CN104502093B - A kind of Helicopter Tail Drive System system fault simulation experimental provision - Google Patents
A kind of Helicopter Tail Drive System system fault simulation experimental provision Download PDFInfo
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- CN104502093B CN104502093B CN201410787493.8A CN201410787493A CN104502093B CN 104502093 B CN104502093 B CN 104502093B CN 201410787493 A CN201410787493 A CN 201410787493A CN 104502093 B CN104502093 B CN 104502093B
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Abstract
A kind of Helicopter Tail Drive System system fault simulation experimental provision, it includes an experimental bench, and the experimental bench includes motor, shaft coupling A, the first decelerator, the second decelerator, shaft coupling B, load motor, bearing；First decelerator is connected through shaft coupling A with motor, and the connecting shaft axis of the first decelerator and the second decelerator is 135 °；Second decelerator is connected through shaft coupling B with load motor；Motor, shaft coupling A, the first decelerator, the second decelerator, shaft coupling B, load motor are linked in sequence and are fixed on bearing；The simulated experiment of the typical faults such as the deflection of Helicopter Tail Drive System system bearing, the spot corrosion of gear, peeling, abrasion, crackle, gluing, and rotor can be realized；It is widely used in Helicopter Tail Drive System system failure evolution mechanism, signal characteristic extracting methods, Incipient Fault Diagnosis method, health maintenance method and strategy study.
Description
Technical field
The invention belongs to Helicopter Tail Drive System system technical field, and in particular to a kind of Helicopter Tail Drive System system failure mould
Draft experiment device.
Background technology
The part that Helicopter Tail Drive System is united as Helicopter Transmission System Structural Dynamics, it is helicopter power train
The important subsystem of system, it is mainly delivered to tail-rotor by transmitting moment of torsion and rotating speed by power from main transmission, to balance
The anti-twisted torque that main rotor is produced, so as to realize the directional control of helicopter, its running status quality directly affects whole biography
The performance of dynamic system or even whole helicopter.If certain bearing, gear part in tail transmission system break down, in tail transmission shaft
Under rotating at a high speed, strong vibration can be caused, part breaking is damaged, cause tail-rotor to manipulate failure, seriously threaten flight peace
Entirely.It is one significant and extremely challenging that accurate status monitoring, fault diagnosis are how carried out to it with optimization operation
Research.
The content of the invention
For above-mentioned situation, united fault simulation experimental provision it is an object of the invention to provide a kind of Helicopter Tail Drive System, it
The allusion quotations such as the deflection of Helicopter Tail Drive System system bearing, the spot corrosion of gear, peeling, abrasion, crackle, gluing, and rotor can be realized
The simulated experiment of type failure, for its failure evolution mechanism, signal characteristic extracting methods, Incipient Fault Diagnosis method, health dimension
The research such as maintaining method and strategy, it is ensured that Helicopter Safety reliability service, and it is simple in construction, it is easy to operate, it is easy to penetration and promotion
Use.
To achieve these goals：A kind of Helicopter Tail Drive System system fault simulation experimental provision, it includes an experimental bench,
The experimental bench includes motor, shaft coupling A, the first decelerator, the second decelerator, shaft coupling B, load motor, bearing；It is described
The first decelerator be connected through shaft coupling A with motor, the connecting shaft axis of the first decelerator and the second decelerator is 135 °,
Second decelerator is connected through shaft coupling B with load motor, motor, shaft coupling A, the first decelerator, the second decelerator, shaft coupling
Device B, load motor, which are linked in sequence, to be fixed on bearing.
To realize structure optimization, further step：First decelerator includes the screw conic that a pair of intersecting axis is 135 °
Gear pair C, spiral bevel gear pair C master and slave moving axis are respectively by double-row conical bearing cantilever support.
Second decelerator includes the spiral bevel gear pair D that a pair of intersecting axis is 90 °, and spiral bevel gear pair D's is driving and driven
Axle is respectively by radial thrust bearing and radial roller bearing in the axial two-side supporting of gear.
Motor is continuously adjustabe variable-frequency motor, and speed adjustable range is in 0 ~ 4000r/min.
First decelerator gearratio is 1.25, and the second decelerator gearratio is 2.78.
Driving and driven gear replaces different type, Injured level, difference respectively in first decelerator and the second decelerator
The failure gear of operating position, the fault type is spot corrosion, peeling, crackle, hypodontia.
Various bearing supports in first decelerator and the second decelerator replace respectively different type, Injured level,
The faulty bearings of different operating position, the fault type is spot corrosion, peeling, abrasion, crackle, gluing.
