CN111076932A - Test system and test method for aerostatic bearing - Google Patents
Test system and test method for aerostatic bearing Download PDFInfo
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- CN111076932A CN111076932A CN202010013048.1A CN202010013048A CN111076932A CN 111076932 A CN111076932 A CN 111076932A CN 202010013048 A CN202010013048 A CN 202010013048A CN 111076932 A CN111076932 A CN 111076932A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
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- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The invention provides a test system and a test method for an aerostatic bearing, wherein a base is provided with a bracket and a sliding table; a thrust plate extending along a vertical plane is arranged on one side of the bracket facing the sliding table; a sliding block is arranged on the upper side of the sliding table, and the sliding table can drive the sliding block to move close to or far away from the thrust plate; one side surface of the sliding block facing the thrust plate is parallel to a vertical plane and is provided with a concave part with an opening facing the thrust plate, the bottom surface of the concave part is parallel to the vertical plane, and the bottom surface of the concave part is provided with a first barometer; the concave part is positioned above the rotating shaft of the thrust plate; the sliding block is also provided with an air supply device, an air outlet of the air supply device is arranged on the bottom surface of the concave part, the air supply device is also provided with an air inlet used for connecting an air source and a second barometer used for measuring the air pressure of the air inlet; and the sliding block is also provided with a distance measuring device for measuring the horizontal distance between the side surface and the thrust plate. The experimental system can simulate an aerostatic bearing.
Description
Technical Field
The invention relates to the technical field of aerostatic bearings, in particular to a test system and a test method for aerostatic bearings.
Background
The aerostatic bearing is a mechanical component for reducing friction by utilizing a gas film to support load, has the advantages of high speed, high precision, low friction, high and low temperature resistance, radiation resistance, cleanness, environmental protection, long service life, simple structure and the like, is mainly applied to the technical fields of ultra-high speed, ultra-precision, low friction and low power consumption support and the like, and has the rotating speed of hundreds of thousands of revolutions per minute.
FIG. 1 shows a block diagram of an aerostatic bearing, comprising: the air compressor comprises a main shaft rotor 11, a radial bearing 12, a bearing shell 13, a radial bearing air inlet 14, a thrust bearing 15 and a thrust bearing air inlet 16, wherein the main shaft rotor 11 is connected with and driven by a motor, and air with certain pressure flows into a throttling hole and an air cavity through the radial bearing air inlet 14 and the thrust bearing air inlet 16 respectively, so that an air film is formed between the inner walls of the main shaft rotor 11 and the bearing shell 13 to support the main shaft rotor 11, and zero friction movement of the main shaft rotor 11 in operation is realized. The radial bearing 12 and the thrust bearing 15 carry and restrict the radial movement and the axial movement of the spindle rotor 11, respectively.
Here, as shown in fig. 1, the thrust bearing 15 rotates in a chamber 17, and the thrust bearing air inlet 16 blows air into the chamber 17 from the first side wall of the chamber 17, it can be understood that the distance between the thrust bearing 15 and the first side wall, and the air pressure of the air blown from the thrust bearing air inlet 16 affect the normal operation of the aerostatic bearing.
Disclosure of Invention
The invention aims to provide a test system for an aerostatic bearing and a test method thereof.
In order to achieve one of the above objects of the invention, an embodiment of the present invention provides a test system for an aerostatic bearing, comprising: the upper surface of the base is oppositely provided with a bracket and a sliding table; a thrust plate extending along a vertical plane is arranged on one side, facing the sliding table, of the support; a sliding block is arranged on the upper side of the sliding table, and the sliding table can drive the sliding block to move close to or far away from the thrust plate; one side surface, facing the thrust plate, of the sliding block is parallel to the vertical plane and is provided with a concave part with an opening facing the thrust plate, the bottom surface of the concave part is parallel to the vertical plane, and the bottom surface of the concave part is provided with a first barometer; the concave part is positioned above the rotating shaft of the thrust plate; the sliding block is also provided with an air supply device, an air outlet of the air supply device is arranged on the bottom surface of the concave part, and the air supply device is also provided with an air inlet used for connecting an air source and a second barometer used for measuring the air pressure of the air inlet; and the sliding block is also provided with a distance measuring device for measuring the horizontal distance between the side surface and the thrust plate.
