) is rotatably connected to the output end of the hydraulic cylinder (6). A top connecting joint (8) is fixedly connected to the top end of the rotating joint (7).

3. A positioning fixture for manufacturing aircraft metal parts according to claim 2, characterized in that: The top end of the top connecting section (8) is fixedly connected to a rotating shaft (9), and a connecting rod (10) is rotatably connected to the inner wall of the rotating shaft (9). Both ends of the connecting rod (10) are rotatably connected to a pulling arm (11).

4. A positioning fixture for manufacturing aircraft metal parts according to claim 3, characterized in that: One end of each of the two pull arms (11) is fixedly connected to a linkage (12), and one side of the outer wall of each of the two linkages (12) is rotatably connected to a rotating frame (13), and one end of each of the two rotating frames (13) is fixedly connected to a fixing plate (14).

5. A positioning fixture for manufacturing aircraft metal parts according to claim 4, characterized in that: The outer walls of the two linkages (12) are rotatably connected to a positioning arm (15) on one side of the rotating frame (13), and the two positioning arms (15) are fixedly connected to a fixed seat (17) at the end away from the linkage (12).

6. A positioning fixture for manufacturing aircraft metal parts according to claim 5, characterized in that: The bottom ends of the two fixed seats (17) are fixedly connected to positioning rods (16), and both positioning rods (16) have parts (18) passing through them.

7. A positioning fixture for manufacturing aircraft metal parts according to claim 1, characterized in that: The top of the base plate (1) is fixedly connected between two bottom fixing seats (5) with a limiting clamp (19). A positioning frame (20) is fixedly connected to one side of the limiting clamp (19), and a placement frame (21) is fixedly connected to the other side of the limiting clamp (19). Parts (18) are provided on the inner walls of the positioning frame (20), the placement frame (21) and the limiting clamp (19).

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