Fixing and clamping device for aircraft part machining
By introducing adjustment processing mechanisms and clamping mechanisms into the aircraft parts processing device, multi-directional and multi-angle processing of parts is achieved, and problems of cumbersome operation and low efficiency in the prior art are solved, and processing efficiency and stability are improved.
Patent Information
- Application Number
- CN202420163240.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-01-23
- Publication Date
- 2024-12-10
- Estimated Expiration
- 2034-01-23
AI Technical Summary
The existing aircraft parts processing and clamping devices are cumbersome to operate, resulting in low processing efficiency, and require frequent unclipping and re-clipping, which affects processing stability and efficiency.
A fixed clamping device including an adjustment processing mechanism and a clamping mechanism is designed to realize the rotation and angle adjustment of aircraft components through the adjustment component. The clamping mechanism adopts a bidirectional threaded rod and a limit rod for stable clamping, adapting to different sizes. and location processing requirements.
It improves the efficiency and stability of aircraft parts processing, allows for multi-directional and multi-angle processing of parts without changing the clamping state, and enhances the practicality and machining accuracy of the device.
Smart Images
Figure CN222134915U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft component processing, fixing and clamping, and in particular to a fixing and clamping device used for aircraft component processing. Background Art
[0002] An aircraft is a flying object manufactured by humans that can take off the ground, fly in space, and be controlled by humans to fly within or outside the atmosphere. During the manufacturing process of an aircraft, aircraft parts need to be processed. In order to ensure processing stability, a fixed clamping device for processing aircraft parts is often used.
[0003] According to the description of a clamping and fixing device for machining mechanical parts disclosed in the patent website (authorization announcement number: CN214444801U), "the utility model discloses a clamping and fixing device for machining mechanical parts, including a clamping table, a fixed frame is fixedly arranged on one side of the top of the clamping table, a supporting frame is fixedly arranged on one side of the fixed frame, a hydraulic cylinder is fixedly arranged on the inner side of the supporting frame, one end of the hydraulic cylinder passes through the fixed frame and a clamping pressure plate is fixedly arranged, both ends of the clamping pressure plate are slidably connected with clamping sliders, the front sides of the two clamping sliders are rotatably connected with a limiting rotating rod, and the back sides of the two clamping sliders are rotatably connected with a force rotating rod. The utility model discloses a clamping and fixing device for machining mechanical parts. The fixing device is scientifically and reasonably designed, simple and compact in structure, simple and convenient to operate, can quickly clamp and fix mechanical parts, the clamping is stable and reliable, and it is not easy to loosen, can meet actual use needs, has high structural strength, can be repeatedly operated and used, and has a long service life."
[0004] In view of the above description, the applicant believes that there are the following problems:
[0005] During the use of the utility model, the clamping and fixing device is first placed stably, and then the mechanical parts to be processed are directly placed stably in the parts placement groove, and then the hydraulic cylinder is operated in the normal operation mode to make it work. The hydraulic cylinder will drive the clamping pressure plate to press down, thereby driving the two clamping slide blocks to slide, and rely on the force-applying rotating rod to apply force to the pushing cross plate, and complete the clamping of the parts through the J-shaped clamping rod to the workpiece. However, in actual application, the device clamps the aircraft parts through the J-shaped clamping rod and then processes them. After completing the processing of the upper end surface of the aircraft parts, it is necessary to first release the clamping state of the J-shaped clamping rod on the aircraft parts, then flip the parts, and then operate the hydraulic cylinder and other devices to clamp the aircraft parts, and then process them. There are problems of cumbersome operation and reduced processing efficiency. Therefore, we urgently need a fixed clamping device for aircraft parts processing to solve the above problems. Utility Model Content
[0006] The purpose of the utility model is to provide a fixing clamping device for processing aircraft parts to solve the problems raised in the above background technology.
