CN103162963B - Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine - Google Patents
Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine Download PDFInfo
- Publication number
- CN103162963B CN103162963B CN201310047229.6A CN201310047229A CN103162963B CN 103162963 B CN103162963 B CN 103162963B CN 201310047229 A CN201310047229 A CN 201310047229A CN 103162963 B CN103162963 B CN 103162963B
- Authority
- CN
- China
- Prior art keywords
- inner ring
- mounting plate
- upper mounting
- bearing
- outer shroud
- 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.)
- Expired - Fee Related
Links
Abstract
The invention relates to a helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine which comprises a support, a base, an inner ring parallel mechanism, an outer ring parallel mechanism, a power transmission mechanism and a control system. The helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine is characterized in that the base is fixed on the support, stand columns are arranged on the same circumference of the base at intervals, an upper cover is arranged on top ends of the stand columns, a main shaft is arranged between the base and the upper cover, the inner ring parallel mechanism is composed of an inner ring upper platform, a joint bearing, a first twist preventing arm, and an electric power booster, the outer ring parallel mechanism is composed of an outer ring lower platform, a first bearing, a first gear, an outer ring upper platform, an adjustable pressure controller, and a second twist preventing arm, the power transmission mechanism comprises a motor and a second gear fixed on a motor shaft, the motor is fixed on the base, and the second gear is meshed with the first gear. The helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine has the advantages of being capable of realizing fatigue experimental tests on a ball hinge bearing, a joint bearing, a double-row contact bearing, and the like in a helicopter rotor system.
Description
Technical field
The invention belongs to ball socket bearing fatigue experimental device field, relate to a kind of helicopter auto-bank unit ball socket bearing comprehensive fatigue testing machine.
Background technology
Ball socket bearing in current China helicopter rotor system is mainly by import, and the production domesticization of rotor system ball socket bearing is China's high performance aircraft hot issue anxious to be resolved, and high efficiency, high-performance fatigue tester are one of its key technologies.University On The Mountain Of Swallows successfully developed First Domestic ball socket bearing fatigue tester in 2007, and this testing machine adopts the traditional holding series-parallel connection of mechanism up and down, and organization volume is comparatively large, power consumption, structure, stability etc. all await raising.
Summary of the invention
The object of the invention is to propose that a kind of volume is little, helicopter auto-bank unit ball socket bearing comprehensive fatigue testing machine that low, the good stability of consuming energy, practical application are strong.
The object of the invention is by realize with under type:
The present invention includes support, base, inner ring parallel institution, outer shroud parallel institution, power drive mechanism and control system, base is fixed on support, base same circumferentially decile be provided with column, upper cover is provided with on the top of column, main shaft is provided with between base and upper cover, and the axle center of main shaft is positioned on the center of circle of column place circumference, inner ring parallel institution is by inner ring upper mounting plate, oscillating bearing, first anti-torque arm, Electric booster is formed, the circular platform on main shaft is enclosed within centered by inner ring upper mounting plate, Electric booster is three, circumferentially decile is arranged between inner ring upper mounting plate and base, and the two ends of Electric booster are connected with inner ring upper mounting plate and base respectively by ball pivot, between inner ring upper mounting plate and main shaft, oscillating bearing is installed, inner ring upper mounting plate is connected with the outer ring of oscillating bearing, lining is provided with between the inner ring of oscillating bearing and main shaft, one end of first anti-torque arm is connected on base, the other end connects the edge of inner ring upper mounting plate by ball pivot, outer shroud parallel institution is by outer shroud lower platform, clutch shaft bearing, first gear, outer shroud upper mounting plate, second bearing, adjustable pressure controller, second anti-torque arm is formed, outer shroud upper mounting plate is the truncated cone-shaped platform that middle part has through hole, outer shroud lower platform is the circular platform that middle part has centre bore, inner ring upper mounting plate bottom is connected to by the second bearing inside outer shroud upper mounting plate, and the inner ring of the second bearing is enclosed within inner ring upper mounting plate, outer shroud lower platform and the first gear are fixed together, the inner ring of the first gear and the outer ring of clutch shaft bearing are fixed, the inner ring of clutch shaft bearing is fixed on main shaft, adjustable pressure controller is three, circumferentially decile is arranged outside between ring upper mounting plate and outer shroud lower platform, its two ends are connected with outer shroud upper mounting plate and outer shroud lower platform respectively by ball pivot, second anti-torque arm one end is connected in the edge of outer shroud lower platform, the other end is by the edge conjunction of ball pivot and outer shroud upper mounting plate, power drive mechanism comprises motor and is fixed on the second gear on motor shaft, and motor is fixed on base, the second gear and the first gears meshing.
