Punching and positioning tool for aircraft board of textile machine

Abstract

The utility model relates to the technical field of positioning tools, in particular to a textile machine airplane board punching positioning tool which comprises a positioning bottom plate, a positioning assembly is installed on the positioning bottom plate, and the positioning assembly is used for positioning an airplane board. The positioning assembly comprises a plurality of positioning clamps A, positioning clamps B and positioning clamps C. The positioning clamps A, the positioning clamps B and the positioning clamps C are the same in structure, the positioning clamps A are used for positioning the front side and the rear side of the aircraft board, the positioning clamps B are used for positioning one side of the aircraft board, and the positioning clamps C are used for positioning the other side of the aircraft board. The supporting vertical seat is arranged between the positioning clamps C, the positioning insertion column is arranged on the supporting vertical seat, and the positioning insertion column can be inserted into a positioning ring of an airplane board so as to be mutually locked with the airplane board, so that the positioning is more accurate, the position stability of the airplane board in the machining process can be ensured, errors and deviation are reduced, and the machining quality is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of positioning tooling, in particular to a positioning tooling for punching holes in an aircraft plate of a textile machine. Background Art

[0002] At present, textile machinery is a kind of machine equipment used to produce textiles, mainly used to process materials such as fibers, threads or yarns into different forms of textiles. Textile machinery includes various types and functions of machine equipment, such as spinning machines, looms, dyeing machines, printing machines, finishing machines, sewing machines, etc.

[0003] The textile machine aircraft plate is an intermediate bracket on the textile machinery. The existing textile machine aircraft plate needs to be accurately positioned during the punching process to ensure that the hole position is accurate. However, due to the special structural dimensions of the aircraft plate, it is not easy to position the aircraft plate, and vibration and offset may occur during the processing of the aircraft plate, resulting in processing errors and deviations, affecting the processing quality and precision.

[0004] Therefore, a textile machine aircraft plate punching and positioning tool is needed to solve the above technical problems. Utility Model Content

[0005] The purpose of the utility model is to provide a textile machine aircraft plate punching positioning tool. The utility model is provided with a supporting seat between the positioning fixtures C, and a positioning pin is provided on the supporting seat. The positioning pin can be inserted into the positioning ring of the aircraft plate, so as to be locked with the aircraft plate, so that the positioning is more accurate, the position of the aircraft plate can be ensured to be stable during the processing, the error and offset can be reduced, and the processing quality can be improved.

[0006] The technical solution adopted by the utility model to solve the above technical problems is: a textile machine aircraft plate punching positioning tool, comprising a positioning base plate, a positioning assembly is installed on the positioning base plate, and the positioning assembly is used to position the aircraft plate;

[0007] The positioning assembly includes a plurality of positioning fixtures A, positioning fixtures B and positioning fixtures C. The positioning fixtures A, positioning fixtures B and positioning fixtures C have the same structure. The positioning fixture A is used to position the front and rear sides of the aircraft panel, the positioning fixture B is used to position one side of the aircraft panel, and the positioning fixture C is used to position the other side of the aircraft panel.

[0008] The positioning fixture A comprises a driving cylinder, a piston rod and a positioning clamping claw, wherein the driving cylinder is fixedly connected to the positioning base plate, the output end of the driving cylinder and the piston rod are mutually drivingly connected, and the positioning clamping claw and the piston rod are mutually connected via a rotating shaft;

[0009] A support stand is provided between the plurality of positioning fixtures C, the support stand is fixedly connected to the positioning base plate, a positioning plug is provided on the support stand, the positioning plug and the support stand are connected to each other through a support rod, and the positioning plug is used to be inserted into the positioning ring of the aircraft plate;

[0010] A sensor is provided on one side of the positioning fixture C, a sensor probe is installed on the sensor, and an output end of the sensor is connected to an input end of the driving cylinder through a signal.

