CN104215458B - A kind of helicopter tail rotor spring bearing fatigue experimental device - Google Patents
A kind of helicopter tail rotor spring bearing fatigue experimental device Download PDFInfo
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- CN104215458B CN104215458B CN201410424827.5A CN201410424827A CN104215458B CN 104215458 B CN104215458 B CN 104215458B CN 201410424827 A CN201410424827 A CN 201410424827A CN 104215458 B CN104215458 B CN 104215458B
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- spring bearing
- bogusware
- housing
- cushion block
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Abstract
A kind of helicopter tail rotor spring bearing fatigue experimental device, belongs to helicopter tail rotor spring bearing fatigue test technology, it is characterised in that bearing spider is monaural shape bearing spider；Spring bearing cushion block is generally square structure, middle fluted, is square platform in the middle of flexible beam bogusware, and two ends are rotary shaft；Spring bearing cushion block is adhered on the square platform of beam bogusware, spring bearing cushion block is installed to after compressing spring bearing with hold-down bolt, housing is fixed on base plate by two rolling bearing assemblies, connected with spring bearing connecting bolt and fasten housing and spring bearing, rolling bearing assembly and fixed rolling bearing carrier setting bolt are installed at flexible beam bogusware two ends, ensure that housing rotation axis and flexible beam bogusware rotation axis are mutually perpendicular to and in the same plane.The present invention realizes angle of flap and becomes elongation synchronization high frequency loading, and true simulation tail-rotor spring bearing reaches the purpose of examination tail-rotor spring bearing fatigue behaviour in the working environment of flight status.
Description
Technical field
The invention belongs to helicopter tail rotor spring bearing fatigue test technology, it is related to a kind of helicopter tail rotor spring bearing tired
Labor experimental rig is designed.
Background technology
Tail-rotor spring bearing is tail-rotor leaf important component, while to bear to wave angular displacement and tail-rotor leaf from flexible beam
Oversleeve housing passes to its displacement angular displacement.In order to grasp tail-rotor spring bearing fatigue behaviour, it is necessary on ground in face of tail-rotor branch
Support bearing carries out fatigue test, grasps tail-rotor spring bearing fatigue properties, and then provide the life-span of tail-rotor spring bearing.At present,
China's tail-rotor spring bearing fatigue experimental device can only carry out displacement angular movement.
The content of the invention
The purpose of the present invention：A kind of helicopter tail rotor spring bearing fatigue experimental device, simulates tail-rotor spring bearing completely
Stress during installation, reaches the purpose of examination tail-rotor spring bearing fatigue behaviour.
Technical scheme：One kind be used for helicopter tail rotor spring bearing fatigue experimental device, by bearing spider 1,
Housing 2, spring bearing 4, spring bearing cushion block 5, flexible beam bogusware 6, strippable gasket 7, base plate 11 are constituted, it is characterised in that bearing
Bearing 1 is monaural shape bearing spider, and spring bearing cushion block 5 is generally square structure, middle fluted 14, there is cunning on groove both sides
Groove 15, for square platform 16 is used to be bonded spring bearing cushion block 5 in the middle of flexible beam bogusware 6, two ends are rotary shaft, are had in rotary shaft
Convex shoulder 17, convex shoulder is symmetrical on square Platform center.Spring bearing cushion block 5 is adhered on the square platform of beam bogusware 6, then with pressure
Spring bearing cushion block 5 is installed to after tight bolt compresses spring bearing 4, housing 2 is fixed on base plate by two rolling bearing assemblies
On 11, chord support bearing cushion block 5 and flexible beam bogusware 6 are co-mounted on housing 2 on spring bearing 4 plus after strippable gasket 7,
Connected with spring bearing connecting bolt 3 and fasten housing 2 and spring bearing 4, rolling bearing assembly is installed at the two ends of flexible beam bogusware 6
And all rolling bearing carrier setting bolts 8 of fixation, ensure the rotation axis of housing 2 be mutually perpendicular to flexible beam bogusware rotation axis and
In same plane.
