Mechanical manufacturing clamp for aircraft

Abstract

The utility model provides a mechanical manufacturing clamp for an aircraft, which relates to the technical field of mechanical manufacturing clamps and comprises a bottom plate, a clamping mechanism is arranged on the top surface of the bottom plate, guide components are arranged on the front side and the rear side of the clamping mechanism, and two angle adjusting structures are arranged on the clamping mechanism. And fixing mechanisms are arranged on the two angle adjusting structures. According to the mechanical manufacturing clamp for the aircraft, two lead screw sliding blocks, two supporting plates, two mounting plates and two U-shaped plates can be close to each other through rotation of a bidirectional lead screw, then aircraft parts are clamped, worm wheels, rotating rods and the U-shaped plates can be driven to rotate through rotation of a worm, and the aircraft parts can be clamped. According to the clamping device, the U-shaped plate is arranged, so that the aircraft parts fixed to the U-shaped plate rotate together, then the effect of adjusting the clamping angle of the aircraft parts in the clamping process of the aircraft parts is achieved, workers can machine the aircraft parts conveniently, and the device is high in flexibility and practicability.

Description

Technical Field

[0001] The utility model relates to a mechanical manufacturing fixture, in particular to a mechanical manufacturing fixture used for aircraft, and belongs to the technical field of mechanical manufacturing fixtures. Background Art

[0002] There are many parts on an aircraft, so fixtures are needed to fix the parts so that they occupy the correct position for construction or inspection. In order for the surface of the parts to meet the technical requirements of size, geometry and relative position accuracy with other surfaces specified in the drawings, the workpiece must be positioned and clamped before processing, and the angle of the parts must be adjusted according to the processing requirements.

[0003] A mechanical manufacturing fixture for aircraft disclosed in Chinese patent application publication specification CN212020523U effectively reduces dust and processing waste from entering the chute by opening chute at the top of both sides of the mounting seat, and effectively ensures the smooth movement of the limit block.

[0004] In actual applications, it is found that in the process of processing aircraft parts, the fixed angle of the aircraft parts needs to be adjusted according to technical requirements to meet processing needs. Judging from the technical solutions and functions of the above-mentioned mechanical manufacturing fixtures for aircraft, its flexibility in clamping aircraft parts needs to be improved. Utility Model Content

[0005] 1. Technical issues to be solved

[0006] The purpose of the utility model is to provide a mechanical manufacturing fixture for aircraft in order to solve the above-mentioned problem, so as to solve the problem in the prior art that it is inconvenient to adjust the clamping angle of aircraft parts during the clamping process.

[0007] (II) Technical solution

[0008] The utility model is implemented through the following technical scheme: a mechanical manufacturing fixture for aircraft, including a base plate, a clamping mechanism is provided on the top surface of the base plate, guide components are provided on the front and rear sides of the clamping mechanism, two angle adjustment structures are provided on the clamping mechanism, and fixing mechanisms are provided on the two angle adjustment structures.

[0009] The clamping mechanism includes a bidirectional screw connected to the top surface of the base plate through a bearing, and the surface of the bidirectional screw is threadedly connected to two screw sliders. The top surfaces of the two screw sliders are fixedly connected to support plates, and the upper ends of the two support plates are fixedly connected to mounting plates.

[0010] The angle adjustment structure includes a worm rotatably connected to the side of the mounting plate through a bearing, and a rotating rod is connected to the mounting plate through a bearing. The rotating rod passes through the mounting plate and extends to both sides of the mounting plate. A worm wheel meshing with the worm is fixedly installed on the surface of the rotating rod near one end of the worm.

[0011] Preferably, mounting holes are provided at the four corners of the bottom plate, and the inner contour of the mounting holes is circular, so that the device can be easily fixed through the mounting holes to improve the stability of the device.

[0012] Preferably, the top surfaces of the two screw sliders are fixedly connected with reinforcement blocks, and the two reinforcement blocks are fixedly connected to the two support plates on one side close to the two support plates respectively. A cross rotating rod is fixedly installed on the right end of the bidirectional screw. The provision of the reinforcement block can improve the strength of the connection between the support plate and the screw slider.

