CN108896313B - Device and method for detecting axial loading of double bearings of aircraft - Google Patents
Device and method for detecting axial loading of double bearings of aircraft Download PDFInfo
- Publication number
- CN108896313B CN108896313B CN201810907228.7A CN201810907228A CN108896313B CN 108896313 B CN108896313 B CN 108896313B CN 201810907228 A CN201810907228 A CN 201810907228A CN 108896313 B CN108896313 B CN 108896313B
- Authority
- CN
- China
- Prior art keywords
- test
- test bearing
- bearing
- digital display
- connecting piece
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims description 5
- 238000001514 detection method Methods 0.000 claims abstract description 21
- 230000003068 static effect Effects 0.000 claims abstract description 14
- 238000009434 installation Methods 0.000 abstract description 2
- 239000011148 porous material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
Classifications
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses an axial loading detection device for double bearings of an aircraft, which comprises a connecting piece, a central shaft, cantilevers, a base and a digital display spring balance with hooks, wherein two ends of the central shaft are provided with two test bearings, inner rings of the two test bearings are in tight fit with the central shaft, the lower end of the central shaft is arranged in a first central hole of the base, the upper end of the central shaft is sleeved in a second central hole at one end of the connecting piece, the other end of the connecting piece is connected with a pressure head of stretching pressure equipment, two cantilevers are radially and symmetrically arranged on the outer wall of the central shaft, and the tail ends of the two cantilevers are respectively connected with the digital display spring balance with the hooks. The invention can simulate the installation state and the stress direction of the double bearings in the aircraft, and combines the adjustable tensile pressure equipment to detect that the working state of the bearings is still good under the condition of bearing larger adjustable axial loading force, and can also test the maximum static friction moment after loading the axial standard load. The invention also discloses an aircraft double-bearing axial loading detection method.
Description
Technical Field
The invention relates to the field of bearings, in particular to an aircraft double-bearing axial loading detection device and a detection method.
Background
Certain duplex bearings installed in aerial vehicles are subject to axial resistance during operation, requiring that the bearings remain in good operation under high axial loading forces. It is therefore necessary to detect whether the duplex bearing installed in the aircraft is rotationally flexible after being loaded in the axial direction, and to test the maximum static friction moment after loading a standard load.
Disclosure of Invention
In order to solve the technical problems, the invention provides an axial loading detection device for an aircraft double-bearing, which is simple in structure and high in detection precision, and provides an axial loading detection method for the aircraft double-bearing.
The technical scheme for solving the problems is as follows: the utility model provides an aircraft duplex bearing axial loading detection device, includes connecting piece, axis, cantilever, base, takes couple digital display spring balance, two test bearings are installed at the axis both ends, two test bearing inner circle and axis are tight fit, the first centre bore in the middle of the base is installed to the axis lower extreme, and the test bearing outer lane of axis lower extreme is loose fit with first centre bore pore wall, the epaxial end cover is installed in the second centre bore of connecting piece one end, and the test bearing outer lane of epaxial end is loose fit with second centre bore pore wall, the connecting piece other end is connected with the pressure head of tensile pressure equipment, radial symmetry is equipped with two cantilevers on the axis outer wall, and one takes couple digital display spring balance is connected respectively to the terminal of two cantilevers.
According to the axial loading detection device for the double-bearing of the aircraft, the middle part of the outer wall of the center shaft is symmetrically provided with the two threaded holes, and the two cantilevers are screwed into the two threaded holes respectively.
According to the device for detecting axial loading of the double bearings of the aircraft, the inner washers are arranged between the inner rings of the two test bearings and the center shaft.
According to the aircraft double-bearing axial loading detection device, the outer washers used for limiting the outer ring of the test bearing are arranged in the first groove in the first central hole of the base and the second groove in the second central hole of one end of the connecting piece.
According to the aircraft double-bearing axial loading detection device, the base is provided with the interface which is installed with the workbench of the stretching pressure equipment.
According to the axial loading detection device for the double-bearing of the aircraft, the pulling force direction of the digital display spring balance with the hook is in the horizontal direction, and the included angle between the pulling force direction of the digital display spring balance with the hook and the length direction of the cantilever is 90 degrees.