[0007] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a fixed clamping device for processing aircraft parts, comprising a processing table, a supporting leg fixedly installed at the bottom of the processing table, an adjusting processing mechanism arranged inside and on the top of the processing table, a clamping mechanism arranged on the top of the adjusting processing mechanism, a movable lifting frame arranged on the back of the processing table, and a processing device arranged on the top of the movable lifting frame.
[0008] The adjustment processing mechanism includes a first adjustment component and a second adjustment component, and the first adjustment component is arranged at the bottom of the second adjustment component.
[0009] Preferably, the first adjustment component includes a fixed plate, the fixed plate is fixedly installed inside the processing table, a first mounting frame is fixedly installed on the top of the fixed plate, a first motor is fixedly installed on the outside of the first mounting frame, a first worm is fixedly installed on the output shaft of the first motor, a first mounting column is rotatably installed on the top of the fixed plate, a connecting sleeve is rotatably installed on the outside of the first mounting column, a first worm gear is fixedly installed on the outside of the connecting sleeve, a limiting frame is fixedly installed on the top of the fixed plate, and a first connecting frame is arranged on the top of the connecting sleeve, so as to realize the rotation of aircraft parts according to actual processing conditions so as to process different positions.
[0010] Preferably, the first worm is meshed with the first worm wheel, the connecting sleeve is rotatably mounted on the limiting frame, and the first connecting frame is fixedly mounted on the connecting sleeve, so as to achieve a stable rotation effect.
[0011] Preferably, the second adjusting assembly includes a second mounting frame, the second mounting frame is fixedly mounted on the top of the fixing plate, a second motor is fixedly mounted on the outside of the second mounting frame, a second worm is fixedly mounted on the output shaft of the second motor, a second worm gear is fixedly mounted on the outside of the first mounting column, a second mounting column is rotatably mounted inside the first connecting frame, a first bevel gear is fixedly mounted on the top of the first mounting column, a second bevel gear is fixedly mounted on the outside of the second mounting column, a second connecting frame is fixedly mounted on the outside of the second mounting column, and a connecting plate is fixedly mounted on the top of the second connecting frame, so as to facilitate changing the angle of aircraft parts according to actual processing conditions and further processing different areas of the parts.
[0012] Preferably, the second worm is meshed with the second worm gear, and the first bevel gear is meshed with the second bevel gear, so as to facilitate changing the angle of the aircraft component.
[0013] Preferably, the clamping mechanism includes a mounting frame, which is fixedly mounted on the top of the connecting plate, a motor seat 1 is fixedly mounted on the outside of the mounting frame, a third motor is fixedly mounted on the inside of the second adjusting assembly, a bidirectional threaded rod is fixedly mounted on the output shaft of the third motor, a limiting rod is fixedly mounted on the inside of the mounting frame, a movable plate is threadedly mounted on the outside of the bidirectional threaded rod, a positioning plate is fixedly mounted on the outside of the movable plate, and a placing plate is fixedly mounted on the inside of the mounting frame, so as to facilitate stable clamping of aircraft parts of different sizes and specifications and avoid the phenomenon of random movement of aircraft parts during processing.
[0014] Preferably, through holes are provided at corresponding positions of the movable plate, the placing plate and the limiting rod, the limiting rod and the placing plate pass through the through holes, and two groups of the movable plate and the positioning plate are provided, and the two groups of the movable plate and the positioning plate are symmetrically arranged on the outside of the two-way threaded rod, so as to facilitate the clamping of aircraft parts and improve processing stability.
[0015] Compared with the prior art, the utility model provides a fixing clamping device for aircraft parts processing, which has the following beneficial effects:
[0016] 1. The fixed clamping device for processing aircraft parts is provided with an adjustment processing mechanism. During use, the first adjustment component provided can realize the rotation of the clamped aircraft parts to process different positions. The second adjustment component provided can adjust the pitch angle of the aircraft parts to process different positions of the aircraft parts without changing the clamping state, thereby improving the processing efficiency and enhancing the practicality of the device.
