Expansion type clamp for aviation part processing test

Abstract

The invention discloses an expansion type clamp for aviation part machining testing, and relates to the technical field of testing devices, the expansion type clamp comprises an expansion core pipe sleeve which is driven to slide for a preset distance along a boring hole formed in the axis of a base, and the section of the port of the first end of the expansion core pipe sleeve is fixedly provided with a folding petal extending to the outer side of the port of the base; a gap groove is formed between every two closure petals, an elastic piece of a wave-shaped structure is arranged in each gap groove, and a hollow soft air bag piece is arranged at the end, facing the inner side of the expansion core pipe sleeve, of each elastic piece; the boring hole is of a circular frustum structure; the device further comprises a detection rod which is fixedly installed, and a probe is rotatably arranged in the detection rod. According to the invention, the contact surface of the to-be-tested part is increased to the maximum, so that the tiny change of the circumference of the part caused by local contact clamping can be avoided, thereby ensuring that the circumference of the aviation part is not deformed due to non-uniform pressure in the processing and testing process of the aviation part.

Description

Technical Field

[0001] The invention relates to the technical field of testing devices, in particular to an expansion clamp for machining and testing aviation parts. Background Art

[0002] This component is a circular component, and its inner and outer rings are both circular structures. It is an important component of the aircraft engine (the specific name of the component is not disclosed in detail). Therefore, after the component is produced, the radius of the inner circle needs to be tested by a testing component to ensure the accuracy of the processed component.

[0003] Referring to Chinese patent, publication number: CN110836648A, a pipeline wall thickness detection device and detection method are disclosed.

[0004] And, Chinese patent, publication number: CN110201895B, discloses a bearing inner ring aperture detection device.

[0005] In the prior art including the above two patents, when performing the inner and outer ring circumference detection, the component needs to be clamped on the fixture, but common fixtures include bench vises, three-jaw chucks, etc. Since the component is a hollow pipe, and the clamping provided by the fixture is a local surface contact method, the force applied to the part of the component during the clamping process will cause the part to be locally stressed, so it is easy to cause micro deformation of the circumference of the component under the clamping force. Summary of the invention

[0006] The purpose of the present invention is to provide an expansion fixture for machining and testing aviation parts to solve the above-mentioned problems.

[0007] In order to achieve the above object, the present invention provides the following technical solutions:

[0008] An expansion fixture for machining and testing aviation parts, comprising an expansion sleeve driven to slide a predetermined distance in a boring hole opened along the axis of a base, and a closing flap extending to the outside of the base port is fixedly arranged on the cross section of the first end port of the expansion sleeve;

[0009] A gap groove is formed between every two of the closed petals, an elastic member with a wave-shaped structure is arranged in the gap groove, and a hollow soft airbag member is arranged at one end of the elastic member facing the inner side of the expansion core sleeve;

[0010] The boring hole is a circular frustum structure;

[0011] It also includes a fixedly installed detection rod, in which a probe is rotatably arranged, a waist groove for the probe to extend out is opened on the detection rod, a compression spring is fixedly arranged in the waist groove, and a pressure sensor is arranged at one end of the compression spring, and the detection surface of the pressure sensor is under negative pressure on the probe.

[0012] Preferably, the elastic member is distributed close to the inner wall of one side of the gap groove;

[0013] It also includes an annular member assembled in the base and assembled with the elastic member near one end of the closing petal;

[0014] When the circumferential radius of the plurality of closed petals is reduced, one end of the elastic member connected to the annular member fits against the outer wall of the other side of the gap groove to be inclined.

[0015] Preferably, the inclination directions of two adjacent elastic members are opposite.

[0016] Preferably, the cross section of the elastic member is a long leg side and a short leg side, and the angle between the long leg side and the short leg side is 90°;

[0017] The inner angle extension lines of the plurality of elastic members intersect at one point, and the soft airbag member is arranged on the inner angle;

[0018] The long legs of two adjacent elastic members are arranged adjacent to each other.

[0019] Preferably, the ends of the long supporting leg and the short supporting leg are both provided with soft rubber contacts.

