Stripping detection device for aviation composite material

Abstract

The utility model discloses a stripping detection device for an aviation composite material, which is used for carrying out stripping detection on an annular composite material, and relates to the technical field of composite layer stripping detection. The first support and the vertical plate are both arranged on the bottom plate. The stripping detection device for the aviation composite material further comprises a chuck which is arranged on one side of the first support and used for fixing an annular composite material; and the rotating body is arranged on one side of the vertical plate. The chuck is arranged at the upper end of the bottom plate, so that the composite material can be fixed, meanwhile, the clamping structure is arranged to clamp a composite layer of the composite material, and the first motor drives the clamping structure to do circular motion around the composite material, so that the composite layer can be stripped from the surface of the composite material; and the peeling strength value of the composite material is obtained by utilizing the tension detector connected with the clamping structure, so that the peeling test on the cylindrical material is realized, and the operation is very convenient.

Description

Technical Field

[0001] The utility model relates to the technical field of composite layer peeling detection, in particular to a peeling detection device for aviation composite materials. Background Art

[0002] Aviation products have special application occasions, so the performance requirements of the materials used to make aviation products are more stringent. One of the materials used to make aviation products is composite materials. The composite sandwich structure consists of five components: upper and lower composite panels, sandwich core, and adhesive. The adhesive bonds the panel and the sandwich core together and transfers the load between the two. The panel bears the compression and tension in the surface, as well as the shear load. At present, the peeling strength test of the annular sandwich composite material is tested by a peeling device;

[0003] After searching, a Chinese utility model patent with authorization announcement number CN209296546U was found, which discloses an aluminum-plastic plate roller peeling detection device, which can be used to detect the peeling strength of annular sandwich composite materials. The device uses the stretching space of an electronic universal testing machine to fix the upper connecting shaft and the lower connecting shaft on the upper and lower pull rod heads respectively, and the upper connecting shaft is equipped with a first T-shaped pull plate welded in advance to fix the core of the aluminum-plastic plate; the second T-shaped pull plate on the lower connecting shaft is connected to the roller, and is connected by two loading belts connected to the roller flange.

[0004] The principle is as follows: an upper connecting shaft and a lower connecting shaft are provided, the upper connecting shaft and the lower connecting shaft are connected to the stretching part of the electronic testing machine, and clamping structures are provided at corresponding positions of the upper connecting shaft and the lower connecting shaft to clamp the aluminum-plastic panel and the core on the surface of the drum respectively, and then the upper connecting shaft and the lower connecting shaft are pulled by the electronic testing machine to generate tension, thereby peeling the core and the aluminum-plastic panel from the surface of the drum, and detecting the peeling strength in combination with the tensile testing device of the electronic testing machine. However, the prior art has the following problems: in the process of peeling the aluminum-plastic panel and the core on the surface of the drum, since the material of the core and the aluminum-plastic panel is relatively soft, the material lacks hard structure support during the peeling process, and is prone to twisting when pressure is applied, so that uneven separation is prone to occur during the peeling process, affecting the accuracy of the peeling strength detection. Utility Model Content

[0005] The utility model aims to provide a peeling detection device for aviation composite materials, so as to solve the technical problem raised by the above background technology that there is a lack of a device capable of quickly performing peeling detection on cylindrical composite materials in the current market.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a peeling detection device for aviation composite materials, used for peeling detection of annular composite materials, comprising:

[0007] Base plate;

[0008] A first bracket and a vertical plate, both of which are arranged on the bottom plate;

[0009] The peeling detection device for aviation composite materials also includes:

[0010] A chuck is disposed on one side of the first bracket and is used to fix the annular composite material;

[0011] A rotating body, which is arranged on one side of the vertical plate;

[0012] A driving structure, which is used to drive the rotating body to rotate around the central axis of the chuck;

[0013] A tension detector, which is arranged on the rotating body;

[0014] A clamp body, which is slidably connected to the inner cavity provided on the lower surface of the rotating body, and the clamp body is fixedly connected to the detection end of the tension detector;

[0015] The clamping structure is arranged on the lower surface of the clamping body, and is used for clamping the peeled portion of the outer side surface of the annular composite material.

