A peeling detection device for aerospace composites

Abstract

The utility model relates to aviation composite material detection technical field, concretely relates to a kind of stripping detection devices for aviation composite material, including detection platform and the middle support and two vertical supports fixed on detection platform, support ring, fixed in middle support, several square holes are equipped on it, radial insertion in square hole's supporting arm, drive part for synchronously pushing several supporting arms to do telescopic motion along radial direction between two vertical supports, fixed part is equipped at the end of supporting arm, the fixed part includes cross brace and the cross groove on cross brace, the cross groove is equipped with press strip in it.The utility model can fix different diameter annular composite material under the premise, and also can fix different length strip-shaped composite material and carry out stripping detection, expand the scope of application by several supporting arms and fixed part equipped at the free end of supporting arm and cooperate drive part synchronously push several supporting arms and fixed part synchronous radial outward unfolding.

Description

Technical Field

[0001] This utility model relates to the field of aerospace composite material testing technology, and in particular to a peeling testing device for aerospace composite materials. Background Technology

[0002] The peel test procedure for composite materials is as follows: two layers of composite material are fixedly bonded together using the adhesive material to be tested. Then, the pre-existing separation ends of the two composite layers are fixed to two clamps on a peeling device. By driving one of the clamps to move at a constant speed, the tensile force generated when peeling off one layer of composite material is measured, thus determining the peel strength. However, when testing relatively soft annular samples, the lack of rigid structural support can easily lead to uneven separation, affecting the accuracy of the test results.

[0003] To address the aforementioned technical problems, prior art patent application number 202323458132.2 discloses a peel detection device for aerospace composite materials. This device uses a chuck to radially support a flexible, annular composite material, and then uses a primary actuator to drive the clamping structure to move in a circular motion around the composite material, thereby completing the peel detection operation. The peel strength value can be obtained by detecting the tensile force data during the peeling process. However, in the aforementioned prior art, this device is difficult to use for peel detection of flexible, strip-shaped composite materials, and its applicability is relatively poor. Utility Model Content

[0004] In view of this, the purpose of this utility model is to propose a peel detection device for aerospace composite materials, so as to solve the problem that it is difficult to perform peel detection on soft strip composite materials and the applicability is relatively poor.

[0005] To achieve the above objectives, this utility model provides a peeling detection device for aerospace composite materials, including a detection table and a central support and two vertical supports fixed on the detection table.

[0006] The support ring is fixed to the central bracket and has several square holes.

[0007] A support arm that is radially inserted into a square hole.

[0008] A drive unit located between two vertical supports to synchronously push several arms to extend and retract radially.

[0009] A fixing part is provided at the end of the support arm. The fixing part includes a cross brace and a cross groove on the cross brace. A pressure strip is provided in the cross groove. A screw hole is provided at the midpoint of the cross groove. A pre-set hole corresponding to the screw hole is provided on the pressure strip. The end of the strip composite material is pressed between the pressure strip and the cross groove by screws.

[0010] Preferably, the cross brace is fixed to the end face of the support arm along the circumference of the support ring, and the cross brace is located outside the support ring.

[0011] Preferably, the pressure strip is coaxial with the cross brace, and one side of the pressure strip matches the interior of the cross groove.

[0012] Preferably, the driving unit includes a wedge-shaped push block coaxially inserted into the support ring. The wedge-shaped push block has several guide grooves arranged in parallel on its outer circumference. A slider is slidably arranged in the guide groove. One side of the slider is fixed on the support arm near one end of the wedge-shaped push block. The wedge-shaped push block has two transverse through holes on one side. A guide rod is inserted into the transverse through hole. The two ends of the guide rod are respectively fixed on two vertical supports. A telescopic cylinder is fixed on one of the vertical supports. The output end of the telescopic cylinder is fixed on one end face of the wedge-shaped push block.

[0013] Preferably, the wedge-shaped pusher has a conical shape, and the smaller diameter end of the wedge-shaped pusher is inserted into the support ring.

[0014] Preferably, the guide grooves are arranged circumferentially on the conical arc surface outside the wedge-shaped pusher, and the vertical cross-sectional shape of the guide grooves is convex.

[0015] Preferably, the shape and size of the slider match the shape and size of the vertical cross-section of the guide groove.