[0020] Preferably, the soft airbag component is in a pendant shape and is divided into a wide end and a narrow end according to the structure, and the wide end extends outward of the elastic component by a predetermined length.

[0021] Preferably, the annular member is fixedly installed, and a wedge-shaped guide member is provided on its inner wall, and the elastic member is slidably assembled on the wedge-shaped guide member through a horizontal connecting member fixedly installed at the end;

[0022] The horizontal connecting member is an arc-shaped elastic metal plate;

[0023] It also includes an arc-shaped elastic pushing member, one end of which is connected to the horizontal connecting member and moves synchronously with the axial movement of the closing petal to push the horizontal connecting member to climb along the wedge-shaped guide member.

[0024] As a preferred embodiment, it further comprises a synchronous member which is slidably assembled in the base and is always in contact with the expansion core sleeve, wherein a supporting member is slidably arranged in the synchronous member;

[0025] An equidistant spring for pushing the supporting member is arranged in the synchronizer;

[0026] A shifting rod is rotatably arranged in the synchronous member, the shaft rod on the supporting member is in contact with the surface of the shifting rod, and one end of the shifting rod is fixedly connected with the arc-shaped elastic pushing member.

[0027] Preferably, the lever is divided into a labor-saving arm and a labor-intensive arm according to function, and the labor-intensive arm is connected to the arc-shaped elastic pushing member.

[0028] In the above technical scheme, the invention provides an expansion clamp for processing and testing aviation parts, which has the following beneficial effects: after the part to be tested is inserted from the end where the closing flap is located, the expansion core sleeve is driven to push and move, and during the movement of the expansion core sleeve, the multiple closing flaps are synchronously reduced due to the decreasing radius of the boring hole, and the circumference radius of the multiple closing flaps is reduced, so that the clamp is clamped on the part. Synchronously, the elastic part moves synchronously with the closing flap, so that the soft airbag part is deformed by contacting the part to be tested as the circumference radius of the multiple closing flaps is reduced, so that the contact surface of the part to be tested is increased to the maximum, thereby avoiding the occurrence of micro changes in the circumference of the part due to local force during the clamping process. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0030] Figure 1 An overall three-dimensional schematic diagram provided for an embodiment of the present invention;

[0031] Figure 2 A schematic diagram of the structure of an expansion core sleeve, an elastic member and an annular member provided in an embodiment of the present invention;

[0032] Figure 3 A schematic diagram of the structure of an expansion core sleeve and an elastic member provided in an embodiment of the present invention;

[0033] Figure 4 The embodiment of the present invention provides Figure 1 Schematic diagram of the cross-section structure;

[0034] Figure 5 A schematic diagram of the position structure of the elastic member in the gap groove provided by an embodiment of the present invention;

[0035] Figure 6 A schematic cross-sectional structure diagram of an annular member and an expansion core sleeve provided in an embodiment of the present invention;

[0036] Figure 7A schematic diagram of the shape and structure of an elastic member provided in an embodiment of the present invention;

[0037] Figure 8 A schematic diagram of the distribution structure of two adjacent arc-shaped elastic pushing members provided in an embodiment of the present invention;

[0038] Fig. 9 A schematic diagram of the implementation structure of the detection rod provided by an embodiment of the present invention;

[0039] Fig.10 A schematic diagram of the cross-sectional structure of a detection rod provided in an embodiment of the present invention.

[0040] Description of reference numerals:

[0041] 1. Base; 11. Boring hole; 2. Expanding core sleeve; 21. Clearance groove; 23. Closing flap; 3. Elastic part; 31. Soft airbag part; 32. Long support foot edge; 33. Short support foot edge; 34. Horizontal connecting part; 4. Ring part; 41. Wedge-shaped guide part; 5. Arc-shaped elastic push part; 6. Synchronous part; 61. Support part; 62. Equidistant spring; 63. Push rod; 64. Push rod; 7. Detection rod; 71. Probe; 72. Compression spring; 73. Pressure sensor; 100. Soft rubber contact. DETAILED DESCRIPTION

[0042] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings.

