An inertial group and a debugging method for reducing line-angle coupling based on a T-type shock absorber

Abstract

The present invention relates to a method for suppressing line-angle coupling of inertial measurement, and in particular to an inertial group and a debugging method for reducing line-angle coupling based on a T-type shock absorber. The inertial group includes an inertial group body, a shock absorber, a bushing, a gasket, a flange, a counterweight, a mounting hole, and a shock absorber set. The debugging method includes an inertial group, and specifically includes: S1, selecting the shock absorber and determining the damping frequency of the shock absorber, S2, determining the radial and axial form and position tolerances of the production mold of the shock absorber, S3, establishing an axial dimension model of the bushing to obtain the optimal axial dimension of the bushing, S4, establishing a radial dimension model of the bushing to obtain the optimal radial dimension of the bushing, S5, establishing an opening dimension model of the flange to obtain the optimal opening dimension of the flange. The present invention can effectively reduce the angular vibrations in three directions caused by the linear vibration along a certain direction in a spatial rectangular coordinate system, thereby reducing the influence of line-angle coupling.

Description

Technical Field

[0001] The invention relates to a method for suppressing line-angle coupling of inertial measurement, and in particular to an inertial group and a debugging method for reducing line-angle coupling based on a T-type shock absorber. Background Art

[0002] The inertial navigation system is a system that does not rely on external information, but relies on its own inertial measurement devices to output angular velocity and acceleration information for the carrier. The navigation information generated has the characteristics of good continuity, low noise, high data update rate and good stability. However, due to the extremely harsh working mechanical environment of the aircraft, such as large vibration acceleration, wide frequency range and long excitation time, the mechanical adaptability requirements of the inertial combination system are more stringent. The vibration reduction design of the inertial measurement system has always been the top priority for its environmental adaptability. If effective measures are not taken during linear vibration, it will cause a large coupling angular vibration.

[0003] The traditional vibration reduction design for inertial measurement systems only uses rubber vibration absorbers and adjusts the center of mass of the carrier to reduce the angular vibration introduced by linear vibration, but the vibration reduction effect is not obvious, so it is urgently needed to be improved. Summary of the invention

[0004] In view of the above-mentioned shortcomings of the prior art, the object of the present invention is to provide an inertial group and a debugging method based on a T-type shock absorber to reduce line-angle coupling, which can effectively reduce the angular vibrations in three directions caused by line vibrations along a certain direction in a spatial rectangular coordinate system.

[0005] To achieve the above-mentioned purpose and other related purposes, the present invention provides a debugging method for reducing line-angle coupling based on a T-type shock absorber, comprising an inertial group, wherein the inertial group comprises:

[0006] An inertial group body, on which a flange is mounted;

[0007] The shock absorber kit comprises:

[0008] a bushing passing through the flange;

[0009] A vibration damper is arranged on the outside of the bushing, and the vibration damper is arranged on both sides of the flange;

[0010] A gasket mounted on the top of the upper shock absorber;

[0011] A plurality of counterweight holes are provided on the outer wall surface of the inertial group body;

[0012] A counterweight block, which is installed on the counterweight hole;

[0013] The debugging method for reducing line-angle coupling based on a T-type vibration damper comprises:

[0014] S1. Selecting the shock absorber and determining the shock absorption frequency of the shock absorber;

[0015] S2, determining the radial and axial geometric tolerances of the production mold of the shock absorber;

[0016] S3, establishing an axial dimension model of the bushing to obtain an optimal axial dimension of the bushing;

[0017] S4, establishing a radial dimension model of the bushing to obtain an optimal radial dimension of the bushing;

[0018] S5. Establishing a hole size model of the flange to obtain an optimal hole size of the flange;

[0019] The step S1 of selecting the shock absorber and determining the shock absorption frequency of the shock absorber includes:

[0020] S11, selecting multiple shock absorbers from the same batch;

[0021] S12, selecting a shock absorber formed in one step;