As a further improvement of an embodiment of the present invention, a stepping motor is provided on a side of the bracket away from the slide table, a rotor of the stepping motor passes through the bracket in a horizontal direction, and the rotor is fixedly connected to the thrust plate.
As a further improvement of an embodiment of the present invention, the distance measuring apparatus includes: grating ruler reading head and grating ruler.
As a further improvement of an embodiment of the present invention, the gas supply device includes: the slide block is provided with a through hole which penetrates through the slide block in the horizontal direction, one end of the through hole, which is communicated with the concave part, is an air outlet, the other end of the through hole is an air inlet, and a restrictor is arranged in the through hole and matched with the through hole.
The embodiment of the invention also provides a test method for the aerostatic bearing, which comprises the following steps: the length L of a concave part in the up-down direction and the average width in the front-back direction in the aerostatic bearing to be tested are obtained
And a target gauge pressure ratio; providing the test system, wherein an air inlet in the test system is connected with an air source; the length of the concave portion in the test system in the up-down direction is L, and the average width in the front-back direction is L
Controlling the air source to provide air and receiving a first air pressure value P acquired by a first air pressure meteroAnd obtained by a second barometerThe second air pressure value P is obtaineds(ii) a In that
Obtaining the distance h, h and P obtained by the distance measuring devicesThe requirements are met; wherein, PaFor atmospheric pressure, a threshold value is preset>0。
Compared with the prior art, the invention has the technical effects that: the embodiment of the invention provides a test system and a test method for an aerostatic bearing, wherein a base is provided with a bracket and a sliding table; a thrust plate extending along a vertical plane is arranged on one side of the bracket facing the sliding table; a sliding block is arranged on the upper side of the sliding table, and the sliding table can drive the sliding block to move close to or far away from the thrust plate; one side surface of the sliding block facing the thrust plate is parallel to a vertical plane and is provided with a concave part with an opening facing the thrust plate, the bottom surface of the concave part is parallel to the vertical plane, and the bottom surface of the concave part is provided with a first barometer; the concave part is positioned above the rotating shaft of the thrust plate; the sliding block is also provided with an air supply device, an air outlet of the air supply device is arranged on the bottom surface of the concave part, the air supply device is also provided with an air inlet used for connecting an air source and a second barometer used for measuring the air pressure of the air inlet; and the sliding block is also provided with a distance measuring device for measuring the horizontal distance between the side surface and the thrust plate. The experimental system can simulate an aerostatic bearing.
Drawings
FIG. 1 is a schematic diagram of a prior art aerostatic bearing;
FIG. 2A is a front view of a testing system in an embodiment of the present invention;
FIG. 2B is a top view of a testing system in an embodiment of the present invention;
fig. 2C is a schematic structural view of the gas supply device in the embodiment of the present invention.
Detailed Description
The present invention will be described in detail below with reference to embodiments shown in the drawings. These embodiments are not intended to limit the present invention, and structural, methodological, or functional changes made by those skilled in the art according to these embodiments are included in the scope of the present invention.
Terms such as "upper," "above," "lower," "below," and the like, used herein to denote relative spatial positions, are used for ease of description to describe one element or feature's relationship to another element or feature as illustrated in the figures. The spatially relative positional terms may be intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" the other elements or features. Thus, the exemplary term "below" can encompass both an orientation of above and below. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
Also, it should be understood that, although the terms first, second, etc. may be used herein to describe various elements or structures, these described elements should not be limited by these terms. These terms are only used to distinguish these descriptive objects from one another. For example, a first barometer may be referred to as a second barometer, and similarly a second barometer may also be referred to as a first barometer, without departing from the scope of the application.