[0017] 2. The fixed clamping device for processing aircraft parts is provided with a clamping mechanism. During use, the aircraft parts to be processed can be placed on the top of the placement plate, and the third motor is turned on to drive the bidirectional threaded rod to rotate. Under the limiting action of the limiting rod, the two sets of movable plates can be moved in the center, and the aircraft parts of different sizes can be clamped and positioned under the action of the positioning plate. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative labor:
[0019] Figure 1 This is a schematic diagram of the appearance of the utility model;
[0020] Figure 2This is a rear view structural diagram of the utility model;
[0021] Figure 3 This is a schematic diagram of the internal structure of the utility model;
[0022] Figure 4 This is a schematic diagram of the disassembled structure of the first adjustment component of the utility model;
[0023] Figure 5 This is a schematic diagram of the disassembled structure of the second adjustment component of the utility model;
[0024] Figure 6 This is a schematic diagram of the disassembled structure of the clamping mechanism of the utility model.
[0025] In the figure: 1, processing table; 2, supporting legs; 3, adjusting processing mechanism; 31, first adjusting component; 311, fixing plate; 312, first mounting frame; 313, first motor; 314, first worm; 315, first mounting column; 316, connecting sleeve; 317, first worm gear; 318, limiting frame; 319, first connecting frame; 32, second adjusting component; 321, second mounting frame; 322, second motor; 323, second worm; 324, second worm gear; 325, second mounting column; 326, first bevel gear; 327, second bevel gear; 328, second connecting frame; 329, connecting plate; 4, clamping mechanism; 41, mounting frame; 42, motor seat 1; 43, third motor; 44, bidirectional threaded rod; 45, limiting rod; 46, movable plate; 47, positioning plate; 48, placing plate; 5, movable lifting frame; 6, processing equipment. DETAILED DESCRIPTION
[0026] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0027] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0028] Embodiment 1:
[0029] See also Figure 1-5 The utility model provides a technical solution: a fixed clamping device for processing aircraft parts, including a processing table 1, a supporting leg 2 is fixedly installed at the bottom of the processing table 1, an adjusting processing mechanism 3 is arranged inside and on the top of the processing table 1, a clamping mechanism 4 is arranged on the top of the adjusting processing mechanism 3, a movable lifting frame 5 is arranged on the back of the processing table 1, and a processing device 6 is arranged on the top of the movable lifting frame 5.
[0030] The adjustment mechanism 3 includes a first adjustment component 31 and a second adjustment component 32 . The first adjustment component 31 is arranged at the bottom of the second adjustment component 32 .
[0031] Furthermore, the first adjustment component 31 includes a fixed plate 311, which is fixedly installed inside the processing table 1, a first mounting frame 312 is fixedly installed on the top of the fixed plate 311, a first motor 313 is fixedly installed on the outside of the first mounting frame 312, a first worm 314 is fixedly installed on the output shaft of the first motor 313, a first mounting column 315 is rotatably installed on the top of the fixed plate 311, a connecting sleeve 316 is rotatably installed on the outside of the first mounting column 315, a first worm gear 317 is fixedly installed on the outside of the connecting sleeve 316, a limiting frame 318 is fixedly installed on the top of the fixed plate 311, and a first connecting frame 319 is arranged on the top of the connecting sleeve 316, so as to realize the rotation of aircraft parts according to actual processing conditions so as to process different positions.
[0032] Furthermore, the first worm 314 is meshed with the first worm wheel 317, the connecting sleeve 316 and the limiting frame 318 are rotatably installed, and the first connecting frame 319 and the connecting sleeve 316 are fixedly installed, so as to achieve a stable rotation effect.