[0016] Preferably, the peeling detection device further includes a peeling section coaxially disposed on the detection stage, the peeling section being used for circumferentially peeling the composite material.

[0017] The beneficial effects of this utility model are:

[0018] This invention uses several circumferentially distributed support arms on a support ring and a fixing part located at the free end of the support arms. In conjunction with the drive unit, the support arms and fixing parts are pushed radially outward in a synchronized manner. This invention can fix annular composite materials of different diameters and strip composite materials of different lengths and perform peel detection, thus expanding the scope of application. It eliminates the need for additional equipment for peel detection of strip composite materials, thereby reducing the cost of use. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only for this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a three-dimensional illustration of the present invention. Figure 1;

[0021] Figure 2 This is a three-dimensional illustration of the present invention. Figure 2 ;

[0022] Figure 3 This is a three-dimensional illustration of the present invention. Figure 3 ;

[0023] Figure 4 This is a three-dimensional illustration of the present invention. Figure 4 ;

[0024] Figure 5 This is a three-dimensional illustration of the present invention. Figure 5 .

[0025] The diagram is marked as follows:

[0026] 1. Testing table; 2. Vertical support; 3. Middle support plate; 4. Support ring; 5. Square hole; 6. Support arm; 7. Fixing part; 71. Horizontal brace; 72. Horizontal groove; 73. Screw hole; 74. Pressure strip; 75. Preset hole; 76. Screw; 8. Driving part; 81. Wedge-shaped push block; 82. Guide groove; 83. Horizontal through hole; 84. Guide rod; 85. Telescopic cylinder; 86. Slider; 9. Peeling part. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to specific embodiments.

[0028] It should be noted that, unless otherwise defined, the technical or scientific terms used in this utility model should have the ordinary meaning understood by one of ordinary skill in the art to which this utility model pertains. The terms "first," "second," and similar terms used in this utility model do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0029] like Figures 1 to 5 As shown, a peeling test device for aerospace composite materials includes a test table 1, a central support 3 and two vertical supports 2 fixed on the test table 1.

[0030] The support ring 4 is fixed on the middle bracket 3 and has several square holes 5, which connect the inside and outside of the support ring 4.

[0031] The support arm 6 is radially inserted into the square hole 5.

[0032] A drive unit 8 is located between two vertical supports 2 to synchronously push several support arms 6 to perform radial extension and retraction movements.

[0033] A fixing part 7 is provided at the end of the support arm 6. The fixing part 7 includes a cross brace 71 and a cross groove 72 provided on the cross brace 71. A pressure strip 74 is provided in the cross groove 72. A screw hole 73 is provided at the midpoint of the cross groove 72. A pre-set hole 75 corresponding to the screw hole 73 is provided on the pressure strip 74. The end of the strip composite material is pressed between the pressure strip 74 and the cross groove 72 by screws 76. In this way, the end of the strip composite material that is reserved at the peeling start end is fixed first. Then, the other end of the strip composite material is fixed in another fixing part 7. In this way, the strip composite material can be circumferentially spread. When fixing the annular composite material, the annular composite material is first circumferentially fitted onto the outside of several fixing parts 7. It is not necessary for the composite material to pass through the pressure strip 74 and the transverse groove 72, but to pass directly through the outside of the pressure strip 74. Then, the driving part 8 drives several support arms 6 to extend radially, so that the annular composite material can be evenly spread circumferentially and tightened and fixed. In this way, annular composite materials of different diameters or strip composite materials of different lengths can be made, expanding the applicable size range. The fixing operation is simple and efficient, and the composite material can be kept under uniform force after being spread.

[0034] like Figure 3 As shown, the cross brace 71 is fixed to the end face of the support arm 6 along the circumference of the support ring 4, and the cross brace 71 is located outside the support ring 4.

[0035] The pressure strip 74 is coaxial with the cross brace 71, and one side of the pressure strip 74 matches the inside of the cross groove 72. This design increases the contact range with the composite material when fixing and supporting the annular or strip composite material, which can improve the uniformity and stability of the stress in the circumferential direction after the composite material is fixed, and avoid the composite material from being poorly supported at a certain position, which would affect the uniformity of peeling.

