Aviation conduit rotation bending test installation device

Abstract

The invention relates to the technical field of aviation conduit fatigue tests, and provides an aviation conduit rotation bending test installation device which is provided with an X-direction linear guide rail pair, a tailstock and an installation station assembly, the X-direction linear guide rail pair is installed on a workbench, the tailstock is installed on the X-direction linear guide rail pair, and the installation station assembly is installed on the tailstock. A Z-direction linear guide rail pair of the installation station assembly is connected with a Z-direction sliding plate through a Z-direction guide rail pair sliding block, a guide rail lock is connected with the Z-direction linear guide rail pair through the Z-direction guide rail pair sliding block, a Y-direction linear guide rail pair is installed on the Z-direction sliding plate and connected with an installation plate through a Y-direction guide rail pair sliding block, and a displacement adjusting bolt is arranged on the Z-direction sliding plate. The state that the Z-direction sliding plate moves along the Y-direction linear guide rail pair and the Z-direction linear guide rail pair is adjusted, the aviation conduit is installed on the installation plate, the aviation conduit is installed on the flexural disc, the stress zeroing precision of the aviation conduit is improved, the operation convenience is improved, meanwhile, the structure has the advantage of being high in rigidity, and resonance is avoided in the rotating bending fatigue testing process.

Description

Technical Field

[0001] The invention relates to the fields of fluid pressure test and rotation bending fatigue test of aviation duct components, and in particular to an installation device for rotation bending fatigue test of aviation ducts. Background Art

[0002] Bending fatigue failure is a form of failure of aviation ducts. In order to improve the reliability of the design of aviation duct components, the fatigue life of aviation duct components under certain stress states is measured by a rotary bending fatigue tester, which is an important technical means for studying fatigue fracture of aviation duct components. According to the test requirements described in the relevant test standards for aviation ducts, the head seat end is used to adjust the deflection, and the tail seat end is used to fix the duct component and connect the pressurized medium. Before the test, the stress at the root of the aviation duct needs to be zeroed. The stress zeroing process is very critical to the entire test process and determines the accuracy of the final test data. Due to the slight deformation of the duct component specimen during the processing process, coupled with the cumulative errors of the equipment parts during the processing and assembly process, the stress of the aviation duct cannot meet the test requirements described in the relevant test standards for aviation ducts after being loaded into the rotary bending fatigue tester, thereby affecting the accuracy of the test data. In the prior art, there is a coaxial adjustment device, in which the Z-direction adjustment of the duct test mount is provided by the rotation of the thread of the fine-tuning nut and the duct test mount to provide Z-direction lifting and lowering, and the fixation is also based on this thread, and there is a certain gap between the threads. The catheter test mount is connected to the catheter test fixture in the form of insertion, and then needs to be tightened with a solid bolt. Because of these factors, the adjustment accuracy is not high enough, the operation is not convenient enough, there is resonance during the test, and the Z-axis adjustment range is too small. Because the catheter sample of the 90° elbow joint needs to occupy a certain high-altitude space, and the Z-axis adjustment range is too small, it is impossible to install the catheter sample of the 90° elbow joint.

[0003] In summary, the existing bending fatigue technology for aviation ducts has technical problems such as insufficient precision in zeroing stress of aviation ducts, inconvenient operation, resonance during testing, and inability to install 90° elbows in duct tests. Summary of the invention

[0004] The purpose of the present invention is to at least solve the deficiencies in the prior art to a certain extent, and to provide an aviation duct rotational bending test installation device to increase the stress zeroing accuracy of the aviation duct, improve the convenience of operation, improve the rigidity and stability of the structure, avoid resonance during rotational bending fatigue testing, and support duct testing with 90° elbows installed.