[0022] S13, determining the effective vibration reduction frequency of the vibration absorber according to the selected vibration absorber;

[0023] The step S3 of establishing the axial dimension model of the bushing to obtain the optimal axial dimension of the bushing includes:

[0024] S31, establishing an axial dimension model of the bushing, the formula is: h2=2h0+h-2ε1h0, wherein ε1 is the axial preload of the shock absorber, h is the thickness of the flange, h2 is the axial length of the bushing, and h0 is the thickness of the shock absorber;

[0025] S32, calculating the ratio σ of the thickness h of the flange to the thickness h0 of the shock absorber, where h=σh0;

[0026] S33. The formula for the thickness h of the flange is: h = h2-2h0+2ε1h0;

[0027] S34, determining the optimal vibration reduction effect of the shock absorber according to the axial preload ε1 and the ratio σ of the shock absorber;

[0028] The step S4 of establishing the radial dimension model of the bushing to obtain the optimal radial dimension of the bushing includes:

[0029] S41, establishing a radial dimension model of the bushing, the formula is: Among them, ε2 is the radial preload of the shock absorber, D0 is the radial size of the bushing, D3-2D1 is the diameter of the middle opening of the shock absorber, and D2 is the radial thickness of the shock absorber;

[0030] S42, determining an optimal vibration reduction effect of the shock absorber according to an axial preload ε1 of the shock absorber and a radial preload ε2 of the shock absorber;

[0031] The step S5 of establishing the opening size model of the flange to obtain the optimal opening size of the flange includes:

[0032] S51, establishing the hole size model of the flange, the formula is: D5=D0+2D2, where D5 is the hole size of the flange;

[0033] S52. Determine the best vibration reduction effect of the shock absorber according to the opening size D5 of the flange.

[0034] In one embodiment of the present invention, the bushing is in an inverted T-shape, the upper shock absorber is in a T-shape, and the lower shock absorber is in an inverted T-shape.

[0035] In one embodiment of the present invention, the radial and axial shape and position tolerances of the production mold of the shock absorber are less than 0.005 mm.

[0036] In one embodiment of the present invention, when the axial preload ε1 of the shock absorber is in the range of 0.068 to 0.075 and the ratio σ is in the range of 4 to 5, the shock absorber has the best vibration reduction effect.

[0037] In one embodiment of the present invention, when the difference between the axial preload ε1 of the shock absorber and the radial preload ε2 of the shock absorber is less than or equal to 0.005, that is, ε1-ε2|≤0.005, and when the machining error of the flange opening size D5 is within 0.005mm and the surface roughness is 0.8, the vibration damping effect of the shock absorber is best.

[0038] As described above, the inertial group and the debugging method based on T-type shock absorber to reduce line-angle coupling of the present invention have the following beneficial effects:

[0039] The debugging method for reducing line-angle coupling based on T-type shock absorber of the present invention includes an inertial group, including the selection of shock absorber, the design of bushing, the design of flange and the adjustment of the center of gravity of carrier. The present invention can effectively reduce the angular vibration in three directions caused by the linear vibration along a certain direction in the spatial rectangular coordinate system, thereby reducing the influence of line-angle coupling.

[0040] The debugging method based on reducing line angle coupling of the T-type shock absorber of the present invention can reduce the friction force of the bushing on the shock absorber, reduce stress concentration, and avoid damaging the shock absorber, and has a good vibration reduction effect.

[0041] The counterweight holes designed based on the debugging method of the T-type shock absorber to reduce the linear angle coupling of the present invention are all far away from the center of mass. By increasing the lever arm, the counterweight efficiency is improved. The counterweight block is small and thin, and multiple blocks can be stacked and used to achieve the purpose of accurately controlling the center of mass. The center of mass position of the inertial group is measured, adjusted, and iterated repeatedly by a center of mass measuring instrument, and the position error between the center of mass and the vibration reduction center is controlled within 0.5mm. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 A structural diagram of an inertial group provided for one embodiment of the present application.