[0036] like Figures 2 to 5As shown, the drive unit 8 includes a wedge-shaped push block 81 coaxially inserted into the support ring 4. Several guide grooves 82 are arranged in parallel on the outer circumference of the wedge-shaped push block 81. A slider 86 is slidably arranged in the guide grooves 82. One side of the slider 86 is fixed on the support arm 6 near one end of the wedge-shaped push block 81. Two transverse holes 83 are axially arranged on one side of the wedge-shaped push block 81. A guide rod 84 is inserted into the transverse hole 83. The two ends of the guide rod 84 are respectively fixed on two vertical supports 2. A telescopic cylinder 85 is fixed on one of the vertical supports 2. The output end of the telescopic cylinder 85 is fixed on one end face of the wedge-shaped push block 81.

[0037] The wedge-shaped pusher 81 has a conical shape, and the small-diameter end of the wedge-shaped pusher 81 is inserted into the support ring 4. The wedge-shaped pusher 81 can be pushed axially and linearly by the telescopic cylinder 85 to move back and forth, so that the diameter of the wedge-shaped pusher 81 in the support ring 4 can gradually increase or decrease, thereby simultaneously pushing several support arms 6 to extend or shorten radially outward. This can increase or decrease the distance between two adjacent fixing parts 7, so as to fix annular composite materials of different diameters or strip composite materials of different lengths, thus expanding the applicable size range of composite materials.

[0038] The guide grooves 82 are arranged circumferentially on the conical arc surface outside the wedge-shaped pusher 81, and the vertical cross-section of the guide grooves 82 is convex.

[0039] The shape and size of the slider 86 are matched with the shape and size of the vertical section of the guide groove 82. With this design, the slider 86 can slide in the guide groove 82 to realize the axial displacement change of the wedge push block 81 into the radial position change of the support arm 6. In this way, several support arms 6 can be pushed to move radially in a synchronous manner, making it suitable for annular or strip composite materials of different sizes.

[0040] like Figure 1 , Figure 4 and Figure 5As shown, the peeling detection device also includes a peeling section 9 coaxially mounted on the detection table 1. The peeling section 9 is used for circumferential peeling of the composite material. The peeling section 9 includes an outer ring fixed on the detection table 1 and inclined support plates fixed to both sides of the outer ring. The bottom end of the inclined support plates is fixed on the detection table 1. The outer ring and the support ring 4 are coaxial. The inner wall of the outer ring is provided with a ring through groove. An external toothed ring is slidably provided in the ring through groove. An installation ring is rotatably sleeved inside the outer ring. The support ring 4 is coaxially located inside the installation ring. The inner wall of the external toothed ring is fixedly connected to the outside of the installation ring. A spur gear and a motor for driving the spur gear are rotatably mounted on the detection table 1. The tooth surface of the spur gear meshes with the tooth surface of the external toothed ring. A tensile detector is provided on the inner wall of the installation ring. The output end is equipped with a U-shaped seat, and a bidirectional lead screw is rotatably mounted inside the U-shaped seat. The threads at both ends of the bidirectional lead screw are in opposite directions, and clamping blocks are threaded onto both ends of the bidirectional lead screw. By rotating the bidirectional lead screw and driving the two clamping blocks to move closer to each other, the reserved end of the layer of material to be peeled off on the composite material can be placed between the two clamping blocks for clamping and fixing. Then, the motor is started to drive the mounting ring to rotate and drive one end of the layer of material to be peeled off to move synchronously, thus completing the peeling operation. At the same time, during the peeling process, the tensile force at two time points within the same time interval can be read and saved by a tensile force detector to improve the comprehensiveness of data collection, reduce data processing errors, and improve the accuracy of peel strength detection.