[0005] The aviation conduit rotation bending test installation device provided by the present invention comprises:

[0006] An X-direction linear guide pair, wherein the X-direction linear guide pair is mounted on a workbench;

[0007] A tailstock, the tailstock being mounted on the X-direction linear guide pair and being movable on the X-direction linear guide pair;

[0008] An installation station assembly is installed on the tail stock, and the installation station assembly includes a Z-direction linear guide pair, a guide lock, a Y-direction linear guide pair, a displacement adjustment bolt, a mounting plate and a Z-direction sliding plate; the Z-direction linear guide pair is connected to the Z-direction sliding plate via a Z-direction guide pair slider, and the guide lock is connected to the Z-direction linear guide pair via the Z-direction guide pair slider; the Y-direction linear guide pair is installed on the Z-direction sliding plate and connected to the mounting plate via a Y-direction guide pair slider; the displacement adjustment bolt is arranged on the Z-direction sliding plate, and is used to adjust the Z-direction sliding plate to move along the Y-direction linear guide pair and the Z-direction linear guide pair to reach the required precise position; a joint at one end of the aviation duct is installed on the mounting plate, and the joint at the other end of the aviation duct is installed on the flexure disk, the flexure disk is installed on the head seat, and the head seat is installed on the workbench.

[0009] Furthermore, the aviation catheter rotation bending test installation device also includes a sliding handle; the sliding handle is installed on the tail stock, and when the sliding handle moves, it drives the installation station assembly to move rapidly along the X-direction on the X-direction linear guide pair.

[0010] Further, the sliding handle includes one handle or two handles. When the sliding handle is one handle, the sliding handle of one handle is arranged on any one side of the two sides of the tail stock; when the sliding handle is two handles, the sliding handles of the two handles are separately arranged on both sides of the tail stock.

[0011] Furthermore, the aviation catheter rotation bending test installation device also includes a moving device; the moving device is a gear and rack structure, the rack is installed on the workbench and parallel to the X-direction linear guide pair, the gear is installed on the tailstock, the gear is driven by a hand wheel, and the hand wheel is turned by hand, the gear and the rack move relatively, so that the entire tailstock moves slowly along the X direction, achieving the purpose of labor-saving and precise positioning.

[0012] Furthermore, the aviation catheter rotation bending test installation device also includes a locking device; the lower end of the locking device passes through the tailstock and faces the workbench, and the upper end of the moving device is erected above the tailstock to form a locking control part; after the target position of the installation station assembly moving along the X-direction on the X-direction linear guide pair is determined, the locking control part is rotated so that the lower end of the moving device is connected to the workbench, and the installation station assembly is locked on the workbench.

[0013] Furthermore, the aviation catheter rotation bending test installation device also includes a Z-direction pointer scale, which is arranged on the side of the Z-direction sliding plate and located on one side of the mounting plate, and is used to provide a rough position reference for the position of the mounting plate.

[0014] Furthermore, the number of the Z-direction pointer scales is selected according to the number of the mounting plates to ensure that a corresponding Z-direction pointer scale exists on the side of each mounting plate.

[0015] Furthermore, a medium inlet is provided on the mounting plate, and the medium inlet is connected to the aviation duct.

[0016] Furthermore, the aviation duct includes an aviation duct direct connector; the aviation duct direct connector is installed on the mounting plate through a transition joint.

[0017] Furthermore, the aviation duct includes an aviation duct 90° elbow joint; the aviation duct 90° elbow joint is installed on a 90° mounting plate through a transition joint, and the 90° mounting plate is installed on top of the mounting plate to form a 90° transition.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] The aviation catheter rotation bending test installation device provided by the present invention is provided with an X-direction linear guide pair, a tailstock and an installation station assembly, wherein the X-direction linear guide pair is installed on a workbench, the tailstock is installed on the X-direction linear guide pair and can move on the X-direction linear guide pair, the installation station assembly is installed on the tailstock, and the installation station assembly includes a Z-direction linear guide pair, a guide lock, a Y-direction linear guide pair, a displacement adjustment bolt, a mounting plate and a Z-direction sliding plate; the Z-direction linear guide pair is connected to the Z-direction sliding plate through a Z-direction guide pair slider, and the guide lock is connected to the Z-direction sliding plate through the Z-direction guide pair slider The Z-direction linear guide pair, the Y-direction linear guide pair is installed on the Z-direction sliding plate, and the mounting plate is connected by the Y-direction guide pair slider; the displacement adjustment bolt is arranged on the Z-direction sliding plate, and is used to adjust the Z-direction sliding plate to move along the Y-direction linear guide pair and the Z-direction linear guide pair to reach the required precise position; the joint at one end of the aviation duct is installed on the mounting plate, the joint at the other end of the aviation duct is installed on the flexure disk, the flexure disk is installed on the head seat, and the head seat is installed on the workbench, so as to achieve the heightened stress zeroing accuracy of the aviation duct, improve the convenience of operation, and avoid resonance during testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without paying any creative labor.