According to the device for detecting axial loading of the double bearings of the aircraft, the pulling directions of the two digital display spring scales with the hooks are opposite.
The method for detecting the axial loading of the duplex bearing of the aircraft comprises the following steps:
step one: two test bearings are respectively arranged at the upper end and the lower end of the center shaft, and the inner rings of the test bearings are tightly matched with the center shaft; then the two cantilevers are screwed into threaded holes in the middle of the outer wall of the center shaft respectively, then the lower end of the center shaft is installed into a first center hole of a base, the outer ring of a test bearing at the lower end of the center shaft is in loose fit with the wall of the first center hole, finally a connecting piece is sleeved on the test bearing at the upper end of the center shaft, and the outer ring of the test bearing at the upper end of the center shaft is in loose fit with the wall of a second center hole of the connecting piece;
step two: the whole detection device is arranged on an equipment workbench through a screw nut, a connecting piece is connected with a pressure head of stretching pressure equipment through a bolt, then hooks of two digital display spring scales with hooks are respectively hooked on grooves at the tail ends of a cantilever, and the pulling force direction of the digital display spring scales with hooks is ensured to be in the horizontal direction and form an included angle of 90 degrees with the length direction of the cantilever;
step three: starting a stretching pressure device, wherein a pressure head of the stretching pressure device applies gradually increased axial pressure to a test bearing through a connecting piece, the test bearing bears the gradually increased axial pressure, when the pressure applied by the stretching pressure device reaches a certain standard value required by the test bearing, the applied pressure is kept at the moment, and the test bearing is pulled to rotate through a digital display spring balance with a hook, so that the maximum static friction moment of the test bearing after the axial standard load is loaded is obtained;
step four: and stopping pulling the test bearing to rotate, removing one of the digital display spring scales with the hooks, continuously adjusting the pressure of the stretching pressure equipment to axially load the test bearing, and continuously pulling the digital display spring scale with the hooks to rotate the test bearing for 1 minute when the axial load of the test bearing is larger than a certain load value required by the test, wherein the test bearing rotates flexibly, and the working state is stable, so that the test is completed.
In the third step, the maximum static friction force value of the test bearing is the maximum reading displayed by the digital display spring balance with the hook before the test bearing starts rotating, and the product of the sum of the diameter of the inner ring and the diameter of the outer ring of the test bearing divided by 2 and the maximum static friction force value is the maximum static friction moment of the test bearing after loading the axial standard load.
The invention has the beneficial effects that: the invention can simulate the installation state and the stress direction of the double bearing in the aircraft, and combines the adjustable stretching pressure equipment to detect whether the working state of the bearing is still good under the condition of bearing larger adjustable axial loading force, and simultaneously can test the maximum static friction moment after loading the axial standard load.
Drawings
FIG. 1 is a schematic diagram of the structure of the detecting device of the present invention.
Fig. 2 is a top view of the present invention.
Detailed Description
The invention is further described below with reference to the drawings and examples.
As shown in fig. 1 and 2, the dual-bearing axial loading detection device for the aircraft comprises a connecting piece 1, an outer gasket 2, an inner gasket 3, a central shaft 4, a cantilever 5, a base 6 and a digital display spring balance 8 with a hook, wherein two test bearings 7 are arranged at two ends of the central shaft 4, the inner gaskets 3 are respectively arranged between the inner rings of the two test bearings 7 and the central shaft 4, the inner rings of the two test bearings 7 are tightly matched with the central shaft 4, the lower end of the central shaft 4 is arranged in a first central hole in the middle of the base 6, the outer rings of the test bearings at the lower end of the central shaft 4 are loosely matched with the wall of the first central hole, and an interface for installing a workbench 11 of a tensile pressure device is reserved on the base 6; the upper end of the center shaft 4 is sleeved in a second center hole at one end of the connecting piece 1, the outer ring of the test bearing at the upper end of the center shaft 4 is in loose fit with the wall of the second center hole, the other end of the connecting piece 1 is connected with a pressure head 9 of a stretching pressure device, and an outer gasket 2 used for limiting the outer ring of the test bearing 7 is arranged in a first groove in the first center hole of the base 6 and in a second groove in the second center hole at one end of the connecting piece 1; two threaded holes are symmetrically formed in the middle of the outer wall of the center shaft 4, two cantilevers 5 are screwed into the two threaded holes respectively, the tail ends of the two cantilevers 5 are connected with a digital display spring balance with hooks respectively, the pulling force direction of the digital display spring balance with hooks is in the horizontal direction, and the included angle between the pulling force direction of the digital display spring balance with hooks and the length direction of the cantilevers 5 is 90 degrees. The pulling force directions of the two digital display spring scales with the hooks are opposite.
