Numerical control machining clamp for clamping plate for aircraft fixture

Abstract

The utility model relates to the technical field of clamping plate machining clamps, and discloses a clamping plate numerical control machining clamp for an airplane jig, which comprises a base, and a clamping device is arranged above the base. According to the clamping plate numerical control machining clamp for the aircraft jig, by arranging the clamping plate, the splicing rod, the mounting blocks, the double-thread screw, a second worm, a second worm gear, a mounting plate, a limiting rod and a spring, the splicing rod is positioned through the limiting rod by means of the tension of the spring, splicing of the splicing rod and the different mounting blocks can be conveniently and rapidly changed, and according to the aircraft jig clamping plates of different sizes, the machining efficiency is improved. The positions of the clamping plates are rapidly adjusted, and a second worm is rotated, so that the clamping plates on the two sides clamp the aircraft fixture clamping plate; by arranging the support, the second motor, the mounting frame, the gear, the gear ring and the sliding rail, the second motor is started, the gear drives the gear ring to rotate, the mounting plate and the aircraft fixture clamping plate can be conveniently controlled to rotate, and the aircraft fixture clamping plate can be conveniently machined in cooperation with a numerical control machining device.

Description

Technical Field

[0001] This utility model relates to the field of clamping fixture technology, specifically a CNC clamping fixture for aircraft frame clamping. Background Technology

[0002] Pallets are generally flat tools used for packaging, transporting, or storing goods. They are placed at the bottom of the goods to protect them and facilitate handling and stacking. For example, in aircraft manufacturing, aircraft jigs are used to secure aircraft parts.

[0003] Chinese patent disclosure (CN217394739U) discloses a CNC machining fixture for aircraft frame clamps. It includes a base plate, a sliding rod whose bottom is fixedly connected to the top of a vertical rod, a bolt threaded to the middle of a horizontal rod, a slider rotatably connected to the lower outer wall of the bolt via a bearing, a through hole on one side of the slider slidingly engaging with the outer wall of the sliding rod, a pin fitting between the through hole on one side of the slider and a groove on one side of the sliding rod, a sloping plate rotatably connected to one side of the sliding sleeve via a pin, a block rotatably connected to the bottom of the sloping plate via a pin, and one side of the block fixedly connected to one side of a clamping plate. This utility model relates to the field of aircraft processing equipment technology. Through the cooperation between the sliding rod, bolt, and slider, the bolt rotation distance is significantly shortened, saving working time and solving the problem of prolonged fixing time due to the long fixing screw in existing devices, thus improving work efficiency.

[0004] However, it still has the following drawbacks: the movement of the clamping plate is accompanied by the rise and fall of the slider. However, when the slider is short, the displacement distance of the clamping plate is limited. When the slider is long, the slider moves too high when clamping large clamping plates, making operation difficult and requiring more space, thus reducing the practicality of the device. Therefore, we propose a CNC machining fixture for aircraft frame clamping plates to solve this problem. Utility Model Content

[0005] The purpose of this utility model is to provide a CNC machining fixture for aircraft frame clamps to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a CNC machining fixture for aircraft frame clamps, comprising a base, wherein a clamping device is provided above the base, and the clamping device includes a clamping part;

[0007] The clamping part includes a limiting rod, a mounting plate and a mounting block. The top surface of the mounting plate is provided with a sliding groove. The outer surface of the mounting block is slidably connected to the inner wall of the sliding groove. The top surface of the mounting block is provided with a mating groove. The outer surface of the limiting rod slides through the outer surface of the mounting block and extends into the interior of the mounting block.

[0008] An adjustment section is provided on the top of the base;

[0009] The adjustment part includes a rotating shaft, the top surface of the base has a mounting hole, the outer surface of the rotating shaft is rotatably connected to the inner wall of the base through a first bearing seat, and a bracket is fixedly sleeved on the outer surface of the rotating shaft.

[0010] A further improvement is that the clamping part also includes a clamping plate, a splicing rod, a double-threaded screw, a second worm gear, a second worm wheel, and a spring. The top surface of the splicing rod is fixedly connected to the bottom surface of the clamping plate, and the outer surface of the bottom end of the splicing rod extends into the interior of the mounting block and slides in connection with the inner wall of the mounting block. By setting the splicing rod and adjusting the splicing rod to splice with different mounting blocks, it is convenient to quickly adjust the position of the clamping plate according to the size of the aircraft frame clamping plate.

