CN103162963A - Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine - Google Patents
Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine Download PDFInfo
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- CN103162963A CN103162963A CN2013100472296A CN201310047229A CN103162963A CN 103162963 A CN103162963 A CN 103162963A CN 2013100472296 A CN2013100472296 A CN 2013100472296A CN 201310047229 A CN201310047229 A CN 201310047229A CN 103162963 A CN103162963 A CN 103162963A
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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
The ball socket bearing of using in China lifting airscrew system at present is mainly by import, and the production domesticization of rotor system ball socket bearing is China's high-performance flight device hot issue anxious to be resolved, and high-level efficiency, high-performance fatigue tester are one of its gordian techniquies.University On The Mountain Of Swallows successfully developed First Domestic ball socket bearing fatigue tester in 2007, this testing machine is to adopt traditional holding series-parallel connection of mechanism up and down, and mechanism's volume is 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, low, the good stability of power consumption, the strong helicopter auto-bank unit ball socket bearing comprehensive fatigue testing machine of practical application.
The objective of the invention is to be realized by following mode:
the present invention includes support, base, interior ring parallel institution, the outer shroud parallel institution, power drive mechanism and control system, base is fixed on support, decile is provided with column on the same circumference of base, top at column is provided with upper cover, be provided with main shaft between base and upper cover, and the axle center of main shaft is positioned on the center of circle of column place circumference, interior ring parallel institution is by interior ring upper mounting plate, oscillating bearing, the first anti-arm of turning round, Electric booster consists of, be enclosed within the circular platform on main shaft centered by interior ring upper mounting plate, Electric booster is three, be arranged between interior ring upper mounting plate and base by circumference equal dividing, and the two ends of Electric booster are connected with base with interior ring upper mounting plate respectively by ball pivot, between interior ring upper mounting plate and main shaft, oscillating bearing is installed, interior ring upper mounting plate is connected with the outer ring of oscillating bearing, be provided with lining between the inner ring of oscillating bearing and main shaft, a first anti-end of turning round arm is connected on base, the edge of ring upper mounting plate in the other end connects by ball pivot, the outer shroud parallel institution is by the outer shroud lower platform, clutch shaft bearing, the first gear, the outer shroud upper mounting plate, the second bearing, the adjustable pressure controller, the second anti-arm of turning round consists of, the outer shroud upper mounting plate is the truncated cone-shaped platform that the middle part has through hole, the outer shroud lower platform is the circular platform that the middle part has center pit, outer shroud upper mounting plate inboard is connected to interior ring upper mounting plate bottom by the second bearing, and the inner ring of the second bearing is enclosed within on interior 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, the adjustable pressure controller is three, be arranged between outer shroud upper mounting plate and outer shroud lower platform by circumference equal dividing, its two ends are connected with the outer shroud lower platform with the outer shroud upper mounting plate respectively by ball pivot, second prevents turning round the edge that arm one end is connected in the outer shroud lower platform, the other end is connected by the edge of ball pivot with the outer shroud upper mounting plate, power drive mechanism comprises motor and the second gear that is fixed on motor shaft, and motor is fixed on base, the second gear and the engagement of the first gear.
Described control system is controlled the revolution of motor and the length variations of Electric booster;
The revolution of described motor changes between per minute 0～640 turns.
Advantage of the present invention is: the moving situation (speed when helicopter simulating main rotor auto-bank unit is worked under various conditions really, acceleration) and stress characteristic (axial load, radial load), possess the characteristics such as energy consumption is low, precision is high, the high-speed motion stationarity is good, simple to operate.Wherein: the variation of three Electric booster length impels interior ring upper mounting plate be moved and rotate, and interior ring upper mounting plate passes to the outer shroud parallel institution with it by bearing, thereby realizes the control to the outer shroud pose; The outer shroud parallel-connection structure rotates around the spindle, and it mainly is applicable to the testing fatigue of ball socket bearing in the lifting airscrew system and rotor side chain two ends oscillating bearing.
