CN105067263B - Tail-rotor formula helicopter tail rotor forms a complete set of joint bearing life testing machine - Google Patents
Tail-rotor formula helicopter tail rotor forms a complete set of joint bearing life testing machine Download PDFInfo
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- CN105067263B CN105067263B CN201510504594.4A CN201510504594A CN105067263B CN 105067263 B CN105067263 B CN 105067263B CN 201510504594 A CN201510504594 A CN 201510504594A CN 105067263 B CN105067263 B CN 105067263B
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Abstract
The present invention discloses a kind of tail-rotor formula helicopter tail rotor and forms a complete set of joint bearing life testing machine.The servo-drive oil cylinder of the testing machine drives the upper end of pitch-change-link to pump by displacement crotch, and the lower end of pitch-change-link drives blade upset, and the upper and lower ends of pitch-change-link are provided with experiment oscillating bearing.Servomotor drives blade high-speed rotation by Timing Belt, central post, spline housing, tail-rotor crotch.Air blower is loaded with active load mode to blade, and magnitude of load is detected by the pull pressure sensor connected firmly with pitch-change-link.The present invention disclosure satisfy that the tail rotor of four support arms forms a complete set of oscillating bearing synthesis service life experiment, the real load and real motion that can be born in the work of each oscillating bearing of accurate simulation, have the advantages that compact conformation, good appearance and easy to operate.
Description
Technical field
Formed a complete set of joint bearing life testing machine the present invention relates to a kind of tail-rotor formula helicopter tail rotor.
Background technology
As people deepen continuously to bearing research, fatigue life and reliability as the most important performance of bearing,
Cause the extensive concern of each Production of bearing business and associated user.But because influence factors of fatigue life is too many, along with bearing is tired
Labor life-span theory still need to it is perfect, carry out life test undoubtedly turn into evaluate this index unique effective way.
The fatigue test of helicopter tail rotor oscillating bearing is typically all using the fatigue test method of plain bearing, and what is drawn is tired
Labor lifetime data reliability is relatively low, and some data are overly conservative, causes many bearings when the rated life time is reached, and its quality remains unchanged
Very well, remain to be continuing with, but due to the rated life time, it has to change, and cause very big waste.Using going straight up to tail
Rotor system is tested, and can obtain most true, most comprehensive test data, but the rotating speed of tail rotor is very high, carries out
There are data and be difficult collection in experiment, maintenance, maintenance cost are high, there are problems that.
The form a complete set of premise of oscillating bearing fatigue life of accurate evaluation helicopter tail rotor is that accurate simulation goes straight up to tail
Rotor forms a complete set of the real load and real motion that are born in oscillating bearing work.
The content of the invention
In order to accurate evaluation helicopter tail rotor forms a complete set of the fatigue life of oscillating bearing, the present invention provides a kind of tail-rotor
Formula helicopter tail rotor forms a complete set of the testing machine in oscillating bearing life-span, and the testing machine being capable of accurate helicopter simulating tail rotor
Form a complete set of real load and real motion of the oscillating bearing in flight course.
The present invention is for the solution technical scheme that is used of its technical problem：A kind of tail-rotor formula helicopter tail rotor matches somebody with somebody set group
Close joint bearing life testing machine, including upper mounting plate, lower platform and four columns, the upper mounting plate, lower platform and four columns
Connect firmly composition experiment machine frame together.Servo-drive cylinder bracket on the upper mounting plate passes through fixed ball pivot and connects servo drive
Dynamic oil cylinder, the piston rod of servo-drive oil cylinder is connected by connecting ball pivot with the upper end of connecting shaft, and the lower end of connecting shaft passes through spiral shell
Bolt, bearing cap, taper roll bearing are connected with the upper end of splined shaft, and the spline housing lower end coordinated with splined shaft is by bolt with
The upper end of column is connected, and spline set upper side is connected by bolt with tail-rotor crotch.Supporting box, air blast are installed on the lower platform
Machine, servomotor are arranged on the left and right sides of supporting box, and multi-diameter shaft, the upper and lower side appearance of multi-diameter shaft are connected firmly above supporting box
Face is engaged by bearing with central post upper and lower side inner surface, and the upper surface of central post is consolidated by bolt with the lower end of spline housing
Connection.