[0043] Figure 2 A structural diagram of an inertial group provided for yet another embodiment of the present application.

[0044] Figure 3 A structural diagram of a shock absorber assembly of an inertial group provided in an embodiment of the present application.

[0045] Figure 4 A schematic diagram of the center of mass position of an inertial group provided in an embodiment of the present application.

[0046] Figure 5 A schematic diagram of center of mass balancing of an inertial group provided in an embodiment of the present application.

[0047] Figure 6 A workflow diagram of a debugging method for reducing line-angle coupling based on a T-type vibration damper provided in an embodiment of the present application.

[0048] Figure 7 A workflow diagram of step S1 of a debugging method for reducing line-angle coupling based on a T-type shock absorber provided in an embodiment of the present application.

[0049] Figure 8 A workflow diagram of step S3 of a debugging method for reducing line-angle coupling based on a T-type shock absorber provided in an embodiment of the present application.

[0050] Fig. 9 A workflow diagram of step S4 of a debugging method for reducing line-angle coupling based on a T-type shock absorber provided in an embodiment of the present application.

[0051] Fig.10 A workflow diagram of step S5 of a debugging method for reducing line-angle coupling based on a T-type vibration damper provided in an embodiment of the present application.

[0052] Fig.11 A structural principle block diagram of a debugging system for reducing line-angle coupling based on a T-type vibration absorber provided in an embodiment of the present application.

[0053] Fig.12 A block diagram of the structural principles of an electronic device provided in an embodiment of the present application.

[0054] Fig.13 A block diagram of the structural principles of a computer-readable storage medium provided in an embodiment of the present application.

[0055] Fig.14 The angular velocity comparison diagram before and after the application of a debugging method for reducing line-angle coupling based on a T-type shock absorber provided in an embodiment of the present application. (a) is an angular velocity comparison diagram without using the method, and (b) is an angular velocity comparison diagram with using the method.

[0056] Component number description

[0057] 1 Inertial group ontology

[0058] 2 Shock absorbers

[0059] 3 Bushing

[0060] 4 Gasket

[0061] 5 Flange

[0062] 6 Counterweight

[0063] 7 Mounting holes

[0064] 8 Shock absorber kit

[0065] 10 Module selection

[0066] 20 Geometric and positional tolerance determination module

[0067] 30 First model building module

[0068] 40 Second model building module

[0069] 50 Third model building module

[0070] 60 processors

[0071] 70 Memory

[0072] 80 Computer readable storage medium

[0073] 90 Computer instructions DETAILED DESCRIPTION

[0074] The following describes the embodiments of the present invention by specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0075] It should be noted that the illustrations provided in the following embodiments are only used to illustrate the basic concept of the present invention in a schematic manner, and thus the illustrations only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0076] See also Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 1 A structural diagram of an inertial group provided for one embodiment of the present application. Figure 2 A structural diagram of an inertial group provided for yet another embodiment of the present application. Figure 3 A structural diagram of a shock absorber assembly of an inertial group provided in an embodiment of the present application. Figure 4 A schematic diagram of the center of mass position of an inertial group provided in an embodiment of the present application. Figure 5 A schematic diagram of the center of mass balancing of an inertial group provided in an embodiment of the present application. The present invention provides an inertial group, including but not limited to an inertial group body 1, a shock absorber 2, a bushing 3, a gasket 4, a flange 5, a counterweight 6, a mounting hole 7, and a shock absorber set 8. A flange 5 is installed on the inertial group body 1, and the shock absorber set 8 includes: the bushing 3 passes through the flange 5, the shock absorber 2 is arranged on the outside of the bushing 3, and the shock absorber 2 is arranged on both sides of the flange 5, the gasket 4 is installed on the top of the upper shock absorber 2, a plurality of counterweight holes are opened on the outer wall of the inertial group body 1, and the counterweight 6 is installed on the counterweight hole.