On function, the present invention has satisfied and has gone straight up to the requirement of rotor system kinematics, can realize ball socket bearing in the lifting airscrew system, the torture test test of the parts such as oscillating bearing and biserial angular contact bearing.Testing machine possesses the rotation around X-axis, around the rotation of Y-axis and along the movement of Z axis with around four degree of freedom such as Z axis rotations.Can realize that the outer shroud revolution regulates speed change between per minute 0～690 turns.Rotate arbitrarily between 0～15 degree at the inclination angle of whole mechanism.The present invention can satisfy the various poses requirement to structure in the actual motion process of lifting airscrew system fully, completes the simulation to the lifting airscrew system.
Description of drawings
Fig. 1 is schematic perspective view of the present invention;
Fig. 2 is that Figure 1A-A is to sectional view.
Embodiment
Illustrated in figures 1 and 2 is helicopter auto-bank unit ball socket bearing comprehensive fatigue testing machine structural drawing.The present invention includes support 1, base 3, interior ring parallel institution, outer shroud parallel institution, power drive mechanism and control system 20, base 3 is fixed on support 1, decile is provided with four columns 9 on the same circumference of base, be provided with upper cover 12 on the top of column 9, be provided with main shaft 6 at base 3 and 12 of upper covers, and the axle center of main shaft 6 is positioned on the center of circle of four column 9 place circumference; Interior ring parallel institution by interior ring upper mounting plate 13, oscillating bearing 15, first anti-ly turn round arm 8, Electric booster 17 consists of, be enclosed within the circular platform on main shaft centered by interior ring upper mounting plate 13, Electric booster 17 is three, be arranged between interior ring upper mounting plate 13 and base 3 by circumference equal dividing, and are connected with base with interior ring upper mounting plate 13 respectively by ball pivot and are connected in the two ends of Electric booster 17, the length of Electric booster 17 change control in ring upper mounting plate 13 be moved and deflection around main shaft 6; At interior ring upper mounting plate 13 and 6, main shaft, oscillating bearing 15 is installed, interior 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, interior ring upper mounting plate 13 can be rotated and along main axle moving around oscillating bearing 15.a first anti-end of turning round arm 8 is connected on base 3, the edge of ring upper mounting plate 13 in the other end connects by ball pivot, and in restriction, ring upper mounting plate 13 rotates around main shaft 6, the outer shroud parallel institution is by outer shroud lower platform 18, clutch shaft bearing 4, the first gear 5, outer shroud upper mounting plate 10, the second bearing 11, adjustable pressure controller 16, the second anti-arm 7 of turning round consists of, outer shroud upper mounting plate 10 has the truncated cone-shaped platform of through hole for the middle part, outer shroud lower platform 18 has the circular platform of center pit for the middle part, outer shroud upper mounting plate 10 inboards are connected to interior ring upper mounting plate 13 bottoms by the second bearing 11, and the inner ring of the second bearing 11 is enclosed within on 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, be arranged between outer shroud upper mounting plate 10 and outer shroud lower platform 18 by circumference equal dividing, are connected with the outer shroud lower platform with outer shroud upper mounting plate 10 respectively by ball pivot and are connected in its two ends, thereby adjustable pressure controller 16 can produce the load that opposition and inertial force helicopter simulating auto-bank unit bear when helicopter is completed exercises when length changes with it during change in location between the platform of outer shroud up and down, second anti-turns round the edge that arm 7 one ends are connected in outer shroud lower platform 18, and the other end is connected by the edge of ball pivot with outer shroud upper mounting plate 10, controls the outer shroud upper mounting plate and follows the outer shroud lower platform around main shaft, synchronously rotation to occur together, be provided with the inner ring of the first gear 5, the first gears 5 in outer shroud lower platform bottom around its center pit and the outer ring of clutch shaft bearing 4 is fixed, power drive mechanism comprises motor 2 and the second gear 19 that is fixed on motor shaft, motor 2 is fixed on base 3, the second gear 19 and the first gear 5 engagements, the second gear 19 passes motion to the outer shroud parallel institution by the first gear 5, realizes the rotation of outer shroud parallel institution.Control system 20 is controlled motor 2 revolutions on the one hand and is changed between per minute 0～640 turns, and controls on the other hand three Electric booster 17 length variations.Motor 2 passes motion to the outer shroud parallel institution by meshing gear, rotates around main shaft 6 thereby control the outer shroud parallel institution.The variation of three Electric booster length impels interior ring upper mounting plate be moved and rotate, and interior ring upper mounting plate passes to the outer shroud upper mounting plate with it by bearing, thereby realizes the control to the parallel institution pose.