[0013] Preferably, the lead angle of the worm is smaller than the equivalent friction angle between the worm wheel meshing with the worm. In this state, the rotating rod can only be driven by the worm, and the worm wheel cannot drive the worm, thereby achieving self-locking.

[0014] Preferably, the guide assembly includes a guide rod fixedly connected to the base plate, and the sides of the two screw sliders are fixedly connected with guide blocks, and the reserved holes of the two guide blocks are slidably connected to the surface of the guide rod. The stability of the movement of the screw slider is further improved through the matching setting between the guide rod and the guide block.

[0015] Preferably, the fixing mechanism includes a U-shaped plate fixedly connected to the end of the rotating rod away from the worm gear, the top surface of the U-shaped plate is fixedly inlaid with a threaded sleeve, the threaded sleeve is threadedly connected to a threaded rod, the threaded rod passes through the lower end of the U-shaped plate and is rotatably connected to a pressure plate, and the top surface of the pressure plate is fixedly connected to two sliding rods that pass through the U-shaped plate and are in sliding contact with the U-shaped plate. The coordination arrangement among the U-shaped plate, the threaded sleeve, the threaded rod, the pressure plate and the sliding rods can improve the stability of the rotation of aircraft parts in a clamped state.

[0016] Preferably, a knob is fixedly mounted at one end of all the worms and all the threaded rods, and the knob provides a reasonable force point for rotating the worm and the threaded rod, which is convenient to use.

[0017] The utility model provides a mechanical manufacturing fixture for aircraft, which has the following beneficial effects:

[0018] 1. The mechanical manufacturing fixture for aircraft can make two screw sliders, two support plates, two mounting plates and two U-shaped plates approach each other through the rotation of the bidirectional screw, thereby achieving the clamping of aircraft parts. The rotation of the worm can drive the worm wheel, the rotating rod and the U-shaped plate to rotate, so that the aircraft parts fixed on the U-shaped plate rotate together, thereby achieving the effect of adjusting the clamping angle during the clamping of the aircraft parts, which is convenient for the staff to process them. The device is flexible and practical.

[0019] 2. The mechanical manufacturing fixture for aircraft can improve the stability of the rotation of aircraft parts in a clamped state through the coordination of the U-shaped plate, threaded sleeve, threaded rod, pressure plate and sliding rod. The knob provides a reasonable force point for rotating the worm and threaded rod, which is convenient to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;

[0021] Figure 2 This is a schematic diagram of the structure of the clamping mechanism of the utility model;

[0022] Figure 3 It is an enlarged schematic diagram of the structure at B of the utility model;

[0023] Figure 4 It is an enlarged schematic diagram of the structure at point A of the present utility model.

[0024] Description of Reference Numerals

[0025] 1. Base plate; 101. Mounting hole;

[0026] 2. Clamping mechanism; 201. Bidirectional screw; 202. Screw slider; 203. Support plate; 204. Mounting plate; 205. Reinforcement block; 206. Cross rotating rod;

[0027] 3. Guide assembly; 301. Guide rod; 302. Guide block;

[0028] 4. Angle adjustment structure; 401. Worm; 402. Rotating rod; 403. Worm wheel;

[0029] 5. Fixing mechanism; 501. U-shaped plate; 502. Threaded sleeve; 503. Threaded rod; 504. Pressing plate; 505. Sliding rod;

[0030] 6. Knob. DETAILED DESCRIPTION

[0031] An embodiment of the utility model provides a mechanical manufacturing fixture for an aircraft.

[0032] Please refer to Figure 1 A mechanical manufacturing fixture for aircraft includes a base plate 1, and four corners of the base plate 1 are provided with mounting holes 101. The inner contour of the mounting holes 101 is circular. The device can be placed on a workbench through the base plate 1, and the base plate 1 can be fixed through the mounting holes 101 to further improve the stability of the device.

[0033] Please refer to Figure 2 A clamping mechanism 2 is provided on the top surface of the base plate 1, and the clamping mechanism 2 includes a bidirectional screw 201 connected to the top surface of the base plate 1 through a bearing. Two screw sliders 202 are threadedly connected to the surface of the bidirectional screw 201. The top surfaces of the two screw sliders 202 are fixedly connected to support plates 203, and the upper ends of the two support plates 203 are fixedly connected to mounting plates 204.