[0043] like Figure 1-10 As shown, an expansion fixture for machining and testing aviation parts includes an expansion core sleeve 2 driven to slide a predetermined distance in a boring hole 11 opened along the axis of a base 1, and a closing flap 23 extending to the outside of the port of the base 1 is fixedly provided on the cross section of the first end of the expansion core sleeve 2;

[0044] A gap groove 21 is formed between each two closed petals 23, and an elastic member 3 with a wave-shaped structure is arranged in the gap groove 21, and a hollow soft airbag member 31 is arranged at one end of the elastic member 3 facing the inner side of the expansion core sleeve 2;

[0045] The boring hole 11 is a circular frustum structure;

[0046] It also includes a fixedly installed detection rod 7, in which a probe 71 is rotatably arranged, the detection rod 7 is provided with a waist groove for the probe 71 to extend, a compression spring 72 is fixedly arranged in the waist groove, and a pressure sensor 73 is arranged at one end of the compression spring 72, and the detection surface of the pressure sensor 73 is under negative pressure on the probe 71.

[0047] Specifically, the outer wall of the closing flap 23 extending out of the boring hole 11 in the above embodiment is provided with a protrusion, and when the expansion sleeve 2 is in the default state, the protrusion abuts against the end surface of the base 1.

[0048] Furthermore, the movement of the expansion core sleeve 2 in the above embodiment can be driven by a hydraulic or pneumatic push rod, or by a stepping screw motor or other driving methods known to those skilled in the art.

[0049] Furthermore, the elastic member 3 in the embodiment is as follows Figure 7 As shown, when the circumference radius of the multiple closed petals 23 shrinks, the closed petals 23 are attached to the surface of the aviation component to be tested, and deformed during the attachment, so that the entire closed petal 23 is completely attached to the surface of the aviation component, and as the closed petal 23 is completely attached, the elastic member 3 is also attached to the surface of the aviation component synchronously with the closed petal 23, and as the compression increases, the angle of the wave of the elastic member 3 increases, that is, the elastic member 3 is a continuously connected V-shaped plate, and the increase in the angle of the wave means that the angle of the V-shaped plate increases. The elastic member 3 is an elastic metal plate, such as stainless steel or elastic steel.

[0050] Furthermore, the detection rod 7 is moved by an xy-axis moving mechanism (which belongs to the prior art and will not be disclosed in detail).

[0051] When the aviation component to be tested is clamped by the multiple closed petals 23 with the circumferential radius contracted, the xy-axis moving mechanism drives the probe 71 to move into the inner ring of the aviation component and contact the inner wall of the aviation component, and the base is driven by the rotary motor to rotate one circle. During one circle, when a bulge appears on the inner ring of the aviation component, the probe 71 will move. Fig.10 As shown, the upward movement drives the compression spring 72 to be stressed, and the pressure sensor 73 detects the pressure applied by the displacement of the probe 71, thereby realizing the circumferential detection of the inner and outer rings of the aviation parts.

[0052] It should be noted that the control program, the driving of the xy-axis moving mechanism and the detection principle of the pressure sensor 73 involved in the above embodiments are all common technical knowledge known to those skilled in the art.

[0053] In the above technology, after the component to be tested is inserted from the end where the closing flap 23 is located, the expansion core sleeve 2 is driven to push and move, and during the movement of the expansion core sleeve 2, the multiple closing flaps 23 are synchronously reduced due to the decreasing radius of the boring hole 11, and the circumference radius of the multiple closing flaps 23 is reduced, so that the clamp is on the component. Synchronously, the elastic member 3 moves synchronously with the closing flap 23, so that the soft airbag member 31 is deformed by contacting the component to be tested as the circumference radius of the multiple closing flaps 23 is reduced, so that the contact surface of the component to be tested is increased to the maximum, thereby avoiding the occurrence of micro changes in the circumference of the component due to local force during the clamping process.

[0054] As an embodiment further provided by the present invention, the elastic member 3 is distributed on the inner wall of one side close to the gap groove 21;

[0055] It also includes a ring member 4 assembled in the base 1 and assembled with the elastic member 3 near the end of the closing petal 23;

[0056] When the circumferential radius of the plurality of closed petals 23 is reduced, the elastic member 3 and the annular member 4 are connected at one end to fit against the outer wall of the other side of the gap groove 21 to form an inclined shape.