[0016] As a preferred technical solution of the utility model, the tension detector is a tension gauge, and the detection end of the tension gauge is fixedly connected to the clamp body.

[0017] As a preferred technical solution of the utility model, the clamping structure:

[0018] Two clamping plates are provided, and the two clamping plates are arranged opposite to each other below the clamping body;

[0019] The output end of the No. 1 electric push rod is fixedly connected to the outer side surface of the clamping plate, and the bottom end of the No. 1 electric push rod is fixed to the clamping body.

[0020] As a preferred technical solution of the utility model, the clamping structure also includes:

[0021] A roller, wherein the top of the inner cavity is provided with a through hole penetrating the upper surface of the rotating body, and the roller is rotatably arranged in the through hole;

[0022] at least one gear mounted on the rotating roller;

[0023] A second bracket, which is fixed on one side of the vertical plate;

[0024] a gear ring connected to the second bracket and meshing with a gear;

[0025] a tape wound around the surface of the rotating roller;

[0026] A connecting plate is connected to the end of the coiled belt, and the connecting plate is fixedly connected to the bottom of the tensile gauge.

[0027] As a preferred technical solution of the present utility model, the clamping structure further includes a guide post, which is arranged on the side wall of the inner cavity and is slidably connected to a guide groove arranged on the side surface of the clamp body.

[0028] As a preferred technical solution of the utility model, the driving structure includes a No. 1 motor, which is installed on the side of the vertical plate. An extension frame is provided on one side of the rotating body, and the output shaft of the No. 1 motor is fixedly connected to the bottom end of the extension frame.

[0029] As a preferred technical solution of the utility model, the peeling detection device for aviation composite materials also includes:

[0030] A slider is arranged at the bottom end of the vertical plate, and the slider is slidably connected to a slide groove arranged on the bottom plate;

[0031] A third bracket, which is arranged at the upper end of the bottom plate;

[0032] One end of the No. 2 electric push rod is fixed to the side of the No. 3 bracket, and the other end of the No. 2 electric push rod is connected to the vertical plate.

[0033] As a preferred technical solution of the utility model, the peeling detection device for aviation composite materials also includes:

[0034] A rotating rod, which is arranged on one side of the chuck;

[0035] The second motor is arranged on one side of the first bracket, and the output shaft of the second motor is connected to the rotating rod.

[0036] Compared with the prior art, the beneficial effects of the utility model are:

[0037] The utility model can fix the composite material by arranging a chuck on the upper end of the bottom plate, and at the same time arranging a clamping structure to clamp the composite layer of the composite material, and then driving the clamping structure to perform circular motion around the composite material by a No. 1 motor, so that the composite layer can be peeled off from the surface of the composite material, and the peeling strength value of the composite material is obtained by using a tension detector connected to the clamping structure, thereby realizing the peeling test of the cylindrical material, which is very convenient. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 It is a schematic diagram of a three-dimensional partial cross-sectional structure of the utility model;

[0039] Figure 2 For the utility model Figure 1The enlarged structural diagram at A in the middle;

[0040] Figure 3 It is a three-dimensional structural schematic diagram of the utility model;

[0041] Figure 4 It is a schematic diagram of the three-dimensional structure of the rotating body of the utility model;

[0042] Figure 5 It is a schematic diagram of the three-dimensional structure of the roller, the winding belt and the connecting plate of the utility model;

[0043] Figure 6 It is a schematic diagram of the three-dimensional structure of the bottom of the clamp body of the present utility model.

