CN219170697U

CN219170697U - Four-axis test fixture for machining aviation parts

Info

Publication number: CN219170697U
Application number: CN202320515602.5U
Authority: CN
Inventors: 任志军
Original assignee: Shanghai Yuecheng Electromechanical Co ltd
Current assignee: Shanghai Yuecheng Electromechanical Co ltd
Priority date: 2023-03-16
Filing date: 2023-03-16
Publication date: 2023-06-13
Anticipated expiration: 2033-03-16

Abstract

The utility model discloses a four-axis test fixture for machining aviation parts, which relates to the technical field of machining of aviation parts and comprises a bottom plate, wherein two supporting seats are arranged on the upper surface of the bottom plate, round seats are arranged in the two supporting seats, a workbench is arranged between the two round seats, two mounting mechanisms are arranged above the workbench, each mounting mechanism comprises a first supporting plate, and the bottom surface of the first supporting plate is fixedly connected with the upper surface of the workbench. It is through the cooperation between installation mechanism and the stop gear, after accomplishing the fixed to the aviation part, can be convenient for overturn the aviation part to can be convenient for detect the positive and negative of aviation part, and then can effectively improve the detection efficiency of aviation part, through cooperation between second backup pad, third backup pad, first spring, first arm-tie, first spliced pole and the grip block, can be more stable carry out the centre gripping to the aviation part fixedly.

Description

Four-axis test fixture for machining aviation parts

Technical Field

The utility model relates to the technical field of aviation part machining, in particular to a four-axis test fixture for aviation part machining.

Background

The processing of the aviation parts mainly refers to the manufacture of various parts of an aviation aircraft, including the manufacture of components of an aircraft body, the manufacture of components of an aviation engine, the manufacture of instruments, airborne equipment, hydraulic systems, accessories and the like, and a series of tests are required to be carried out on the aviation parts before the aviation parts are used, so that a four-axis test fixture is required to be used.

When the existing four-axis test fixture for machining the aviation parts is used, the aviation parts are not convenient to turn over, so that the front and back sides of the aviation parts are not convenient to detect; therefore, the four-axis test fixture for machining the aviation parts solves the problems.

Disclosure of Invention

The utility model aims to make up the defects of the prior art and provides a four-axis test fixture for machining aviation parts.

In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides a four-axis test fixture of aviation part processing, includes the bottom plate, two supporting seats are installed to the upper surface mounting of bottom plate, two circular seat is all installed to the inside of supporting seat, two install the workstation between the circular seat, the top of workstation is provided with two installation mechanism, installation mechanism includes first backup pad, the bottom surface of first backup pad and the upper surface fixed connection of workstation, the upper surface fixed connection of first backup pad has the fourth backup pad, two be provided with two stop gear between the circular seat.

Further, the installation mechanism further comprises a threaded rod, the outer surface of the threaded rod is in threaded connection with a threaded plate, and the bottom surface of the threaded plate is fixedly connected with the upper surface of the first supporting plate.

Further, the surface rotation of threaded rod is connected with the U shaped plate, the one side fixedly connected with movable plate of spiral shell board is kept away from to the U shaped plate, the bottom surface of movable plate and the upper surface sliding connection of first backup pad.

Further, the inside of movable plate and the inside of fourth backup pad are all rotated and are connected with the rotor plate, two the equal fixedly connected with second backup pad of one side that the rotor plate is close to each other and third backup pad, two the top of third backup pad all is provided with first arm-tie, two the equal fixedly connected with of upper surface of third backup pad two first springs, and the one end and the bottom surface fixed connection of first arm-tie of third backup pad are kept away from to first spring.

Further, two the top of second backup pad all is provided with the grip block, two the equal fixedly connected with of bottom surface of first arm-tie two first spliced poles, and the one end that first spliced pole kept away from first arm-tie runs through the third backup pad and with the last fixed surface of grip block be connected.