[0057] Specifically, the elastic member 3 is in a vertical state in the default state in the embodiment. When the expansion core sleeve 2 is driven to push and move, the multiple closing petals 23 are synchronously reduced by the decreasing radius of the boring hole 11 so as to completely fit on the surface of the aviation component.

[0058] During the process, the annular member 4 is driven to rotate, so that the elastic member 3 and the annular member 4 are connected to one end and fit the outer wall of the other side of the gap groove 21 in an inclined shape, arranged in a clockwise direction. During the tilting process, the turnover damping force and the axial sliding damping force applied by the elastic member 3 can be increased, so that the multiple closed petals 23 are completely fitted on the surface of the fitted aviation parts to share the force together, thereby increasing the contact area of ​​the inserted aviation parts, and at the same time, in cooperation with the elastic member 3, the clamping and locking force of the aviation parts is increased.

[0059] As another embodiment further provided by the present invention, the cross section of the elastic member 3 is a long leg side 32 and a short leg side 33, and the angle between the long leg side 32 and the short leg side 33 is 90°;

[0060] The inner angle extension lines of the multiple elastic members 3 intersect at one point, and the soft airbag member 31 is arranged on the inner angle;

[0061] The long legs 31 of two adjacent elastic members 3 are arranged adjacent to each other;

[0062] Soft rubber contacts 100 are provided at the ends of the long leg edge 32 and the short leg edge 33 .

[0063] Specific, combined Figure 5 As shown, during the implementation process, multiple closing petals 23 are completely attached to the surface of the aviation component, and the entire elastic member 3 moves synchronously with the closing petals 23 to fit the aviation component. As the elastic member 3 fits the aviation component, it is deformed, so that the angle between the long support leg 32 and the short support leg 33 increases from 90°, thereby increasing the separation angle between the long support leg 32 and the short support leg 33. During the process, the soft rubber contact 100 contacts the aviation component and is deformed due to the separation of the long support leg 32 and the short support leg 33.

[0064] As the angle between the long leg edge 32 and the short leg edge 33 increases, the airbag component 31 contacts the aviation component, thereby forming a three-point contact, further optimizing the damping force applied by the elastic component 3 to the aviation component.

[0065] Secondly, combined Figure 5 As shown, the soft airbag component 31 is round and pendant-shaped, and is divided into a wide end and a narrow end according to the structure, and the wide end extends to a predetermined length (1mm-2mm) outside the elastic component 3. As the angle between the long leg edge 32 and the short leg edge 33 increases, the airbag component 31 contacts the aviation component, and the contact surface between the deformed soft airbag component 31 and the aviation component is further increased, so that the damping force applied by the elastic component 3 to the aviation component is further optimized.

[0066] As another embodiment further provided by the present invention, the annular member 4 is fixedly installed, and a wedge-shaped guide member 41 is provided on its inner wall, and the elastic member 3 is slidably assembled on the wedge-shaped guide member 41 through a horizontal connecting member 34 fixedly installed at the end;

[0067] The horizontal connecting member 34 is an arc-shaped elastic metal plate;

[0068] It also includes an arc-shaped elastic pushing member 5, one end of which is connected to the horizontal connecting member 34 and moves synchronously with the axial movement of the closing petals 23 to push the horizontal connecting member 34 to climb along the wedge-shaped guide member 41.

[0069] Specifically, in the embodiment, the annular member 4 is fixed in the base 1, and then when the expansion core sleeve 2 is driven to move, it moves toward Figure 1 As shown in the right side movement, after moving to the maximum range of motion, the multiple closed petals 23 are completely attached to the surface of the aviation component, and the entire elastic member 3 moves synchronously with the closed petals 23 to fit the aviation component. During the process, the arc-shaped elastic push member 5 is divided into a vertical part and an arc-shaped part according to the structure, and the arc-shaped part is connected to the horizontal connecting member 34. When the expansion core sleeve 2 is driven to move, the arc-shaped elastic push member 5 pulls the arc-shaped part to deform, so that the elastic member 3 and the annular member 4 are connected to one end to fit the outer wall of the other side of the gap groove 21 to be inclined.