[0077] Specifically, the counterweight holes can be set to six, the counterweight holes are provided with mounting holes 7, the counterweight block 6 is also provided with a counterweight block, the bushing 3 is in an inverted T shape, the upper shock absorber 2 is in a T shape, and the lower shock absorber 2 is in an inverted T shape. If the fillet at the opening of the flange 5 is too large, stress concentration is easily formed, and if the fillet is too small or there is no fillet, the shock absorber 2 will be damaged and the vibration reduction effect will be affected. After experimental verification, the fillet at the opening of the flange 5 is selected to be R0.3.

[0078] like Figure 2 As shown, the center of mass of the inertial group body 1 coincides with the vibration reduction center of multiple shock absorbers 2. The vibration reduction center is shown as point P. The horizontal position is located at the center of the line connecting the four shock absorbers 2, and the vertical position is located at the vertical height center of the flange 5.

[0079] When the inertial group of the present invention is three-dimensionally modeled, the mass and mass distribution of each part and component (shock absorber 2, bushing 3, gasket 4, three orthogonally placed gyroscopes, three orthogonally placed add-on meters, three circuit boards, four power modules, and several aluminum alloy brackets) are accurately modeled, and the position error in each direction is controlled within 0.1mm. Counterweight positions are reserved on the six outer wall surfaces of the inertial group body 1 for fine-tuning the center of mass after the inertial group is installed. The counterweight block 6 is designed to be small and thin, and multiple blocks can be stacked and used to achieve the purpose of accurately controlling the center of mass. The counterweight holes are all far away from the center of mass. By increasing the lever arm, the counterweight efficiency is improved. The center of mass position of the inertial group is measured, adjusted, and iterated repeatedly by a center of mass measuring instrument, and the position error between the center of mass of the inertial group and the center of vibration reduction is controlled within 0.5mm. The shape and position tolerance of the mold used to produce the shock absorber 2 can be controlled between 0.003-0.005.

[0080] See also Figure 6 , Figure 6 The present invention also provides a debugging method based on a T-type shock absorber to reduce the line angle coupling, including the above-mentioned inertial group, and the debugging method based on the T-type shock absorber to reduce the line angle coupling includes:

[0081] Step S1, selecting the shock absorber 2 and determining the shock absorption frequency of the shock absorber 2.

[0082] Step S2: determining radial and axial geometric tolerances of the production mold of the shock absorber 2.

[0083] Step S3, establishing an axial dimension model of the bushing 3 to obtain the optimal axial dimension of the bushing 3.

[0084] Step S4: establishing a radial dimension model of the bushing 3 to obtain an optimal radial dimension of the bushing 3.

[0085] Step S5, establishing a hole size model of the flange 5 to obtain the optimal hole size of the flange 5.

[0086] See also Figure 7 , Figure 7 The flowchart of step S1 of a debugging method for reducing line angle coupling based on a T-type shock absorber provided in an embodiment of the present application. The step S1 of selecting the shock absorber 2 and determining the shock absorption frequency of the shock absorber 2 includes:

[0087] Step S11, selecting a plurality of shock absorbers 2 from the same batch. Specifically, the shock absorber 2 is a rubber shock absorber, and the first three order resonance frequencies are provided by finite element simulation. The resonance frequency of the shock absorber 2 is determined to be 80 Hz by the given resonance frequency.

[0088] Step S12, selecting the shock absorber 2 formed at one time.

[0089] Step S13: determining the effective vibration damping frequency of the vibration damper 2 according to the selected vibration damper 2.

[0090] Specifically, the radial and axial shape and position tolerances of the production mold of the shock absorber 2 are less than 0.005 mm. The stiffness of the shock absorbers 2 of the same batch is measured by a machine, and the stiffness of the shock absorbers 2 used in the same set of equipment must be the same.

[0091] See also Figure 8 , Figure 8 The workflow diagram of step S3 of a debugging method for reducing line-angle coupling based on a T-type shock absorber provided in an embodiment of the present application. The step S3 of establishing an axial dimension model of the bushing 3 to obtain the optimal axial dimension of the bushing 3 includes:

[0092] Step S31, establish the axial dimension model of the bushing 3, the formula is: h2=2h0+h-2ε1h0, wherein ε1 is the axial preload of the shock absorber 2, h is the thickness of the flange 5, h2 is the axial length of the bushing 3, and h0 is the thickness of the shock absorber 2.

[0093] Step S32, calculating the ratio σ of the thickness h of the flange 5 and the thickness h0 of the shock absorber 2, where h=σh0.

[0094] Step S33, the formula of the thickness h of the flange 5 is: h=h2-2h0+2ε1h0.

[0095] Step S34, determining the best vibration reduction effect of the shock absorber 2 according to the axial preload ε1 and the ratio σ of the shock absorber 2.

[0096] See also Fig. 9 , Fig. 9 The workflow diagram of step S4 of a debugging method for reducing line-angle coupling based on a T-type shock absorber provided in an embodiment of the present application. The step S4 of establishing a radial dimension model of the bushing 3 to obtain the optimal radial dimension of the bushing 3 includes:

[0097] Step S41, establishing a radial dimension model of the bushing 3, the formula is: Among them, ε2 is the radial preload of the shock absorber 2, D0 is the radial size of the bushing 3, D3-2D1 is the middle opening diameter of the shock absorber 2, and D2 is the radial thickness of the shock absorber 2.

[0098] Step S42 , determining the best vibration reduction effect of the shock absorber 2 according to the axial preload ε1 of the shock absorber 2 and the radial preload ε2 of the shock absorber 2 .

[0099] Specifically, when the bushing 3 is machined, the radial thickness dimension D2 of the shock absorber 2 and the axial length dimension h2 of the bushing 3 are positioned as key dimensions, and the dimension tolerance is set to 0.005. In order to reduce the friction force of the bushing 3 on the rubber shock absorber and reduce stress concentration, the surface roughness value of the contact surface between the bushing 3 and the shock absorber 2 is set to 0.8.

[0100] See also Fig.10 , Fig.10 The flowchart of step S5 of a debugging method for reducing line-angle coupling based on a T-type shock absorber provided in an embodiment of the present application. The step S5 of establishing the opening size model of the flange 5 to obtain the optimal opening size of the flange 5 includes:

[0101] Step S51 , establishing a hole size model of the flange 5 , the formula is: D5=D0+2D2, wherein D5 is the hole size of the flange 5 .

[0102] Step S52: Determine the best vibration reduction effect of the vibration absorber 2 according to the opening size D5 of the flange 5.

[0103] When the machining error of the opening size D5 of the flange 5 is within 0.005 mm and the surface roughness is 0.8, the vibration reduction effect of the vibration absorber 2 is the best. When the upper and lower mounting surfaces of the flange 5 are parallel and perpendicular to the axis of the mounting hole 7, and the verticality is 0.1, the vibration reduction effect is the best.

[0104] See also Fig.11 , Fig.11 A block diagram of the structural principle of a debugging system based on a T-type shock absorber to reduce line angle coupling provided in an embodiment of the present application. Similar to the principle of a debugging method based on a T-type shock absorber to reduce line angle coupling of the present invention, the present invention also provides a debugging system based on a T-type shock absorber to reduce line angle coupling, and the debugging system based on a T-type shock absorber to reduce line angle coupling includes a selection module 10, a shape and position tolerance determination module 20, a first model establishment module 30, a second model establishment module 40, and a third model establishment module 50. The selection module 10 is used to select the shock absorber 2 and determine the damping frequency of the shock absorber 2. The shape and position tolerance determination module 20 is used to determine the radial and axial shape and position tolerances of the production mold of the shock absorber 2. The first model establishment module 30 is used to establish an axial dimension model of the bushing 3 to obtain the optimal axial dimension of the bushing 3. The second model establishment module 40 is used to establish a radial dimension model of the bushing 3 to obtain the optimal radial dimension of the bushing 3. The third model building module 50 is used to build a hole size model of the flange 5 to obtain the optimal hole size of the flange 5 .

[0105] See also Fig.12 , Fig.12A block diagram of the structural principle of an electronic device provided in an embodiment of the present application. The present invention also proposes an electronic device, the electronic device includes a processor 60 and a memory 70, the memory 70 stores program instructions, and the processor 60 runs the program instructions to implement the above-mentioned debugging method based on T-type shock absorber to reduce line angle coupling. The processor 60 can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application specific integrated circuit (ASIC) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components; the memory 70 may include a random access memory (RAM), and may also include a non-volatile memory, such as at least one disk storage. The memory 70 may also be an internal memory of the random access memory (RAM) type, and the processor 60 and the memory 70 may be integrated into one or more independent circuits or hardware, such as an application specific integrated circuit (ASIC). It should be noted that the computer program in the above-mentioned memory 70 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, which is stored in a storage medium and includes a number of instructions for a computer device (which may be a personal computer, an electronic device, or a network device, etc.) to perform all or part of the steps of the methods of each embodiment of the present invention.

[0106] Fig.13 , Fig.13A block diagram of the structural principle of a computer-readable storage medium provided in an embodiment of the present application. The present invention also proposes a computer-readable storage medium 80, wherein the computer-readable storage medium 80 stores computer instructions 90, and the computer instructions 90 are used to enable the computer to execute the above-mentioned debugging method based on T-type vibration damper to reduce line angle coupling. The computer-readable storage medium 80 can be an electronic medium, a magnetic medium, an optical medium, an electromagnetic medium, an infrared medium or a semiconductor system or a propagation medium. The computer-readable storage medium 80 can also include semiconductor or solid-state memory, a magnetic tape, a removable computer disk, a random access memory (RAM), a read-only memory (ROM), a hard disk and an optical disk. The optical disk can include a compact disk-read only memory (CD-ROM), a compact disk-read / write (CD-RW) and a DVD.

[0107] See also Fig.14 , Fig.14 A comparison diagram of angular velocities before and after the application of a debugging method for reducing line-angle coupling based on a T-type shock absorber provided in an embodiment of the present application. (a) is an angular velocity comparison diagram without using the method, and (b) is an angular velocity comparison diagram using the method. The present invention can effectively reduce the angular vibrations in three directions caused by line vibrations along a certain direction in a spatial rectangular coordinate system, thereby reducing the impact of line-angle coupling. Taking the line vibration in the X-axis direction as an example, after using the debugging method of the present invention, the angular vibration rates in the other three directions are reduced from being controlled within 30° / s to being controlled within 8° / s.

[0108] In summary, the debugging method for reducing line-angle coupling based on T-type shock absorber of the present invention includes an inertial group, including the selection of shock absorber, the design of bushing, the design of flange and the adjustment of the center of gravity of carrier. The present invention can effectively reduce the angular vibration in three directions caused by the linear vibration along a certain direction in the spatial rectangular coordinate system, thereby reducing the influence of line-angle coupling.

[0109] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A debugging method for reducing line-angle coupling based on a T-type vibration absorber, characterized in that: A kind of inertial group is included, and the inertial group comprises: An inertial group body (1) on which a flange (5) is mounted; A shock absorber kit (8), comprising: A bushing (3) passing through the flange (5); A vibration damper (2) is arranged on the outside of the bushing (3), and the vibration damper (2) is arranged on both sides of the flange (5); A gasket (4) mounted on the top of the upper shock absorber (2); A plurality of counterweight holes are provided on the outer wall surface of the inertial group body (1); A counterweight block (6), which is mounted on the counterweight hole; The debugging method for reducing line-angle coupling based on a T-type vibration damper comprises: S1, selecting the shock absorber (2) and determining the shock absorption frequency of the shock absorber (2); S2, determining the radial and axial geometric tolerances of the production mold of the shock absorber (2); S3, establishing an axial dimension model of the bushing (3) to obtain an optimal axial dimension of the bushing (3); S4, establishing a radial dimension model of the bushing (3) to obtain an optimal radial dimension of the bushing (3); S5, establishing a hole size model of the flange (5) to obtain the optimal hole size of the flange (5); The step S1 of selecting the shock absorber (2) and determining the shock absorption frequency of the shock absorber (2) comprises: S11, selecting a plurality of shock absorbers (2) from the same batch; S12, selecting a vibration damper (2) formed in one step; S13, determining the effective vibration reduction frequency of the vibration absorber (2) according to the selected vibration absorber (2); The step S3 of establishing an axial dimension model of the bushing (3) to obtain the optimal axial dimension of the bushing (3) includes: S31, establishing an axial dimension model of the bushing (3), the formula is: h2=2h0+h-2ε1h0, wherein ε1 is the axial preload of the shock absorber (2), h is the thickness of the flange (5), h2 is the axial length of the bushing (3), and h0 is the thickness of the shock absorber (2); S32, calculating the ratio σ of the thickness h of the flange (5) and the thickness h0 of the shock absorber (2), h=σh0; S33, the formula for the thickness h of the flange (5) is: h = h2-2h0+2ε1h0; S34, determining the optimal vibration reduction effect of the vibration reducer (2) according to the axial preload amount ε1 and the ratio σ of the vibration reducer (2); The step S4 of establishing a radial dimension model of the bushing (3) to obtain the optimal radial dimension of the bushing (3) includes: S41, establishing a radial dimension model of the bushing (3), the formula is: Wherein, ε2 is the radial preload of the shock absorber (2), D0 is the radial dimension of the bushing (3), D3-2D1 is the diameter of the middle opening of the shock absorber (2), and D2 is the radial thickness of the shock absorber (2); S42, determining the optimal vibration reduction effect of the vibration reducer (2) according to the axial preload ε1 of the vibration reducer (2) and the radial preload ε2 of the vibration reducer (2); The step S5 of establishing the opening size model of the flange (5) to obtain the optimal opening size of the flange (5) includes: S51, establishing a hole size model of the flange (5), the formula is: D5 = D0 + 2D2, where D5 is the hole size of the flange (5); S52. Determine the optimal vibration reduction effect of the vibration damper (2) according to the opening size D5 of the flange (5).

2. The debugging method for reducing line-angle coupling based on a T-type vibration absorber according to claim 1 is characterized in that: The bushing (3) is in an inverted T-shape, the upper shock absorber (2) is in a T-shape, and the lower shock absorber (2) is in an inverted T-shape.

3. The debugging method for reducing line-angle coupling based on a T-type vibration absorber according to claim 1 is characterized in that: The radial and axial shape and position tolerances of the production mold of the vibration damper (2) are less than 0.005 mm.

4. The debugging method for reducing line-angle coupling based on a T-type vibration absorber according to claim 1 is characterized in that: When the axial preload ε1 of the shock absorber (2) is in the range of 0.068 to 0.075 and the ratio σ is in the range of 4 to 5, the shock absorber (2) has the best vibration reduction effect.

5. The debugging method for reducing line-angle coupling based on a T-type vibration absorber according to claim 1 is characterized in that: When the difference between the axial preload ε1 of the shock absorber (2) and the radial preload ε2 of the shock absorber (2) is less than or equal to 0.005, that is, |ε1-ε2|≤0.005, and when the machining error of the opening size D5 of the flange (5) is within 0.005 mm and the surface roughness is 0.8, the shock absorber (2) has the best vibration reduction effect.

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