[0041] Working principle: When fixing the strip composite material, first place the end of the strip composite material with the peeling start point reserved between one of the pressure strips 74 and the transverse groove 72. Then, use screws 76 to pass through the preset holes 75 on the pressure strip 74, the reserved end of the composite material, and thread them into the screw holes 73, and fix the pressure strip 74 to fix the reserved end of the composite material. Then fix the other end of the strip composite material in another fixing part 7. In this way, the strip composite material can be stretched and tightened circumferentially. When fixing the annular composite material, first circumferentially fit the annular composite material on the outside of several fixing parts 7. It is not necessary for the composite material to pass through the pressure strip 74 and the transverse groove 72, but to pass directly through the outside of the pressure strip 74. By driving several support arms 6 radially through the drive unit 8, the annular composite material can be evenly spread and tightened around its circumference. This allows for the production of annular composite materials of different diameters or strip composite materials of different lengths, expanding the applicable size range. The fixing operation is simple and efficient, and the composite material can maintain uniform force after being spread. After the composite material is fixed, the pre-peeled end of the composite material is clamped and fixed between two clamping blocks. Then, the motor is started to drive the mounting ring and clamping blocks to rotate synchronously until the peeling is completed and the machine stops. The tensile detector will read and save the tensile force at each time point during the peeling process, improving the comprehensiveness of data collection, reducing the error range of data processing, and improving the accuracy of peel strength detection.

[0042] Those skilled in the art should understand that the discussion of any of the above embodiments is merely exemplary and is not intended to imply that the scope of the present invention (including the claims) is limited to these examples; within the framework of the present invention, the technical features of the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations of the different aspects of the present invention as described above, which are not provided in the details for the sake of brevity.

[0043] This utility model is intended to cover all such substitutions, modifications, and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A peel testing device for aerospace composite materials, comprising a testing table (1) and a central support (3) and two vertical supports (2) fixed on the testing table (1), characterized in that: The support ring (4) is fixed on the middle bracket (3) and has several square holes (5). A support arm (6) is radially inserted into a square hole (5); A drive unit (8) is located between two vertical supports (2) for synchronously pushing several arms (6) to perform radial telescopic movements. A fixing part (7) is provided at the end of the support arm (6). The fixing part (7) includes a cross brace (71) and a cross groove (72) provided on the cross brace (71). A pressure strip (74) is provided in the cross groove (72). A screw hole (73) is provided at the midpoint inside the cross groove (72). A preset hole (75) corresponding to the screw hole (73) is provided on the pressure strip (74). The end of the strip composite material is pressed between the pressure strip (74) and the cross groove (72) by a screw (76).

2. The peel detection device for aerospace composite materials according to claim 1, characterized in that, The cross brace (71) is fixed to the end face of the arm (6) along the circumference of the support ring (4), and the cross brace (71) is located outside the support ring (4).

3. The peeling detection device for aerospace composite materials according to claim 2, characterized in that, The pressure strip (74) is coaxial with the cross brace (71), and one side of the pressure strip (74) matches the interior of the cross groove (72).

4. The peel detection device for aerospace composite materials according to claim 1, characterized in that, The drive unit (8) includes a wedge-shaped push block (81) coaxially inserted into the support ring (4). The wedge-shaped push block (81) has several guide grooves (82) arranged in parallel on its outer circumference. A slider (86) is slidably arranged in the guide grooves (82). One side of the slider (86) is fixed on the support arm (6) near one end of the wedge-shaped push block (81). The wedge-shaped push block (81) has two transverse through holes (83) axially arranged on one side. A guide rod (84) is inserted in the transverse through hole (83). The two ends of the guide rod (84) are respectively fixed on two vertical supports (2). A telescopic cylinder (85) is fixed on one of the vertical supports (2). The output end of the telescopic cylinder (85) is fixed on one end face of the wedge-shaped push block (81).

5. The peel detection device for aerospace composite materials according to claim 4, characterized in that, The wedge-shaped pusher (81) has a conical shape, and the smaller diameter end of the wedge-shaped pusher (81) is inserted into the support ring (4).

6. The peel detection device for aerospace composite materials according to claim 4, characterized in that, The guide groove (82) is circumferentially arranged on the conical arc surface outside the wedge-shaped pusher (81), and the vertical cross-section of the guide groove (82) is convex.

7. The peel detection device for aerospace composite materials according to claim 6, characterized in that, The shape and size of the slider (86) match the shape and size of the vertical cross section of the guide groove (82).

8. The peeling detection device for aerospace composite materials according to claim 1, characterized in that, The peeling detection device also includes a peeling part (9) coaxially disposed on the detection stage (1), the peeling part (9) being used for circumferential peeling of the composite material.

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