[0021] Figure 1 This is a schematic diagram of a use state of the aviation catheter rotation bending test installation device according to an embodiment of the present invention;

[0022] Figure 2 This is a schematic diagram of an assembly structure of an aviation duct rotation bending test installation device according to an embodiment of the present invention;

[0023] Figure 3 This is another schematic diagram of the assembly structure of the aviation duct rotation bending test installation device according to an embodiment of the present invention;

[0024] Figure 4 It is a structural schematic diagram of an embodiment of the present invention in which an aviation conduit direct connector is connected to a mounting plate via an auxiliary fixing plate;

[0025] Figure 5 It is a structural schematic diagram of an embodiment of the present invention in which an aviation conduit direct connector is directly connected to a mounting plate;

[0026] Figure 6 It is a structural schematic diagram of an aviation duct 90° elbow joint connected to a 90° mounting plate through an auxiliary fixing plate according to an embodiment of the present invention;

[0027] Figure 7 It is a structural schematic diagram of an aviation duct 90° elbow joint directly connected to a 90° elbow joint mounting plate according to an embodiment of the present invention.

[0028] Description of reference numerals:

[0029] 1. Aviation duct rotation bending test installation device; 11. X-direction linear guide pair; 12. Tail stock; 13. Installation station assembly; 1301. Z-direction limit block; 1302. Z-direction linear guide pair; 1303. Guide lock; 1304. Y-direction linear guide pair; 1305. Displacement adjustment bolt; 1306. Mounting plate; 1307. Z-direction sliding plate; 1308. Auxiliary fixing plate; 1309. Y-direction pointer scale; 1310. Transition joint; 1 311. 90° mounting plate; 14. Sliding handle; 1 5. Locking device; 1 6. Moving device; 17. Z-direction pointer scale;

[0030] 2. Aviation catheter; 21. Aviation catheter straight connector; 22. Aviation catheter 90° elbow connector;

[0031] 3. Flexion disc:

[0032] 4. Head seat;

[0033] 5. Workbench. DETAILED DESCRIPTION

[0034] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar methods or methods having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, but are not to be construed as limiting the present invention. All other embodiments obtained by ordinary technicians in the field without creative work based on the embodiments of the present invention are within the scope of protection of the present invention.

[0035] See also Figure 1-Figure 4 The embodiment of the present invention provides an aviation catheter rotation bending test installation device, comprising:

[0036] An X-direction linear guide pair 11, wherein the X-direction linear guide pair 11 is installed on the workbench 5;

[0037] A tailstock 12, wherein the tailstock 12 is mounted on the X-direction linear guide pair 11 and can move on the X-direction linear guide pair 11;

[0038] The installation station assembly 13 is installed on the tailstock 12, and the installation station assembly 13 includes a Z-direction linear guide pair 1302, a guide lock 1303, a Y-direction linear guide pair 1304, a displacement adjustment bolt 1305, a mounting plate 1306 and a Z-direction sliding plate 1307; the Z-direction linear guide pair 1302 is connected to the Z-direction sliding plate 1307 through a Z-direction guide pair slider, and the guide lock 1303 is connected to the Z-direction linear guide pair 1302 through a Z-direction guide pair slider; the Y-direction linear guide pair 1304 is installed on the Z-direction sliding plate 1307 and connected to the mounting plate 1306 through a Y-direction guide pair slider; the displacement adjustment bolt 1305 is arranged on the Z-direction sliding plate 1307, and is used to adjust the state of the Z-direction sliding plate 1307 moving along the Y-direction linear guide pair 1304 and the Z-direction linear guide pair 1302 to reach the required precise position; the mounting plate 1 A joint at one end of the aviation conduit 2 is installed on 306 , a joint at the other end of the aviation conduit 2 is installed on the flexure disk 3 , the flexure disk 3 is installed on the head seat 4 , and the head seat 4 is installed on the workbench 5 .

