Clamping tool for aviation composite board detection

Abstract

The utility model discloses an aviation composite board detection clamping tool, which belongs to the technical field of composite board detection, and comprises a detection table and nut seats oppositely arranged on the detection table, and the detection table is provided with a driving part for driving the two nut seats to move close to each other or away from each other. Supporting frames are rotationally arranged on the opposite surfaces of the two nut seats, and the clamping parts are arranged on the supporting frames and used for clamping and fixing the boundary of the aviation composite board. According to the clamping device, the two bearing parts which are hinged to each other are arranged between the two clamping parts, the bearing area between the two clamping parts is increased, the width edge of the aviation composite board with the large length can be clamped, and the length edge of the aviation composite board with the large length can also be clamped; concave deformation of the middle of the aviation composite board due to large span is avoided, and detection data precision is prevented from being affected.

Description

TECHNICAL FIELD

[0001] The utility model relates to composite board detection technical field, concretely to aviation composite board detection clamping tool. BACKGROUND

[0002] Aviation composite board is two or more than two new material components optimized combination. Aviation composite board has all the properties of combined materials, and its overall performance is much better than that of the board made of single material. Due to the excellent performance of aviation composite board, and also can be customized according to the performance requirements, it is widely used in performance automobile, aerospace and other fields. Aviation composite board needs to detect the reliability of its related performance before leaving the factory, and needs to be fixed by using clamping tool, so as to reduce the influence of external force on aviation composite board detection data precision.

[0003] The existing patent application number: 202121921416.9 discloses a kind of composite board weld detection fixed clamp, the device can be clamped and fixed from the two sides of composite board by the cooperation of two placement plates and the clamping plate in placement plate, and cooperate with driving cylinder, by pushing and pulling the movable rod articulated between the output end of driving cylinder and connecting plate, so that connecting plate is close to each other or far away on guide rod, to facilitate clamping and fixing composite board of different length-width size.In the above prior art, when the length span of the device is relatively large and the thickness of the composite board is relatively thin, the middle of the composite board is not supported, and is easy to be concave to arc surface due to gravity, which affects the precision of composite board detection data. UTILITY MODEL CONTENTS

[0004] The utility model aims at providing aviation composite board detection clamping tool, to solve the problem that the length span of the composite board is relatively large and the thickness is relatively thin, and the middle of the composite board is easy to be concave to arc surface due to gravity, which affects the precision of detection data.

[0005] To achieve the above purpose, the utility model adopts the following technical scheme:

[0006] The utility model provides a kind of aviation composite board detection clamping tool, including detection table and the nut seat opposite being located on the detection table, the detection table is equipped with the driving part for driving two nut seats to move close to each other or far away, the opposite face of two nut seats is all equipped with support frame, and the aviation composite board detection clamping tool further includes:

[0007] The support frame is equipped with the clamping part for clamping and fixing the boundary of aviation composite board.

[0008] Four supporting parts arranged between the two clamping parts for supporting the surface of the aviation composite panel.

[0009] The clamping part comprises:

[0010] A fixed clamping block fixed on the support frame.

[0011] A support block fixed on the fixed clamping block.

[0012] A connecting block penetrating the guide groove arranged on the support block.

[0013] A movable clamping block fixed on one end of the connecting block.

[0014] The supporting part comprises two support links hingedly connected to each other, one end of the support link is fixedly provided with a support shaft, the opposite surfaces of the fixed clamping block and the movable clamping block are each provided with a horizontal recess, a plurality of shaft holes are arranged in the horizontal recess, the open end of the support shaft penetrates one of the shaft holes, the open end of the support shaft is provided with a insertion hole, and a plug is transversely screwed in the insertion hole.

[0015] Further, the clamping part further comprises:

[0016] An outer protruding block fixed on one side of the fixed clamping block.

[0017] A screw rod rotatably arranged on the top of the outer protruding block.

[0018] A movable block threadedly arranged on the screw rod, the movable block being fixed on the remaining end of the connecting block.

[0019] Further, the support block is located between the movable block and the movable clamping block, and the movable clamping block is located between the opposite surfaces of the two support blocks.