The tail-rotor crotch has four structure identical support arms, and each support arm is connected by ball pivot I, ball pivot II and blade respectively
Connect.
Displacement crotch is installed in the upper end of the splined shaft by bolt, bearing cap, and the displacement crotch has four structure phases
Same support arm.
Each support arm of the displacement crotch is connected by testing the upper end of oscillating bearing I, bearing pin I, axle sleeve I and pitch-change-link
Connect, the lower end of pitch-change-link is connected by testing oscillating bearing II, bearing pin II, axle sleeve II with corresponding tail-rotor crotch support arm.
The output end of the servomotor is bonded with driving pulley and connects, driving pulley by synchronous cog belt, be arranged on
The driven pulley of column lower end drives central post to rotate.
It is an advantage of the invention that：The testing machine disclosure satisfy that the helicopter tail rotor of the 4 support arms oscillating bearing that forms a complete set of is comprehensive
Service life experiment is closed, the real working condition condition such as load, motion that can be born in the work of each oscillating bearing of accurate simulation has
There are compact conformation, good appearance and easy to operate.
Brief description of the drawings
Fig. 1 forms a complete set of joint bearing life testing machine structural representation for tail-rotor formula helicopter tail rotor；
Fig. 2 forms a complete set of joint bearing life testing machine annexation schematic diagram for tail-rotor formula helicopter tail rotor；
Fig. 3 is the A-A sectional views of Fig. 2；
Fig. 4 is displacement crotch of the present invention and tail-rotor crotch annexation schematic diagram；
Fig. 5 is the structural representation of pitch-change-link of the present invention；
Fig. 6 is the structural representation of displacement crotch of the present invention；
Fig. 7 is the structural representation of tail-rotor crotch of the present invention.
In above-mentioned accompanying drawing：1. servo-drive cylinder bracket, 2. upper mounting plate, 3. column, 4. supporting box, 5. lower platform,
6. ball pivot is fixed, 7. servo-drive oil cylinder, 8. connect ball pivot, 9. connecting shaft, 10. bearing cap, 11. displacement crotch, 12. displacements draw
Bar, 13. blades, 14. splined shafts, 15. spline housings, 16. central posts, 17. multi-diameter shafts, 18. synchronous cog belts, 19. driving pulleys,
20. servomotors, 21. air blowers, 22. driven pulleys, 23. ball pivot I, 24. ball pivot II, 25. tail-rotor crotch, 26. oscillating bearings
I, the 27. oscillating bearing inner ring oscillating bearing of I, 28. oscillating bearing outer ring I, 29. II, 30. oscillating bearing inner ring II, 31. joint shafts
Bearing outer-ring II, 32. axle sleeve I, 33. bearing pin I, 34. axle sleeve II, 35. bearing pin II, 36. bearing (ball) covers, 37. fixation end caps.
Specific embodiment
Fig. 1~Fig. 7 is one embodiment disclosed by the invention.Because the size of helicopter tail rotor is simultaneously little, therefore, the examination
Test machine drives helicopter tail rotor to rotate at a high speed using servomotor, by the way of air blower carries out active loading to tail-rotor, comes
The real motion and real load of oscillating bearing are combined in the system support of simulation tail rotor.The testing machine includes displacement system, tail
Oar system, drive system, loading system.In the present embodiment, upper mounting plate 2, lower platform 5 connected firmly with four columns 3 together with group
Into experiment machine frame, servo-drive cylinder bracket 1 is connected firmly on testing machine upper mounting plate 2, and supporting box 4 is connected firmly puts down under testing machine
On platform 5.
The servo-drive oil cylinder 7 of displacement system passes through fixed ball pivot 6 and is arranged on servo-drive cylinder bracket 1, connecting shaft 9
Upper end be connected with the piston rod of servo-drive oil cylinder 7 by connecting ball pivot 8, the lower end of connecting shaft 9 passes through four bolts, bearings
Lid 10, taper roll bearing, round nut are connected with the upper end of splined shaft 14.Displacement crotch 11 passes through four bolts, bearing caps 10
Installed in the upper end of splined shaft 14.
