CN114152376A - Heavy load micro-torque testing device based on air bearing - Google Patents
Heavy load micro-torque testing device based on air bearing Download PDFInfo
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- CN114152376A CN114152376A CN202111269875.8A CN202111269875A CN114152376A CN 114152376 A CN114152376 A CN 114152376A CN 202111269875 A CN202111269875 A CN 202111269875A CN 114152376 A CN114152376 A CN 114152376A
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- 238000012360 testing method Methods 0.000 title claims abstract description 29
- 238000009434 installation Methods 0.000 claims description 2
- 238000005188 flotation Methods 0.000 claims 7
- 210000005069 ears Anatomy 0.000 claims 3
- 230000002093 peripheral effect Effects 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 6
- 238000012545 processing Methods 0.000 description 10
- 230000009471 action Effects 0.000 description 4
- 230000006872 improvement Effects 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
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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
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- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The invention discloses a heavy-load micro-moment testing device based on air bearing, and relates to the technical field of spacecrafts. The invention comprises a cylindrical base, wherein an outer sleeve is sleeved at the top end in the cylindrical base; the inner wall of the outer sleeve is connected with an air floating sleeve in an interference manner; the outer wall of the top end of the outer sleeve is fixedly connected with a supporting seat through a bolt; the top end part of the supporting seat is sleeved with an air floating plate; the top end part of the air floating plate is fixedly connected with a table top through a bolt; the inner wall of the air floating sleeve is sleeved with a main shaft sleeve; the top end part of the main shaft pipe sleeve is fixedly connected with the table top through a bolt. According to the invention, the first air nozzle and the table top form an axial air thrust bearing, the second air nozzle and the main shaft pipe sleeve form a radial air journal bearing, and based on the design of the air bearing, a shaft system with large bearing capacity, small friction force, small noise, small vibration, high axis rotation precision and long service life can be obtained, so that the moment acting on a spacecraft and an arrow body can be accurately collected.
Description
Technical Field
The invention belongs to the technical field of spacecrafts, and particularly relates to a heavy-load micro-moment testing device based on air bearing.
Background
The appearance of the spacecraft expands the range of human activities from the earth atmosphere to a wide boundless universe space, causes the leap of human understanding nature and nature improvement, and has great influence on social economy and social life.
The spacecraft and the rocket body are subjected to a large external force in the launching and launching process, and the spacecraft and the rocket body can be damaged, so that internal equipment loses working capacity, and the spacecraft fails. Therefore, a stress simulation test is needed in the design process of the spacecraft and the rocket body, and the designed structure of the spacecraft and the rocket body is more reasonable by effectively collecting test data and carrying out optimization design, so that the use requirement can be met, and the energy-saving requirement can be met. However, the spacecraft and the arrow body are generally heavier, and the friction torque of the detection device based on the common bearing support is larger, so that the accuracy of stress data applied to the spacecraft and the arrow body is influenced.
Disclosure of Invention
The invention aims to provide a heavy-load micro-torque testing device based on air bearing, wherein an axial air thrust bearing is formed by a first air nozzle and a table board, a radial air journal bearing is formed by a second air nozzle and a main shaft pipe sleeve, and the problem of large friction torque of the conventional detecting device supported by a common bearing is solved based on the design of the air bearing.
In order to solve the technical problems, the invention is realized by the following technical scheme:
the invention relates to a heavy-load micro-moment testing device based on air bearing, which comprises a cylindrical base,
an outer sleeve is sleeved at the top end in the cylindrical base; the inner wall of the outer sleeve is connected with an air floating sleeve in an interference manner;
the outer wall of the top end of the outer sleeve is fixedly connected with a supporting seat through a bolt; the top end part of the supporting seat is sleeved with an air floating plate; the top end part of the air floating plate is fixedly connected with a table top through a bolt;
a main shaft pipe sleeve is sleeved on the inner wall of the air floating sleeve; the top end part of the main shaft pipe sleeve is fixedly connected with the table top through a bolt.
Furthermore, the inner wall of the cylindrical base is provided with a mounting lug; the cylindrical base is fixedly connected with a mounting plate through mounting lugs and bolts; the upper surface of the mounting plate is fixedly connected with a torque collector through bolts.
Further, the lower surface of the air floating plate is provided with first air nozzles in an annular array; a first annular groove matched with the first air nozzle is formed in the upper surface of the supporting seat.
Further, the first air nozzle and the table top form an axial air thrust bearing.
Further, a second air nozzle is arranged on the inner wall of the air floatation sleeve in an annular array; and a second annular groove matched with the second air nozzle is formed in the outer wall of the main shaft pipe sleeve.
Further, the second air nozzle and the main shaft pipe sleeve form a radial air journal bearing.
Further, the main shaft pipe sleeve is designed to be of a shaft shoulder-free structure.
Furthermore, the upper surface of the table top is a test piece mounting surface; the lower surface of the table top is flush with the top end of the spindle pipe sleeve and the upper surface of the air floating plate.