An embodiment of the present invention provides a test system for an aerostatic bearing, as shown in fig. 2A and 2B, including:
the device comprises a base 2, wherein a support 3 and a sliding table 4 are oppositely arranged on the upper surface of the base 2; here, as shown in fig. 2A, a block 21 may be further provided on the upper surface of the base 2, and the slide table 4 is mounted on the upper side of the block 21, and optionally, the block 21 is integrally formed with the base 2.
A thrust plate 31 extending along a vertical plane is arranged on one side of the bracket 3 facing the sliding table 4; a sliding block 5 is arranged on the upper side of the sliding table 4, and the sliding table 4 can drive the sliding block 5 to move close to or far away from the thrust plate 31; here, in the case shown in fig. 2A and 2B, the right side of the cradle 3 is provided with a thrust plate 31. The sliding table 4 may include a sliding rail and a screw rod, the lower surface of the sliding block 5 is provided with a concave portion matching with the sliding rail, and the screw rod can drive the sliding table 4 to move close to or away from the thrust plate 31.
One side surface of the slider 5 facing the thrust plate 31 is parallel to the vertical plane, and is provided with a concave part 51 with an opening facing the thrust plate 31, the bottom surface of the concave part 51 is parallel to the vertical plane, and the bottom surface of the concave part 51 is provided with a first barometer 52; the concave part 51 is positioned above the rotating shaft of the thrust plate 31; the sliding block 5 is further provided with an air supply device 6, an air outlet of the air supply device 6 is arranged on the bottom surface of the concave part 51, and the air supply device 6 is further provided with an air inlet used for being connected with an air source and a second barometer used for measuring air pressure of the air inlet; here, the left side surface of the slider 5 faces the thrust plate 31, the distance between the left side surface of the slider 5 and the right side surface of the thrust plate 31 is h, the length of the concave portion 51 in the vertical direction is L, and the average width in the front-rear direction is a. Here, since the opening of the recess 52 faces the thrust plate 31, the right side surface of the recess 52 is the bottom surface of the recess 52.
The slider 5 is further provided with a distance measuring device 53 for measuring the horizontal distance between the side surface and the thrust plate 31. Here, the gas supply device 6 will receive a pressure PsAnd will have a pressure of PoIs ejected through its air outlet, thereby forming a film of air between the right side surface of the thrust plate 31 and the left side surface of the slider, which is understood to be a simulation of the thrust bearing 15 and the chamber 17 in fig. 1.
In this embodiment, a stepping motor 32 is disposed on one side of the bracket 3 away from the sliding table 4, and a rotor of the stepping motor 32 passes through the bracket 3 in the horizontal direction and is fixedly connected to the thrust plate 31. Here, the stepping motor 32 can drive the thrust plate 31 to rotate at a set speed, and in practice, even under the same conditions, the rotation of the thrust bearing 15 has an influence on the stability of the spindle rotor 11, and therefore, this situation can be simulated by the stepping motor 32.
In this embodiment, the distance measuring device 53 includes: a grating scale reading head 531 and a grating scale 532. Here, the distance measuring device 53 can measure the horizontal distance between the side surface and the thrust plate 31 with the cooperation of the scale reading head 531 and the scale 532.
In this embodiment, the gas supply device 6 includes: a through hole 62 horizontally penetrating the slider 5, one end of the through hole communicating with the concave part 51 being an air outlet and the other end being an air inlet, a throttle 63 being provided in the through hole 62, the throttle 63 being fitted with the through hole 62. Here, as shown in fig. 2C, an air inlet joint 61 is installed at the air inlet of the through hole 62, the air inlet joint 61 is communicated with an air source, and the throttle 63 is matched with the through hole 62, that is, the air flowing in from the air inlet joint 61 can only pass through the throttle 63, so that the throttle 63 can adjust the air speed and the air output of the air outlet.