[0033] Furthermore, the second adjustment component 32 includes a second mounting frame 321, which is fixedly mounted on the top of the fixing plate 311, a second motor 322 is fixedly mounted on the outside of the second mounting frame 321, a second worm 323 is fixedly mounted on the output shaft of the second motor 322, a second worm gear 324 is fixedly mounted on the outside of the first mounting column 315, a second mounting column 325 is rotatably mounted inside the first connecting frame 319, a first bevel gear 326 is fixedly mounted on the top of the first mounting column 315, a second bevel gear 327 is fixedly mounted on the outside of the second mounting column 325, a second connecting frame 328 is fixedly mounted on the outside of the second mounting column 325, and a connecting plate 329 is fixedly mounted on the top of the second connecting frame 328, so as to facilitate the change of the angle of the aircraft parts according to the actual processing conditions and further process different areas of the parts.
[0034] Furthermore, the second worm 323 is meshed with the second worm wheel 324, and the first bevel gear 326 is meshed with the second bevel gear 327, so as to facilitate changing the angle of the aircraft parts.
[0035] Embodiment 2:
[0036] See also Figure 6 In combination with the first embodiment, it is further obtained that the clamping mechanism 4 includes a mounting frame 41, the mounting frame 41 is fixedly mounted on the top of the connecting plate 329, a motor seat 42 is fixedly mounted on the outside of the mounting frame 41, a third motor 43 is fixedly mounted on the inside of the second adjusting component 32, a bidirectional threaded rod 44 is fixedly mounted on the output shaft of the third motor 43, a limiting rod 45 is fixedly mounted on the inside of the mounting frame 41, a movable plate 46 is threadedly mounted on the outside of the bidirectional threaded rod 44, a positioning plate 47 is fixedly mounted on the outside of the movable plate 46, and a placing plate 48 is fixedly mounted on the inside of the mounting frame 41, so as to facilitate the stable clamping of aircraft parts of different sizes and specifications, and avoid the phenomenon of random movement of aircraft parts during processing.
[0037] Furthermore, through holes are opened at corresponding positions of the movable plate 46, the placement plate 48 and the limiting rod 45, the limiting rod 45 and the placement plate 48 pass through the through holes, and two groups of movable plates 46 and positioning plates 47 are provided. The two groups of movable plates 46 and positioning plates 47 are symmetrically arranged on the outside of the two-way threaded rod 44, which is convenient for clamping aircraft parts and improving processing stability.
[0038] In actual operation, when the device is used, when it is necessary to process aircraft parts, the aircraft parts to be processed can be placed on the top of the placement plate 48, and then the third motor 43 is turned on to drive the bidirectional threaded rod 44 to rotate. Under the limiting action of the limiting rod 45, the two sets of movable plates 46 can be moved in a centering manner. Under the action of the positioning plate 47, the placed aircraft parts can be clamped and positioned. After clamping, the movable lifting frame 5 and the processing equipment 6 can be operated to process the aircraft parts. When it is necessary to process different positions of the aircraft parts, the first motor 313 can be turned on first to drive the first worm 314 to rotate, thereby rotating the first worm gear 317 meshing therewith, and then the connecting sleeve 313 is connected to the first motor 313. 16, the first connecting frame 319 can be rotated, so that the connecting plate 329 can rotate synchronously, and then the clamped aircraft parts can be rotated, so that different positions of the aircraft parts can be processed. When it is necessary to process the aircraft parts at different angles, the second motor 322 can be turned on to drive the second worm 323 to rotate, so that the second worm gear 324 can rotate, so that the first bevel gear 326 can be rotated, and then the second bevel gear 327 can be rotated, so that the second mounting column 325 can be rotated, driving the second connecting frame 328 to rotate synchronously, so that the connecting plate 329 can swing, thereby changing the angle of the aircraft parts, so as to process different areas of the aircraft parts, improve the processing effect, and enhance the practicality of the device.
[0039] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.