[0070] Furthermore, during the process, as the elastic member 3 is deformed by fitting the aviation component, the angle between the long leg edge 32 and the short leg edge 33 increases from 90°, and during the process, the soft rubber contact 100 contacts the aviation component and deforms because the long leg edge 32 and the short leg edge 33 are separated. Thus, the contact area with the inserted aviation component is increased, and the clamping and locking force of the aviation component is also increased in cooperation with the elastic member 3.

[0071] Furthermore, the wedge-shaped guide member 41 in the embodiment includes a low position and a high position, the high position is close to the axis of the expansion core sleeve 2, and the low position is far from the axis of the expansion core sleeve 2. In the default state, that is, when the elastic member 3 is in a vertical state, the horizontal connecting member 34 is located at the low position of the wedge-shaped guide member 41, and as the multiple closed petals 23 are completely attached to the surface of the attached aviation component, the elastic member 3 and one end of the horizontal connecting member 34 are moved toward the axis to apply a squeezing force on the axial direction of the aviation component.

[0072] As another embodiment further provided by the present invention, the inclined directions of two adjacent elastic members 3 are opposite.

[0073] Specific, combined Figure 8 As shown, in the embodiment, the inner arc tops of the arc parts of two adjacent arc-shaped elastic push members 5 are pulled in opposite directions, so that the two adjacent elastic members 3 are pulled closer to each other at one end connected to the horizontal connecting member 34, so that one is tilted clockwise and the other is tilted counterclockwise, thereby applying two opposite axial rotation damping forces. In this way, the contact area with the inserted aviation parts is increased, and the clamping and locking force of the aviation parts is also increased in cooperation with the elastic member 3.

[0074] As another embodiment further provided by the present invention, it also includes a synchronous member 6 which is slidably assembled in the base 1 and is always in contact with the expansion core sleeve 2, and a supporting member 61 is slidably arranged in the synchronous member 6;

[0075] An equidistant spring 62 is provided in the synchronizer 6 for pushing the supporting member 61;

[0076] A lever 63 is rotatably disposed in the synchronous member 6 , and the shaft on the supporting member 61 is in contact with the surface of the lever 63 , and one end of the lever 63 is fixedly connected to the arc-shaped elastic pushing member 5 .

[0077] Specifically, in the above embodiment, the lever 63 is divided into a labor-saving arm and a labor-intensive arm according to their functions, and the labor-intensive arm is slidably connected to a push rod 64 that moves vertically in the synchronizer 6, and the vertical portion of the arc-shaped elastic push member 5 is fixedly connected to the push rod 64.

[0078] Furthermore, the hydraulic or pneumatic push rod drives the synchronous member 6 to slide in the base 1, so that the expansion sleeve 2 is driven to push and move. During the pushing process, the aviation component to be tested will contact the supporting member 61, so that the supporting member 61 moves with the movement of the expansion sleeve 2, that is, the expansion sleeve 2 moves in opposite directions to the supporting member 61, so that the supporting member 61 exerts force on the effort arm of the lever 63, so that the effort arm is lifted, thereby pushing the arc-shaped elastic pushing member 5 to move, thereby deforming. During the process, the pushing horizontal connecting member 34 is located at the low position of the wedge-shaped guide member 41, and as the multiple closed petals 23 are completely attached to the surface of the aviation component, the elastic member 3 and one end of the horizontal connecting member 34 are moved toward the axis to apply an extrusion force on the axial diameter direction of the aviation component. One is tilted clockwise and the other is tilted counterclockwise, thereby applying two opposite axial rotation damping forces.

[0079] Furthermore, as the elastic member 3 is finally deformed by being attached to the aviation component, the angle between the long leg edge 32 and the short leg edge 33 increases from 90°, and during the process, the soft rubber contact 100 contacts the aviation component and deforms because the long leg edge 32 and the short leg edge 33 are separated. This increases the contact area with the inserted aviation component, and also increases the clamping and locking force of the aviation component in cooperation with the elastic member 3.