The method for detecting the axial loading of the duplex bearing of the aircraft comprises the following steps:
step one: after the inner washers 3 are arranged at the upper end and the lower end of the center shaft 4, two test bearings 7 are respectively arranged, and the inner rings of the test bearings 7 are tightly matched with the center shaft 4; then two cantilevers 5 are screwed into threaded holes in the middle of the outer wall of a center shaft 4 respectively, then an outer gasket 2 is arranged in a first groove of a first center hole of a base 6 and a second groove of a second center hole of a connecting piece 1, the lower end of the center shaft 4 is arranged in the first center hole of the base 6, a test bearing outer ring at the lower end of the center shaft 4 is in loose fit with the wall of the first center hole, finally the connecting piece 1 is sleeved on a test bearing at the upper end of the center shaft 4, and the test bearing outer ring at the upper end of the center shaft 4 is in loose fit with the wall of the second center hole of the connecting piece 1;
step two: the whole detection device is arranged on a workbench 11 of a stretching pressure device through a screw nut, a connecting piece 1 is connected with a pressure head 9 of the stretching pressure device through a bolt 10, then hooks of two digital display spring scales 8 with hooks are respectively hooked on grooves at the tail end of a cantilever 5, and the pulling force direction of the digital display spring scales 8 with hooks is ensured to be in the horizontal direction and form an included angle of 90 degrees with the length direction of the cantilever 5;
step three: starting a stretching pressure device, wherein a pressure head 9 of the stretching pressure device applies gradually increased axial pressure to a test bearing 7 through a connecting piece 1, the test bearing 7 bears the gradually increased axial pressure, when the pressure applied by the stretching pressure device reaches a certain standard value required by the test bearing 7, the applied pressure is kept at the moment, the test bearing 7 is pulled to rotate through a digital display spring balance 8 with a hook, the maximum static friction value of the test bearing 7 takes the maximum reading displayed by the digital display spring balance 8 with the hook before the test bearing 7 starts to rotate, and the product of the sum of the diameter of the inner ring and the diameter of the outer ring of the test bearing 7 divided by the maximum static friction value is the maximum static friction moment of the test bearing 7 after the axial standard load is loaded;
step four: stopping pulling the test bearing 7 to rotate, removing one of the digital display spring scales 8 with the hooks, continuously adjusting the pressure of the stretching pressure equipment to axially load the test bearing 7, and continuously pulling the digital display spring scale 8 with the hooks to rotate the test bearing 7 for 1 minute when the axial load of the test bearing 7 is larger than a certain load value required by the test, wherein the test bearing rotates flexibly, and the working state is stable, so that the test is completed.