[0044] In the figure: 1, bottom plate; 2, bracket No. 1; 3, chuck; 4, bracket No. 3; 5, vertical plate; 6, slider; 7, slide groove; 8, electric push rod No. 2; 9, motor No. 1; 10, rotating body; 1001, inner cavity; 11, roller; 12, gear; 13, bracket No. 2; 14, gear ring; 15, belt; 16, connecting plate; 17, tension detector; 18, clamping body; 19, guide groove; 20, guide column; 21, electric push rod No. 1; 22, clamping plate; 23, motor No. 2; 24, composite material. DETAILED DESCRIPTION

[0045] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments.

[0046] See also Figure 1-6 The utility model provides a technical solution: a peeling detection device for aviation composite materials, which is used to perform peeling detection on annular composite materials 24, comprising:

[0047] Bottom plate 1;

[0048] A first bracket 2 and a vertical plate 5, both of which are arranged on the bottom plate 1;

[0049] The peeling detection device for aviation composite materials also includes:

[0050] A chuck 3 is provided at one side of the first bracket 2, and the chuck 3 is used to fix the annular composite material 24;

[0051] A rotating body 10, which is arranged on one side of the vertical plate 5;

[0052] A driving structure, which is used to drive the rotating body 10 to rotate around the central axis of the chuck 3; the driving structure includes a No. 1 motor 9, which is installed on the side of the vertical plate 5, and an extension frame is provided on one side of the rotating body 10, and the output shaft of the No. 1 motor 9 is fixedly connected to the bottom end of the extension frame;

[0053] The tension detector 17 is arranged on the rotating body 10; the tension detector 17 is a tension meter, and a WDF push-pull force meter of the WD / Weidu brand can be selected, and the detection end of the tension meter is fixedly connected to the clamp body 18;

[0054] A clamp body 18 is slidably connected to an inner cavity 1001 provided on the lower surface of the rotating body 10, and the clamp body 18 is fixedly connected to a detection end of a tension detector 17;

[0055] A clamping structure, which is arranged on the lower surface of the clamping body 18, and the clamping structure is used to clamp the peeled portion of the outer side surface of the annular composite material 24; the clamping structure: a clamping plate 22, which is provided with two, and the two clamping plates 22 are relatively arranged below the clamping body 18; a No. 1 electric push rod 21, whose output end is fixedly connected to the outer side surface of the clamping plate 22, and the bottom end of the No. 1 electric push rod 21 is fixed to the clamping body 18.

[0056] The above technical solution can realize the clamping and peeling detection of the cylindrical composite material 24. When in use, the cylindrical composite material 24 is fixed with the chuck 3 to prevent it from shaking; then determine the range of the composite material 24 to be tested, and randomly select a position on the surface of the composite material 24, and cut the composite layer on the surface of the composite material 24 into a strip of a certain width along the circumferential direction as the test end, pry up one end, and put the test end between the clamps 22, start the No. 1 electric push rod 21 to drive the clamp 22 to clamp the test end; then start to peel off the composite layer, start the No. 1 motor 9 to drive the rotating body 10 to rotate around the circumference of the composite material 24, the rotating body 10 drives the clamp body 18 to rotate, the clamp body 18 drives the clamp 22 and the test end clamped by the clamp 22 to rotate, so that the composite layer on the surface of the composite material 24 is torn and peeled off, and then with the force applied by the No. 1 motor 9, the force displayed in the tension detector 17 continues to increase, and the composite layer is continuously peeled off. When the peeling reaches a certain length, the No. 1 motor 9 stops running, and the result displayed by the tension detector 17 is the test data of the composite material 24.

[0057] Further, such as Figure 4 and Figure 5 As shown, the clamping structure also includes: a roller 11, a through hole penetrating the upper surface of the rotating body 10 is provided at the top of the inner cavity 1001, and the roller 11 is rotatably arranged in the through hole; at least one gear 12, which is installed on the roller 11; a second bracket 13, which is fixedly arranged on one side of the vertical plate 5; a gear ring 14, which is connected to the second bracket 13, and the gear ring 14 is meshed with the gear 12; a tape 15, which is wound on the surface of the roller 11; a connecting plate 16, which is connected to the end of the tape 15, and the connecting plate 16 is fixedly connected to the bottom of the tensile gauge; the clamping structure also includes a guide column 20, which is arranged on the side wall of the inner cavity 1001, and the guide column 20 is slidably connected to a guide groove 19 arranged on the side of the clamp body 18;