[0011] Furthermore, two shock absorbing mechanisms are installed on the positioning base plate, and the shock absorbing mechanisms include a supporting base plate, a damping rod and a shock absorbing support plate. The supporting base plate is fixedly connected to the upper end of the positioning base plate, and the shock absorbing support plate is located above the supporting base plate. The shock absorbing support plate is used to support the aircraft plate. The supporting base plate and the shock absorbing support plate are interconnected through a damping rod, and a shock absorbing spring is provided on the outer sleeve of the damping rod.

[0012] Furthermore, an elastic support column is provided on one side of the positioning fixture A, and the elastic support column is fixedly connected to the positioning base plate, and the elastic support column is used to support the plug-in portion of the aircraft panel.

[0013] Furthermore, the sensor is any one of a laser ranging sensor or an ultrasonic sensor.

[0014] Furthermore, a plurality of lifting rings are fixedly connected to the upper end of the positioning base plate.

[0015] Furthermore, a support column is fixedly connected to the positioning base plate, and a limit stop column is fixedly connected to the upper end of the support column, and the limit stop column is used to block and limit the aircraft panel.

[0016] The utility model has the advantages that: the utility model provides a textile machine aircraft plate punching positioning tool, which has the following technical effects:

[0017] 1. The positioning assembly in the present invention includes a plurality of positioning fixtures A, positioning fixtures B and positioning fixtures C. Since the present application adopts a plurality of positioning fixtures A, positioning fixtures B and positioning fixtures C, different sides of the aircraft panel can be positioned respectively, thereby making the positioning more accurate; the present invention is provided with supporting seats between the positioning fixtures C, and positioning pins are provided on the supporting seats. The positioning pins can be inserted into the positioning ring of the aircraft panel, thereby locking with the aircraft panel, making the positioning more accurate, ensuring the stable position of the aircraft panel during the processing, reducing errors and offsets, and improving the processing quality.

[0018] 2. The utility model is provided with a sensor on one side of the positioning fixture C. The output end of the sensor is connected to the input end of the driving cylinder through a signal. The sensor can adjust the clamping position of the clamp according to the thickness of the workpiece detected by the sensor probe. The sensor can control the driving cylinder, and the driving cylinder drives the piston rod to rise and fall, thereby controlling the up and down position of the positioning clamp, which can be suitable for aircraft panels of different specifications.

[0019] 3. The utility model has two shock absorbing mechanisms installed on the positioning base plate, and the shock absorbing mechanisms include a supporting base plate, a damping rod and a shock absorbing support plate. The supporting base plate and the shock absorbing support plate are connected to each other through the damping rod, and a shock absorbing spring is arranged on the outer sleeve of the damping rod. During the processing of the aircraft plate, the shock absorbing mechanism provides stable support for the aircraft plate, and can reduce the vibration of the aircraft plate during the processing, reduce processing errors and deviations, and help improve the accuracy and quality of aircraft plate processing. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the specific implementation methods of the utility model or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;

[0022] Figure 2 It is an enlarged structural schematic diagram of the positioning fixture A in the utility model;

[0023] Figure 3 This is a schematic diagram of the main structure of the utility model;

[0024] in:

[0025] 1. Positioning base plate; 2. Aircraft plate; 201. Plug-in part;

[0026] 202. Positioning ring; 3. Elastic support column; 4. Positioning fixture A;

[0027] 401, driving cylinder; 402, piston rod; 403, positioning clamping claw;

[0028] 5. Positioning fixture B; 6. Positioning fixture C; 7. Support stand;

[0029] 8. Support rod; 9. Positioning column; 10. Support column;

[0030] 11. Limit stop column; 12. Sensor; 1201. Sensor probe;

[0031] 13. Lifting ring; 14. Damping rod; 15. Shock-absorbing spring;

[0032] 16. Shock-absorbing support plate; 17. Support base plate. DETAILED DESCRIPTION

[0033] The technical solution of the utility model will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of 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.