Further, the stop gear includes the fifth backup pad, the surface fixedly connected with second spliced pole of fifth backup pad, the one end and the surface fixed connection of one of them pivoted plate of fifth backup pad are kept away from to the second spliced pole.

Further, stop gear still includes the second arm-tie, the surface fixedly connected with of second arm-tie two second springs and two gag lever posts, two the one end that the second arm-tie was kept away from to the second spring all is connected with the surface fixedly of fifth backup pad, two the one end that the second arm-tie was kept away from to the gag lever post all runs through the fifth backup pad and peg graft in the inside of fourth backup pad.

Compared with the prior art, the four-axis test fixture for machining the aviation part has the following beneficial effects:

1. according to the utility model, through the cooperation between the mounting mechanism and the limiting mechanism, after the fixing of the aviation part is completed, the aviation part can be turned over conveniently, so that the front and back sides of the aviation part can be detected conveniently, and the detection efficiency of the aviation part can be improved effectively.

2. According to the utility model, through the cooperation among the second supporting plate, the third supporting plate, the first spring, the first pulling plate, the first connecting column and the clamping plate, the aviation part can be clamped and fixed more stably.

Drawings

FIG. 1 is a schematic perspective elevation view of the present utility model;

FIG. 2 is a schematic perspective view of the mounting mechanism and spacing mechanism of the present utility model;

fig. 3 is a schematic diagram showing the connection of the rotating plate and the second support plate according to the present utility model.

In the figure: 1. a bottom plate; 2. a support base; 3. a circular seat; 4. a work table; 5. a mounting mechanism; 501. a first support plate; 502. a threaded rod; 503. a thread plate; 504. a U-shaped plate; 505. a moving plate; 506. a rotating plate; 507. a second support plate; 508. a third support plate; 509. a first spring; 510. a first pulling plate; 511. a first connection post; 512. a clamping plate; 513. a fourth support plate; 6. a limiting mechanism; 601. a second connection post; 602. a fifth support plate; 603. a second spring; 604. a second pulling plate; 605. and a limit rod.

Detailed Description

The principles and features of the present utility model are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the utility model and are not to be construed as limiting the scope of the utility model.

The embodiment provides a four-axis test fixture of aviation part processing, the device is used for carrying out a series of tests to aviation part, through the installation mechanism 5 and the stop gear 6 that set up, after accomplishing the fixed to aviation part, can be convenient for overturn to aviation part to can be convenient for detect aviation part's positive and negative, and then can effectively improve aviation part's detection efficiency.

Referring to fig. 1 to 3, a four-axis test fixture for machining aviation parts comprises a base plate 1, wherein two supporting seats 2 are installed on the upper surface of the base plate 1, round seats 3 are installed inside the two supporting seats 2, a workbench 4 is installed between the two round seats 3, two installation mechanisms 5 are arranged above the workbench 4, each installation mechanism 5 comprises a first supporting plate 501, the bottom surface of the first supporting plate 501 is fixedly connected with the upper surface of the workbench 4, a fourth supporting plate 513 is fixedly connected with the upper surface of the first supporting plate 501, and two limiting mechanisms 6 are arranged between the two round seats 3.

The two mounting mechanisms 5 are symmetrical about the center point of the workbench 4, and after the fixing of the aviation part is completed, the aviation part can be turned over conveniently through the cooperation between the mounting mechanisms 5 and the limiting mechanisms 6, so that the front and back sides of the aviation part can be detected conveniently, and the detection efficiency of the aviation part can be improved effectively.

The installation mechanism 5 further comprises a threaded rod 502, the outer surface of the threaded rod 502 is in threaded connection with a threaded plate 503, the bottom surface of the threaded plate 503 is fixedly connected with the upper surface of the first supporting plate 501, the outer surface of the threaded rod 502 is rotationally connected with a U-shaped plate 504, one surface of the U-shaped plate 504, which is far away from the threaded plate 503, is fixedly connected with a movable plate 505, the bottom surface of the movable plate 505 is in sliding connection with the upper surface of the first supporting plate 501, one end of the threaded rod 502 is provided with a cylindrical handle, and a sliding groove which is matched with the movable plate 505 is formed in the first supporting plate 501.