The setting height(from bottom) of motor and load motor is adjustable, for model rotor deflection fault.
Also include three-way vibration acceleration transducer, vibration displacement sensor, foil gauge, described three-way vibration acceleration
Sensor is separately positioned on the bearing block of double-row conical bearing, radial thrust bearing and radial roller bearing；Vibrate position
Displacement sensor is separately positioned on driving motor output shaft, the connecting shaft of the first decelerator and the second decelerator, load motor input
The both sides of axle, in 90 ° of distributions；Foil gauge is separately positioned on spiral bevel gear pair C, spiral bevel gear pair D root portion, and drives
Dynamic motor output shaft, the connecting shaft of the first decelerator and the second decelerator, on the axle of load motor input shaft；Three-way vibration accelerates
Degree sensor, vibration displacement sensor, foil gauge are transmitted to computer through data acquisition unit connection.
A kind of built-in Helicopter Tail Drive System system fault simulation software of experimental bench, the software is set up by prototype of experimental bench
Virtual prototype, can emulate the gear of the ascending different faults type of degree of injury and different operating position, bearing, turn
Sub- failure, and extract displacement, acceleration, stress simulation signal.
A kind of Helicopter Tail Drive System system fault simulation experimental provision of the present invention, it includes an experimental bench, the experimental bench bag
Include motor, shaft coupling A, the first decelerator, the second decelerator, shaft coupling B, load motor, bearing；First decelerator is through connection
Axle device A is connected with motor, and the connecting shaft axis of the first decelerator and the second decelerator is 135 °；Second decelerator is through shaft coupling
Device B is connected with load motor；Motor, shaft coupling A, the first decelerator, the second decelerator, shaft coupling B, load motor order
It is connected and fixed on bearing；Helicopter Tail Drive System system bearing, the spot corrosion of gear, peeling, abrasion, crackle, gluing etc. can be realized
The simulated experiment of typical fault.
The present invention compared with the prior art, with advantages below：
I. the structure design that the present invention unites according to actual Helicopter Tail Drive System, basic structure form is with actually going straight up to tail
Transmission system matches, and carries out fault simulation on this basis, with actual motion state consistency；
II. the first decelerator and the second decelerator are split, it is easy to study the different installation sites of Helicopter Tail Drive System system
Bearing, gear typical fault feature and micromechanism of damage, are easy to identification each or combined failure；
III. the first decelerator from double-row conical bearing cantilever support, the second decelerator from radial thrust bearing and to
Heart roller bearing two supports, steady reliable, the convenient disassembly of transmission；
IV. can be with helicopter simulating tail transmission system by the r/min of continuous control motor 0 ~ 4000 output speed
Variable-speed operation state, for studying under variable speed, Helicopter Tail Drive System system state monitoring method and failure evolution mechanism；
V. by acceleration transducer, displacement transducer, foil gauge arrangement, for many reference amounts under different running statuses
Measurement, is easy to more fully failure evolution mechanism, signal characteristic extracting methods, Incipient Fault Diagnosis method, health maintenance method
With strategy study；
VI. by a kind of built-in Helicopter Tail Drive System system fault simulation software, facilitate degree of injury ascending not
With fault type and single or combined failure the analog simulation of abort situation, and extract displacement, acceleration, stress simulation letter
Number, extend the function of physical experiment table.Be easy to deeper into, comprehensive failure evolution mechanism, signal characteristic extracting methods, early stage therefore
Hinder diagnostic method, health maintenance method and strategy study.
The present invention is widely used in Helicopter Tail Drive System system failure evolution mechanism, signal characteristic extracting methods, early stage event
Hinder diagnostic method, health maintenance method and strategy study.
The embodiment to the present invention is described in further details below in conjunction with the accompanying drawings.
Brief description of the drawings
Fig. 1 is structural representation of the invention；
Fig. 2 is the first reducer structure schematic diagram of the invention；
Fig. 3 is the second reducer structure schematic diagram of the invention；
Fig. 4 is acceleration of the present invention and displacement transducer layout drawing；
Fig. 5 is foil gauge layout drawing of the present invention；
Fig. 6 is double-row conical bearing inner ring pitting fault time-domain signal figure；
Fig. 7 is double-row tapered roller bearing outer ring pitting fault time-domain signal figure；
Fig. 8 is double-row conical bearing ball pitting fault time-domain signal figure；
Fig. 9 is spiral bevel gear pitting fault software emulation signal graph；
In figure：1. bearing, 2. motors, 3 shaft coupling A, 4. first decelerators, 41. double-row conical bearings, 42.
Spiral bevel gear pair C, 5. second decelerators, 51. radial thrust bearings, 52. spiral bevel gear pair D, 53. radial roller axles
Hold, 6. shaft coupling B, 7. load motors, 8. vibration displacement sensors, 9. three-way vibration acceleration transducers, 10. foil gauges.
Embodiment
As shown in figure 1, a kind of Helicopter Tail Drive System system fault simulation experimental provision, it includes an experimental bench, the experiment
Platform includes motor 2, shaft coupling A3, the first decelerator 4, the second decelerator 5, shaft coupling B6, load motor 7, bearing 1；Institute
The first decelerator 4 stated is connected through shaft coupling A3 with motor 2, the connecting shaft axis of the first decelerator 4 and the second decelerator 5
For 135 °, the second decelerator 5 is connected through shaft coupling B6 with load motor 7, motor 2, shaft coupling A3, the first decelerator 4,
Two decelerators 5, shaft coupling B6, load motor 7, which are linked in sequence, to be fixed on bearing 1.
Referring to the drawings, installation requirement of the invention：First decelerator 4 includes the screw conic tooth that a pair of intersecting axis is 135 °
Wheel set C42, spiral bevel gear pair C42 master and slave moving axis respectively by the cantilever support of double-row conical bearing 41, it is simple in construction can
Lean on, it is easy for installation；Second decelerator 5 includes the spiral bevel gear pair D52, spiral bevel gear pair D52 that a pair of intersecting axis is 90 °
Master and slave moving axis respectively by radial thrust bearing 51 and radial roller bearing 53 in the axial two-side supporting of gear, can effectively ensure that
Gear operation is steadily flexible；Motor 2 is continuously adjustabe variable-frequency motor, and speed adjustable range is in 0 ~ 4000r/min；First decelerator
4 gearratios are 1.25, and the gearratio of the second decelerator 5 is 2.78；Driving and driven gear point in first decelerator 4 and the second decelerator 5
Not Zhi Huan different type, Injured level, the failure gear of different operating position, the fault type be spot corrosion, peel off, split
Line, hypodontia；Various bearing supports in first decelerator 4 and the second decelerator 5 replace different type, different damage journeys respectively
Degree, the faulty bearings of different operating position, the fault type are spot corrosion, peeling, abrasion, crackle, gluing；The He of motor 2
The setting height(from bottom) of load motor 7 is adjustable, and adjustable extent is 0 ~ 5mm, using 0.5mm as ladder, for model rotor deflection fault；Also
Including three-way vibration acceleration transducer 9, vibration displacement sensor 8, foil gauge 10, described three-way vibration acceleration transducer
9 are separately positioned on the bearing block of double-row conical bearing 41, radial thrust bearing 51 and radial roller bearing 53；Vibrate position
Displacement sensor 8 is separately positioned on the output shaft of motor 2, the connecting shaft of the first decelerator 4 and the second decelerator 5, load motor 7
The both sides of input shaft, in 90 ° of distributions；Foil gauge 10 is separately positioned on spiral bevel gear pair C42, spiral bevel gear pair D52 tooth
Root, and the output shaft of motor 2, the connecting shaft of the first decelerator 4 and the second decelerator 5, the axle of the input shaft of load motor 7
On；Three-way vibration acceleration transducer 9, vibration displacement sensor 8, foil gauge 10 are transmitted to calculating through data acquisition unit connection
Machine；A kind of built-in Helicopter Tail Drive System system fault simulation software of experimental bench, the software is set up virtually by prototype of experimental bench
PM prototype model, gear, bearing, the rotor that can emulate the ascending different faults type of degree of injury and different operating position is former
Barrier, and extract displacement, acceleration, stress simulation signal.
Operation principle：
The power that motor 2 is exported passes to spiral bevel gear pair C42 driving wheel, spiral shell through output shaft, shaft coupling A3
The driven pulley for revolving bevel gear pair C42 drives spiral bevel gear pair D52, is exported through shaft coupling B6 to load motor, by load motor
Consume power.
Fault simulation experiment includes following several：
A. the failure of bearing, type has：Double-row conical bearing (41), radial thrust bearing (51) and radial roller axle
Hold (53) bearing inner race, outer ring, the spot corrosion of rolling element, peeling, abrasion, crackle, glued failure；
B. the failure of gear, type has：The spot corrosion of spiral bevel gear, peeling, abrasion, crackle, hypodontia failure；
C. rotor deflection failure；
D. rotating speed and load of the regulation motor 2 with load motor 7, simulate above-mentioned various malfunctions in friction speed
Fault signature under the conditions of different loads.