[0034] In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside" and the like indicate the orientation or position relationship based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the present utility model and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. The terms "installed", "connected", and "connected" 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 it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0035] Embodiment 1:

[0036] Figure 1 It is a three-dimensional structural schematic diagram of the utility model. Figure 2 This is an enlarged structural diagram of the positioning fixture A in the utility model. Figure 3 It is a schematic diagram of the main structure of the utility model, as shown in Figure 1 , Figure 2 and Figure 3 The shown one kind of textile machine aircraft plate punching positioning tool comprises a positioning base plate 1, a positioning assembly is installed on the positioning base plate 1, the positioning assembly is used to position the aircraft plate 2, the utility model also has a plurality of lifting rings 13 fixedly connected to the upper end of the positioning base plate 1, which is convenient for lifting and transporting the positioning base plate 1, the utility model has a support column 10 fixedly connected to the positioning base plate 1, and a limited stop column 11 is fixedly connected to the upper end of the support column 10, and the limited stop column 11 is used to block and limit the aircraft plate 2;

[0037] The positioning assembly in the utility model includes a plurality of positioning fixtures A4, positioning fixtures B5 and positioning fixtures C6, and the structures of the positioning fixtures A4, positioning fixtures B5 and positioning fixtures C6 are the same. The positioning fixture A4 is used to position the front and rear sides of the aircraft board 2. An elastic support column 3 is provided on one side of the positioning fixture A4, and the elastic support column 3 is fixedly connected to the positioning base plate 1. The elastic support column 3 is used to support the plug-in portion 201 of the aircraft board 2. The positioning fixture B5 in the utility model is used to position one side of the aircraft board 2, and the positioning fixture C6 is used to position the other side of the aircraft board 2. The utility model can position different sides of the aircraft board 2 respectively through the positioning fixtures A4, positioning fixtures B5 and positioning fixtures C6;

[0038] The positioning fixture A4 in the utility model includes a driving cylinder 401, a piston rod 402 and a positioning clamp 403. The driving cylinder 401 is fixedly connected to the positioning base plate 1, the output end of the driving cylinder 401 and the piston rod 402 are mutually driven and connected, and the positioning clamp 403 and the piston rod 402 are mutually connected through a rotating shaft; the utility model is provided with a sensor 12 on one side of the positioning fixture C6, and a sensor probe 1201 is installed on the sensor 12. The output end of the sensor 12 and the input end of the driving cylinder 401 are connected through a signal The sensor 12 is preferably a laser ranging sensor. The laser ranging sensor uses a laser beam to scan the aircraft plate 2, and determines the distance of the aircraft plate 2 by measuring the reflection time or phase difference of the laser beam, thereby realizing the measurement of the thickness and shape of the aircraft plate 2. The sensor 12 can adjust the clamping position of the positioning jaw 403 according to the thickness of the workpiece detected by the sensor probe 1201. The sensor 12 can control the driving cylinder 401, and drive the piston rod 402 to rise and fall through the driving cylinder 401, thereby controlling the up and down position of the positioning jaw 403.

[0039] In the utility model, a support seat 7 is arranged between a plurality of positioning fixtures C6, the support seat 7 and the positioning base plate 1 are fixedly connected to each other, a positioning plug post 9 is arranged on the support seat 7, the positioning plug post 9 and the support seat 7 are connected to each other through a support rod 8, when the aircraft panel 2 is positioned, the positioning plug post 9 can be inserted into the positioning ring 202 of the aircraft panel 2, so that the aircraft panel 2 and the positioning plug post 9 are locked with each other, so that the positioning of the aircraft panel 2 is more accurate and firm.

[0040] In the utility model, two shock absorbing mechanisms are installed on the positioning base plate 1, and the shock absorbing mechanisms include a supporting base plate 17, a damping rod 14 and a shock absorbing supporting plate 16. The supporting base plate 17 is fixedly connected to the upper end of the positioning base plate 1, and the shock absorbing supporting plate 16 is located above the supporting base plate 17. The shock absorbing supporting plate 16 is used to support the aircraft plate 2. The supporting base plate 17 and the shock absorbing supporting plate 16 are connected to each other through the damping rod 14. A shock absorbing spring 15 is provided on the outer sleeve of the damping rod 14. The above-mentioned shock absorbing mechanism can provide stable support for the aircraft plate 2, thereby reducing processing errors and deviations.