[0034] The rotation of the bidirectional screw 201 can drive the two screw sliders 202 to move toward each other, and then drive the two support plates 203 to move toward each other. The two support plates 203 moving toward each other will drive the two mounting plates 204 to move toward each other.

[0035] Please refer to Figure 2 The top surfaces of the two screw sliders 202 are fixedly connected with reinforcement blocks 205, and the two reinforcement blocks 205 are respectively fixedly connected to the two support plates 203 on one side thereof close to the two support plates 203. The reinforcement blocks 205 can improve the strength of the connection between the support plates 203 and the screw sliders 202. A cross rotating rod 206 is fixedly installed on the right end of the bidirectional screw rod 201, and the cross rotating rod 206 provides a reasonable force point for rotating the bidirectional screw rod 201, which is more convenient to use.

[0036] Please refer to Figure 3 Two angle adjustment structures 4 are provided on the clamping mechanism 2. The angle adjustment structure 4 includes a worm 401 rotatably connected to the side of the mounting plate 204 through a bearing. A rotating rod 402 is connected to the mounting plate 204 through a bearing. The rotating rod 402 penetrates the mounting plate 204 and extends to both sides of the mounting plate 204. A worm wheel 403 meshing with the worm 401 is fixedly installed on the surface of the rotating rod 402 close to one end of the worm 401.

[0037] The lead angle of the worm 401 is smaller than the equivalent friction angle between the worm wheel 403 meshing with the worm 401. In this state, only the worm 401 can drive the rotating rod 402, and the worm wheel 403 cannot drive the worm 401 to rotate, thereby achieving self-locking and improving the stability of clamping aircraft parts. The rotation of the worm 401 can drive the worm wheel 403 to rotate, and the worm wheel 403 will drive the rotating rod 402 and the U-shaped plate 501 fixed at the other end of the rotating rod 402 to rotate, so as to achieve angle adjustment of aircraft parts.

[0038] Please refer to Figure 1 , guide assemblies 3 are provided on the front and rear sides of the clamping mechanism 2, and the guide assemblies 3 include a guide rod 301 fixedly connected to the base plate 1, and the sides of the two screw sliders 202 are fixedly connected with guide blocks 302, and the reserved holes of the two guide blocks 302 are slidably connected to the surface of the guide rod 301. When the two screw sliders 202 move toward each other, the guide blocks 302 will also be driven to slide on the surface of the guide rod 301 along the axial direction of the bidirectional screw rod 201. The cooperation of the guide rod 301 and the guide block 302 can limit the screw slider 202 so that it cannot rotate in the axial direction of the bidirectional screw rod 201.

[0039] Please refer to Figure 4 , a fixing mechanism 5 is provided on the two angle adjustment structures 4, and the fixing mechanism 5 includes a U-shaped plate 501 fixedly connected to the end of the rotating rod 402 away from the worm 401, and a threaded sleeve 502 is fixedly inlaid on the top surface of the U-shaped plate 501, and a threaded rod 503 is connected to the inner thread of the threaded sleeve 502. The threaded rod 503 passes through the lower end of the U-shaped plate 501 and is rotatably connected to a pressing plate 504. The top surface of the pressing plate 504 is fixedly connected with two sliding rods 505 that pass through the U-shaped plate 501 and are in sliding contact with the U-shaped plate 501.

[0040] The rotation of the threaded rod 503 can perform spiral lifting and lowering in the threaded sleeve 502, thereby driving the pressure plate 504 to lift and lower in the U-shaped plate 501. The sliding rod 505 can limit the pressure plate 504, further improving the stability of the lifting and lowering of the pressure plate 504. The pressure plate 504 can be used to fix aircraft parts to prevent them from falling during the process of adjusting the angle.

[0041] Please refer to Figure 3 and Figure 4 A knob 6 is fixedly mounted at one end of all worms 401 and all threaded rods 503, and the knob 6 provides a reasonable force point for rotating the worm 401 and the threaded rod 503, which is convenient to use and has strong practicality.

[0042] When the utility model is in use, firstly, the bidirectional screw rod 201 is rotated by the cross rotating rod 206, and the rotation of the bidirectional screw rod 201 can drive the two screw sliders 202 to move toward each other, and then drive the two support plates 203 to move toward each other, and the two support plates 203 moving toward each other will drive the two mounting plates 204 to move toward each other, so that the two rotating rods 402 respectively drive the two U-shaped plates 501 to move closer to each other, until the aircraft parts are fixed in the horizontal direction, and then the threaded rod 503 is rotated by the knob 6, so that the threaded rod 503 drives the pressing plate 50 4 is lifted and lowered, and the aircraft parts can be processed after being fixed in the vertical direction. When the angle needs to be adjusted, the worm 401 is rotated by the knob 6, and the worm 401 will drive the worm wheel 403 and the rotating rod 402 to rotate. The rotation of the rotating rod 402 will drive the U-shaped plate 501 fixed at the other end thereof to rotate, thereby rotating the aircraft parts. The device can adjust the angle of the aircraft parts while clamping and fixing them, and has strong flexibility, which is convenient for the staff to process the parts.

[0043] The above shows and describes the basic principle and main features of the utility model and the advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments. The above embodiments and descriptions are only for explaining the principle of the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, which fall within the scope of the utility model to be protected. The scope of protection claimed by the utility model is defined by the attached claims and their equivalents.

Claims

1. A mechanical manufacturing fixture for an aircraft, comprising a base plate (1), characterized in that: The top surface of the bottom plate (1) is provided with a clamping mechanism (2), the front and rear sides of the clamping mechanism (2) are provided with guide components (3), the clamping mechanism (2) is provided with two angle adjustment structures (4), and the two angle adjustment structures (4) are provided with fixing mechanisms (5); The clamping mechanism (2) comprises a bidirectional screw (201) connected to the top surface of the base plate (1) via a bearing, two screw sliders (202) are threadedly connected to the surface of the bidirectional screw (201), the top surfaces of the two screw sliders (202) are fixedly connected to a support plate (203), and the upper ends of the two support plates (203) are fixedly connected to a mounting plate (204); The angle adjustment structure (4) comprises a worm (401) rotatably connected to a side of a mounting plate (204) via a bearing, a rotating rod (402) is connected to the mounting plate (204) via a bearing, the rotating rod (402) passes through the mounting plate (204) and extends to both sides of the mounting plate (204), and a worm wheel (403) meshing with the worm (401) is fixedly mounted on a surface of the rotating rod (402) close to one end of the worm (401).

2. A mechanical manufacturing fixture for aircraft according to claim 1, characterized in that: The four corners of the base plate (1) are each provided with a mounting hole (101), and the inner contour of the mounting hole (101) is circular.

3. The mechanical manufacturing fixture for aircraft according to claim 1, characterized in that: The top surfaces of the two screw sliders (202) are fixedly connected with reinforcement blocks (205), and the two reinforcement blocks (205) are respectively fixedly connected with the two support plates (203) on one side thereof close to the two support plates (203), and a cross rotating rod (206) is fixedly installed on the right end of the bidirectional screw (201).

4. The mechanical manufacturing fixture for aircraft according to claim 1, characterized in that: The lead angle of the worm (401) is smaller than the equivalent friction angle between the worm wheel (403) meshing with the worm (401).

5. The mechanical manufacturing fixture for aircraft according to claim 1, characterized in that: The guide assembly (3) comprises a guide rod (301) fixedly connected to the base plate (1), the sides of the two screw sliders (202) are fixedly connected with guide blocks (302), and the reserved holes of the two guide blocks (302) are slidably connected to the surface of the guide rod (301).

6. The mechanical manufacturing fixture for aircraft according to claim 1, characterized in that: The fixing mechanism (5) comprises a U-shaped plate (501) fixedly connected to one end of the rotating rod (402) away from the worm gear (401); a threaded sleeve (502) is fixedly embedded on the top surface of the U-shaped plate (501); a threaded rod (503) is internally threadedly connected to the threaded sleeve (502); the threaded rod (503) passes through the lower end of the U-shaped plate (501) and is rotatably connected to a pressing plate (504); and two sliding rods (505) that pass through the U-shaped plate (501) and are in sliding contact with the U-shaped plate (501) are fixedly connected to the top surface of the pressing plate (504).

7. The mechanical manufacturing fixture for aircraft according to claim 6, characterized in that: A knob (6) is fixedly mounted on one end of all the worms (401) and all the threaded rods (503).

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