The inside of movable plate 505 and the inside of fourth backup pad 513 are all rotated and are connected with rotor plate 506, and the equal fixedly connected with second backup pad 507 of the one side that two rotor plates 506 are close to each other and third backup pad 508, and the top of two third backup pads 508 all is provided with first arm-tie 510, and the upper surface of two third backup pads 508 all fixedly connected with two first springs 509, and the one end that third backup pad 508 was kept away from to first spring 509 and the bottom surface fixed connection of first arm-tie 510, and third backup pad 508 is located the top of second backup pad 507, and two first springs 509 are about the central point symmetry of first arm-tie 510.

The clamping plates 512 are arranged above the two second support plates 507, the two first connecting columns 511 are fixedly connected to the bottom surfaces of the two first support plates 510, one end of each first connecting column 511, which is far away from the first support plate 510, penetrates through the third support plate 508 and is fixedly connected with the upper surface of the clamping plate 512, through holes matched with the first connecting columns 511 are formed in the third support plate 508, one of the first support plates 510 is pulled upwards, the first support plate 510 can drive the first connecting columns 511 and the clamping plates 512 to move upwards and stretch the first springs 509, when the clamping plates 512 move upwards to the maximum distance, one side surface of an aviation part to be detected is abutted against one of the rotating plates 506 and the first support plates 510 are loosened, under the action of the first springs 509, the first support plates 510, the clamping plates 512 and the like can move towards the direction of the aviation part, the aviation part can be clamped primarily, then the other first support plate 510 is pulled upwards and is screwed clockwise, the first support plate 502 can be rotated clockwise to drive the U504, the moving plate 505, the other rotating plate 506 and the other first support plate 506 are screwed clockwise, and the other aviation part 510 can be clamped stably, and the other aviation part is clamped by the first support plate 510 is realized.

The stop gear 6 includes fifth backup pad 602, the surface fixedly connected with second spliced pole 601 of fifth backup pad 602, the one end that fifth backup pad 602 was kept away from to second spliced pole 601 and the surface fixedly connected with of one of them rotation board 506, stop gear 6 still includes second arm-tie 604, the surface fixedly connected with two second springs 603 of second arm-tie 604 and two gag lever posts 605, the one end that second arm-tie 604 was kept away from to two second springs 603 all is connected with the surface fixedly of fifth backup pad 602, the one end that second arm-tie 605 was kept away from to two gag lever posts 605 all runs through fifth backup pad 602 and peg graft in the inside of fourth backup pad 513, two spacing holes have been seted up to the inside of fourth backup pad 513, two spacing holes respectively with two gag lever posts 605 looks adaptation.

Working principle: when the utility model is used, one of the first pull plates 510 is pulled upwards, the first pull plate 510 can drive the first connecting column 511 and the clamping plate 512 to move upwards and stretch the first spring 509, when the clamping plate 512 moves upwards to the maximum distance, one side surface of the aviation part to be detected is abutted against one of the rotating plates 506 and the first pull plate 510 is loosened, under the action of the first spring 509, the first pull plate 510, the clamping plate 512 and the like can move towards the direction of the aviation part, so that the aviation part can be primarily clamped, then the other first pull plate 510 is pulled upwards and the threaded rod 502 is screwed clockwise, the threaded rod 502 can drive the U-shaped plate 504, the moving plate 505, the other rotating plate 506, the other first pull plate 510 and the like to move towards the direction of the aviation part, the second step of fixing the aviation part is realized, then the other first pull plate 510 is loosened to realize the third step of fixing the aviation part, thereby realizing the stable clamping of the aviation part, when the other surface of the aviation part is required to be detected, the second pull plate 604 is pulled in the direction far away from the fourth support plate 513, the second pull plate 604 can drive the limiting rod 605 to move in the direction far away from the fourth support plate 513 and lengthen the second spring 603, when the limiting rod 605 is completely removed from the inside of the fourth support plate 513, the second pull plate 604, the limiting rod 605, the rotating plate 506, the aviation part and the like can be rotated, after the aviation part rotates for one hundred eighty degrees, the second pull plate 604 is loosened, the limiting rod 605 can be spliced in the inside of the fourth support plate 513 again under the action of the second spring 603, thereby fixing the rotating plate 506, the aviation part and the like, at this time, the overturning of the aviation part is completed.