Described control system controls the revolution of motor and the length variations of Electric booster;
The revolution of described motor changes between 0 ~ 640 turn per minute.
Advantage of the present invention is: can moving situation (speed when helicopter simulating main rotor auto-bank unit works under various conditions really, acceleration) and stress characteristic (axial load, radial load), possess the features such as energy consumption is low, precision is high, high-speed motion stationarity is good, simple to operate.Wherein: the change of three Electric booster length impels inner ring upper mounting plate be moved and rotate, and it is passed to outer shroud parallel institution by bearing by inner ring upper mounting plate, thus realize control to outer shroud pose; Outer shroud parallel-connection structure rotates around the spindle, and it is mainly applicable to the testing fatigue of ball socket bearing and rotor side chain two ends oscillating bearing in helicopter rotor system.
Functionally, present invention accomplishes and go straight up to the requirement of rotor system kinematics, can realize ball socket bearing in helicopter rotor system, the fatigue test test of the parts such as oscillating bearing and double row angular contact bearing.Testing machine possesses the rotation around X-axis, the rotation around Y-axis and the movement along Z axis and around four frees degree such as Z axis rotations.Outer shroud revolution can be realized between 0 ~ 690 turn per minute, regulate speed change.The inclination angle of whole mechanism is rotated arbitrarily between 0 ~ 15 degree.The present invention can meet helicopter rotor system various pose in actual motion process completely and, to the requirement of structure, complete the simulation to helicopter rotor system.
Accompanying drawing explanation
Fig. 1 is schematic perspective view of the present invention;
Fig. 2 is that Figure 1A-A is to profile.
Detailed description of the invention
Shown in Fig. 1 and Fig. 2 is helicopter auto-bank unit ball socket bearing comprehensive fatigue testing machine structure chart.The present invention includes support 1, base 3, inner ring parallel institution, outer shroud parallel institution, power drive mechanism and control system 20, base 3 is fixed on support 1, base same circumferentially decile be provided with four columns 9, upper cover 12 is provided with on the top of column 9, between base 3 and upper cover 12, be provided with main shaft 6, and the axle center of main shaft 6 is positioned on the center of circle of four column 9 place circumference; Inner ring parallel institution is made up of inner ring upper mounting plate 13, the anti-torque arm 8 of oscillating bearing 15, first, Electric booster 17, the circular platform on main shaft is enclosed within centered by inner ring upper mounting plate 13, Electric booster 17 is three, circumferentially decile is arranged between inner ring upper mounting plate 13 and base 3, and the two ends of Electric booster 17 are connected with inner ring upper mounting plate 13 and base 3 respectively by ball pivot, the length of Electric booster 17 changes control inner ring upper mounting plate 13 and is moved around main shaft 6 and deflects; Oscillating bearing 15 is installed between inner ring upper mounting plate 13 and main shaft 6, inner ring upper mounting plate 13 is connected with the outer ring of oscillating bearing 15, be provided with lining 14 between the inner ring of oscillating bearing 15 and main shaft, inner ring upper mounting plate 13 can be rotated and along main axle moving around oscillating bearing 15.One end of first anti-torque arm 8 is connected on the base 3, and the other end connects the edge of inner ring upper mounting plate 13 by ball pivot, and restriction inner ring upper mounting plate 13 rotates around main shaft 6, outer shroud parallel institution is by outer shroud lower platform 18, clutch shaft bearing 4, first gear 5, outer shroud upper mounting plate 10, second bearing 11, adjustable pressure controller 16, second anti-torque arm 7 is formed, outer shroud upper mounting plate 10 has the truncated cone-shaped platform of through hole for middle part, outer shroud lower platform 18 has the circular platform of centre bore for middle part, inner ring upper mounting plate 13 bottom is connected to by the second bearing 11 inside outer shroud upper mounting plate 10, and the inner ring of the second bearing 11 is enclosed within the outer ring of oscillating bearing 15, outer shroud lower platform 18 is connected on main shaft 6 by clutch shaft bearing 4, adjustable pressure controller 16 is air spring, have three, circumferentially decile is arranged outside between ring upper mounting plate 10 and outer shroud lower platform 18, its two ends are connected with outer shroud upper mounting plate 10 and outer shroud lower platform 18 respectively by ball pivot, adjustable pressure controller 16 can produce opposition and inertia force thus the helicopter simulating auto-bank unit load of bearing when helicopter completes various action when length changes with it during change in location between the upper and lower platform of outer shroud, second anti-torque arm 7 one end is connected in the edge of outer shroud lower platform 18, and the other end, by the edge conjunction of ball pivot and outer shroud upper mounting plate 10, controls outer shroud upper mounting plate with outer shroud lower platform together around main shaft generation synchronous axial system, the outer ring of the inner ring and clutch shaft bearing 4 that are provided with the first gear 5, first gear 5 around its centre bore in outer shroud lower platform bottom is fixed, the second gear 19 that power drive mechanism comprises motor 2 and is fixed on motor shaft, motor 2 is fixing on the base 3, second gear 19 engages with the first gear 5, and the second gear 19 passes motion to outer shroud parallel institution by the first gear 5, realizes the rotation of outer shroud parallel institution.Control system 20 1 aspect controls motor 2 revolution and changes between 0 ~ 640 turn per minute, controls three Electric booster 17 length variations on the other hand.Motor 2 passes motion to outer shroud parallel institution by meshing gear, thus control outer shroud parallel institution rotates around main shaft 6.The change of three Electric booster length impels inner ring upper mounting plate be moved and rotate, and it is passed to outer shroud upper mounting plate by bearing by inner ring upper mounting plate, thus realizes the control to parallel institution pose.