Bearing spider middle (center) bearing installs centerline hole in same level when the bearing spider 1 is installed.Relative two
Bearing spider middle (center) bearing installs centerline hole on the same axis when bearing spider 1 is installed.
It is rectangle mount structure in the middle of the housing 2, has the axis of a rotary shaft and rotary shaft respectively at rectangle frame two ends
On rectangle frame plane of symmetry intersecting lens, there is the shaft shoulder to limit it in the rotary shaft of two ends and horizontally slip.
The axis of the rotary shaft at the two ends of flexible beam bogusware 6 on the same axis, has the shaft shoulder to limit in the rotary shaft of two ends
It is made to horizontally slip.
The thickness centre position of square platform is the center of the bending motion of spring bearing 4 in the middle of the flexible beam bogusware 6.
The bearing spider 1 is monaural shape bearing spider, and there is fixedly connected hole on rest base both sides, is opened on bearing spider
There are bearing mounting hole, bearing stop shoulder 12 and end ring groove 13.
The roller bearings component is made up of rolling bearing bearing 1, end ring 9 and rolling bearing 10.
Advantages of the present invention：The present invention realizes angle of flap and becomes elongation synchronization high frequency loading, true simulation tail-rotor support
Bearing reaches the purpose of examination tail-rotor spring bearing fatigue behaviour in the working environment of flight status.
Brief description of the drawings
Fig. 1 is helicopter tail rotor spring bearing fatigue experimental device schematic diagram
Fig. 2 is rolling bearing bearing schematic diagram
Fig. 3 is spring bearing cushion block schematic diagram
Fig. 4 is flexible beam bogusware schematic diagram
Fig. 5 is flexible beam bogusware, spring bearing cushion block and spring bearing installation diagram
Fig. 6 housing schematic diagrames
Specific embodiment
This patent is described in further details below in conjunction with the accompanying drawings.
One kind is used for helicopter tail rotor spring bearing fatigue experimental device, is connected by bearing spider 1, housing 2, spring bearing
Bolt 3, spring bearing 4, spring bearing cushion block 5, flexible beam bogusware 6, strippable gasket 7, rolling bearing carrier setting bolt 8, bearing rib
Circle 9, rolling bearing 10, base plate 11 are constituted；
Bearing spider 1 is monaural shape bearing spider, and there is fixedly connected hole on rest base both sides, axle is provided with bearing spider
Mounting hole, bearing stop shoulder and end ring groove are held, Fig. 1 is seen.It is rectangle mount structure in the middle of housing 2, at rectangle frame two ends
There is the axis of a rotary shaft and rotary shaft respectively on rectangle frame plane of symmetry intersecting lens, there is the shaft shoulder to limit in the rotary shaft of two ends
It horizontally slips, and sees Fig. 6.Spring bearing cushion block 5 is generally square structure, and there is chute on middle fluted structure, groove both sides,
See Fig. 2.The axis of the rotary shaft at the two ends of flexible beam bogusware 6 on the same axis, has the shaft shoulder to limit it left in the rotary shaft of two ends
Right slip.The thickness centre position of square platform is the center of the bending motion of spring bearing 4 in the middle of flexible beam bogusware 6.
Time of day is simulated in flexible beam bogusware bag glass cloth.Housing size truly simulates tail-rotor leaf oversleeve housing, experiment
Load applies to realize angle of flap and becomes the synchronous loading of elongation by the executing agency that load bar is connected.In flexible beam bogusware 6
Between be square platform bonding spring bearing cushion block 5, two ends are rotary shaft, there is convex shoulder in rotary shaft, and convex shoulder is in square platform
The heart is symmetrical.See Fig. 3.Spring bearing cushion block 5 is adhered on the square platform of beam bogusware 6, then compresses spring bearing 4 with hold-down bolt
After be installed to spring bearing cushion block 5, see Fig. 4.Rolling bearing bearing 1, end ring 9, rolling bearing 10 are assembled into rolling bearing
Support component, housing 2 is fixed on base plate 11 by two rolling bearing assemblies, is connected on spring bearing 4 plus after strippable gasket 7
Spring bearing cushion block 5 and flexible beam bogusware 6 are co-mounted on housing 2, are connected with spring bearing connecting bolt 3 and are fastened housing 2
With spring bearing 4, and apply corresponding torque, rolling bearing assembly is installed at the two ends of flexible beam bogusware 6 and all rollings are fixed
Bearing spider bolt 8, it is ensured that the rotation axis of housing 2 is mutually perpendicular to flexible beam bogusware rotation axis and in the same plane, tries
Load is tested by the executing agency being connected to apply to wave angular displacement and displacement angular displacement.