Claims (2)
1. The axial loading detection method of the double-bearing of the aircraft is realized based on an axial loading detection device of the double-bearing of the aircraft, the axial loading detection device of the double-bearing of the aircraft comprises a connecting piece, a central shaft, cantilevers, a base and a digital display spring balance with a hook, two test bearings are arranged at two ends of the central shaft, two test bearing inner rings are in tight fit with the central shaft, the lower end of the central shaft is arranged in a first central hole in the middle of the base, a test bearing outer ring at the lower end of the central shaft is in loose fit with the wall of the first central hole, the upper end of the central shaft is sleeved in a second central hole at one end of the connecting piece, the test bearing outer ring at the upper end of the central shaft is in loose fit with the wall of the second central hole, the other end of the connecting piece is connected with a pressure head of a tensile pressure device, two cantilevers are radially symmetrically arranged on the outer wall of the central shaft, and the tail ends of the two cantilevers are respectively connected with the digital display spring balance with the hook;
an inner gasket is arranged between the inner rings of the two test bearings and the center shaft;
an outer gasket used for limiting the outer ring of the test bearing is arranged in the first groove in the first central hole of the base and in the second groove in the second central hole at one end of the connecting piece;
the pulling direction of the digital display spring balance with the hook is in the horizontal direction, and the included angle between the pulling direction of the digital display spring balance with the hook and the length direction of the cantilever is 90 degrees;
the pulling force directions of the two digital display spring scales with hooks are opposite;
the detection method comprises the following steps:
step one: two test bearings are respectively arranged at the upper end and the lower end of the center shaft, and the inner rings of the test bearings are tightly matched with the center shaft; then the two cantilevers are screwed into threaded holes in the middle of the outer wall of the center shaft respectively, then the lower end of the center shaft is installed into a first center hole of a base, the outer ring of a test bearing at the lower end of the center shaft is in loose fit with the wall of the first center hole, finally a connecting piece is sleeved on the test bearing at the upper end of the center shaft, and the outer ring of the test bearing at the upper end of the center shaft is in loose fit with the wall of a second center hole of the connecting piece;
step two: the whole detection device is arranged on an equipment workbench through a screw nut, a connecting piece is connected with a pressure head of stretching pressure equipment through a bolt, then hooks of two digital display spring scales with hooks are respectively hooked on grooves at the tail ends of a cantilever, and the pulling force direction of the digital display spring scales with hooks is ensured to be in the horizontal direction and form an included angle of 90 degrees with the length direction of the cantilever;
step three: starting a stretching pressure device, wherein a pressure head of the stretching pressure device applies gradually increased axial pressure to a test bearing through a connecting piece, the test bearing bears the gradually increased axial pressure, when the pressure applied by the stretching pressure device reaches a certain standard value required by the test bearing, the applied pressure is kept at the moment, and the test bearing is pulled to rotate through a digital display spring balance with a hook, so that the maximum static friction moment of the test bearing after the axial standard load is loaded is obtained;
step four: and stopping pulling the test bearing to rotate, removing one of the digital display spring scales with the hooks, continuously adjusting the pressure of the stretching pressure equipment to axially load the test bearing, and continuously pulling the digital display spring scale with the hooks to rotate the test bearing for 1 minute when the axial load of the test bearing is larger than a certain load value required by the test, wherein the test bearing rotates flexibly, and the working state is stable, so that the test is completed.
2. The method for aircraft duplex bearing axial loading detection according to claim 1, wherein: and in the third step, the maximum static friction force value of the test bearing is taken as the maximum reading displayed by the digital display spring balance with the hook before the test bearing starts to rotate, and the product of the sum of the diameter of the inner ring and the diameter of the outer ring of the test bearing divided by 2 and the maximum static friction force value is the maximum static friction moment of the test bearing after the axial standard load is loaded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810907228.7A CN108896313B (en) | 2018-08-10 | 2018-08-10 | Device and method for detecting axial loading of double bearings of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810907228.7A CN108896313B (en) | 2018-08-10 | 2018-08-10 | Device and method for detecting axial loading of double bearings of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108896313A CN108896313A (en) | 2018-11-27 |