[0058] The adoption of the above technical solution can shorten the rotation angle required for the rotating body 10 to peel off the composite layer of the composite material 24 of the same length; the same steps are no longer repeated, when the No. 1 motor 9 drives the rotating body 10 to rotate, the gear 12 of the roller 11 is continuously engaged with the gear ring 14, thereby driving the roller 11 to rotate, and the roller 11 reels the tape 15, and the tape 15 pulls the connecting plate 16, the tension detector 17 and the clamp body 18, thereby pulling the test end into the inner cavity 1001, so that the composite layer of the composite material 24 can be peeled off without the rotating body 10 rotating a large angle, thereby improving efficiency.

[0059] Further, such as Figure 1 As shown, the peeling detection device for aviation composite materials also includes:

[0060] A slider 6 is arranged at the bottom end of the vertical plate 5, and the slider 6 is slidably connected to a slide groove 7 arranged on the bottom plate 1; a third bracket 4 is arranged at the upper end of the bottom plate 1; a second electric push rod 8, one end of which is fixed to the side of the third bracket 4, and the other end of the second electric push rod 8 is connected to the vertical plate 5;

[0061] The above technical solution can facilitate the disassembly and assembly of the composite material 24. After the composite material 24 is fixed on the chuck 3 for peeling inspection, in order to facilitate the removal of the composite material 24, the No. 2 electric push rod 8 can be started to drive the vertical plate 5 to slide away from the chuck 3 and the composite material 24, and then the composite material 24 can be removed from the chuck 3. At the same time, it can prevent the rotating body 10 from blocking the composite material 24 and the chuck 3, resulting in obstruction of the line of sight during clamping.

[0062] Further, such as Figure 1 and Figure 3 As shown, the peeling detection device for aviation composite materials further includes: a rotating rod, which is arranged on one side of the chuck 3; a second motor 23, which is arranged on one side of the first bracket 2, and the output shaft of the second motor 23 is connected to the rotating rod;

[0063] The above technical solution can increase the stripping length and obtain more detailed data. While the No. 1 motor 9 drives the rotating body 10 to rotate, the No. 2 motor 23 can be started to drive the chuck 3 to rotate in the opposite direction of the rotating body 10 to ensure that the composite layer on the surface of the composite material 24 can be completely stripped off.

[0064] Working principle: When in use, first fix the cylindrical composite material 24 with the chuck 3 to prevent it from shaking;

[0065] Then determine the range of the composite material 24 to be tested, and randomly select a position on the surface of the composite material 24, and cut the composite layer on the surface of the composite material 24 into a strip of a certain width along the circumferential direction as the test end, pry up one end, and put the test end between the clamping plates 22, and start the No. 1 electric push rod 21 to drive the clamping plates 22 to clamp the test end;

[0066] Next, the composite layer is peeled off. The No. 1 motor 9 is started to drive the rotating body 10 to rotate around the circumference of the composite material 24. The rotating body 10 drives the clamping body 18 to rotate. The clamping body 18 drives the clamping plate 22 and the test end clamped by the clamping plate 22 to rotate, so that the composite layer on the surface of the composite material 24 is torn off. Then, as the force of the No. 1 motor 9 is applied, the force displayed in the tension detector 17 is continuously increased, and the composite layer is continuously peeled off. When the peeling reaches a certain length, the No. 1 motor 9 stops running, and the result displayed by the tension detector 17 is the test data of the composite material 24.

[0067] In order to increase the stripping length and obtain more detailed data, while the No. 1 motor 9 drives the rotating body 10 to rotate, the No. 2 motor 23 can be started to drive the chuck 3 to rotate in the opposite direction of the rotating body 10 to ensure that the composite layer on the surface of the composite material 24 can be completely stripped off.