The servomotor 20 of drive system is fixed on the right side of supporting box 4, and multi-diameter shaft 17 is fixed on the upper of supporting box
Side.The output end of servomotor 20 is bonded with driving pulley 19 and connects, and central post 16 passes through angular contact ball bearing, round nut, bearing
End cap 36 is fixed on the lower end of multi-diameter shaft 17, and driven pulley 22 passes through fixed end cap 37 and four are bolted to central post 16
Lower end.The lower end of spline housing 15 passes through four spiral shells by four upper ends for being bolted to central post 16, the upper end of spline housing 15
Bolt is connected with tail-rotor crotch 25.Tail-rotor crotch 25 has four support arms, and each support arm passes through ball pivot I23, ball pivot II24 and oar respectively
Leaf 13 is connected.
The upper and lower ends of the pitch-change-link 12 of displacement system are provided with experiment oscillating bearing (oscillating bearing I26, oscillating bearing
II29).Oscillating bearing inner ring I27, oscillating bearing outer ring I28, axle sleeve that the upper end of pitch-change-link 12 passes through oscillating bearing I26
I32, bearing pin I33 are connected with a support arm of displacement crotch 11, and the lower end of pitch-change-link 12 passes through the joint of oscillating bearing II29
Bearing inner race II30, oscillating bearing outer ring II31, axle sleeve II34, bearing pin II35 are connected with blade 13.
The air blower 21 of loading system is fixed on the left side of supporting box 4.
In the course of the work, the piston of servo-drive oil cylinder 7 is driven by connecting ball pivot 8, connecting shaft 9, displacement crotch 11
The upper end of pitch-change-link 12 pumps, and the lower end of pitch-change-link 12 drives blade 13 to overturn, and realizes tail rotor displacement
The simulation of motion.The output end of servomotor 20 is driven neutral by driving pulley 19, synchronous cog belt 18 and driven pulley 22
The center high-speed rotation of post 16, spline housing 15, tail-rotor crotch 25 around multi-diameter shaft 17；Spline housing 15 is engaged with splined shaft 14, is driven
The high-speed rotation of displacement crotch 11；Tail-rotor crotch 25 drives the high-speed rotation of blade 13 by ball pivot I23, ball pivot II24；Pitch-change-link
12 with displacement crotch 11 and the high-speed rotation of blade 13.Air blower 21 is loaded with active load mode to blade 13, and load is big
The small pull pressure sensor detection by being connected firmly with pitch-change-link 12, carrys out helicopter simulating tail rotor suffered in operation process with this
The influence of wind-force.
Displacement crotch 11 has four support arms, each support arm difference identical pitch-change-link 12 of attachment structure, therefore is somebody's turn to do
Testing machine disclosure satisfy that the tail rotor of 4 support arms form a complete set of oscillating bearing synthesis service life experiment.
Claims (6)
1. a kind of tail-rotor formula helicopter tail rotor forms a complete set of joint bearing life testing machine, including upper mounting plate, lower platform and four
Individual column, the upper mounting plate, lower platform and four columns connect firmly composition experiment machine frame together, it is characterized in that：It is described flat
Servo-drive cylinder bracket on platform passes through fixed ball pivot and connects servo-drive oil cylinder, and the piston rod of servo-drive oil cylinder is by connecting
Hinge of receiving is connected with the upper end of connecting shaft, and the lower end of connecting shaft is by the upper of bolt, bearing cap, taper roll bearing and splined shaft
End is connected, and the lower end of the spline housing coordinated with splined shaft is connected firmly by bolt with the upper end of central post, and spline set upper side passes through spiral shell
Bolt is connected with tail-rotor crotch；Supporting box is installed, air blower, servomotor are arranged on the left and right of supporting box on the lower platform
Both sides, connect firmly multi-diameter shaft above supporting box, the upper and lower side of multi-diameter shaft is engaged by bearing with lower inner surface on central post, in
The upper surface of column is connected firmly by bolt with the lower end of spline housing.
2. tail-rotor formula helicopter tail rotor according to claim 1 forms a complete set of joint bearing life testing machine, its feature
It is：The tail-rotor crotch has four structure identical support arms, and each support arm is connected by ball pivot I, ball pivot II with blade respectively.
3. tail-rotor formula helicopter tail rotor according to claim 1 forms a complete set of joint bearing life testing machine, its feature
It is：Displacement crotch is installed in the upper end of the splined shaft by bolt, bearing cap, and the displacement crotch has four structure identicals
Support arm.