Bearing spider middle (center) bearing installs centerline hole in same level when four bearing spiders 1 are installed.Relative two
Bearing spider middle (center) bearing installs centerline hole on the same axis when bearing spider 1 is installed.
Claims (7)
1. a kind of helicopter tail rotor spring bearing fatigue experimental device, including bearing spider (1), housing (2), spring bearing (4),
Spring bearing cushion block (5), flexible beam bogusware (6), strippable gasket (7) and base plate (11), it is characterised in that bearing spider (1) is
Monaural shape bearing spider；Spring bearing cushion block (5) is generally square structure, middle fluted (14), and there is chute on groove both sides
(15) it is, square platform (16) in the middle of flexible beam bogusware (6), for being bonded spring bearing cushion block (5), two ends are rotary shaft, rotation
There is convex shoulder (17) in rotating shaft, convex shoulder is on square platform (16) Central Symmetry；Spring bearing cushion block (5) is adhered to beam bogusware (6)
Square platform on, be installed to spring bearing cushion block (5) after compressing spring bearing (4) with hold-down bolt, housing (2) is by two
Rolling bearing assembly is fixed on base plate (11), and strippable gasket (7) is added on spring bearing (4), and chord supports bearing cushion block (5) afterwards
It is co-mounted on housing (2) with flexible beam bogusware (6), is connected with spring bearing connecting bolt (3) and fasten housing (2) and support
Bearing (4), rolling bearing assembly and all rolling bearing carrier setting bolts (8) of fixation are installed at flexible beam bogusware (6) two ends, are ensured
Housing (2) rotation axis and flexible beam bogusware rotation axis are mutually perpendicular to and in the same plane；
It is rectangle mount structure in the middle of the housing (2), has a rotary shaft respectively at rectangle frame two ends and the axis of rotary shaft exists
On rectangle frame plane of symmetry intersecting lens.
2. helicopter tail rotor spring bearing fatigue experimental device according to claim 1, it is characterised in that the bearing branch
Bearing spider middle (center) bearing installs centerline hole in same level when seat (1) is installed, when two relative bearing spiders (1) are installed
Bearing spider middle (center) bearing installs centerline hole on the same axis.
3. helicopter tail rotor spring bearing fatigue experimental device according to claim 1, it is characterised in that：In housing (2)
There is the shaft shoulder to limit it in the rotary shaft of two ends to horizontally slip.
4. helicopter tail rotor spring bearing fatigue experimental device according to claim 1, it is characterised in that：The flexible beam
The axis of the rotary shaft at bogusware (6) two ends on the same axis, has the shaft shoulder to limit it in the rotary shaft of two ends and horizontally slips.
5. helicopter tail rotor spring bearing fatigue experimental device according to claim 1, it is characterised in that：The flexible beam
The thickness centre position of square platform is the center of spring bearing (4) bending motion in the middle of bogusware (6).
6. helicopter tail rotor spring bearing fatigue experimental device according to claim 1, it is characterised in that：The bearing branch
Seat (1) is monaural shape bearing spider, and there is fixedly connected hole on rest base both sides, and bearing mounting hole, axle are provided with bearing spider
Hold stop shoulder (12) and end ring groove (13).