[0068] Thereby completing a series of tasks, the contents not described in detail in this specification belong to the prior art known to professional and technical personnel in this field.

[0069] It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be regarded as exemplary and non-restrictive from any point of view, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention. Any reference numeral in a claim should not be regarded as limiting the claim to which it relates.

Claims

1. A peeling detection device for aviation composite materials, used for performing peeling detection on annular composite materials (24), comprising: Bottom plate (1); A first bracket (2) and a vertical plate (5), both of which are arranged on the bottom plate (1); Characterized in that the peeling detection device for aviation composite materials also includes: A chuck (3) disposed on one side of the first bracket (2), and the chuck (3) is used to fix the annular composite material (24); A rotating body (10) disposed on one side of the vertical plate (5); A driving structure, used for driving the rotating body (10) to rotate around the central axis of the chuck (3); A tension detector (17) disposed on the rotating body (10); A clamp body (18) which is slidably connected to an inner cavity (1001) provided on the lower surface of the rotating body (10), and the clamp body (18) is fixedly connected to a detection end of a tension detector (17); A clamping structure is arranged on the lower surface of the clamping body (18), and the clamping structure is used to clamp the peeled portion of the outer side surface of the annular composite material (24).

2. The peeling detection device for aviation composite materials according to claim 1, characterized in that: The tension detector (17) is a tension gauge, and a detection end of the tension gauge is fixedly connected to the clamp body (18).

3. The peeling detection device for aviation composite materials according to claim 2, characterized in that: The clamping structure: Two clamping plates (22) are provided, and the two clamping plates (22) are arranged opposite to each other below the clamp body (18); The output end of the first electric push rod (21) is fixedly connected to the outer side surface of the clamping plate (22), and the bottom end of the first electric push rod (21) is fixed to the clamping body (18).

4. The peeling detection device for aviation composite materials according to claim 3, characterized in that: The clamping structure also includes: A rotating roller (11), wherein the top of the inner cavity (1001) is provided with a through hole penetrating the upper surface of the rotating body (10), and the rotating roller (11) is rotatably arranged in the through hole; at least one gear (12) mounted on the rotating roller (11); A second bracket (13), which is fixedly arranged on one side of the vertical plate (5); a gear ring (14), which is connected to the second bracket (13), and the gear ring (14) is meshed with the gear (12); A coil (15) wound on the surface of the rotating roller (11); A connecting plate (16) is connected to the end of the coiled belt (15), and the connecting plate (16) is fixedly connected to the bottom of the tensile gauge.

5. The peeling detection device for aviation composite materials according to claim 3 or 4, characterized in that: The clamping structure further comprises a guide post (20), wherein the guide post (20) is arranged on the side wall of the inner cavity (1001), and the guide post (20) is slidably connected to a guide groove (19) arranged on the side of the clamp body (18).

6. The peeling detection device for aviation composite materials according to claim 1, characterized in that: The driving structure comprises a No. 1 motor (9), wherein the No. 1 motor (9) is mounted on a side of the vertical plate (5), an extension frame is provided on one side of the rotating body (10), and an output shaft of the No. 1 motor (9) is fixedly connected to the bottom end of the extension frame.

7. The peeling detection device for aviation composite materials according to claim 1, characterized in that: The peeling detection device for aviation composite materials also includes: A sliding block (6) is arranged at the bottom end of the vertical plate (5), and the sliding block (6) is slidably connected to a sliding groove (7) arranged on the bottom plate (1); A third bracket (4), which is arranged at the upper end of the bottom plate (1); One end of the No. 2 electric push rod (8) is fixed to the side surface of the No. 3 bracket (4), and the other end of the No. 2 electric push rod (8) is connected to the vertical plate (5).

8. The debonding detection device for aviation composite materials according to claim 1, characterized in that: The peeling detection device for aviation composite materials also includes: A rotating rod, which is arranged on one side of the chuck (3); A second motor (23) is arranged on one side of the first bracket (2), and an output shaft of the second motor (23) is connected to the rotating rod.

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