Furthermore, a mounting flange is arranged on the circumferential side face of the bottom end of the cylindrical base.
The invention has the following beneficial effects:
1. according to the invention, the first air nozzle and the table top form an axial air thrust bearing, the second air nozzle and the main shaft pipe sleeve form a radial air journal bearing, and based on the design of the air bearing, a shaft system with large bearing capacity, small friction force, small noise, small vibration, high axis rotation precision and long service life can be obtained, so that the moment acting on a spacecraft and an arrow body can be accurately collected.
2. In the invention, the main shaft sleeve is designed without a shaft shoulder, so that the processing difficulty of the end surface of the shaft shoulder and the outer circle is reduced, and the processing precision of the perpendicularity of the outer circle and the end surface of the shaft is improved.
3. According to the invention, the upper flat surface of the table top is set as a test piece mounting surface, the lower surface of the table top and the top end of the main shaft pipe sleeve and the air floating plate are in the same plane, and one-time grinding is adopted during processing, so that a uniform reference is provided for subsequent assembly, the flatness, the parallelism processing precision and the shafting assembly precision of the upper plane and the lower plane are favorably improved, and the requirement of practical use is met.
Of course, it is not necessary for any product in which the invention is practiced to achieve all of the above-described advantages at the same time.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a heavy-load micro-moment testing device based on air bearing.
Fig. 2 is a schematic cross-sectional structural view of a heavy-load micro-moment testing device based on an air bearing.
In the drawings, the components represented by the respective reference numerals are listed below:
1-cylindrical base, 2-outer sleeve, 3-air floating sleeve, 4-supporting base, 5-air floating plate, 6-table top, 7-main shaft sleeve, 8-mounting plate, 9-torque collector, 10-first air nozzle, 11-second air nozzle, 12-mounting lug and 13-mounting flange.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-2, the invention relates to a heavy load micro-torque testing device based on air bearing, comprising a cylindrical base 1, wherein an outer sleeve 2 is sleeved at the top end in the cylindrical base 1; the inner wall of the outer sleeve 2 is connected with an air floating sleeve 3 in an interference manner; the outer wall of the top end of the outer sleeve 2 is fixedly connected with a supporting seat 4 through a bolt; the top end part of the supporting seat 4 is sleeved with an air floating plate 5; the top end part of the air floating plate 5 is fixedly connected with a table top 6 through bolts; the inner wall of the air floating sleeve 3 is sleeved with a main shaft sleeve 7; the top end part of the main shaft sleeve 7 is fixedly connected with the table top 6 through a bolt.
Wherein, the inner wall of the cylindrical base 1 is provided with a mounting lug 12; the cylindrical base 1 is fixedly connected with a mounting plate 8 through a mounting lug 12 and a bolt; the upper surface of the mounting plate 8 is fixedly connected with a torque collector 9 through bolts.
Wherein, the lower surface of the air floating plate 5 is provided with a first air nozzle 10 in an annular array; the upper surface of the supporting seat 4 is provided with a first annular groove matched with the first air nozzle 10; the first air nozzle 10 and the table-board 6 form an axial air thrust bearing, in short, under the action of continuous operation of the first air nozzle 10, the pressure in the first annular groove is increased, and the axial air thrust bearing is formed because the pressure relief gap is smaller, so that the air floating plate 5 is ensured to be suspended.
Wherein, the inner wall of the air floatation sleeve 3 is provided with a second air nozzle 11 in an annular array; the outer wall of the main shaft pipe sleeve 7 is provided with a second annular groove matched with the second air nozzle 11; the second air nozzle 11 and the main shaft sleeve 7 form a radial air journal bearing, in short, under the action of continuous operation of the second air nozzle, the pressure in the second annular groove is increased, and the radial air journal bearing is formed due to the small pressure relief gap, so that the suspension of the main shaft sleeve 7 is ensured.
The main shaft pipe sleeve 7 is designed to be of a shaft shoulder-free structure, and in short, the shaft shoulder-free design is adopted, so that the processing difficulty of the end face of the shaft shoulder and the outer circle is reduced, and the perpendicularity processing precision of the outer circle and the end face of the shaft is favorably improved.
Wherein, the upper surface of the table-board 6 is a mounting surface of a test piece; the lower surface of the table top 6, the top end of the spindle pipe sleeve 7 and the upper surface of the air floating plate 5 are parallel and level with each other, in short, one-time grinding is adopted when machining is conducted, a uniform reference is provided for subsequent assembly, improvement of the flatness of the upper plane and the lower plane, machining accuracy of parallelism and assembly accuracy of a shaft system is facilitated, and the requirement of practical use is met.
Wherein, the periphery of the bottom end of the cylindrical base 1 is provided with a mounting flange 13, in short, when a stress simulation test is carried out, the heavy-load micro-torque testing device is fixedly mounted through the mounting flange 13 at the bottom end of the cylindrical base 1.