7. helicopter tail rotor spring bearing fatigue experimental device according to claim 1, it is characterised in that：The axis of rolling
Support component is held to be made up of bearing spider (1), end ring (9) and rolling bearing (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410424827.5A CN104215458B (en) | 2014-08-26 | 2014-08-26 | A kind of helicopter tail rotor spring bearing fatigue experimental device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410424827.5A CN104215458B (en) | 2014-08-26 | 2014-08-26 | A kind of helicopter tail rotor spring bearing fatigue experimental device |
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| Publication Number | Publication Date |
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| CN104215458A CN104215458A (en) | 2014-12-17 |
| CN104215458B true CN104215458B (en) | 2017-06-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410424827.5A Active CN104215458B (en) | 2014-08-26 | 2014-08-26 | A kind of helicopter tail rotor spring bearing fatigue experimental device |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181333A (en) * | 2015-08-18 | 2015-12-23 | 鹰领航空高端装备技术秦皇岛有限公司 | Helicopter tail rotor system supporting combination joint bearing test machine |
| CN106802242B (en) * | 2015-11-26 | 2019-02-26 | 中国直升机设计研究所 | A kind of tail-rotor spring bearing twisting property experimental rig |
| CN105841992B (en) * | 2016-05-23 | 2019-03-15 | 中国工程物理研究院总体工程研究所 | Six directional acceleration test fixture of portable |
| CN106679976B (en) * | 2016-11-29 | 2019-02-26 | 中国直升机设计研究所 | A kind of shimmy displacement load testing machine of tail-rotor spring bearing |
| CN106737316A (en) * | 2016-12-13 | 2017-05-31 | 惠阳航空螺旋桨有限责任公司 | A kind of setting tool |
| CN108169015B (en) * | 2017-12-01 | 2020-06-09 | 中国直升机设计研究所 | Tail rotor flexible beam torque loading test device |
| CN109520736A (en) * | 2018-11-12 | 2019-03-26 | 中国直升机设计研究所 | A kind of spring bearing durability test device |
| CN112407319B (en) * | 2020-12-15 | 2023-08-18 | 芜湖中科飞机制造有限公司 | Tail support frame of small training machine |
| CN113532859B (en) * | 2021-08-27 | 2024-06-07 | 中浙高铁轴承有限公司 | Engine input end shafting bearing testing machine and testing method |
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| US5677488A (en) * | 1994-08-01 | 1997-10-14 | Ntn Corporation | Piezoelectric film transducer sytem for bearings |
| CN1818600A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Apparatus for fatigue test of horizontal hinge bearing of helicopter |
| CN101363787A (en) * | 2008-10-08 | 2009-02-11 | 燕山大学 | Slow-speed heavy-load fibrage composite self-lubricating bearing strip performance test machine |
| CN102840984A (en) * | 2012-09-21 | 2012-12-26 | 哈尔滨电机厂有限责任公司 | Double-steering bi-directional-loading thrust bearing test device |
| CN103076175A (en) * | 2013-01-10 | 2013-05-01 | 哈尔滨东安发动机（集团）有限公司 | Bearing test method for tail transmission shaft of helicopter |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005315681A (en) * | 2004-04-28 | 2005-11-10 | Nsk Ltd | Bearing testing device |
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2014
- 2014-08-26 CN CN201410424827.5A patent/CN104215458B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5677488A (en) * | 1994-08-01 | 1997-10-14 | Ntn Corporation | Piezoelectric film transducer sytem for bearings |
| CN1818600A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Apparatus for fatigue test of horizontal hinge bearing of helicopter |
| CN101363787A (en) * | 2008-10-08 | 2009-02-11 | 燕山大学 | Slow-speed heavy-load fibrage composite self-lubricating bearing strip performance test machine |
| CN102840984A (en) * | 2012-09-21 | 2012-12-26 | 哈尔滨电机厂有限责任公司 | Double-steering bi-directional-loading thrust bearing test device |
| CN103076175A (en) * | 2013-01-10 | 2013-05-01 | 哈尔滨东安发动机（集团）有限公司 | Bearing test method for tail transmission shaft of helicopter |
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| CN104215458A (en) | 2014-12-17 |
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