[0020] Further, the plug is arranged along the radial direction of the shaft hole, and the length of the plug is greater than the inner diameter of the shaft hole.

[0021] Further, the supporting part is located between the two movable clamping blocks, and the two supporting parts are oppositely arranged on the movable clamping blocks.

[0022] Further, the supporting part is also located between the two fixed clamping blocks, and the remaining two supporting parts are oppositely arranged on the fixed clamping blocks.

[0023] Further, the aviation composite panel detection clamping tool further comprises a limiting insertion rod slidingly arranged on the nut seat, one end of the limiting insertion rod being inserted into the limiting hole arranged on the support frame.

[0024] Compared with the prior art, the above one or more technical solutions have the following beneficial effects:

[0025] 1. The utility model discloses a bearing part is set between two clamping parts, increases the bearing area between two clamping parts, can be clamped to the width side of the lengthier aviation composite board material, also can be clamped to the length side of the lengthier aviation composite board material, avoids the middle of aviation composite board material because of the larger span and appears the concave deformation, and the detection data precision is affected,

[0026] 2. The utility model discloses a plurality of jack -plug is set up and is matched with the detachable design of support connecting rod, expands the width size upper limit of aviation composite board material that clamping part can clamping fixed, and through the mutual cooperation of clamping part and bearing part, in the size applicable range, can clamping fixed shape regular aviation composite board material also can clamping fixed shape irregular aviation composite board material, expands its applicable range. ACCURACY

[0027] Fig. 1 It is the axonometric drawing of the utility model;

[0028] Fig. 2 It is the axonometric drawing of the utility model clamping part and bearing part;

[0029] Fig. 3 It is the partial section view of the utility model clamping part.

[0030] In the drawing: 1. Detection table;2. Nut seat;3. Driving part;4. Support frame;5. Clamping part;51. Fixed clamp block;52. Support block;53. Outer convex block;54. Screw;55. Movable block;56. Connecting block;57. Guide groove;58. Movable clamp block;6. Bearing part;61. Horizontal recess;62. Shaft hole;63. Support shaft;64. Jack -plug;65. Jack;66. Support connecting rod;7. Limiting hole;8. Limiting plug rod. DETAILED DESCRIPTION

[0031] In order to make the personnel in the technical field better understand the scheme of the application, the technical scheme in the application examples will be clearly and completely described below in combination with the drawings in the application examples.

[0032] As Figs. 1 to 3 The utility model discloses a kind of aviation composite board material detection clamping tool, including detection table 1 and the nut seat 2 being oppositely arranged on detection table 1, detection table 1 is equipped with the driving part 3 for driving two nut seats 2 to move mutually close or away, driving part 3 includes two support seats being oppositely fixed on detection table 1, rotatingly equipped with screw rod between two support seats, the thread direction on the both ends of screw rod is opposite, screw rod is threadedly connected with nut seat 2, one of support seats is equipped with servo motor for driving screw rod rotation, the opposite surface of two nut seats 2 is rotatably equipped with support frame 4, aviation composite board material detection clamping tool further includes:

[0033] The clamping part 5 is arranged on the support frame 4 and used for clamping and fixing the boundary of the aviation composite panel.

[0034] The four supporting parts 6 are arranged between the two clamping parts 5 and used for supporting the surface of the aviation composite panel.

[0035] The clamping part 5 comprises:

[0036] The fixed clamping block 51 is fixed on the support frame 4.

[0037] The support block 52 is fixed on the fixed clamping block 51.

[0038] The connecting block 56 is inserted into the guide groove 57 arranged on the support block 52.

[0039] The movable clamping block 58 is fixed on one end of the connecting block 56.

[0040] The supporting part 6 comprises two support connecting rods 66 hingedly connected to each other, one end of the support connecting rod 66 is fixedly provided with a support shaft 63, the opposite surfaces of the fixed clamping block 51 and the movable clamping block 58 are each provided with a horizontal recess groove 61, a plurality of shaft holes 62 are arranged in the horizontal recess groove 61, the open end of the support shaft 63 is inserted into one of the shaft holes 62, the open end of the support shaft 63 is provided with a insertion hole 64, and a plug pin 65 is transversely screwed into the insertion hole 64.