[0011] A further improvement is that the outer surface of the double-threaded screw is rotatably connected to the inner wall of the mounting plate through the second bearing seat, the outer surface of the mounting block is provided with a threaded hole, the outer surface of the limiting rod is provided with a through hole, and the mounting block is threadedly sleeved on the outer surface of the double-threaded screw. By setting the double-threaded screw, it is easy to drive the mounting block to move, and it is easy to make the clamping plate clamp and position the aircraft frame plate.

[0012] A further improvement is that one end of the spring is fixedly connected to the outer surface of the mounting block, and the other end of the spring is fixedly connected to the limiting rod. By setting the spring, it is easy to limit the limiting rod. By pulling the limiting rod, the splicing rod can be positioned, which facilitates quick adjustment of the position of the clamping plate.

[0013] A further improvement is that the second worm gear is fixedly sleeved on the outer surface of the double-threaded screw, and the outer surface of the bottom end of the second worm rotates through the top surface of the mounting plate and extends into the interior of the mounting plate via a bearing. By setting the second worm gear and the second worm, rotating the second worm can drive the double-threaded screw to rotate.

[0014] A further improvement is that the adjustment unit also includes a first motor, a first worm gear, a first worm wheel, a second motor, a mounting bracket, a gear, a gear ring, and a slide rail. The bottom surface of the first motor is fixedly connected to the top surface of the base. The first worm wheel is fixedly sleeved on the outer surface of the rotating shaft. The outer surface of the first worm gear is fixedly connected to the outer surface of the output shaft of the first motor. The top surface of the bracket is fixedly connected to the bottom surface of the slide rail. The bottom surface of the mounting plate has an annular groove. The outer surface of the slide rail extends into the annular groove and slides in connection with the inner wall of the mounting plate. By setting the first motor, the first worm gear, and the second worm wheel, the pitch angle of the aircraft frame plate can be adjusted after the first motor is started.

[0015] A further improvement is that the mounting bracket is fixedly sleeved on the outer surface of the second motor, and the outer surface of the mounting bracket is fixedly connected to the outer surface of the support. The gear is fixedly sleeved on the outer surface of the output shaft of the second motor, and the outer surface of the gear ring is fixedly connected to the bottom surface of the mounting plate. By setting the second motor, gear, and gear ring, the second motor is started to control the rotation of the aircraft frame clamping plate and adjust the processing position of the aircraft frame clamping plate.

[0016] Compared with the prior art, the beneficial effects of this utility model are as follows: This CNC machining fixture for aircraft frame clamps, by setting clamping plates, splicing rods, mounting blocks, double-threaded screws, second worm gears, second worm wheels, mounting plates, limit rods, and springs, utilizes the tension of the springs to position the splicing rods with the limit rods, facilitating quick changes in the splicing of the splicing rods with different mounting blocks. According to different sizes of aircraft frame clamps, the position of the clamping plates can be quickly adjusted, and the second worm gear can be rotated to clamp the aircraft frame clamps on both sides. By setting a bracket, a second motor, a mounting frame, gears, a gear ring, and a slide rail, starting the second motor causes the gears to drive the gear ring to rotate, facilitating the control of the rotation of the mounting plate and the aircraft frame clamp, and facilitating the processing of the aircraft frame clamps with a CNC machining device. By setting a first motor, a first worm gear, a first worm wheel, and a rotating shaft, starting the first motor drives the bracket and mounting plate to deflect, facilitating the adjustment of the pitch angle of the aircraft frame clamps. Attached Figure Description

[0017] Figure 1 This is a three-dimensional structural diagram of the clamping device of this utility model;

[0018] Figure 2 This is a front sectional view of the three-dimensional structure of the clamping device of this utility model;

[0019] Figure 3 for Figure 2 Enlarged view of the structure at point A in the middle;

[0020] Figure 4 This is a three-dimensional structural cross-sectional view of the clamping device of this utility model;

[0021] Figure 5 This is a partial cross-sectional view of the three-dimensional structure of the clamping device of this utility model.

[0022] In the diagram: 1. Base; 2. Clamping device; 21. Adjustment part; 22. Clamping part; 211. Bracket; 212. First motor; 213. First worm gear; 214. First worm wheel; 215. Rotating shaft; 216. Second motor; 217. Mounting bracket; 218. Gear; 219. Gear ring; 210. Slide rail; 221. Clamping plate; 222. Splicing rod; 223. Mounting block; 224. Double threaded screw; 225. Second worm gear; 226. Second worm wheel; 227. Mounting plate; 228. Limiting rod; 229. Spring. Detailed Implementation

[0023] 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.