[0080] The above description is only by way of illustration of certain exemplary embodiments of the present invention. It is undoubted that those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. An expansion fixture for machining and testing aviation parts, characterized in that: It comprises an expansion sleeve (2) which is driven to slide a predetermined distance in a boring hole (11) opened along the axis of a base (1), and a closing flap (23) extending to the outside of the port of the base (1) is fixedly provided on the cross section of the first end port of the expansion sleeve (2); A gap groove (21) is formed between each two of the closed petals (23), an elastic member (3) with a wave-shaped structure is arranged in the gap groove (21), and a hollow soft airbag member (31) is arranged at one end of the elastic member (3) facing the inner side of the expansion core sleeve (2); The boring hole (11) is a circular frustum structure; It also comprises a fixedly mounted detection rod (7), a probe (71) being rotatably arranged in the detection rod (7), a waist groove through which the probe (71) extends out being provided on the detection rod (7), a compression spring (72) being fixedly arranged in the waist groove, a pressure sensor (73) being arranged at one end of the compression spring (72), and a detection surface of the pressure sensor (73) exerting negative pressure on the probe (71).

2. The expansion fixture for machining and testing aviation parts according to claim 1, characterized in that: The elastic member (3) is distributed on the inner wall of one side close to the gap groove (21); It also includes an annular member (4) assembled in the base (1) and assembled with the elastic member (3) at one end close to the closing flap (23); When the circumferential radius of the plurality of closed petals (23) is reduced, one end of the elastic member (3) connected to the annular member (4) fits against the outer wall of the other side of the gap groove (21) to form an inclined shape.

3. The expansion fixture for machining and testing aviation parts according to claim 2, characterized in that: The cross section of the elastic member (3) comprises a long support leg (32) and a short support leg (33), and the angle between the long support leg (32) and the short support leg (33) is 90°; The extended lines of the inner angles of the plurality of elastic members (3) intersect at one point, and the soft airbag member (31) is arranged on the inner angle; The long supporting legs (31) of two adjacent elastic members (3) are arranged adjacent to each other.

4. The expansion fixture for machining and testing aviation parts according to claim 3, characterized in that: Soft rubber contacts (100) are provided at the ends of the long supporting foot edge (32) and the short supporting foot edge (33).

5. The expansion fixture for machining and testing aviation parts according to claim 3, characterized in that: The soft airbag component (31) is round and pendant-shaped, and is divided into a wide end and a narrow end according to the structure, and the wide end extends outside the elastic component (3) by a predetermined length.

6. The expansion fixture for machining and testing aviation parts according to claim 2, characterized in that: The annular member (4) is fixedly installed, and a wedge-shaped guide member (41) is provided on its inner wall. The elastic member (3) is slidably assembled on the wedge-shaped guide member (41) via a horizontal connecting member (34) fixedly installed at the end; The horizontal connecting member (34) is an arc-shaped elastic metal plate; It also includes an arc-shaped elastic pushing member (5), one end of which is connected to the horizontal connecting member (34) and moves synchronously with the axial movement of the closing petal (23) to push the horizontal connecting member (34) to climb along the wedge-shaped guide member (41).

7. The expansion fixture for machining and testing aviation parts according to claim 6, characterized in that: The inclination directions of two adjacent elastic members (3) are opposite.

8. The expansion fixture for machining and testing aviation parts according to claim 6, characterized in that: It also includes a synchronous member (6) which is slidably assembled in the base (1) and is always in contact with the expansion core sleeve (2), and a supporting member (61) is slidably arranged in the synchronous member (6); An equidistant spring (62) is provided in the synchronizer (6) for pushing the supporting member (61); A lever (63) is rotatably arranged inside the synchronous member (6), the shaft on the supporting member (61) is in contact with the surface of the lever (63), and one end of the lever (63) is fixedly connected to the arc-shaped elastic pushing member (5).

9. The expansion fixture for machining and testing aviation parts according to claim 8, characterized in that: The lever (63) is divided into a labor-saving arm and a labor-intensive arm according to function, and the labor-intensive arm is connected to the arc-shaped elastic pushing member (5).

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