[0039] It should be noted that, in this embodiment, by using the linear guide pairs in the three directions of X, Y, and Z (X-direction linear guide pair 11, Y-direction linear guide pair 1304, and Z-direction linear guide pair 1302) and the Z-direction sliding plate 1307, the installation station assembly 13 has a multi-directional precise displacement adjustment function. Through the combination of these guide rails, the tester can accurately locate the installation position of the aviation duct to ensure that there is no initial stress when the duct is installed. In addition, the design of the displacement adjustment bolt allows the position of the sliding plate in the Z direction to be fine-tuned, further improving the zeroing accuracy, ensuring that the stress of the duct is zero in the initial state, and helping to accurately zero the stress of the aviation duct and improve the accuracy of the test. In addition, the tailstock 12 can slide along the X-direction linear guide pair 11, so that the operator can easily perform the installation operation at different X positions, thereby simplifying the installation and adjustment process, and there is no need to repeatedly adjust the position of the entire device, thereby improving the convenience of operation. In addition, the guide rail lock can help fix the final position of the Z-direction sliding plate to avoid position offset during the installation process, and at the same time, it can maintain a stable positioning after the adjustment is completed, reducing complex adjustment steps, thereby simplifying the operation. In addition, the multiple guide rail pair design of the installation station assembly 13 and the tailstock 12 can ensure that the entire structure has good stability in all directions. The combination of the guide rail pair and the guide rail lock 1303 can effectively reduce the degree of freedom between components, which helps to reduce the risk of structural vibration. In addition, one end of the aviation duct is fixed to the installation station assembly 13 through the mounting plate 1306, and the other end is installed on the headstock 4 through the flexure disk 3. Such a two-point fixing method can effectively reduce the swing amplitude of the duct during the test process and reduce the possibility of resonance.

[0040] It should also be noted that, in this embodiment, the installation device 1 for the rotational bending fatigue test of an aviation duct may have one or more installation station components 13. For example, the installation device 1 for the rotational bending fatigue test of an aviation duct may have three installation station components 13. It is understandable that the number of installation station components 13 of the installation device 1 for the rotational bending fatigue test of an aviation duct may be set according to actual needs.

[0041] It should also be noted that, in this embodiment, the mounting plate 1306 is a key component for zeroing the stress at the root of the aviation duct 2, and its position in the Y and Z directions determines the magnitude of the stress at the root of the aviation duct 2. The joint at one end of the aviation duct 2 is installed on the flexure plate 3, and the other end is installed on the mounting plate 1306. When the geometric coaxiality of the two ends of the aviation duct 2 is close to 0, the root stress of the aviation duct 2 is also very small, and the relevant standards require that the root stress is ≤20με. Through precise adjustment of the displacement adjustment bolt 1305, the mounting plate 1306 can be moved along the Y-direction linear guide pair 1304 and the Z-direction linear guide pair 1302 to achieve a precise position, so that the root stress of the aviation duct 2 meets the requirements of the relevant standards. After the position adjustment of the mounting plate 1306 is completed, that is, the root stress adjustment of the aviation duct 2 is completed, the guide rail lock 1303 fixes the slider that slides and connects the linear guide pair in the Y and Z directions to the guide rail, so that the position of the mounting plate 1306 no longer changes, that is, the stress at the root of the aviation duct 2 no longer changes.

[0042] In some preferred embodiments, the aviation catheter rotary bending test installation device further includes a sliding handle 14; the sliding handle 14 is arranged on the tailstock 12, and when the sliding handle 14 moves, it drives the installation station assembly 13 to move rapidly along the X direction on the X-direction linear guide pair 11. Specifically, the sliding handle 14 includes one handle or two handles. When the sliding handle 14 is one handle, the sliding handle 14 of one handle is arranged on any one side of the two sides of the tailstock 12; when the sliding handle 14 is two handles, the sliding handles 14 of the two handles are separately arranged on both sides of the tailstock 12. It should be noted that the sliding handle 14 is installed on the tailstock 12, and can directly drive the installation station assembly 13 to move rapidly on the X-direction linear guide pair 11, allowing the tester to quickly adjust the position of the installation station through the sliding handle during operation, so as to achieve efficient rough positioning, which complements the slow and precise positioning of the moving device 16.