Claims (2)
1. a helicopter auto-bank unit ball socket bearing comprehensive fatigue testing machine, comprise support, base, inner ring parallel institution, outer shroud parallel institution, power drive mechanism and control system, it is characterized in that: base is fixed on support, base same circumferentially decile be provided with column, upper cover is provided with on the top of column, main shaft is provided with between base and upper cover, and the axle center of main shaft is positioned on the center of circle of column place circumference, inner ring parallel institution is by inner ring upper mounting plate, oscillating bearing, first anti-torque arm, Electric booster is formed, the circular platform on main shaft is enclosed within centered by inner ring upper mounting plate, Electric booster is three, circumferentially decile is arranged between inner ring upper mounting plate and base, and the two ends of Electric booster are connected with inner ring upper mounting plate and base respectively by ball pivot, between inner ring upper mounting plate and main shaft, oscillating bearing is installed, inner ring upper mounting plate is connected with the outer ring of oscillating bearing, lining is provided with between the inner ring of oscillating bearing and main shaft, one end of first anti-torque arm is connected on base, the other end connects the edge of inner ring upper mounting plate by ball pivot, outer shroud parallel institution is by outer shroud lower platform, clutch shaft bearing, first gear, outer shroud upper mounting plate, second bearing, adjustable pressure controller, second anti-torque arm is formed, outer shroud upper mounting plate is the truncated cone-shaped platform that middle part has through hole, outer shroud lower platform is the circular platform that middle part has centre bore, inner ring upper mounting plate bottom is connected to by the second bearing inside outer shroud upper mounting plate, and the inner ring of the second bearing is enclosed within inner ring upper mounting plate, outer shroud lower platform and the first gear are fixed together, the inner ring of the first gear and the outer ring of clutch shaft bearing are fixed, the inner ring of clutch shaft bearing is fixed on main shaft, adjustable pressure controller is three, circumferentially decile is arranged outside between ring upper mounting plate and outer shroud lower platform, its two ends are connected with outer shroud upper mounting plate and outer shroud lower platform respectively by ball pivot, second anti-torque arm one end is connected in the edge of outer shroud lower platform, the other end is by the edge conjunction of ball pivot and outer shroud upper mounting plate, power drive mechanism comprises motor and is fixed on the second gear on motor shaft, and motor is fixed on base, the second gear and the first gears meshing, described control system controls the revolution of motor and the length variations of Electric booster.