[0024] Please see Figures 1-5 The present invention provides a technical solution: a CNC machining fixture for aircraft frame clamps, including a base 1, a clamping device 2 is provided above the base 1, and the clamping device 2 includes a clamping part 22;

[0025] The clamping part 22 includes a limiting rod 228, a mounting plate 227 and a mounting block 223. The top surface of the mounting plate 227 is provided with a sliding groove. The outer surface of the mounting block 223 is slidably connected to the inner wall of the sliding groove. The top surface of the mounting block 223 is provided with a mating groove. The outer surface of the limiting rod 228 slides through the outer surface of the mounting block 223 and extends into the interior of the mounting block 223. The clamping part 22 also includes a clamping plate 221, a splicing rod 222, a double threaded screw 224, a second worm gear 225, a second worm wheel 226 and a spring 229.

[0026] The outer surface of the double threaded screw 224 is rotatably connected to the inner wall of the mounting plate 227 through the second bearing seat. The outer surface of the mounting block 223 is provided with a threaded hole, and the outer surface of the limiting rod 228 is provided with a through hole. The mounting block 223 is threadedly sleeved on the outer surface of the double threaded screw 224.

[0027] The top surface of the splicing rod 222 is fixedly connected to the bottom surface of the clamping plate 221, and the outer surface of the bottom end of the splicing rod 222 extends into the interior of the mounting block 223 and slides in connection with the inner wall of the mounting block 223.

[0028] One end of the spring 229 is fixedly connected to the outer surface of the mounting block 223, and the other end of the spring 229 is fixedly connected to the limiting rod 228.

[0029] The second worm gear 226 is fixedly sleeved on the outer surface of the double threaded screw 224. The outer surface of the bottom end of the second worm 225 rotates through the top surface of the mounting plate 227 via a bearing and extends into the interior of the mounting plate 227. By setting up a clamping plate 221, splicing rod 222, mounting block 223, double threaded screw 224, second worm 225, second worm gear 226, mounting plate 227, limiting rod 228 and spring 229, the tension of the spring 229 is used to position the limiting rod 228 on the splicing rod 222, which facilitates quick changes in the splicing of the splicing rod 222 with different mounting blocks 223. According to different sizes of aircraft frame plates, the position of the clamping plate 221 can be quickly adjusted, and the second worm 225 can be rotated so that the clamping plates 221 on both sides clamp the aircraft frame plate.

[0030] An adjustment part 21 is provided on the top of the base 1;

[0031] The adjustment unit 21 includes a rotating shaft 215. The top surface of the base 1 has a mounting hole. The outer surface of the rotating shaft 215 is rotatably connected to the inner wall of the base 1 through a first bearing seat. A bracket 211 is fixedly sleeved on the outer surface of the rotating shaft 215. The adjustment unit 21 also includes a first motor 212, a first worm 213, a first worm wheel 214, a second motor 216, a mounting bracket 217, a gear 218, a gear ring 219, and a slide rail 210.

[0032] An annular groove is provided on the bottom surface of the mounting plate 227, and the outer surface of the slide rail 210 extends into the annular groove and slides in connection with the inner wall of the mounting plate 227.

[0033] Mounting bracket 217 is fixedly sleeved on the outer surface of the second motor 216, and the outer surface of mounting bracket 217 is fixedly connected to the outer surface of bracket 211.

[0034] The bottom surface of the first motor 212 is fixedly connected to the top surface of the base 1, the first worm gear 214 is fixedly sleeved on the outer surface of the rotating shaft 215, the outer surface of the first worm 213 is fixedly connected to the outer surface of the output shaft of the first motor 212, and the top surface of the bracket 211 is fixedly connected to the bottom surface of the slide rail 210. By setting the first motor 212, the first worm 213, the first worm gear 214 and the rotating shaft 215, the first motor 212 is started, driving the bracket 211 and the mounting plate 227 to deflect, which facilitates the adjustment of the pitch angle of the aircraft frame plate.

[0035] Gear 218 is fixedly sleeved on the outer surface of the output shaft of the second motor 216, and the outer surface of the gear ring 219 is fixedly connected to the bottom surface of the mounting plate 227. By setting up the bracket 211, the second motor 216, the mounting bracket 217, the gear 218, the gear ring 219 and the slide rail 210, the second motor 216 is started, which causes the gear 218 to drive the gear ring 219 to rotate. This facilitates the control of the rotation of the mounting plate 227 and the aircraft frame clamping plate, and facilitates the processing of the aircraft frame clamping plate with the CNC machining device.

[0036] In use, pull the limiting rod 228 so that it no longer limits the splicing rod 222, then lift the clamping plate 221 upwards. According to the size of the aircraft frame clamping plate, control the splicing rod 222 to splice with the corresponding mounting block 223. Utilizing the elastic force of the spring 229, the limiting rod 228 at the corresponding position positions the splicing rod 222. Rotate the second worm gear 225, which drives the second worm wheel 226 to rotate. The second worm wheel 226 drives the double-threaded screw 224 to rotate, and the double-threaded screw 224 drives the mounting block 223. The movement causes the two clamping plates 221 to hold the aircraft frame plate, driving the second motor 216. The output shaft of the second motor 216 drives the gear 218 to rotate, the gear 218 drives the gear ring 219 to rotate, and the gear ring 219 drives the mounting plate 227 and the aircraft frame plate to rotate. The first motor 212 is started, and the output shaft of the first motor 212 drives the first worm gear 213 to rotate. The first worm gear 213 drives the first worm wheel 214 to rotate, and the first worm wheel 214 drives the rotating shaft 215 and the bracket 211 to rotate, thereby adjusting the pitch angle of the aircraft frame plate.

[0037] 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 the 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 numerical control machining fixture for an aircraft jig board, comprising a base (1), characterized in that: The clamping device (2) is arranged above the base (1), and the clamping device (2) comprises a clamping part (22); The clamping part (22) comprises a limiting rod (228), a mounting plate (227) and a mounting block (223), the top surface of the mounting plate (227) is provided with a sliding groove, the outer surface of the mounting block (223) is in sliding connection with the inner wall of the sliding groove, the top surface of the mounting block (223) is provided with a butt joint groove, and the outer surface of the limiting rod (228) is in sliding penetration with the outer surface of the mounting block (223) and extends into the mounting block (223). An adjusting part (21) is arranged above the base (1); The adjusting part (21) comprises a rotating shaft (215), the top surface of the base (1) is provided with a mounting hole, the outer surface of the rotating shaft (215) is in rotating connection with the inner wall of the base (1) through a first bearing seat, and the outer surface of the rotating shaft (215) is fixedly provided with a support (211).

2. The numerical control machining fixture for the aircraft jig board according to claim 1, characterized in that: The clamping part (22) further comprises a clamping plate (221), a splicing rod (222), a double-thread screw rod (224), a second worm (225), a second worm wheel (226) and a spring (229), the top surface of the splicing rod (222) is fixedly connected with the bottom surface of the clamping plate (221), and the bottom end of the splicing rod (222) extends to the inside of the mounting block (223) and is in sliding connection with the inner wall of the mounting block (223).

3. The numerical control machining fixture for the aircraft jig board according to claim 2, characterized in that: The outer surface of the double-thread screw rod (224) is in rotating connection with the inner wall of the mounting plate (227) through a second bearing seat, the outer surface of the limiting rod (228) is provided with a through hole, and the mounting block (223) is threadedly provided on the outer surface of the double-thread screw rod (224).

4. The numerically controlled machining fixture for the aircraft jacking card according to claim 2, characterized in that: One end of the spring (229) is fixedly connected with the outer surface of the mounting block (223), and the other end of the spring (229) is fixedly connected with the limiting rod (228).

5. The numerically controlled machining fixture for an aircraft jig board according to claim 2, characterized in that: The second worm wheel (226) is fixedly provided on the outer surface of the double-thread screw rod (224), and the bottom end of the second worm (225) is in rotating penetration with the top surface of the mounting plate (227) through a bearing and extends to the inside of the mounting plate (227).

6. The numerically controlled machining fixture for an aircraft jig board according to claim 1, characterized in that: The adjusting part (21) further comprises a first motor (212), a first worm (213), a first worm wheel (214), a second motor (216), a mounting frame (217), a gear (218), a gear ring (219) and a sliding rail (210), the bottom surface of the first motor (212) is fixedly connected with the top surface of the base (1), the first worm wheel (214) is fixedly provided on the outer surface of the rotating shaft (215), the outer surface of the first worm (213) is fixedly connected with the outer surface of the output shaft of the first motor (212), the top surface of the support (211) is fixedly connected with the bottom surface of the sliding rail (210), the bottom surface of the mounting plate (227) is provided with an annular groove, and the outer surface of the sliding rail (210) extends to the inside of the annular groove and is in sliding connection with the inner wall of the mounting plate (227).

7. The numerically controlled machining fixture for an aircraft jig board according to claim 6, characterized in that: The mounting frame (217) is fixedly sleeved on the outer surface of the second motor (216), the outer surface of the mounting frame (217) is fixedly connected with the outer surface of the support (211), the gear (218) is fixedly sleeved on the outer surface of the output shaft of the second motor (216), and the outer surface of the gear ring (219) is fixedly connected with the bottom surface of the mounting plate (227).

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