[0043] In some preferred embodiments, the aviation catheter rotation bending test installation device also includes a moving device 16; the moving device 16 is a gear and rack structure, the rack is installed on the workbench 5, parallel to the X-direction linear guide pair 11, the gear is installed on the tailstock 12, the gear is driven by a handwheel, and the handwheel is turned by hand, and the gear and the rack move relatively, so that the entire tailstock 12 moves slowly along the X direction, achieving a labor-saving and precise positioning purpose. It should be noted that when the operator turns the handwheel by hand, the gear and the rack move relatively, so that the entire tailstock 12 moves slowly along the X direction, and the position of the installation station assembly 13 is fine-tuned to achieve higher accuracy, ensuring that the initial stress zeroing of the catheter can be more accurate during the installation and testing process, reducing human errors. In addition, turning the handwheel is more stable than direct manual sliding operation. Turning the handwheel can gradually and smoothly move the installation station to avoid sudden displacement or shaking. Especially when it is necessary to maintain a high-precision position, the slow movement mechanism of the moving device 16 can achieve a labor-saving and precise positioning purpose.

[0044] In some preferred embodiments, the aviation catheter rotary bending test installation device further includes a locking device 15; the lower end of the locking device 15 passes through the tailstock 12 and faces the workbench 5, and the upper end of the moving device 15 stands upright above the tailstock 12 to form a locking control part; after the target position of the installation station assembly 13 moving along the X-direction on the X-direction linear guide pair 11 is determined, the lower end of the moving device 15 is connected to the workbench 5 by rotating the locking control part, and the installation station assembly 13 is locked on the workbench 5. It should be noted that after the target position of the installation station assembly 13 is determined, the locking device 15 is firmly connected to the workbench 5 by rotating the locking control part, and the position of the installation station assembly 13 is fixed, so as to avoid displacement of the installation station assembly 13 due to vibration or external force during the test, and ensure the initial stress zeroing accuracy of the catheter and the accuracy of the test. In addition, the locking device 15 can complete position locking through a simple rotation of the locking control part, avoiding the need for complex fixing operations after determining the position, improving the convenience of operation, and reducing unnecessary repeated adjustment steps.

[0045] In some preferred embodiments, the aviation duct rotation bending test installation device further includes a Z-direction pointer scale 17, which is arranged on the side of the Z-direction sliding plate 1307 and located on one side of the mounting plate 1306, and is used to provide a rough position reference for the position of the mounting plate 1306. The number of the Z-direction pointer scales 17 is selected according to the number of the mounting plates 1306 to ensure that there is a corresponding Z-direction pointer scale 17 on the side of each mounting plate 1306. It should be noted that the Z-direction pointer scale 17 provides a position reference of the mounting plate 1306 in the Z direction, so that the operator can obtain instant rough positioning information through the pointer scale when adjusting the position of the mounting plate. This visual reference helps to quickly and intuitively determine the approximate position of the mounting plate, especially when multiple adjustments are required, which can reduce the number of repeated adjustments and tests. In addition, a corresponding Z-direction pointer scale 17 is set on the side of each mounting plate 1306 to ensure that in the case of multiple stations, the Z-direction position of each mounting plate can be achieved through the ruler reference to achieve consistency.

[0046] In some further preferred embodiments, the installation station assembly 13 further includes a Y-direction pointer scale 1309; the Y-direction pointer scale 1309 is disposed on the Z-direction sliding plate 1307 and is located above the installation plate 1306. It should be noted that the Y-direction pointer scale 1309 provides an intuitive scale reference for the position of the installation plate 1306 in the Y direction, so that the operator can quickly understand the current position state, greatly simplify the precise adjustment in the Y direction, avoid the error caused by adjustment based solely on experience, and improve the installation accuracy.