4. tail-rotor formula helicopter tail rotor according to claim 3 forms a complete set of joint bearing life testing machine, its feature
It is：The one of support arm of displacement crotch is connected by testing the upper end of oscillating bearing I, bearing pin I, axle sleeve I and pitch-change-link
Connect, the lower end of pitch-change-link is connected by testing oscillating bearing II, bearing pin II, axle sleeve II a support arm corresponding with tail-rotor crotch
Connect.
5. tail-rotor formula helicopter tail rotor according to claim 4 forms a complete set of joint bearing life testing machine, its feature
It is：The experiment oscillating bearing I is connected with the upper end of pitch-change-link, the lower end of pitch-change-link by test oscillating bearing II with
One support arm connection of tail-rotor crotch；Oscillating bearing inner ring II, oscillating bearing outer ring II, the axle sleeve of the experiment oscillating bearing II
II, bearing pin II are connected with a support arm of tail-rotor crotch.
6. tail-rotor formula helicopter tail rotor according to claim 1 forms a complete set of joint bearing life testing machine, its feature
It is：The output end of the servomotor is bonded with driving pulley and connects, and driving pulley is by synchronous cog belt, installed in central post
The driven pulley of lower end drives central post to rotate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510504594.4A CN105067263B (en) | 2015-08-18 | 2015-08-18 | Tail-rotor formula helicopter tail rotor forms a complete set of joint bearing life testing machine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510504594.4A CN105067263B (en) | 2015-08-18 | 2015-08-18 | Tail-rotor formula helicopter tail rotor forms a complete set of joint bearing life testing machine |
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| CN105067263A CN105067263A (en) | 2015-11-18 |
| CN105067263B true CN105067263B (en) | 2017-06-30 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN107060736B (en) * | 2017-06-13 | 2023-05-16 | 徐州徐工基础工程机械有限公司 | Mechanism for testing lifting force and pressurizing force of drill rod in rotation and testing method |
| CN109229420B (en) * | 2018-09-01 | 2021-08-20 | 哈尔滨工程大学 | Variable-pitch actuating structure of helicopter tail rotor test bed |
| CN109552600B (en) * | 2018-11-06 | 2024-01-19 | 珠海隆华直升机科技有限公司 | Linear electric direct-drive double-tail-rotor mechanism assembly of helicopter and helicopter |
| CN110901951B (en) * | 2019-11-15 | 2023-01-13 | 哈尔滨飞机工业集团有限责任公司 | Multifunctional tail rotor test system |
| CN113551910B (en) * | 2021-08-27 | 2024-04-05 | 中浙高铁轴承有限公司 | Helicopter rotor system matched bearing testing machine and method |
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| RU2065145C1 (en) * | 1993-11-11 | 1996-08-10 | Московский вертолетный завод им.М.Л.Миля | Method of detection of structural damages in multistream toothed driving mechanisms |
| CN1818598A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter |
| CN101363770A (en) * | 2008-10-08 | 2009-02-11 | 燕山大学 | Fatigue-tesing machine for ball socket bearing of helicopter main rotor |
| CN102401764A (en) * | 2011-11-17 | 2012-04-04 | 中国航空动力机械研究所 | Model loading device |
| CN103162963A (en) * | 2013-02-06 | 2013-06-19 | 燕山大学 | Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine |
| CN103900811A (en) * | 2012-12-25 | 2014-07-02 | 中国直升机设计研究所 | Rotation load applying device for tail rotor shaft fatigue test |
| CN104344931A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Rotor head pulling and twisting strip type propeller hub for helicopter blade dynamic balance test table |
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2015
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Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2065145C1 (en) * | 1993-11-11 | 1996-08-10 | Московский вертолетный завод им.М.Л.Миля | Method of detection of structural damages in multistream toothed driving mechanisms |
| CN1818598A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter |
| CN101363770A (en) * | 2008-10-08 | 2009-02-11 | 燕山大学 | Fatigue-tesing machine for ball socket bearing of helicopter main rotor |
| CN102401764A (en) * | 2011-11-17 | 2012-04-04 | 中国航空动力机械研究所 | Model loading device |
| CN103900811A (en) * | 2012-12-25 | 2014-07-02 | 中国直升机设计研究所 | Rotation load applying device for tail rotor shaft fatigue test |
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