Claims
1. A fixing and clamping device for aircraft parts processing, comprising a processing table (1), characterized in that: The processing table (1) has a support leg (2) fixedly mounted at the bottom, an adjustment processing mechanism (3) is arranged inside and on the top of the processing table (1), a clamping mechanism (4) is arranged on the top of the adjustment processing mechanism (3), a movable lifting frame (5) is arranged on the back of the processing table (1), and a processing device (6) is arranged on the top of the movable lifting frame (5); The adjustment processing mechanism (3) comprises a first adjustment component (31) and a second adjustment component (32), wherein the first adjustment component (31) is arranged at the bottom of the second adjustment component (32).
2. A fixing and clamping device for aircraft parts processing according to claim 1, characterized in that: The first adjustment component (31) comprises a fixed plate (311), the fixed plate (311) is fixedly mounted inside the processing table (1), a first mounting frame (312) is fixedly mounted on the top of the fixed plate (311), a first motor (313) is fixedly mounted on the outside of the first mounting frame (312), a first worm (314) is fixedly mounted on the output shaft of the first motor (313), a first mounting column (315) is rotatably mounted on the top of the fixed plate (311), a connecting sleeve (316) is rotatably mounted on the outside of the first mounting column (315), a first worm gear (317) is fixedly mounted on the outside of the connecting sleeve (316), a limiting frame (318) is fixedly mounted on the top of the fixed plate (311), and a first connecting frame (319) is arranged on the top of the connecting sleeve (316).
3. A fixing and clamping device for aircraft parts processing according to claim 2, characterized in that: The first worm (314) is meshed with the first worm wheel (317), the connecting sleeve (316) is rotatably mounted on the limiting frame (318), and the first connecting frame (319) is fixedly mounted on the connecting sleeve (316).
4. The fixing and clamping device for aircraft parts processing according to claim 2, characterized in that: The second adjustment assembly (32) comprises a second mounting frame (321), the second mounting frame (321) is fixedly mounted on the top of the fixing plate (311), a second motor (322) is fixedly mounted on the outside of the second mounting frame (321), a second worm (323) is fixedly mounted on the output shaft of the second motor (322), a second worm gear (324) is fixedly mounted on the outside of the first mounting column (315), a second mounting column (325) is rotatably mounted inside the first connecting frame (319), a first bevel gear (326) is fixedly mounted on the top of the first mounting column (315), a second bevel gear (327) is fixedly mounted on the outside of the second mounting column (325), a second connecting frame (328) is fixedly mounted on the outside of the second mounting column (325), and a connecting plate (329) is fixedly mounted on the top of the second connecting frame (328).
5. The fixing and clamping device for aircraft parts processing according to claim 4, characterized in that: The second worm (323) meshes with the second worm wheel (324), and the first bevel gear (326) meshes with the second bevel gear (327).
6. The fixing and clamping device for aircraft parts processing according to claim 1, characterized in that: The clamping mechanism (4) comprises a mounting frame (41), wherein the mounting frame (41) is fixedly mounted on the top of the connecting plate (329), a motor seat (42) is fixedly mounted on the outside of the mounting frame (41), a third motor (43) is fixedly mounted on the inside of the second adjusting assembly (32), a bidirectional threaded rod (44) is fixedly mounted on the output shaft of the third motor (43), a limiting rod (45) is fixedly mounted on the inside of the mounting frame (41), a movable plate (46) is threadedly mounted on the outside of the bidirectional threaded rod (44), a positioning plate (47) is fixedly mounted on the outside of the movable plate (46), and a placement plate (48) is fixedly mounted on the inside of the mounting frame (41).
7. A fixing and clamping device for aircraft parts processing according to claim 6, characterized in that: Through holes are provided at corresponding positions of the movable plate (46), the placement plate (48) and the limiting rod (45), and the limiting rod (45) and the placement plate (48) pass through the through holes. The movable plate (46) and the positioning plate (47) are each provided with two groups, and the two groups of the movable plates (46) and the positioning plates (47) are symmetrically arranged outside the bidirectional threaded rod (44).