The embodiment of the invention provides a test method for an aerostatic bearing, which comprises the following steps:
step 1: the length L of the concave portion 51 in the up-down direction and the average width in the front-back direction in the aerostatic bearing to be tested were obtained
And a target gauge pressure ratio;
step 2: providing the test system in the first embodiment, wherein an air inlet in the test system is connected with an air source; the length of the recess 51 in the vertical direction in the test system is L, and the average width in the front-rear direction is L
And step 3: controls the air supply to supply air and receives the first air pressure value P acquired by the first air pressure gauge 52oAnd a second barometric pressure value P obtained by the second barometers；
And 4, step 4: in that
The distance h obtained by the distance measuring device 53 is obtained, and h and PsThe requirements are met; wherein, PaFor atmospheric pressure, a threshold value is preset>0。
Here, Ps＞Po＞PaAnd therefore, the first and second electrodes are,
gauge pressure ratio
Is a core index for describing the aerostatic bearing, therefore, when
Then h and P are representedsAll meet the requirements, the actual aerostatic bearing is designed so that the distance between the thrust bearing 15 and the first side wall of the chamber 17 is h, and the air pressure of the air input to the thrust bearing air inlet 16 is Ps。
Optionally, in
The following steps are continuously performed: the sliding table 4 is controlled to adjust the distance between the sliding block 5 and the thrust plate 31 or adjust the pressure drop value of the throttler 63, and the third air pressure value P acquired by the first air pressure gauge 52 is receivedo', and a fourth air pressure value P obtained by the second air pressure gauges'; up to
Here, an important theoretical basis in the design of the aerostatic bearing is the novi-scotch (Navier Stokes) equation, which, based on the deduction and simplification of Powell, yields the following important fundamental equations of the hydrostatic bearing:
where μ, R, T are constants associated with air and m is the air consumption, therefore, when
Need to adjust PsAnd PoThe difference between h and P can be adjusted accordinglyoEventually make
Optionally, in the
The following steps are continuously performed: controlling the sliding table 4 to increase the distance between the sliding block 5 and the thrust plate 31 and receiving a third air pressure value P acquired by the first air pressure gauge 52o', and a fourth air pressure value P obtained by the second air pressure gauges'; up to
Here, when
Description of the preferred embodimentssAnd PoIf the difference between the values is too large, the value of h can be increased to ensure that
Become smaller, eventually make
Optionally, in the
The following steps are continuously performed: controlling the sliding table 4 to reduce the distance between the sliding block 5 and the thrust plate 31, and receiving a third air pressure value P acquired by the first air pressure gauge 52o', and a fourth air pressure value P obtained by the second air pressure gauges'; up to
Here, when
Description of the preferred embodimentssAnd PoIf the difference between the values is too large, the value of h can be reduced to ensure that
Become larger, eventually make
Optionally, in the
The following steps are continuously performed: the pressure drop value of the throttle 63 is reduced, and the third air pressure value P acquired by the first air pressure gauge 52 is receivedo', and a fourth air pressure value P obtained by the second air pressure gauges'; up to
Here, when
Description of the preferred embodimentssAnd PoIf the difference between the values is too large, P can be made to be large by reducing the pressure drop value of the throttle 63oBecome larger, eventually make
Optionally, in the
The following steps are continuously performed: the pressure drop value of the throttle 63 is increased, and the third air pressure value P acquired by the first air pressure gauge 52 is receivedo', and a fourth air pressure value P obtained by the second air pressure gauges'; up to
Here, when
Description of the preferred embodimentssAnd PoIf the difference therebetween is too small, the pressure drop value of the throttle 63 can be increased or decreased so that P is smalleroBecome smaller, eventually make
It should be understood that although the present description refers to embodiments, not every embodiment contains only a single technical solution, and such description is for clarity only, and those skilled in the art should make the description as a whole, and the technical solutions in the embodiments can also be combined appropriately to form other embodiments understood by those skilled in the art.