Claims (2)
1. helicopter auto-bank unit ball socket bearing comprehensive fatigue testing machine, comprise support, base, interior ring parallel institution, the outer shroud parallel institution, power drive mechanism and control system, it is characterized in that: base is fixed on support, decile is provided with column on the same circumference of base, top at column is provided with upper cover, be provided with main shaft between base and upper cover, and the axle center of main shaft is positioned on the center of circle of column place circumference, interior ring parallel institution is by interior ring upper mounting plate, oscillating bearing, the first anti-arm of turning round, Electric booster consists of, be enclosed within the circular platform on main shaft centered by interior ring upper mounting plate, Electric booster is three, be arranged between interior ring upper mounting plate and base by circumference equal dividing, and the two ends of Electric booster are connected with base with interior ring upper mounting plate respectively by ball pivot, between interior ring upper mounting plate and main shaft, oscillating bearing is installed, interior ring upper mounting plate is connected with the outer ring of oscillating bearing, be provided with lining between the inner ring of oscillating bearing and main shaft, a first anti-end of turning round arm is connected on base, the edge of ring upper mounting plate in the other end connects by ball pivot, the outer shroud parallel institution is by the outer shroud lower platform, clutch shaft bearing, the first gear, the outer shroud upper mounting plate, the second bearing, the adjustable pressure controller, the second anti-arm of turning round consists of, the outer shroud upper mounting plate is the truncated cone-shaped platform that the middle part has through hole, the outer shroud lower platform is the circular platform that the middle part has center pit, outer shroud upper mounting plate inboard is connected to interior ring upper mounting plate bottom by the second bearing, and the inner ring of the second bearing is enclosed within on interior 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, the adjustable pressure controller is three, be arranged between outer shroud upper mounting plate and outer shroud lower platform by circumference equal dividing, its two ends are connected with the outer shroud lower platform with the outer shroud upper mounting plate respectively by ball pivot, second prevents turning round the edge that arm one end is connected in the outer shroud lower platform, the other end is connected by the edge of ball pivot with the outer shroud upper mounting plate, power drive mechanism comprises motor and the second gear that is fixed on motor shaft, and motor is fixed on base, the second gear and the engagement of the first gear.
2. helicopter auto-bank unit ball socket bearing comprehensive fatigue testing machine according to claim 1, it is characterized in that: the revolution of described motor changes between per minute 0～640 turns.
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 |
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| 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 |
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| Publication Number | Publication Date |
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| CN103162963A true CN103162963A (en) | 2013-06-19 |
| CN103162963B CN103162963B (en) | 2015-03-25 |
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| CN201310047229.6A Expired - Fee Related CN103162963B (en) | 2013-02-06 | 2013-02-06 | Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103383310A (en) * | 2013-07-22 | 2013-11-06 | 燕山大学 | Centering double-oscillating-follower double-swash-plate-end-face-cam knuckle bearing high-speed testing machine |
| CN103383309A (en) * | 2013-07-22 | 2013-11-06 | 燕山大学 | Joint bearing high-speed tester with double parallel swing shafts, double disc cams and four swing rods |
| CN103383307A (en) * | 2013-07-22 | 2013-11-06 | 燕山大学 | Vertical double-swing-shaft four-disc-cam four-oscillating-bar knuckle bearing high-speed testing machine |
| CN104142246A (en) * | 2014-08-26 | 2014-11-12 | 长春机械科学研究院有限公司 | Multi-group bearing loading simulation test system |
| CN104236880A (en) * | 2014-08-26 | 2014-12-24 | 中国直升机设计研究所 | Fatigue test device for torque arm assembly |