| CN108896313B true CN108896313B (en) | 2024-01-23 |
Family
ID=64353829
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810907228.7A Active CN108896313B (en) | 2018-08-10 | 2018-08-10 | Device and method for detecting axial loading of double bearings of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108896313B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2894920A1 (en) * | 2005-12-20 | 2007-06-22 | Skf Ab | Steering wheel system for motor vehicle, has detection device detecting torque exerted by driver on steering wheel and with detection unit detecting radial load applied by drive pinion on connection part |
| CN102032848A (en) * | 2010-12-02 | 2011-04-27 | 洛阳轴研科技股份有限公司 | Method for detecting multiple technical indexes of turntable bearing by using detecting platform |
| DE102010056118A1 (en) * | 2010-12-23 | 2012-06-28 | Werner Stehr | Testing device for tribological examining of shaft bearings, has applying apparatus for applying load on shaft bearing, where retainer is held with two force measuring devices |
| CN102901594A (en) * | 2012-09-29 | 2013-01-30 | 中国航天科技集团公司第五研究院第五一〇研究所 | Device for testing friction moment of pairing rolling bearing |
| CN105466619A (en) * | 2015-12-15 | 2016-04-06 | 西安航天动力研究所 | Swing bearing friction characteristics measuring device and method under joint actions of axial and radial load |
| CN107976314A (en) * | 2017-11-24 | 2018-05-01 | 四川凌峰航空液压机械有限公司 | Calibration tape carries the device of bearing frictional torque |
| CN208653798U (en) * | 2018-08-10 | 2019-03-26 | 江南工业集团有限公司 | A kind of axially loaded detection device of aircraft duplex bearing |
-
2018
- 2018-08-10 CN CN201810907228.7A patent/CN108896313B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2894920A1 (en) * | 2005-12-20 | 2007-06-22 | Skf Ab | Steering wheel system for motor vehicle, has detection device detecting torque exerted by driver on steering wheel and with detection unit detecting radial load applied by drive pinion on connection part |
| CN102032848A (en) * | 2010-12-02 | 2011-04-27 | 洛阳轴研科技股份有限公司 | Method for detecting multiple technical indexes of turntable bearing by using detecting platform |
| DE102010056118A1 (en) * | 2010-12-23 | 2012-06-28 | Werner Stehr | Testing device for tribological examining of shaft bearings, has applying apparatus for applying load on shaft bearing, where retainer is held with two force measuring devices |
| CN102901594A (en) * | 2012-09-29 | 2013-01-30 | 中国航天科技集团公司第五研究院第五一〇研究所 | Device for testing friction moment of pairing rolling bearing |
| CN105466619A (en) * | 2015-12-15 | 2016-04-06 | 西安航天动力研究所 | Swing bearing friction characteristics measuring device and method under joint actions of axial and radial load |
| CN107976314A (en) * | 2017-11-24 | 2018-05-01 | 四川凌峰航空液压机械有限公司 | Calibration tape carries the device of bearing frictional torque |
| CN208653798U (en) * | 2018-08-10 | 2019-03-26 | 江南工业集团有限公司 | A kind of axially loaded detection device of aircraft duplex bearing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108896313A (en) | 2018-11-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104568443B (en) | Space rolling bearing comprehensive performance experiment device | |
| CN201152812Y (en) | Radial directional hydrodynamic-hydrostatic gas bearing experiment bench | |
| CN102636397B (en) | Device and method for rapidly testing comprehensive mechanical properties of anchor bolt | |
| CN108318165B (en) | Bearing dynamic friction torque tester | |
| CN202938765U (en) | Tool for measuring axial clearance of gear box gear shaft bearing | |
| CN202471397U (en) | Elastic support parts flexibility tester | |
| CN110132592A (en) | The effective prefastening load measurement method of assembly bearing | |
| CN108426712B (en) | Full circumferential sliding radial testing and loading device | |
| CN204286791U (en) | Bearing fatigue simulator stand | |
| CN108896313B (en) | Device and method for detecting axial loading of double bearings of aircraft | |
| CN109282753A (en) | A kind of double inner ring two-row ball bearing axial deformation measurement toolings | |
| CN109341509A (en) | A kind of measuring device and its test method of rolling bearing lubrication film thickness | |
| CN202770631U (en) | Radial sliding bearing static load loading device | |
| CN208653798U (en) | A kind of axially loaded detection device of aircraft duplex bearing | |
| CN210293505U (en) | Clutch bearing starting torque detection device | |
| CN104568282B (en) | Vehicle wheel bearing bolt pretightening force detection device | |
| CN208705043U (en) | A kind of aero-vehicle bearing radial loaded detection device | |
| CN207487868U (en) | A kind of spring steel wire detection device for elasticity | |
| CN108760314B (en) | Device and method for detecting radial loading of aircraft bearing | |
| CN203561473U (en) | Hub bearing bolt pretightening force detection device | |
| CN203148657U (en) | Device for detecting comprehensive mechanical properties of anchor rods | |
| CN104316314B (en) | Bearing pin side-by-side size sensor transformational structure | |
| CN206038286U (en) | Aerogenerator locking dish static load capacity test bench | |
| CN205015158U (en) | Friction torque's testing arrangement is prevented changeing by bearing under gland nut effect | |
| CN109720602B (en) | Test device for simulating torque conversion test of working state of propeller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |