CN204269368U - Helicopter Tail Drive System system fault diagnosis comprehensive experiment table - Google Patents
Helicopter Tail Drive System system fault diagnosis comprehensive experiment table Download PDFInfo
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- CN204269368U CN204269368U CN201420804478.5U CN201420804478U CN204269368U CN 204269368 U CN204269368 U CN 204269368U CN 201420804478 U CN201420804478 U CN 201420804478U CN 204269368 U CN204269368 U CN 204269368U
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Abstract
Helicopter Tail Drive System system fault diagnosis comprehensive experiment table, it comprises an experiment table, and this experiment table comprises drive motor, shaft coupling A, the first speed reduction unit, the second speed reduction unit, shaft coupling B, load motor, bearing; First speed reduction unit is connected with drive motor through shaft coupling A, and the coupling shaft axis of the first speed reduction unit and the second speed reduction unit is 135 °; Second speed reduction unit is connected with load motor through shaft coupling B; Drive motor, shaft coupling A, the first speed reduction unit, the second speed reduction unit, shaft coupling B, load motor are linked in sequence and are fixed on bearing; Can realize Helicopter Tail Drive System system bearing, gear spot corrosion, peel off, wear and tear, crackle, gummed, and the simulated experiment of the typical fault such as the deflection of rotor; Be widely used in Helicopter Tail Drive System system failure evolution mechanism, signal characteristic extracting methods, Incipient Fault Diagnosis method, the research of health maintenance approach and strategy.
Description
Technical field
The utility model belongs to Helicopter Tail Drive System system technical field, is specifically related to Helicopter Tail Drive System system fault diagnosis comprehensive experiment table.
Background technology
Helicopter Tail Drive System system is as a part for Helicopter Transmission System Structural Dynamics, it is the important subsystem of Helicopter Transmission System, power is mainly delivered to tail-rotor from main transmission by transmitting torque and rotating speed by it, to balance the anti-twisted moment that main rotor produces, thus realizing the directional control of helicopter, its running status quality directly affects the performance of whole kinematic train and even whole helicopter.If certain bearing in tail kinematic train, gear part break down, under tail transmission shaft High Rotation Speed, can cause strong vibration, part breaking is damaged, cause tail-rotor to be handled and lost efficacy, serious threat is to flight safety.How carry out status monitoring, fault diagnosis and optimizing operation accurately to it to be one and significantly to have again challenging research.
Summary of the invention
For above-mentioned situation, the purpose of this utility model provides Helicopter Tail Drive System system fault diagnosis comprehensive experiment table, it can realize Helicopter Tail Drive System system bearing, gear spot corrosion, peel off, wear and tear, crackle, gummed, and the simulated experiment of the typical fault such as the deflection of rotor, for researchs such as its failure evolution mechanism, signal characteristic extracting methods, Incipient Fault Diagnosis method, health maintenance approach and strategy, guarantee Helicopter Safety reliability service, and structure is simple, easy to operate, be easy to promote the popularization use.
To achieve these goals: Helicopter Tail Drive System system fault diagnosis comprehensive experiment table, it comprises an experiment table, and this experiment table comprises drive motor, shaft coupling A, the first speed reduction unit, the second speed reduction unit, shaft coupling B, load motor, bearing; The first described speed reduction unit is connected with drive motor through shaft coupling A, the coupling shaft axis of the first speed reduction unit and the second speed reduction unit is 135 °, second speed reduction unit is connected with load motor through shaft coupling B, and drive motor, shaft coupling A, the first speed reduction unit, the second speed reduction unit, shaft coupling B, load motor are linked in sequence and are fixed on bearing.
For realizing structure optimization, further step: the first speed reduction unit comprises the spiral bevel gear pair C that pair of intersecting axis is 135 °, the master and slave moving axis of spiral bevel gear pair C is respectively by double-row conical bearing cantilever support.
Second speed reduction unit comprises the spiral bevel gear pair D that pair of intersecting axis is 90 °, the master and slave moving axis of spiral bevel gear pair D respectively by radial thrust bearing and radial roller bearing at gear shaft to two-side supporting.
Drive motor is continuously adjustabe variable-frequency motor, and speed adjustable range is at 0 ~ 4000r/min.
First speed reduction unit ratio of gear is 1.25, and the second speed reduction unit ratio of gear is 2.78.