In experimental bench in use, its process includes the following steps：
A. failure part is replaced：According to the fault type, degree of injury and operating position to be simulated, corresponding failure is selected
Part, replaces original normal part, builds malfunction test platform；
B. signal acquisition：Start motor to suitable rotational speed, according to gear, bearing, axle architectural feature, selection includes
The point position of maximum fault information, carries out acceleration, displacement, stress signal collection；
C. signal analysis：Select suitable signal analysis method, and construct rational parameter, extract gear, bearing, axle
Acceleration, displacement, stress signal feature, so that their running statuses can be reflected by obtaining；
D. state recognition：According to the signal characteristic of extraction, seek the mapping relations of fault signature and malfunction, judge it
The state of operation；
E. failure evolution Analysis on Mechanism：Using the Helicopter Tail Drive System system fault simulation software built in experimental bench, pass through
The fault simulation of degree of injury from shallow to deep, extracts and analyzes emulation signal, discloses failure evolution mechanism；
F. diagnostic analysis：According to the result of state recognition, combination failure evolution mechanism further analyzes gear, bearing, axle
Trouble location, property, type, reason and development trend etc.；
G. decision-making is diagnosed：Made a policy according to gear, bearing, axle operating mode and development trend, such as adjustment, maintenance, control or
Change etc..
The double-row conical bearing inner ring pitting fault of embodiment 1 is simulated.
First decelerator driving wheel supporting double-row conical bearing 41 is replaced into the failure that there is inner ring pitting fault
Bearing, starts motor 2, sets input speed as 1800r/min, connects Sensor output to B＆K data collecting systems,
B＆K data collecting systems are converted analog signals into after data signal, and computer data acquiring is transferred data to by netting twine
Software, obtains vibration acceleration time series signal, its time domain signal graph such as Fig. 6.
The double-row tapered roller bearing outer ring pitting fault of embodiment 2 is simulated
First decelerator driving wheel supporting double-row conical bearing 41 is replaced into the failure that there is outer ring pitting fault
Bearing, starts motor 2, sets input speed as 1800r/min, connects Sensor output to B＆K data collecting systems,
B＆K data collecting systems are converted analog signals into after data signal, and computer data acquiring is transferred data to by netting twine
Software, obtains vibration acceleration time series signal, its time domain signal graph such as Fig. 7.
The double-row conical bearing roller pitting fault of embodiment 3 is simulated
The driving wheel of first decelerator 4 supporting double-row conical bearing 41 is replaced into the failure that there is roller pitting fault
Bearing, starts motor 2, sets input speed as 1800r/min, connects Sensor output to B＆K data collecting systems,
B＆K data collecting systems are converted analog signals into after data signal, and computer data acquiring is transferred data to by netting twine
Software, obtains vibration acceleration time series signal, its time domain signal graph such as Fig. 8.
The spiral bevel gear pitting fault software emulation of embodiment 4
Using experimental bench as prototype, experimental bench Catia threedimensional models are built, Adams are imported, in a model the first decelerator 4
Active spiral bevel gear on be implanted into pitting fault, exposure parameter is set, simulated conditions are set：Driving rotating speed is set to STEP
（Time, 0,0,0.2,10800d）, simulation input rotating speed is 1800r/min running status, and the time is 1s, and step number is 20000.
Time-domain-simulation signal graph after 0.2s is stable, is shown in Fig. 9.
Claims (7)
- The fault simulation experimental provision 1. a kind of Helicopter Tail Drive System is united, it is characterised in that it includes an experimental bench, the experimental bench Including motor (2), shaft coupling A (3), the first decelerator (4), the second decelerator (5), shaft coupling B (6), load motor (7), bearing (1)；Described the first decelerator (4) is connected through shaft coupling A (3) with motor (2), the first decelerator (4) with The connecting shaft axis of second decelerator (5) is 135 °, and the second decelerator (5) is connected through shaft coupling B (6) with load motor (7), is driven Dynamic motor (2), shaft coupling A (3), the first decelerator (4), the second decelerator (5), shaft coupling B (6), load motor (7) sequentially connect Connect and be fixed on bearing (1)；The setting height(from bottom) of the motor (2) and load motor (7) is adjustable and adjustable extent be 0~ 5mm, for model rotor deflection fault；First decelerator (4) includes the spiral bevel gear that a pair of intersecting axis is 135 ° Secondary C (42), spiral bevel gear pair C (42) master and slave moving axis are respectively by double-row conical bearing (41) cantilever support；It is described Second decelerator (5) includes the spiral bevel gear pair D (52) that a pair of intersecting axis is 90 °, spiral bevel gear pair D's (52) Master and slave moving axis is respectively by radial thrust bearing (51) and radial roller bearing (53) in the axial two-side supporting of gear；The experiment Platform also includes transmitting to the three-way vibration acceleration transducer of computer (9), vibration displacement sensor through data acquisition unit connection (8), foil gauge (10) and built-in fault simulation software.
