An expansion clamp for testing of an aeronautical component

Abstract

The application discloses an expansion type clamp for aviation part machining test, and relates to the technical field of test devices, which comprises a core pipe sleeve that is driven to slide in a borehole at the center of a base by a predetermined distance, a first end port of the core pipe sleeve is fixedly provided with a folding lobe extending to the outside of a base port, a gap groove is formed between every two folding lobes, an elastic member in a wave shape structure is arranged in the gap groove, a soft air bag member is arranged at one end of the core pipe sleeve, the borehole is in a circular conical structure, a detection rod is fixedly arranged, and a probe is rotatably arranged in the detection rod. The application can increase the contact surface of the part to be tested to the maximum, can avoid the change of the circumference of the part caused by local contact and clamping, and can ensure that the circumference of the aviation part will not be deformed due to uneven pressure during the machining test of the aviation part.

Description

Technical Field

[0001] This invention relates to the field of testing equipment technology, and more specifically to an expansion fixture for testing the processing of aerospace parts. Background Technology

[0002] This component is a circular part, with both its inner and outer rings being circular structures. It is an important component of an aero-engine (the specific name of the component will not be disclosed in detail). Therefore, after the component is manufactured, the radius of its inner circle needs to be tested by an inspection component to ensure the accuracy of the machined component.

[0003] Referring to Chinese Patent Publication No. CN110836648A, a device and method for detecting pipe wall thickness are disclosed.

[0004] And, Chinese Patent, Publication No.: CN110201895B, discloses a bearing inner ring bore diameter testing device.

[0005] In the prior art, including the two patents mentioned above, when performing inner and outer circumference inspection, the component needs to be clamped on a tooling fixture. However, common tooling fixtures include bench vises and three-jaw chucks. Since the component is a hollow tube, and the clamping provided by the tooling fixture is a localized surface contact method, applying force to a localized area of ​​the component during clamping will cause localized stress on the component, making it prone to minute deformation of the component's circumference under clamping force. Summary of the Invention

[0006] The purpose of this invention is to provide an expansion fixture for processing and testing aerospace parts, in order to solve the above-mentioned problems.

[0007] To achieve the above objectives, the present invention provides the following technical solution:

[0008] An expansion fixture for processing and testing aerospace parts includes an expansion core sleeve that slides a predetermined distance within a boring hole opened along the axis of a base. A closing flap extending to the outside of the base port is fixedly provided on the cross-section of the first end port of the expansion core sleeve.

[0009] A gap groove is formed between each two closing petals. An elastic element with a wave-shaped structure is provided in the gap groove, and a hollow soft airbag is provided at the end of the elastic element facing the inner side of the expansion tube sleeve.

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

[0011] It also includes a fixedly installed detection rod, in which a probe is rotatably installed. The detection rod has a groove on which the probe extends. A compression spring is fixedly installed in the groove, and a pressure sensor is installed at one end of the compression spring. The detection surface of the pressure sensor is under negative pressure on the probe.

[0012] Preferably, the elastic element is distributed on the inner wall near the side of the gap groove;

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

[0014] Furthermore, when the circumference of the multiple closing petals decreases, the end of the elastic element connected to the annular element is attached to the outer wall of the other side of the gap groove in an inclined manner.

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

[0016] Preferably, the cross-section of the elastic element is a long support side and a short support side, and the included angle between the long support side and the short support side is 90°;

[0017] The extended lines of the inner included angles of the plurality of elastic elements converge at a point, and the soft airbag element is arranged on the inner included angle;

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

[0019] Preferably, both the long and short support legs are provided with soft rubber contacts at their ends.

[0020] Preferably, the soft airbag component is a cylindrical shape and is divided into a wide end and a narrow end according to its structure, with the wide end extending a predetermined length beyond the outer side of the elastic component.

[0021] Preferably, the annular component is fixedly installed, and its inner wall is provided with a wedge-shaped guide. The elastic component is slidably assembled onto the wedge-shaped guide through a horizontally connected component fixedly installed at the end.

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

[0023] It also includes an arc-shaped elastic pusher, one end of which is connected to the horizontal connector and moves synchronously with the axial movement of the closing flap, so as to push the horizontal connector to climb along the wedge-shaped guide.