In first speed reduction unit and the second speed reduction unit, the fault gear of dissimilar, Injured level, different operating position replaced respectively by driving and driven gear, and described fault type is spot corrosion, peel off, crackle, hypodontia.
Various block bearings in first speed reduction unit and the second speed reduction unit replace the faulty bearings of dissimilar, Injured level, different operating position respectively, and described fault type is spot corrosion, peel off, wear and tear, crackle, gummed.
The setting height(from bottom) of drive motor and load motor is adjustable, for model rotor deflection fault.
Also comprise three-way vibration acceleration transducer, vibration displacement sensor, foil gauge, described three-way vibration acceleration transducer is separately positioned on the bearing seat of double-row conical bearing, radial thrust bearing and radial roller bearing; Vibration displacement sensor is separately positioned on the coupling shaft of drive motor output shaft, the first speed reduction unit and the second speed reduction unit, the both sides of load motor input shaft, in 90 ° of distributions; Foil gauge is separately positioned on the tooth root portion of spiral bevel gear pair C, spiral bevel gear pair D, and the coupling shaft of drive motor output shaft, the first speed reduction unit and the second speed reduction unit, load motor input shaft axle on; Three-way vibration acceleration transducer, vibration displacement sensor, foil gauge transfer to computing machine through data acquisition unit connection.
Experiment table is built-in a kind of Helicopter Tail Drive System system fault simulation software, this software is that prototype sets up virtual prototype with experiment table, gear, bearing, the rotor fault of the ascending different faults type of degree of injury and different operating position can be emulated, and extract displacement, acceleration, stress simulation signal.
The utility model Helicopter Tail Drive System system fault diagnosis comprehensive experiment table, it comprises an experiment table, and this experiment table comprises drive motor, shaft coupling A, the first speed reduction unit, the second speed reduction unit, shaft coupling B, load motor, bearing; First speed reduction unit is connected with drive motor through shaft coupling A, and the coupling shaft axis of the first speed reduction unit and the second speed reduction unit is 135 °; Second speed reduction unit is connected with load motor through shaft coupling B; Drive motor, shaft coupling A, the first speed reduction unit, the second speed reduction unit, shaft coupling B, load motor are linked in sequence and are fixed on bearing; Can realize Helicopter Tail Drive System system bearing, gear spot corrosion, peel off, wear and tear, the simulated experiment of the typical fault such as crackle, gummed.
The utility model hinge structure, has the following advantages:
I. the utility model structural design of uniting according to actual Helicopter Tail Drive System, basic structure form and actual Helicopter Tail Drive System are united and are matched, and carry out fault simulation on this basis, with actual motion state consistency;
II. the first speed reduction unit and the second speed reduction unit split, and are easy to study Helicopter Tail Drive System and unite the bearing of different installation site, gear typical fault feature and micromechanism of damage, be convenient to identify separately or combined failure;
III. the first speed reduction unit is by double-row conical bearing cantilever support, the second speed reduction unit by radial thrust bearing and radial roller bearing two supports, transmits steadily reliable, easy accessibility;
IV. can the variable-speed operation state of helicopter simulating tail kinematic train by the output speed of stepless control drive motor 0 ~ 4000 r/min, for research under variable speed, Helicopter Tail Drive System system state monitoring method and failure evolution mechanism;
V. by the layout of acceleration transducer, displacement transducer, foil gauge, measure for the many reference amounts under different running status, be convenient to more fully failure evolution mechanism, signal characteristic extracting methods, Incipient Fault Diagnosis method, the research of health maintenance approach and strategy;
VI. by built-in a kind of Helicopter Tail Drive System system fault simulation software, the analog simulation of the different faults type facilitating degree of injury ascending and the single or combined failure of abort situation, and extract displacement, acceleration, stress simulation signal, the function of expansion physical experiment table.Be convenient to more deep, comprehensive failure evolution mechanism, signal characteristic extracting methods, Incipient Fault Diagnosis method, the research of health maintenance approach and strategy.
The utility model is widely used in Helicopter Tail Drive System system failure evolution mechanism, signal characteristic extracting methods, Incipient Fault Diagnosis method, the research of health maintenance approach and strategy.