- 2. a kind of Helicopter Tail Drive System system fault simulation experimental provision according to claim 1, it is characterised in that driving The speed adjustable range of motor (2) is in 0~4000r/min.
- 3. a kind of Helicopter Tail Drive System system fault simulation experimental provision according to claim 1, it is characterised in that first Decelerator (4) gearratio is 1.25, and the second decelerator (5) gearratio is 2.78.
- 4. a kind of Helicopter Tail Drive System system fault simulation experimental provision according to claim 1, it is characterised in that first Driving and driven gear replaces different type, Injured level, different operating position respectively in decelerator (4) and the second decelerator (5) The failure gear put, the fault type is spot corrosion, peeling, crackle, hypodontia.
- 5. a kind of Helicopter Tail Drive System system fault simulation experimental provision according to claim 1, it is characterised in that first Various bearing supports in decelerator (4) and the second decelerator (5) replace different type, Injured level, different works respectively Make the faulty bearings of position, the fault type is spot corrosion, peeling, abrasion, crackle, gluing.
- 6. a kind of Helicopter Tail Drive System system fault simulation experimental provision according to claim 1, it is characterised in that described Three-way vibration acceleration transducer (9) be separately positioned on double-row conical bearing (41), radial thrust bearing (51) and to On the bearing block of heart roller bearing (53)；Vibration displacement sensor (8) is separately positioned on motor (2) output shaft, first subtracted The connecting shaft of fast device (4) and the second decelerator (5), the both sides of load motor (7) input shaft, in 90 ° of distributions；Foil gauge (10) point Spiral bevel gear pair C (42), spiral bevel gear pair D (52) root portion, and motor (2) output shaft, are not arranged on In the connecting shaft of one speed reducer (4) and the second decelerator (5), the axle of load motor (7) input shaft.
- 7. a kind of Helicopter Tail Drive System system fault simulation experimental provision according to claim 1, it is characterised in that failure Simulation software sets up virtual prototype by prototype of experimental bench, can emulate the ascending different faults type of degree of injury and Gear, bearing, the rotor fault of different operating position, and extract displacement, acceleration, stress simulation signal.
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| CN201410787493.8A CN104502093B (en) | 2014-12-19 | 2014-12-19 | A kind of Helicopter Tail Drive System system fault simulation experimental provision |
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| CN201410787493.8A CN104502093B (en) | 2014-12-19 | 2014-12-19 | A kind of Helicopter Tail Drive System system fault simulation experimental provision |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106017914B (en) * | 2016-05-11 | 2018-11-16 | 湖南科技大学 | A kind of Helicopter Transmission System Vibration Noise Study test platform |
| CN108168875B (en) * | 2017-12-01 | 2019-12-20 | 中国直升机设计研究所 | Helicopter tail transmission system fault implantation test bed |
| CN110793771A (en) * | 2019-10-18 | 2020-02-14 | 中国直升机设计研究所 | Test bench of simulation helicopter main reducing gear trouble |
| CN111238806A (en) * | 2020-04-27 | 2020-06-05 | 北京清航紫荆装备科技有限公司 | Testing device for transmission system of cross dual-rotor unmanned helicopter |
| CN114955001A (en) * | 2022-06-17 | 2022-08-30 | 重庆大学 | Helicopter tail transmission system simulation experiment system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN201429498Y (en) * | 2009-07-03 | 2010-03-24 | 中国航空动力机械研究所 | Mechanical power closed test device |
| CN101900640B (en) * | 2010-07-23 | 2012-05-30 | 北京工业大学 | Fault simulation combined test table of machine drive system |
| CN102353534A (en) * | 2011-06-29 | 2012-02-15 | 西安交通大学 | Fault simulation experiment table for step-up drive system of wind-driven generator set |
| CN102759449A (en) * | 2012-07-11 | 2012-10-31 | 三峡大学 | Fault diagnosis device for transmission system of wind turbine generator and simulation method |
| 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 |
| CN204269368U (en) * | 2014-12-19 | 2015-04-15 | 湖南科技大学 | Helicopter Tail Drive System system fault diagnosis comprehensive experiment table |
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