[0024] Preferably, the system also includes a synchronizing element that is slidably assembled within the base and always in contact with the expanded core sleeve, wherein a supporting element is slidably disposed within the synchronizing element;

[0025] The synchronizing component is equipped with an equidistant spring for pushing the supporting component.

[0026] A lever is rotatably mounted inside the synchronizing member, and the shaft on the supporting member is in contact with the surface of the lever. One end of the lever is fixedly connected to the arc-shaped elastic pushing member.

[0027] Preferably, the lever is divided into a force-saving arm and a force-consuming arm according to its function, and the force-consuming arm is connected to the arc-shaped elastic pusher.

[0028] In the above technical solution, the expansion clamp for processing and testing aerospace parts provided by the present invention has the following beneficial effects: After the part to be tested is inserted from the end where the closing petals are located, the expansion core sleeve is driven to push and move. During the movement of the expansion core sleeve, the multiple closing petals decrease synchronously due to the decreasing radius of the boring hole, and the circumferential radius of the multiple closing petals shrinks, thereby clamping onto the part. Simultaneously, the elastic element moves synchronously with the closing petals, so that the soft airbag element abuts against the part to be tested and deforms as the circumferential radius of the multiple closing petals shrinks, thereby increasing the contact surface of the part to be tested to the maximum, thereby avoiding the occurrence of minute changes in the circumference of the part due to localized force during the clamping process. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this invention. For those skilled in the art, other drawings can be obtained based on these drawings.

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

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

[0032] Figure 3 This is a schematic diagram of the structure of the expanded core sleeve and elastic element provided in an embodiment of the present invention;

[0033] Figure 4 Provided for embodiments of the present invention Figure 1 Schematic diagram of cross-section structure;

[0034] Figure 5 This is a schematic diagram of the position structure of the elastic element in the gap groove provided in an embodiment of the present invention;

[0035] Figure 6 A cross-sectional structural diagram of the annular component and the expanded core sleeve provided in an embodiment of the present invention;

[0036] Figure 7This is a schematic diagram of the shape and structure of the elastic element provided in an embodiment of the present invention;

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

[0038] Figure 9 This is a schematic diagram of the implementation structure of the detection rod provided in an embodiment of the present invention;

[0039] Figure 10 This is a schematic cross-sectional view of the detection rod provided in an embodiment of the present invention.

[0040] Explanation of reference numerals in the attached figures:

[0041] 1. Base; 11. Boring hole; 2. Expanded core sleeve; 21. Gap groove; 23. Closing flap; 3. Elastic component; 31. Soft airbag component; 32. Long support leg; 33. Short support leg; 34. Horizontal connector; 4. Ring component; 41. Wedge guide component; 5. Arc-shaped elastic push component; 6. Synchronizing component; 61. Support component; 62. Equidistant spring; 63. Toggle lever; 64. Push rod; 7. Detection rod; 71. Probe; 72. Compression spring; 73. Pressure sensor; 100. Soft rubber contact. Detailed Implementation

[0042] 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 processing and testing aerospace parts includes an expansion tube sleeve 2 that slides a predetermined distance within a boring hole 11 opened along the axis of a base 1. 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 tube sleeve 2.

[0044] A gap groove 21 is formed between each two closing petals 23. An elastic element 3 with a wave-shaped structure is provided in the gap groove 21, and a hollow soft airbag element 31 is provided at the end of the elastic element 3 facing the inner side of the expansion tube sleeve 2.

[0045] Boring hole 11 has a circular frustum structure;

[0046] It also includes a fixedly installed detection rod 7, a probe 71 is rotatably installed inside the detection rod 7, a waist groove is opened on the detection rod 7 for the probe 71 to extend out, a compression spring 72 is fixedly installed in the waist groove, and a pressure sensor 73 is installed at one end of the compression spring 72, and the detection surface of the pressure sensor 73 is negatively pressed on the probe 71.

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

[0048] Furthermore, in the above embodiments, the movement of the expansion tube sleeve 2 can be driven by hydraulic or pneumatic push rods, or by a driving method known to those skilled in the art, such as stepper screw motor drive.