Below in conjunction with accompanying drawing, embodiment of the present utility model is described in further details.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the first reducer structure schematic diagram of the present utility model;
Fig. 3 is the second reducer structure schematic diagram of the present utility model;
Fig. 4 is the utility model acceleration and displacement transducer arrangenent diagram;
Fig. 5 is the utility model foil gauge arrangenent diagram;
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 to simulate signal figure;
In figure: 1. bearing, 2. drive motor, 3 shaft coupling A, 4. the first speed reduction unit, 41. double-row conical bearings, 42. spiral bevel gear pair C, 5. the second speed reduction unit, 51. radial thrust bearings, 52. spiral bevel gear pair D, 53. radial roller bearings, 6. shaft coupling B, 7. load motor, 8. vibration displacement sensor, 9. three-way vibration acceleration transducer, 10. foil gauge.
Embodiment
As shown in Figure 1, Helicopter Tail Drive System system fault diagnosis comprehensive experiment table, it comprises an experiment table, and this experiment table comprises drive motor 2, shaft coupling A3, the first speed reduction unit 4, second speed reduction unit 5, shaft coupling B6, load motor 7, bearing 1; The first described speed reduction unit 4 is connected with drive motor 2 through shaft coupling A3, the coupling shaft axis of the first speed reduction unit 4 and the second speed reduction unit 5 is 135 °, second speed reduction unit 5 is connected with load motor 7 through shaft coupling B6, and drive motor 2, shaft coupling A3, the first speed reduction unit 4, second speed reduction unit 5, shaft coupling B6, load motor 7 are linked in sequence and are fixed on bearing 1.
With reference to accompanying drawing, installation requirement of the present utility model: the first speed reduction unit 4 comprises the spiral bevel gear pair C42 that pair of intersecting axis is 135 °, the master and slave moving axis of spiral bevel gear pair C42 is respectively by double-row conical bearing 41 cantilever support, simple and reliable for structure, easy for installation; Second speed reduction unit 5 comprises the spiral bevel gear pair D52 that pair of intersecting axis is 90 °, the master and slave moving axis of spiral bevel gear pair D52 respectively by radial thrust bearing 51 and radial roller bearing 53 at gear shaft to two-side supporting, effectively can ensure that gear operation is steadily flexible; Drive motor 2 is continuously adjustabe variable-frequency motor, and speed adjustable range is at 0 ~ 4000r/min; First speed reduction unit 4 ratio of gear is 1.25, and the second speed reduction unit 5 ratio of gear is 2.78; In first speed reduction unit 4 and the second speed reduction unit 5, the fault gear of dissimilar, Injured level, different operating position replaced respectively by driving and driven gear, and described fault type is spot corrosion, peel off, crackle, hypodontia; Various block bearings in first speed reduction unit 4 and the second speed reduction unit 5 replace the faulty bearings of dissimilar, Injured level, different operating position respectively, and described fault type is spot corrosion, peel off, wear and tear, crackle, gummed; The setting height(from bottom) of drive motor 2 and load motor 7 is adjustable, and adjustable extent is 0 ~ 5mm, take 0.5mm as ladder, for model rotor deflection fault; Also comprise three-way vibration acceleration transducer 9, vibration displacement sensor 8, foil gauge 10, described three-way vibration acceleration transducer 9 is separately positioned on the bearing seat of double-row conical bearing 41, radial thrust bearing 51 and radial roller bearing 53; Vibration displacement sensor 8 is separately positioned on drive motor 2 output shaft, the first speed reduction unit 4 and the coupling shaft of the second speed reduction unit 5, the both sides of load motor 7 input shaft, in 90 ° of distributions; Foil gauge 10 is separately positioned on the tooth root portion of spiral bevel gear pair C42, spiral bevel gear pair D52, and the coupling shaft of drive motor 2 output shaft, the first speed reduction unit 4 and the second speed reduction unit 5, load motor 7 input shaft axle on; Three-way vibration acceleration transducer 9, vibration displacement sensor 8, foil gauge 10 transfer to computing machine through data acquisition unit connection; Experiment table is built-in a kind of Helicopter Tail Drive System system fault simulation software, this software is that prototype sets up virtual prototype with experiment table, gear, bearing, the rotor fault of the ascending different faults type of degree of injury and different operating position can be emulated, and extract displacement, acceleration, stress simulation signal.
principle of work of the present utility model:the power that drive motor 2 exports passes to the driving wheel of spiral bevel gear pair C42 through output shaft, shaft coupling A3, and the engaged wheel of spiral bevel gear pair C42 drives spiral bevel gear pair D52, exports to load motor, by load motor consumed power through shaft coupling B6.
the utility modelfault simulation experiment comprises following several:
A. the fault of bearing, type has: the spot corrosion of double-row conical bearing (41), radial thrust bearing (51) and radial roller bearing (53) bearing inner race, outer ring, rolling body, peel off, wear and tear, crackle, gummed fault;
B. the fault of gear, type has: the spot corrosion of spiral bevel gear, peel off, wear and tear, crackle, hypodontia fault;
C. rotor deflection fault;
D. regulate rotating speed and the load of drive motor 2 and load motor 7, simulate the fault signature of above-mentioned various malfunction under friction speed different loads condition.
In the use of experiment table, its process comprises the following steps:
A. fault part displacement: according to the fault type that will simulate, degree of injury and working position, selects corresponding fault part, replaces original normal part, build malfunction test platform;
B. signals collecting: start drive motor to suitable rotational speed, according to the architectural feature of gear, bearing, axle, selects the point position comprising 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, the acceleration of axle, displacement, stress signal feature, thus acquisition can reflect their running statuses;
D. state recognition: according to the signal characteristic extracted, seek the mapping relations of fault signature and malfunction, judge its state run;
E. failure evolution Analysis on Mechanism: the Helicopter Tail Drive System system fault simulation software utilizing experiment table built-in, by degree of injury fault simulation from shallow to deep, extracts and analyzes simulate signal, disclosing failure evolution mechanism;
F. diagnostic analysis: according to the result of state recognition, in conjunction with failure evolution mechanism, analyzes gear, bearing, the trouble location of axle, character, type, reason and development trend etc. further;
G. decision-making is diagnosed: make a policy according to gear, bearing, axle operating mode and development trend, as adjustment, maintenance, control or replacing etc.
Embodiment 1 double-row conical bearing inner ring pitting fault is simulated.
First speed reduction unit driving wheel supporting double-row conical bearing 41 is replaced into the faulty bearings that there is inner ring pitting fault, start drive motor 2, setting input speed is 1800r/min, connecting sensor output line is to B & K data acquisition system, after simulating signal is converted to digital signal by B & K data acquisition system, transfer data to computer data acquiring software by netting twine, obtain vibration acceleration time series signal, its time domain signal graph is as Fig. 6.
Embodiment 2 double-row tapered roller bearing outer ring pitting fault is simulated
First speed reduction unit driving wheel supporting double-row conical bearing 41 is replaced into the faulty bearings that there is outer ring pitting fault, start drive motor 2, setting input speed is 1800r/min, connecting sensor output line is to B & K data acquisition system, after simulating signal is converted to digital signal by B & K data acquisition system, transfer data to computer data acquiring software by netting twine, obtain vibration acceleration time series signal, its time domain signal graph is as Fig. 7.
Embodiment 3 double-row conical bearing roller pitting fault is simulated
First speed reduction unit 4 driving wheel supporting double-row conical bearing 41 is replaced into the faulty bearings that there is roller pitting fault, start drive motor 2, setting input speed is 1800r/min, connecting sensor output line is to B & K data acquisition system, after simulating signal is converted to digital signal by B & K data acquisition system, transfer data to computer data acquiring software by netting twine, obtain vibration acceleration time series signal, its time domain signal graph is as Fig. 8.
Embodiment 4 spiral bevel gear pitting fault software emulation
Take experiment table as prototype, build experiment table Catia three-dimensional model, import Adams, the active spiral bevel gear of the first speed reduction unit 4 in a model implants pitting fault, exposure parameter is set, simulated conditions is set: drive rotating speed to be set to STEP(time, 0,0,0.2,10800d), analog input rotating speed is the running status of 1800r/min, time is 1s, and step number is 20000.Time-domain-simulation signal graph after 0.2s stablizes, is shown in Fig. 9.
Claims (10)
1. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table, it is characterized in that it comprises an experiment table, this experiment table comprises drive motor (2), shaft coupling A (3), the first speed reduction unit (4), the second speed reduction unit (5), shaft coupling B (6), load motor (7), bearing (1); Described the first speed reduction unit (4) is connected with drive motor (2) through shaft coupling A (3), first speed reduction unit (4) is 135 ° with the coupling shaft axis of the second speed reduction unit (5), second speed reduction unit (5) is connected with load motor (7) through shaft coupling B (6), and drive motor (2), shaft coupling A (3), the first speed reduction unit (4), the second speed reduction unit (5), shaft coupling B (6), load motor (7) are linked in sequence and are fixed on bearing (1).
2. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that the first speed reduction unit (4) comprises the spiral bevel gear pair C (42) that pair of intersecting axis is 135 °, the master and slave moving axis of spiral bevel gear pair C (42) is respectively by double-row conical bearing (41) cantilever support.
3. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that the second speed reduction unit (5) comprises the spiral bevel gear pair D (52) that pair of intersecting axis is 90 °, the master and slave moving axis of spiral bevel gear pair D (52) respectively by radial thrust bearing (51) and radial roller bearing (53) at gear shaft to two-side supporting.
4. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that drive motor (2) is for continuously adjustabe variable-frequency motor, speed adjustable range is at 0 ~ 4000r/min.
5. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that the first speed reduction unit (4) ratio of gear is 1.25, the second speed reduction unit (5) ratio of gear is 2.78.
6. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that the fault gear of dissimilar, Injured level, different operating position replaced respectively by driving and driven gear in the first speed reduction unit (4) and the second speed reduction unit (5), described fault type be spot corrosion, peel off, crackle, hypodontia.
7. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table according to claim 1, the various block bearings that it is characterized in that in the first speed reduction unit (4) and the second speed reduction unit (5) replace the faulty bearings of dissimilar, Injured level, different operating position respectively, and described fault type is spot corrosion, peel off, wear and tear, crackle, gummed.
8. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table according to claim 1, is characterized in that the setting height(from bottom) of drive motor (2) and load motor (7) is adjustable, for model rotor deflection fault.
9. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table according to claim 1, characterized by further comprising three-way vibration acceleration transducer (9), vibration displacement sensor (8), foil gauge (10), described three-way vibration acceleration transducer (9) is separately positioned on the bearing seat of double-row conical bearing (41), radial thrust bearing (51) and radial roller bearing (53); Vibration displacement sensor (8) is separately positioned on the coupling shaft of drive motor (2) output shaft, the first speed reduction unit (4) and the second speed reduction unit (5), the both sides of load motor (7) input shaft, in 90 ° of distributions; Foil gauge (10) is separately positioned on the tooth root portion of spiral bevel gear pair C (42), spiral bevel gear pair D (52), and the coupling shaft of drive motor (2) output shaft, the first speed reduction unit (4) and the second speed reduction unit (5), load motor (7) input shaft axle on; Three-way vibration acceleration transducer (9), vibration displacement sensor (8), foil gauge (10) transfer to computing machine through data acquisition unit connection.
10. Helicopter Tail Drive System system fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that the built-in a kind of Helicopter Tail Drive System system fault simulation software of experiment table, this software is that prototype sets up virtual prototype with experiment table, gear, bearing, the rotor fault of the ascending different faults type of degree of injury and different operating position can be emulated, and extract displacement, acceleration, stress simulation signal.
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| CN201420804478.5U CN204269368U (en) | 2014-12-19 | 2014-12-19 | Helicopter Tail Drive System system fault diagnosis comprehensive experiment table |
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| CN201420804478.5U CN204269368U (en) | 2014-12-19 | 2014-12-19 | Helicopter Tail Drive System system fault diagnosis comprehensive experiment table |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104502093A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation experiment device for helicopter tail transmission system |
| CN105954028A (en) * | 2016-05-23 | 2016-09-21 | 合肥工业大学 | Vertical shaft decelerator testing stand |
| CN112345197A (en) * | 2020-10-23 | 2021-02-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Transmission, tilting and vibration reduction system of icing wind tunnel helicopter test device |
-
2014
- 2014-12-19 CN CN201420804478.5U patent/CN204269368U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104502093A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation experiment device for helicopter tail transmission system |
| CN105954028A (en) * | 2016-05-23 | 2016-09-21 | 合肥工业大学 | Vertical shaft decelerator testing stand |
| CN112345197A (en) * | 2020-10-23 | 2021-02-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Transmission, tilting and vibration reduction system of icing wind tunnel helicopter test device |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150415 Termination date: 20181219 |
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| CF01 | Termination of patent right due to non-payment of annual fee |