One specific application of this embodiment is: in a stress simulation test, a heavy-load micro-torque testing device is fixedly installed through an installation flange 13 at the bottom end of a cylindrical base 1, under the action of continuous operation of a first air nozzle 10, the pressure in a first annular groove is increased, an axial air thrust bearing is formed due to small pressure relief gaps, the air floating plate 5 is ensured to suspend, under the action of continuous operation of a second air nozzle, the pressure in a second annular groove is increased, and a radial air journal bearing is formed due to small pressure relief gaps, the main shaft pipe sleeve 7 is ensured to suspend, based on the design of the air bearing, a shaft system with large bearing capacity, small friction, small noise, small vibration, high axis rotation precision and long service life can be obtained, so that the torque applied to a spacecraft and an arrow body can be accurately acquired, and the main shaft pipe sleeve 7 is designed to be of a shaft-shoulder-free structure, so that the processing difficulty of the end face and the excircle of the shaft shoulder is reduced, the processing precision of the verticality of the excircle and the shaft end face is improved, and meanwhile, the upper surface of the table top 6 is a test piece mounting surface; the lower surface of the table top 6, the top end of the spindle pipe sleeve 7 and the upper surface of the air floating plate 5 are parallel and level with each other, one-time grinding is adopted when processing is convenient, a unified reference is provided for subsequent assembly, improvement of the flatness of the upper plane and the lower plane, the processing precision of the parallelism and the assembly precision of a shaft system is facilitated, and the requirement of practical use is met.
In the description herein, references to the description of "one embodiment," "an example," "a specific example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111269875.8A CN114152376A (en) | 2021-10-29 | 2021-10-29 | Heavy load micro-torque testing device based on air bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111269875.8A CN114152376A (en) | 2021-10-29 | 2021-10-29 | Heavy load micro-torque testing device based on air bearing |
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| CN114152376A true CN114152376A (en) | 2022-03-08 |
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| CN202111269875.8A Pending CN114152376A (en) | 2021-10-29 | 2021-10-29 | Heavy load micro-torque testing device based on air bearing |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10160639A (en) * | 1996-12-02 | 1998-06-19 | Hitachi Powdered Metals Co Ltd | Bearing-testing machine |
| JP2004340760A (en) * | 2003-05-15 | 2004-12-02 | Sankyo Seiki Mfg Co Ltd | Rotational runout inspection device and rotational runout test method |
| JP3137543U (en) * | 2007-05-25 | 2007-11-29 | 達鵬科技股▲分▼有限公司 | Spindle unit |
| CN102650560A (en) * | 2012-04-24 | 2012-08-29 | 上海卫星工程研究所 | Large-scale rotary load high-precision dynamic balance measuring device for spacecraft |
| CN103759871A (en) * | 2014-01-02 | 2014-04-30 | 上海大学 | Device for testing dynamic friction torque of air static-pressure axial thrust bearing |
| CN106989854A (en) * | 2016-11-30 | 2017-07-28 | 哈尔滨工业大学 | The micro- impulse measurement device of jet based on air floating table |
| CN108344534A (en) * | 2018-02-07 | 2018-07-31 | 哈尔滨工业大学 | A kind of combined load lower bearing friction torque test device and method |
| CN212844347U (en) * | 2020-08-14 | 2021-03-30 | 洛阳汇智测控技术有限公司 | Multifunctional bearing friction torque measuring instrument |
-
2021
- 2021-10-29 CN CN202111269875.8A patent/CN114152376A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10160639A (en) * | 1996-12-02 | 1998-06-19 | Hitachi Powdered Metals Co Ltd | Bearing-testing machine |
| JP2004340760A (en) * | 2003-05-15 | 2004-12-02 | Sankyo Seiki Mfg Co Ltd | Rotational runout inspection device and rotational runout test method |
| JP3137543U (en) * | 2007-05-25 | 2007-11-29 | 達鵬科技股▲分▼有限公司 | Spindle unit |
| CN102650560A (en) * | 2012-04-24 | 2012-08-29 | 上海卫星工程研究所 | Large-scale rotary load high-precision dynamic balance measuring device for spacecraft |
| CN103759871A (en) * | 2014-01-02 | 2014-04-30 | 上海大学 | Device for testing dynamic friction torque of air static-pressure axial thrust bearing |
| CN106989854A (en) * | 2016-11-30 | 2017-07-28 | 哈尔滨工业大学 | The micro- impulse measurement device of jet based on air floating table |
| CN108344534A (en) * | 2018-02-07 | 2018-07-31 | 哈尔滨工业大学 | A kind of combined load lower bearing friction torque test device and method |
| CN212844347U (en) * | 2020-08-14 | 2021-03-30 | 洛阳汇智测控技术有限公司 | Multifunctional bearing friction torque measuring instrument |
Non-Patent Citations (1)
| Title |
|---|
| 郑伟英, 中国工业出版社 * |
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Application publication date: 20220308 |