[0049] Furthermore, the elastic element 3 in the embodiment is as follows: Figure 7 As shown, when the circumference of the multiple closing petals 23 shrinks, the closing petals 23 adhere to the surface of the aerospace component to be tested, and deform under the adhesion, so that the entire closing petal 23 completely adheres to the surface of the aerospace component. As the closing petals 23 are completely adhered, the elastic element 3 also adheres to the surface of the aerospace component synchronously with the closing petals 23. With compression, the included angle of the wave of the elastic element 3 increases, that is, the elastic element 3 is a continuously connected V-shaped plate, and the increase of the included angle of the wave refers to the increase of the included angle of the V-shaped plate. The elastic element 3 is an elastic metal plate, such as stainless steel or elastic steel.

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

[0051] After the aerospace component to be tested is clamped by the circumferential contraction of multiple closing flaps 23, the xy-axis moving mechanism drives the probe 71 to move into the inner ring of the aerospace component and contact the inner wall of the aerospace component. Meanwhile, the base is driven by a rotary motor to rotate one revolution. During one revolution, if a bulge appears on the inner ring of the aerospace component, the probe 71 will move. The probe 71 then... Figure 10 As shown, the spring 72 is lifted, thereby causing it to be subjected to force, 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 aerospace component.

[0052] It should be noted that the control program, the drive 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 petals 23 are located, the expansion core sleeve 2 is driven to push and move. During the movement, the multiple closing petals 23 decrease synchronously due to the decreasing radius of the boring hole 11, and the circumferential radius of the multiple closing petals 23 shrinks, thus clamping onto the component. Simultaneously, the elastic element 3 moves synchronously with the closing petals 23, so that the soft airbag element 31 deforms against the component to be tested as the circumferential radius of the multiple closing petals 23 shrinks, thereby increasing the contact surface of the component to be tested to the maximum, thus avoiding the occurrence of slight changes in the circumference of the component due to localized force during the clamping process.

[0054] As a further embodiment of the present invention, the elastic element 3 is distributed on the inner wall near the gap groove 21;

[0055] It also includes an annular component 4, which is assembled in the base 1 and is assembled with the elastic component 3 near the end of the closing petal 23;

[0056] Furthermore, when the circumference of the multiple closing petals 23 decreases, the end of the elastic element 3 connected to the annular element 4 is attached to the outer wall of the other side of the gap groove 21 in an inclined manner.

[0057] Specifically, in the default state of the embodiment, the elastic element 3 is in a vertical state. When the expansion core sleeve 2 is driven to push and move, the multiple closing petals 23 decrease synchronously due to the decreasing radius of the boring hole 11, thus completely fitting onto the surface of the aerospace component.

[0058] During the process, the annular component 4 is driven to rotate, causing the elastic component 3 to be inclined and clockwise, with one end of the connection between the elastic component 3 and the annular component 4 fitting against the outer wall of the gap groove 21. During the inclination process, the rotational damping force and axial sliding damping force applied by the elastic component 3 can be increased, thereby cooperating with the multiple closing petals 23 to fully fit against the surface of the aerospace component and exert force together, thereby increasing the contact area of ​​the inserted aerospace component, and at the same time increasing the clamping and locking force of the aerospace component with the cooperation of the elastic component 3.

[0059] As another embodiment of the present invention, the cross-section of the elastic member 3 is a long support side 32 and a short support side 33, and the included angle between the long support side 32 and the short support side 33 is 90°.

[0060] The extended lines of the inner included angles of multiple elastic elements 3 intersect at a point, and the soft airbag element 31 is arranged on the inner included angle;

[0061] The long support legs 31 of two adjacent elastic elements 3 are arranged adjacently;

[0062] Both the long support leg 32 and the short support leg 33 are provided with soft rubber contacts 100.

[0063] Specifically, in combination Figure 5 As shown, during the implementation process, multiple closing petals 23 are completely attached to the surface of the aerospace component. The entire elastic element 3 moves synchronously with the closing petals 23 and is attached to the aerospace component. As the elastic element 3 is attached to the aerospace component, it deforms, thereby increasing the angle between the long support leg 32 and the short support leg 33 from 90°. This increases the separation angle between the long support leg 32 and the short support leg 33. During the process, the soft rubber contact 100 abuts against the aerospace component and deforms because the long support leg 32 and the short support leg 33 separate.

[0064] Furthermore, as the angle between the long support leg 32 and the short support leg 33 increases, the airbag component 31 forms a three-point contact by abutting against the aviation component, further optimizing the damping force applied by the elastic component 3 to the aviation component.

[0065] Secondly, combining Figure 5 As shown, the soft airbag component 31 is a cylindrical shape and is divided into a wide end and a narrow end according to its structure. The outer side of the elastic component 3 extends to a predetermined length (1mm-2mm) at the wide end. As the separation angle between the long support leg 32 and the short support leg 33 increases, the contact surface between the deformed soft airbag component 31 and the aerospace component further increases due to the contact between them, thereby further optimizing the damping force applied by the elastic component 3 to the aerospace component.

[0066] As another embodiment of the present invention, 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 through a horizontal connector 34 fixedly installed at the end.

[0067] Horizontal connector 34 is an arc-shaped elastic metal plate;

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

[0069] Specifically, in this embodiment, the annular component 4 is fixed inside the base 1, and then when the expanded core sleeve 2 is driven to move, it moves towards... Figure 1 As shown in the diagram, the rightward movement, after reaching its maximum range of motion, causes multiple closing petals 23 to fully adhere to the surface of the aerospace component. Simultaneously, the entire elastic element 3 moves synchronously with the closing petals 23, adhering to the aerospace component. During this process, the arc-shaped elastic pusher 5, structurally divided into a vertical section and an arc-shaped section, connects to the horizontal connecting element 34. When the expanded core sleeve 2 is driven to move, the arc-shaped elastic pusher 5 pulls, causing the arc-shaped section to deform, so that one end of the elastic element 3 connected to the annular element 4 adheres to the outer wall of the gap groove 21 at an angle.

[0070] Furthermore, as the elastic element 3 deforms and adheres to the aerospace component during the process, the angle between the long support edge 32 and the short support edge 33 increases from 90°. During this process, the soft rubber contact point 100 deforms against the aerospace component as the long support edge 32 and the short support edge 33 separate. This increases the contact area with the inserted aerospace component and, in conjunction with the elastic element 3, increases the clamping and locking force on the aerospace component.

[0071] Furthermore, the wedge-shaped guide 41 in the embodiment includes a low position and a high position. The high position is close to the axis of the expansion tube sleeve 2, while the low position is far from the axis of the expansion tube sleeve 2. In the default state, that is, when the elastic member 3 is vertical, the horizontal connector 34 is located at the low position of the wedge-shaped guide 41. As the multiple closing petals 23 are fully attached to the surface of the aerospace component, one end of the elastic member 3 and the horizontal connector 34 move towards the axis to apply a compressive force on the axial direction of the aerospace component.

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

[0073] Specifically, in combination Figure 8 As shown in the embodiment, the inner arc apexes of the two adjacent arc-shaped elastic pushers 5 are pulled in opposite directions, thereby causing the two adjacent elastic members 3 and the horizontal connector 34 to move closer together under the pull, so that one tilts clockwise and the other tilts counterclockwise, thus applying two opposite axial rotational damping forces. This increases the contact area with the inserted aerospace components, and also increases the clamping and locking force of the aerospace components with the cooperation of the elastic members 3.

[0074] As another embodiment of the present invention, it further includes a synchronizing member 6 that is slidably assembled in the base 1 and is always in contact with the expansion tube sleeve 2, and a supporting member 61 is slidably disposed in the synchronizing member 6;

[0075] The synchronizing component 6 is equipped with an equidistant spring 62 for the jacking support component 61;

[0076] A lever 63 is rotatably mounted inside the synchronizing component 6. The shaft on the supporting component 61 is in contact with the surface of the lever 63. One end of the lever 63 is fixedly connected to the arc-shaped elastic pushing component 5.

[0077] Specifically, in the above embodiment, the lever 63 is divided into a force-saving arm and a force-consuming arm according to its function. The force-consuming arm is slidably connected to the push rod 64 that moves vertically inside the synchronizing member 6, while the vertical part of the arc-shaped elastic push member 5 is fixedly connected to the push rod 64.

[0078] Furthermore, a hydraulic or pneumatic push rod drives the synchronizing member 6 to slide within the base 1, thereby driving the expansion core sleeve 2 to push and move. During the pushing process, the aerospace component to be tested will abut against the support member 61, causing the support member 61 to move along with the expansion core sleeve 2, i.e., the expansion core sleeve 2 and the support member 61 move in opposite directions. This causes the support member 61 to apply a force-reducing arm to the lever 63, causing the force-reducing arm to rise, thereby pushing the arc-shaped elastic push member 5 to move and deform. During the process, the pushing horizontal connecting member 34 is located at the lower position of the wedge-shaped guide member 41. As the multiple closing petals 23 are fully attached to the surface of the aerospace component, one end of the elastic member 3 and the horizontal connecting member 34 move towards the axis to apply a compressive force in the axial direction of the aerospace component. One tilts clockwise and the other tilts counterclockwise, thereby applying two opposite axial rotational damping forces.

[0079] Furthermore, as the elastic element 3 deforms and finally conforms to the aerospace component, the angle between the long support edge 32 and the short support edge 33 increases from 90°. During this process, the soft rubber contact point 100 deforms against the aerospace component as the long support edge 32 and the short support edge 33 separate. This increases the contact area with the inserted aerospace component and, in conjunction with the elastic element 3, increases the clamping and locking force on the aerospace component.

[0080] The foregoing has only described certain exemplary embodiments of the present invention by way of illustration. Undoubtedly, 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 foregoing 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 aerospace parts, characterized in that, The expansion tube sleeve (2) is driven to slide a predetermined distance in the bore (11) opened at the center of the base (1). 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 tube sleeve (2). A gap groove (21) is formed between each two closing petals (23). An elastic element (3) with a wave-shaped structure is provided in the gap groove (21), and a hollow soft airbag element (31) is provided at one end of the elastic element (3) facing the inner side of the expansion tube sleeve (2). The boring hole (11) is a circular frustum structure; It also includes a fixedly installed detection rod (7), in which a probe (71) is rotatably arranged. A groove is opened on the detection rod (7) for the probe (71) to extend out. A compression spring (72) is fixedly arranged in the groove, and a pressure sensor (73) is arranged at one end of the compression spring (72). The detection surface of the pressure sensor (73) is negatively pressed on the probe (71).

2. The expansion fixture for machining and testing aerospace parts according to claim 1, characterized in that, The elastic element (3) is distributed on the inner wall of the side near the gap groove (21); It also includes an annular component (4) assembled inside the base (1) and assembled with the elastic component (3) near one end of the closing petal (23); Furthermore, when the circumference of the multiple closing petals (23) decreases, the elastic element (3) and the annular element (4) are connected at one end to the outer wall of the other side of the gap groove (21) in an inclined manner.

3. The expansion fixture for machining and testing aerospace parts according to claim 2, characterized in that, The cross-section of the elastic element (3) is a long support side (32) and a short support side (33), and the included angle between the long support side (32) and the short support side (33) is 90°; The extended lines of the inner included angles of the plurality of elastic elements (3) converge at a point, and the soft airbag element (31) is arranged on the inner included angle; The long support edges (31) of two adjacent elastic elements (3) are arranged adjacently.

4. The expansion fixture for machining and testing aerospace parts according to claim 3, characterized in that, The ends of the long support leg (32) and the short support leg (33) are provided with soft rubber contacts (100).

5. The expansion fixture for machining and testing aerospace parts according to claim 3, characterized in that, The soft airbag component (31) is a round pendant and is divided into a wide end and a narrow end according to its structure. The wide end extends a predetermined length beyond the outer side of the elastic component (3).

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

7. The expansion fixture for machining and testing aerospace parts according to claim 6, characterized in that, The two adjacent elastic elements (3) are tilted in opposite directions.

8. The expansion fixture for machining and testing aerospace parts according to claim 6, characterized in that, It also includes a synchronizing element (6) that is slidably assembled in the base (1) and always in contact with the expansion tube sleeve (2), and a supporting element (61) is slidably provided in the synchronizing element (6). The synchronizing component (6) is provided with an equidistant spring (62) for pushing the supporting component (61). The synchronizing member (6) is rotatably provided with a lever (63), 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 push member (5).

9. An expansion fixture for machining and testing aerospace parts according to claim 8, characterized in that, The lever (63) is divided into a force-saving arm and a force-consuming arm according to its function. The force-consuming arm is connected to the arc-shaped elastic pusher (5).

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