2. helicopter auto-bank unit ball socket bearing comprehensive fatigue testing machine according to claim 1, is characterized in that: the revolution of described motor changes between 0 ~ 640 turn per minute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310047229.6A CN103162963B (en) | 2013-02-06 | 2013-02-06 | Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310047229.6A CN103162963B (en) | 2013-02-06 | 2013-02-06 | Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103162963A CN103162963A (en) | 2013-06-19 |
| CN103162963B true CN103162963B (en) | 2015-03-25 |
Family
ID=48586230
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310047229.6A Expired - Fee Related CN103162963B (en) | 2013-02-06 | 2013-02-06 | Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103162963B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108169014A (en) * | 2017-12-01 | 2018-06-15 | 中国直升机设计研究所 | A kind of upper mounting plate fatigue test loading device |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103383307B (en) * | 2013-07-22 | 2015-06-10 | 燕山大学 | Vertical double-swing-shaft four-disc-cam four-oscillating-bar knuckle bearing high-speed testing machine |
| CN103383309B (en) * | 2013-07-22 | 2015-06-10 | 燕山大学 | Joint bearing high-speed tester with double parallel swing shafts, double disc cams and four swing rods |
| CN103383310B (en) * | 2013-07-22 | 2015-07-29 | 燕山大学 | To the two oscillating follower two inclined plate edge cam oscillating bearing high-speed tester (HST) of the heart |
| CN104236880B (en) * | 2014-08-26 | 2018-02-23 | 中国直升机设计研究所 | A kind of torsional arm component fatigue experimental device |
| CN104142246B (en) * | 2014-08-26 | 2017-01-11 | 长春机械科学研究院有限公司 | Multi-group bearing loading simulation test system |
| CN104729846A (en) * | 2015-04-07 | 2015-06-24 | 中国直升机设计研究所 | Automatic inclinator nonrotating ring fatigue test device |
| CN104908976A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Simple rotor mechanism of coaxial dual-rotor helicopter test stand |
| CN104986354B (en) * | 2015-06-23 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Reusable tilting rotorcraft test stand |
| CN105067263B (en) * | 2015-08-18 | 2017-06-30 | 鹰领航空高端装备技术秦皇岛有限公司 | Tail-rotor formula helicopter tail rotor forms a complete set of joint bearing life testing machine |
| CN105136459B (en) * | 2015-08-18 | 2017-12-08 | 燕山大学 | Joint bearing testing machine is combined in the system support of oscillating oil cylinder formula helicopter tail rotor |
| CN105710805B (en) * | 2016-03-25 | 2017-07-25 | 哈尔滨飞机工业集团有限责任公司 | A kind of helicopter auto-bank unit stop instrument |
| CN106644477B (en) * | 2016-12-19 | 2019-11-05 | 兰州空间技术物理研究所 | A kind of radial direction oscillating bearing running in machine |
| CN113176084B (en) * | 2021-04-20 | 2022-10-18 | 中国直升机设计研究所 | Helicopter upper platform test device |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3817044B2 (en) * | 1997-09-05 | 2006-08-30 | 株式会社ジェイテクト | Bearing seal test method and test apparatus |
| CN100485345C (en) * | 2006-03-17 | 2009-05-06 | 燕山大学 | Apparatus for testing fatigue strength of axial hinge bearing of helicopter |
| CN101363770B (en) * | 2008-10-08 | 2010-06-16 | 燕山大学 | Fatigue-tesing machine for ball socket bearing of helicopter main rotor |
| CN202453185U (en) * | 2012-02-17 | 2012-09-26 | 昆山福维斯精密机械有限公司 | Simulation testing machine for endurance life of hub bearing of automobile |
| CN102809488B (en) * | 2012-08-09 | 2014-12-03 | 浙江传媒学院 | Loading mechanism of mute life testing machine of rolling bearing |
-
2013
- 2013-02-06 CN CN201310047229.6A patent/CN103162963B/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108169014A (en) * | 2017-12-01 | 2018-06-15 | 中国直升机设计研究所 | A kind of upper mounting plate fatigue test loading device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103162963A (en) | 2013-06-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103162963B (en) | Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine | |
| CN202468386U (en) | 360-degree unidirectional rotary fan | |
| CN204704303U (en) | A kind of changes mechanical energy is the energy regenerative vibration damper of electric energy | |
| CN202605730U (en) | Multi-rotor aircraft | |
| CN103670941B (en) | A kind of feather vertical axis aerogenerator | |
| CN104155109A (en) | Working condition simulation testing machine for bearing of dual-mass flywheel | |
| CN205841637U (en) | A kind of planet-gear speed reducer | |
| CN203796490U (en) | Transmission gear based vertical-axis wind turbine with movable blades | |
| CN204156076U (en) | A kind of single shaft compact aerial seat | |
| EP2657522A2 (en) | Power generator with a flywheel. | |
| CN202228267U (en) | Hub drilled with holes | |
| CN103939289A (en) | Vertical-axis wind turbine capable of adjusting angle of attack automatically | |
| CN104088754B (en) | Vertical-axis wind turbine | |
| CN202833322U (en) | Synchronous adjusting device of high-speed centrifugal fan inlet guide blades | |
| CN203109542U (en) | Bearing running-in device | |
| CN203783817U (en) | Vertical axis wind power generator capable of increasing speed | |
| CN202278268U (en) | Workbench in gear processing machine | |
| CN205445885U (en) | Birotor trend generator | |
| KR101028748B1 (en) | Wind power generator of large size | |
| CN209212955U (en) | Shift fork driving mechanism and automatic gear shifting system | |
| CN204606213U (en) | A kind of bevel gear driving drum wing type lift force device | |
| CN205013208U (en) | A acceleration rate rotor system for biological kinetic energy pull -alongs power generation system | |
| CN204301987U (en) | Efp performance testing device | |
| CN203945248U (en) | A kind of sealing pair eccentric grinder | |
| CN205879531U (en) | High power wind generator becomes oar bearing fretting wear testing arrangement |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150325 Termination date: 20210206 |