The above-listed detailed description is only a specific description of a possible embodiment of the present invention, and they are not intended to limit the scope of the present invention, and equivalent embodiments or modifications made without departing from the technical spirit of the present invention should be included in the scope of the present invention.
Claims (5)
1. A testing system for aerostatic bearings, comprising:
the device comprises a base (2), wherein a support (3) and a sliding table (4) are oppositely arranged on the upper surface of the base (2);
a thrust plate (31) extending along a vertical plane is arranged on one side, facing the sliding table (4), of the support (3);
a sliding block (5) is arranged on the upper side of the sliding table (4), and the sliding table (4) can drive the sliding block (5) to move close to or far away from the thrust plate (31);
one side surface, facing the thrust plate (31), of the sliding block (5) is parallel to the vertical plane, a concave part (51) with an opening facing the thrust plate (31) is arranged, the bottom surface of the concave part (51) is parallel to the vertical plane, and a first air pressure gauge (52) is arranged on the bottom surface of the concave part (51); the concave part (51) is positioned above the rotating shaft of the thrust plate (31); the sliding block (5) is further provided with an air supply device (6), an air outlet of the air supply device (6) is arranged on the bottom surface of the concave part (51), and the air supply device (6) is further provided with an air inlet used for being connected with an air source and a second barometer used for measuring air pressure of the air inlet;
and the sliding block (5) is also provided with a distance measuring device (53) for measuring the horizontal distance between the side surface and the thrust plate (31).
2. The testing system of claim 1, wherein:
one side of the bracket (3) far away from the sliding table (4) is provided with a stepping motor (32), and a rotor of the stepping motor (32) penetrates through the bracket (3) in the horizontal direction and is fixedly connected to the thrust plate (31).
3. Testing system according to claim 1, characterized in that the distance measuring device (53) comprises: a grating ruler reading head (531) and a grating ruler (532).
4. Testing system according to claim 1, characterized in that the gas supply device (6) comprises: a through hole (62) penetrating through the sliding block (5) in the horizontal direction, wherein one end of the through hole communicated with the concave part (51) is an air outlet, the other end of the through hole is an air inlet, a throttle (63) is arranged in the through hole (62), and the throttle (63) is matched with the through hole (62).
5. A test method for aerostatic bearings, characterized by comprising the steps of:
the length L of a concave part (51) in the vertical direction and the average width in the front-rear direction in the aerostatic bearing to be tested are obtained
And a target gauge pressure ratio;
providing a test system according to any one of claims 1-4, wherein the gas inlet of the test system is connected to a gas source; the length of the recess (51) in the vertical direction in the test system is L, and the average width in the front-rear direction is L
Controlling the air supply to provide air, receiving a first air pressure value P acquired by a first air pressure gauge (52)oAnd a second barometric pressure value P obtained by the second barometers；
In that
Then, the distance h obtained by the distance measuring device (53) is obtained, and h and PsThe requirements are met; wherein, PaFor atmospheric pressure, a threshold value is preset>0。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010013048.1A CN111076932A (en) | 2020-01-07 | 2020-01-07 | Test system and test method for aerostatic bearing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010013048.1A CN111076932A (en) | 2020-01-07 | 2020-01-07 | Test system and test method for aerostatic bearing |
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| Publication Number | Publication Date |
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| CN111076932A true CN111076932A (en) | 2020-04-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010013048.1A Pending CN111076932A (en) | 2020-01-07 | 2020-01-07 | Test system and test method for aerostatic bearing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114659787A (en) * | 2022-04-11 | 2022-06-24 | 哈尔滨工业大学 | Device and method for testing dual-purpose performance of ultra-high-speed rolling bearing and gas thrust bearing |
-
2020
- 2020-01-07 CN CN202010013048.1A patent/CN111076932A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114659787A (en) * | 2022-04-11 | 2022-06-24 | 哈尔滨工业大学 | Device and method for testing dual-purpose performance of ultra-high-speed rolling bearing and gas thrust bearing |
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