[0041] Before clamping and fixing the aviation composite panel, the plug pins 65 at the two ends of the two groups of support connecting rods 66 between the two movable clamping blocks 58 can be unscrewed and removed, so that the supporting part 6 can be quickly disassembled, the aviation composite panel can be placed between the two clamping parts 5, and the subsequent clamping and fixing operation of the aviation composite panel is facilitated.

[0042] The two nut seats 2, the support frame 4 and the clamping part 5 are driven to move close to or away from each other by the driving part 3, so that the two groups of support connecting rods 66 transversely distributed relative to each other between the two clamping parts 5 are deformed, that is, the hinge points in the middle of the two groups of support connecting rods 66 move close to or away from each other in a direction perpendicular to the screw rod, so that the two groups of support connecting rods 66 form a rectangular or rhombus supporting surface, which is used for increasing the contact surface with the aviation composite panel, avoiding the problem that the aviation composite panel is deformed in a concave shape in the middle due to a large span, keeping the aviation composite panel in a flat state during detection, avoiding affecting the data detection accuracy of the aviation composite panel, and adjusting the length and width dimensions of the supporting surface formed by the two groups of support connecting rods 66 transversely distributed relative to each other, so as to support the surface of the aviation composite panel of different sizes, and in the applicable size range, any shaped aviation composite panel can be clamped and fixed and supported.

[0043] In this embodiment, the clamping part 5 further comprises:

[0044] The outer protruding block 53 is fixed to one side of the fixed clamping block 51.

[0045] The screw rod 54 is arranged on the top of the outer protruding block 53.

[0046] The movable block 55 is sleeved on the screw rod 54, and the movable block 55 is fixed to the remaining one end of the connecting block 56.

[0047] After the boundary of the aviation composite plate is arranged between the movable clamping block 58 and the fixed clamping block 51, and the supporting part 6 is installed in place, the screw rod 54 is screwed to drive the movable block 55 to move close to the fixed clamping block 51, and the connecting block 56 and the movable clamping block 58 are driven to move synchronously until the boundary of the aviation composite plate is clamped and fixed. A driving member can be arranged at one end of the screw rod to facilitate the synchronous operation of the two screw rods 54 and avoid interfering with the structural stability of the supporting part 6.

[0048] In the embodiment, the supporting block 52 is located between the movable block 55 and the movable clamping block 58, and the movable clamping block 58 is located between the opposite surfaces of the two supporting blocks 52. In this way, the movable clamping block 58 can be driven to move, and the two clamping parts 5 can clamp and fix the two opposite boundaries on the aviation composite plate, avoiding the interference between the operation of adjusting the movement of the movable clamping block 58 and the clamping action, and ensuring the smooth operation of the clamping part 5.

[0049] In the embodiment, the pin 65 is arranged along the radial direction of the shaft hole 62, and the length of the pin 65 is greater than the inner diameter of the shaft hole 62. In this way, the supporting shaft 63 can be limited in the shaft hole 62, and the circumferential freedom of the supporting shaft 63 in the shaft hole 62 is not affected, so that the supporting connecting rod 66 can be deflected, and the spacing between the two clamping parts 5 can be adjusted to synchronously adjust the size of the supporting surface formed by the two supporting parts 6 arranged between the two movable clamping blocks 58 and the two fixed clamping blocks 51, so that the supporting surface can match the surface of the aviation composite plate to be supported.

[0050] In the embodiment, the supporting part 6 is located between the two movable clamping blocks 58, and the two supporting parts 6 are oppositely arranged on the movable clamping block 58.

[0051] The supporting part 6 is also located between the two fixed clamping blocks 51, and the remaining two supporting parts 6 are oppositely arranged on the fixed clamping block 51.

[0052] In this way, the two supporting parts 6 between the two movable clamping blocks 58 and the two supporting parts 6 between the two fixed clamping blocks 51 can form two identical supporting surfaces on both sides of the aviation composite plate, so that the aviation composite plate with a large span can be fixed without deformation and affecting the accuracy of subsequent detection data.