[0047] In some preferred embodiments, a medium inlet is provided on the mounting plate 1306, and the medium inlet is connected to the aviation conduit 2. It should be noted that during the rotation bending fatigue test of the aviation conduit 2, a high-pressure medium needs to be input into its inner cavity, and the high-pressure medium enters the inner cavity of the aviation conduit 2 from the medium inlet of the mounting plate 1306 through a pipeline.

[0048] In some preferred embodiments, the aviation duct 2 includes an aviation duct straight joint 21 or an aviation duct 90° elbow joint 22; the aviation duct straight joint 21 is installed on the mounting plate 1306 through a transition joint 1310; the aviation duct 90° elbow joint 22 is installed on a 90° mounting plate 1311 through a transition joint 1310, and the 90° mounting plate 1311 is installed in a superimposed manner with the mounting plate 1306 to form a 90° transition. Further, for the aviation duct 90° elbow joint 22, the high-pressure medium needs to enter the inner cavity of the aviation duct 2 through the 90° mounting plate 1311 while passing through the pipeline from the medium inlet of the mounting plate 1306. It should be noted that the aviation duct may include two structures of a straight joint and a 90° elbow joint in actual application. In this embodiment, the straight joint 21 and the 90° elbow joint 22 are respectively installed on different mounting plates through the transition joint 1310, so that the test device can adapt to a variety of duct types, thereby meeting diverse test requirements and improving the flexibility and scope of application of the equipment. In addition, in order to ensure the stability and correct installation angle of the 90° elbow joint 22, the 90° mounting plate 1311 is superimposed on the mounting plate 1306 to form a 90° transfer, which can ensure that the direction and angle of the elbow joint are consistent during installation, meet the installation state under actual working conditions, make the test more in line with the actual working conditions, and help to obtain more real and accurate test results. In addition, during the test process, it is necessary to simulate the high-pressure medium environment that the catheter is subjected to in actual work. In this embodiment, through the setting of the 90° mounting plate 1311, the high-pressure medium can enter the inner cavity of the aviation catheter from the medium inlet of the mounting plate 1306 and pass through the 90° mounting plate 1311 at the same time, ensuring that the high-pressure medium can enter the inner cavity of the elbow joint along the correct path, so that the test process is closer to the actual use conditions. In addition, in the installation of the elbow joint, the addition of the 90° mounting plate 1311 not only realizes the angle transfer, but also provides additional structural support. Elbow joints may generate greater stress concentration at corners. The 90° mounting plate is used to support and disperse and bear part of the stress, preventing the elbow joints from excessive displacement or deformation during high-voltage testing, improving the stability of the installation, and ensuring the accuracy and reliability of the test results.

[0049] In some further preferred embodiments, the installation station assembly 13 further includes an auxiliary fixing plate 1308, and after the transition joint 1310 is installed on the 90° mounting plate 1311, the auxiliary fixing plate 1308 connects the transition joint 1310 and the 90° mounting plate 1311 to perform auxiliary reinforcement on the transition joint 1310. It should be noted that after the transition joint 1310 is installed on the 90° mounting plate 1311, the auxiliary fixing plate 1308 further connects and reinforces the connection between the transition joint and the 90° mounting plate, effectively preventing the transition joint from loosening during the high pressure or rotation bending test, thereby improving the safety and reliability of the test device.

[0050] In some further preferred embodiments, the installation station assembly 13 further includes an auxiliary fixing plate 1308; when the aviation conduit direct connector 21 is installed on the installation plate 1306 through the transition joint 1310, the installation plate 1306 is connected through the auxiliary fixing plate 1308 to auxiliary reinforce the transition joint 1310. It should be noted that after the transition joint 1310 is installed on the installation plate 1306, the auxiliary fixing plate 1308 further connects and reinforces the connection between the transition joint and the installation plate 1306, effectively preventing the transition joint from loosening during the high pressure or rotation bending test, thereby improving the safety and reliability of the test device.

[0051] In some further preferred embodiments, the installation station assembly 13 further includes a Z-direction limit block 1301; the Z-direction limit block 1301 is arranged below the Z-direction sliding plate 1307, and is used to limit the downward movement of the Z-direction sliding plate 1307.