[0041] Working principle: When the utility model is in use, the staff aligns and plugs the positioning ring 202 of the aircraft panel 2 with the positioning plug post 9, blocks and limits the aircraft panel 2 through the limit stop post 11, and after locking the aircraft panel 2, detects the thickness and shape of the aircraft panel 2 through the sensor 12. The sensor 12 adjusts the clamping position of the positioning claw 403 according to the thickness of the aircraft panel 2 detected by the sensor probe 1201, and positions and clamps the aircraft panel 2 through the positioning claw 403. After the aircraft panel 2 is positioned, the aircraft panel 2 is punched through the externally arranged punching device.

[0042] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model, rather than to limit it. Although the utility model has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments can still be modified, or some or all of the technical features therein can be replaced by equivalents. However, these modifications or replacements do not make the essence of the corresponding technical solution deviate from the scope of the technical solution of the embodiments of the utility model.

Claims

1. A textile machine aircraft panel punching and positioning tool, comprising a positioning base plate (1), on which a positioning component is mounted, the positioning component being used to position an aircraft panel (2); Features: The positioning assembly comprises a plurality of positioning fixtures A (4), a positioning fixture B (5) and a positioning fixture C (6), wherein the positioning fixtures A (4), the positioning fixtures B (5) and the positioning fixture C (6) have the same structure, wherein the positioning fixture A (4) is used to position the front and rear sides of the aircraft panel (2), the positioning fixture B (5) is used to position one side of the aircraft panel (2), and the positioning fixture C (6) is used to position the other side of the aircraft panel (2); The positioning fixture A (4) comprises a driving cylinder (401), a piston rod (402) and a positioning clamp (403); the driving cylinder (401) is fixedly connected to the positioning base plate (1); the output end of the driving cylinder (401) and the piston rod (402) are mutually drivingly connected; and the positioning clamp (403) and the piston rod (402) are mutually connected via a rotating shaft; A support stand (7) is arranged between the plurality of positioning fixtures C (6); the support stand (7) and the positioning base plate (1) are fixedly connected to each other; a positioning plug post (9) is arranged on the support stand (7); the positioning plug post (9) and the support stand (7) are connected to each other via a support rod (8); the positioning plug post (9) is used to be inserted into a positioning ring (202) of the aircraft plate (2); A sensor (12) is provided on one side of the positioning fixture C (6), a sensor probe (1201) is installed on the sensor (12), and an output end of the sensor (12) is connected to an input end of the driving cylinder (401) via a signal.

2. A textile machine aircraft plate punching and positioning tool according to claim 1, characterized in that: Two shock absorbing mechanisms are installed on the positioning base plate (1), and the shock absorbing mechanisms include a supporting base plate (17), a damping rod (14) and a shock absorbing support plate (16). The supporting base plate (17) is fixedly connected to the upper end of the positioning base plate (1), and the shock absorbing support plate (16) is located above the supporting base plate (17). The shock absorbing support plate (16) is used to support the aircraft board (2). The supporting base plate (17) and the shock absorbing support plate (16) are connected to each other through the damping rod (14), and a shock absorbing spring (15) is provided on the outer sleeve of the damping rod (14).

3. The punching and positioning tool for textile machine aircraft plate according to claim 1, characterized in that: An elastic support column (3) is provided on one side of the positioning fixture A (4), and the elastic support column (3) is fixedly connected to the positioning base plate (1). The elastic support column (3) is used to support the plug-in portion (201) of the aircraft plate (2).

4. The punching and positioning tool for textile machine aircraft plate according to claim 1, characterized in that: The sensor (12) is any one of a laser distance measuring sensor and an ultrasonic sensor.

5. The punching and positioning tool for textile machine aircraft plate according to claim 1, characterized in that: A plurality of lifting rings (13) are fixedly connected to the upper end of the positioning base plate (1).

6. The punching and positioning tool for textile machine aircraft plate according to claim 1, characterized in that: A support column (10) is fixedly connected to the positioning base plate (1), and a limit stop column (11) is fixedly connected to the upper end of the support column (10). The limit stop column (11) is used to block and limit the aircraft panel (2).

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