[0053] In the embodiment, the aviation composite board detection clamping tool further comprises a limiting plug rod 8 slidingly sleeved on the nut seat 2, one end of the limiting plug rod 8 is inserted with a limiting hole 7 arranged on the support frame 4, the number of the limiting hole 7 is two, and the two limiting holes 7 are oppositely distributed on the axial sides of the rotating positions of the nut seat 2 and the support frame 4, so that the aviation composite board can be fixed by turning over during the aviation composite board detection process, the two surfaces of the aviation composite board can be comprehensively detected, and the comprehensiveness of the detection data collection is improved.

[0054] The above is only the preferred embodiment of the present application, and the parts not described in the present application can be realized by using or referring to the existing technology. Of course, the above description is not a limitation of the present application, and the present application is not limited to the above examples. Changes, modifications, additions or replacements made by the person skilled in the art within the essential scope of the present application should also belong to the protection scope of the present application.

Claims

1. An aviation composite panel detection clamping tool, comprising a detection table (1) and a nut seat (2) oppositely arranged on the detection table (1), the detection table (1) is provided with a driving part (3) for driving two nut seats (2) to move close to or away from each other, a supporting frame (4) is rotatably arranged on the opposite surface of each of the two nut seats (2), characterized in that, The aviation composite board detection clamping tool further comprises: The clamping part (5) is arranged on the support frame (4) and used for clamping and fixing the boundary of the aviation composite board; Four supporting parts (6) are arranged between the two clamping parts (5) and used for supporting the surface of the aviation composite board; The clamping part (5) comprises: The fixed clamping block (51) is fixed on the support frame (4); The support block (52) is fixed on the fixed clamping block (51); The connecting block (56) is inserted into the guide groove (57) arranged on the support block (52); The movable clamping block (58) is fixed on one end of the connecting block (56); The supporting link (66) is arranged on the opposite surface of the fixed clamping block (51) and the movable clamping block (58) and comprises a support shaft (63) arranged at one end of the supporting link (66), a horizontal recess (61) arranged on the opposite surface of the fixed clamping block (51) and the movable clamping block (58), a plurality of shaft holes (62) arranged in the horizontal recess (61), and a plug hole (64) arranged on the open end of the support shaft (63), wherein a plug pin (65) is transversely screwed in the plug hole (64).

2. The detection and clamping tool for the aviation composite panel according to claim 1, characterized in that: The clamping part (5) further comprises: The outer convex block (53) is fixed on one side of the fixed clamping block (51); The screw rod (54) is rotatably arranged on the top of the outer convex block (53); The movable block (55) is screwed on the screw rod (54) and fixed on the remaining end of the connecting block (56).

3. The detection and clamping tool for the aviation composite panel according to claim 2, characterized in that: The support block (52) is arranged between the movable block (55) and the movable clamping block (58), and the movable clamping block (58) is arranged between the opposite surfaces of the two support blocks (52).

4. The detection and clamping tool for the aviation composite panel according to claim 3, characterized in that: The plug pin (65) is arranged along the radial direction of the shaft hole (62), and the length of the plug pin (65) is greater than the inner diameter of the shaft hole (62).

5. The detection and clamping tool for the aviation composite panel according to claim 4, characterized in that: The supporting part (6) is arranged between the two movable clamping blocks (58), and the two supporting parts (6) are arranged on the opposite surfaces of the movable clamping block (58).

6. The detection and clamping tool for the aviation composite panel according to claim 5, characterized in that: The supporting part (6) is also arranged between the two fixed clamping blocks (51), and the remaining two supporting parts (6) are arranged on the opposite surfaces of the fixed clamping block (51).

7. The detection and clamping tool for the aviation composite panel according to claim 6, characterized in that: The aviation composite board detection clamping tool further comprises a limiting plug rod (8) slidably arranged on the nut seat (2), and one end of the limiting plug rod (8) is inserted into the limiting hole (7) arranged on the support frame (4).

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