[0052] The above is a description of the technical solution provided by the present invention. For those skilled in the art, according to the ideas of the embodiments of the present invention, there may be changes in the specific implementation methods and application scopes. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. An aviation catheter rotation bending test installation device, characterized in that: include: An X-direction linear guide pair, wherein the X-direction linear guide pair is mounted on a workbench; A tailstock, the tailstock being mounted on the X-direction linear guide pair and being movable on the X-direction linear guide pair; An installation station assembly is installed on the tail stock, and the installation station assembly includes a Z-direction linear guide pair, a guide lock, a Y-direction linear guide pair, a displacement adjustment bolt, a mounting plate and a Z-direction sliding plate; the Z-direction linear guide pair is connected to the Z-direction sliding plate via a Z-direction guide pair slider, and the guide lock is connected to the Z-direction linear guide pair via the Z-direction guide pair slider; the Y-direction linear guide pair is installed on the Z-direction sliding plate and connected to the mounting plate via a Y-direction guide pair slider; the displacement adjustment bolt is arranged on the Z-direction sliding plate, and is used to adjust the Z-direction sliding plate to move along the Y-direction linear guide pair and the Z-direction linear guide pair to reach the required precise position; a joint at one end of the aviation duct is installed on the mounting plate, and the joint at the other end of the aviation duct is installed on the flexure disk, the flexure disk is installed on the head seat, and the head seat is installed on the workbench.

2. The aviation conduit rotation bending test installation device according to claim 1, characterized in that: The aviation catheter rotation bending test installation device also includes a sliding handle; the sliding handle is installed on the tail stock, and when the sliding handle moves, it drives the installation station assembly to move quickly along the X-direction on the X-direction linear guide pair.

3. The aviation conduit rotation bending test installation device as claimed in claim 2, characterized in that: The sliding handle includes one handle or two handles. When the sliding handle is one handle, the sliding handle of one handle is arranged on any one side of the two sides of the tail stock; when the sliding handle is two handles, the sliding handles of the two handles are separately arranged on both sides of the tail stock.

4. The aviation conduit rotation bending test installation device as claimed in claim 2, characterized in that: The aviation catheter rotation bending test installation device also includes a moving device; the moving device is a gear and rack structure, the rack is installed on the workbench and parallel to the X-direction linear guide pair, the gear is installed on the tailstock, the gear is driven by a hand wheel, and the hand wheel is turned by hand, the gear and the rack move relatively, so that the entire tailstock moves slowly along the X direction, achieving a labor-saving and precise positioning purpose.

5. The aviation conduit rotation bending test installation device according to claim 4, characterized in that: The aviation catheter rotation bending test installation device also includes a locking device; the lower end of the locking device passes through the tailstock and faces the workbench, and the upper end of the moving device stands upright above the tailstock to form a locking control part; after the target position of the installation station component moving along the X-direction on the X-direction linear guide pair is determined, the locking control part is rotated so that the lower end of the moving device is connected to the workbench, and the installation station component is locked on the workbench.

6. The aviation conduit rotation bending test installation device according to claim 1, characterized in that: The aviation catheter rotation bending test installation device also includes a Z-direction pointer scale, which is arranged on the side of the Z-direction sliding plate and located on one side of the mounting plate, and is used to provide a rough position reference for the position of the mounting plate.

7. The aviation conduit rotation bending test installation device according to claim 6, characterized in that: The number of the Z-direction pointer scales is selected according to the number of the mounting plates to ensure that a corresponding Z-direction pointer scale exists on the side of each mounting plate.

8. The aviation conduit rotation bending test installation device according to claim 1, characterized in that: The mounting plate is provided with a medium inlet, and the medium inlet is connected to the aviation duct.

9. The aviation conduit rotation bending test installation device according to any one of claims 1 to 8, characterized in that: The aviation duct comprises an aviation duct direct connector; the aviation duct direct connector is installed on the mounting plate via a transition joint.

10. The aviation conduit rotation bending test installation device according to any one of claims 1 to 8, characterized in that: The aviation duct comprises an aviation duct 90° elbow joint; the aviation duct 90° elbow joint is installed on a 90° mounting plate through a transition joint, and the 90° mounting plate is installed on top of the mounting plate to form a 90° transition.

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