The foregoing description of the preferred embodiments of the utility model is not intended to limit the utility model to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the utility model are intended to be included within the scope of the utility model.

Claims

1. Four-axis test fixture of aviation part processing, including bottom plate (1), its characterized in that: the utility model discloses a novel automatic lifting device for the floor comprises a base plate (1), wherein two supporting seats (2) are installed on the upper surface of the base plate (1), two circular seats (3) are installed in the supporting seats (2), two work tables (4) are installed between the circular seats (3), two installation mechanisms (5) are arranged above the work tables (4), each installation mechanism (5) comprises a first supporting plate (501), the bottom surface of each first supporting plate (501) is fixedly connected with the upper surface of each work table (4), a fourth supporting plate (513) is fixedly connected with the upper surface of each first supporting plate (501), and two limiting mechanisms (6) are arranged between the circular seats (3).

2. The four-axis test fixture for machining of aerospace parts of claim 1, wherein: the mounting mechanism (5) further comprises a threaded rod (502), the outer surface of the threaded rod (502) is in threaded connection with a threaded plate (503), and the bottom surface of the threaded plate (503) is fixedly connected with the upper surface of the first supporting plate (501).

3. The four-axis test fixture for machining of aerospace parts of claim 2, wherein: the outer surface of threaded rod (502) rotates and is connected with U-shaped plate (504), one side that threaded plate (503) was kept away from to U-shaped plate (504) is fixedly connected with movable plate (505), the bottom surface of movable plate (505) and the upper surface sliding connection of first backup pad (501).

4. A four-axis test fixture for machining an aerospace part according to claim 3, wherein: inside and the inside of fourth backup pad (513) of movable plate (505) all rotate and be connected with rotor plate (506), two equal fixedly connected with second backup pad (507) of one side that rotor plate (506) are close to each other and third backup pad (508), two the top of third backup pad (508) all is provided with first arm-tie (510), two equal fixedly connected with of upper surface of third backup pad (508) two first springs (509), and the one end that third backup pad (508) were kept away from to first spring (509) and the bottom surface fixed connection of first arm-tie (510).

5. The four-axis test fixture for machining of aerospace parts of claim 4, wherein: two the top of second backup pad (507) all is provided with grip block (512), two the bottom surface of first arm-tie (510) all fixedly connected with two first spliced poles (511), and the one end that first spliced pole (511) kept away from first arm-tie (510) runs through third backup pad (508) and with the last fixed surface of grip block (512) is connected.

6. The four-axis test fixture for machining of aerospace parts of claim 4, wherein: the limiting mechanism (6) comprises a fifth supporting plate (602), a second connecting column (601) is fixedly connected to the outer surface of the fifth supporting plate (602), and one end, far away from the fifth supporting plate (602), of the second connecting column (601) is fixedly connected with the outer surface of one of the rotating plates (506).

7. The four-axis test fixture for machining of aerospace parts of claim 6, wherein: stop gear (6) still include second arm-tie (604), the surface fixed connection of second arm-tie (604) has two second springs (603) and two gag lever post (605), two the one end that second spring (603) kept away from second arm-tie (604) all is connected with the surface fixed of fifth backup pad (602), two the one end that second arm-tie (605) kept away from second arm-tie (604) all runs through fifth backup pad (602) and peg graft in the inside of fourth backup pad (513).