| 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 |
| CN104986354A (en) * | 2015-06-23 | 2015-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Reusable tilting rotorcraft test stand |
| CN105067263A (en) * | 2015-08-18 | 2015-11-18 | 鹰领航空高端装备技术秦皇岛有限公司 | Endurance tester for combined joint bearing matching with tail rotor of tail rotor type helicopter |
| CN105136459A (en) * | 2015-08-18 | 2015-12-09 | 燕山大学 | Testing machine for joint bearings combined and matched with swing cylinder type helicopter tail rotor system |
| CN105710805A (en) * | 2016-03-25 | 2016-06-29 | 哈尔滨飞机工业集团有限责任公司 | Locking tool for automatic inclinator of helicopter |
| CN106644477A (en) * | 2016-12-19 | 2017-05-10 | 兰州空间技术物理研究所 | Radial joint bearing running-in device |
| CN113176084A (en) * | 2021-04-20 | 2021-07-27 | 中国直升机设计研究所 | Helicopter upper platform test device |
| CN115258148A (en) * | 2022-08-11 | 2022-11-01 | 上海喆航航空科技有限公司 | Automatic inclinator structure of helicopter |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108169014B (en) * | 2017-12-01 | 2020-04-03 | 中国直升机设计研究所 | Loading device for upper platform fatigue test |
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| JPH1183679A (en) * | 1997-09-05 | 1999-03-26 | Koyo Seiko Co Ltd | Method and device for testing bearing seal |
| CN1818599A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Apparatus for testing fatigue strength of axial hinge bearing of helicopter |
| CN101363770A (en) * | 2008-10-08 | 2009-02-11 | 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 |
| CN102809488A (en) * | 2012-08-09 | 2012-12-05 | 浙江传媒学院 | Loading mechanism of mute life testing machine of rolling bearing |
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2013
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH1183679A (en) * | 1997-09-05 | 1999-03-26 | Koyo Seiko Co Ltd | Method and device for testing bearing seal |
| CN1818599A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Apparatus for testing fatigue strength of axial hinge bearing of helicopter |
| CN101363770A (en) * | 2008-10-08 | 2009-02-11 | 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 |
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Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103383310A (en) * | 2013-07-22 | 2013-11-06 | 燕山大学 | Centering double-oscillating-follower double-swash-plate-end-face-cam knuckle bearing high-speed testing machine |
| CN103383309A (en) * | 2013-07-22 | 2013-11-06 | 燕山大学 | Joint bearing high-speed tester with double parallel swing shafts, double disc cams and four swing rods |
| CN103383307A (en) * | 2013-07-22 | 2013-11-06 | 燕山大学 | Vertical double-swing-shaft four-disc-cam four-oscillating-bar knuckle bearing high-speed testing machine |
| 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 |
| CN104142246A (en) * | 2014-08-26 | 2014-11-12 | 长春机械科学研究院有限公司 | Multi-group bearing loading simulation test system |
| CN104236880A (en) * | 2014-08-26 | 2014-12-24 | 中国直升机设计研究所 | Fatigue test device for torque arm assembly |
| 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 |
| CN104986354A (en) * | 2015-06-23 | 2015-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Reusable tilting rotorcraft 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 |
| CN105067263A (en) * | 2015-08-18 | 2015-11-18 | 鹰领航空高端装备技术秦皇岛有限公司 | Endurance tester for combined joint bearing matching with tail rotor of tail rotor type helicopter |
| CN105136459A (en) * | 2015-08-18 | 2015-12-09 | 燕山大学 | Testing machine for joint bearings combined and matched with swing cylinder type helicopter tail rotor system |
| 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 |
| CN105710805A (en) * | 2016-03-25 | 2016-06-29 | 哈尔滨飞机工业集团有限责任公司 | Locking tool for automatic inclinator of helicopter |
| 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 |
| CN106644477A (en) * | 2016-12-19 | 2017-05-10 | 兰州空间技术物理研究所 | Radial joint bearing running-in device |
| 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 |
| CN113176084A (en) * | 2021-04-20 | 2021-07-27 | 中国直升机设计研究所 | Helicopter upper platform test device |
| CN113176084B (en) * | 2021-04-20 | 2022-10-18 | 中国直升机设计研究所 | Helicopter upper platform test device |
| CN115258148A (en) * | 2022-08-11 | 2022-11-01 | 上海喆航航空科技有限公司 | Automatic inclinator structure of helicopter |
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