CN204269367U - Helicopter Main driving unit fault diagnosis comprehensive experiment table - Google Patents
Helicopter Main driving unit fault diagnosis comprehensive experiment table Download PDFInfo
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- CN204269367U CN204269367U CN201420804464.3U CN201420804464U CN204269367U CN 204269367 U CN204269367 U CN 204269367U CN 201420804464 U CN201420804464 U CN 201420804464U CN 204269367 U CN204269367 U CN 204269367U
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Abstract
Helicopter Main driving unit fault diagnosis comprehensive experiment table, it comprises an experimental provision, and this experimental provision comprises variable-frequency motor, shaft coupling A, first order speed reduction unit, shaft coupling B, second level speed reduction unit, shaft coupling C, detent, bearing; Described variable-frequency motor is through shaft coupling A and first order speed reduction unit level connection joint, and second level speed reduction unit is vertically connected with first order speed reduction unit through shaft coupling B; Detent is connected with second level speed reduction unit through shaft coupling C; Variable-frequency motor, first order speed reduction unit, second level speed reduction unit and detent order is fixed on the technical scheme on bearing; Can be used for the independent or combined failure of helicopter simulating main transmission bevel gear, planetary gear, sun gear, bearing, the condition monitoring and fault diagnosis for Helicopter Main kinematic train provides theoretical foundation and technological guidance; Extensively be adapted to supporting the use of Helicopter Main driving unit fault simulated experiment.
Description
Technical field
The utility model relates to machine driven system fault simulation experimental technique field, is specifically related to Helicopter Main driving unit fault diagnosis comprehensive experiment table.
Background technology
Main transmission is the core component of Helicopter Transmission System, and one or multi-engined torsional moment gather by it, passes to rotor, main oar and miscellaneous part by a certain percentage; Complex structure, the size of main transmission are large, weight is large, the safety and reliability of the helicopter of his running status relation; The fault that a variety of causes of Helicopter Main kinematic train causes accounts for more than 50% of driving unit fault; Therefore, the safe and reliable flight of condition monitoring and fault diagnosis method to helicopter studying Helicopter Main kinematic train has great importance.
Summary of the invention
For above-mentioned situation, the purpose of this utility model is to provide Helicopter Main driving unit fault to diagnose comprehensive experiment table, independent or the combined failure of helicopter simulating main transmission bevel gear, planetary gear, sun gear, bearing can be used for, condition monitoring and fault diagnosis for Helicopter Main kinematic train provides theoretical foundation and technological guidance, ensure that the safe and reliable flight of helicopter, and structure is simple, easy to operate, be easy to penetration and promotion.
For achieving the above object, Helicopter Main driving unit fault diagnosis comprehensive experiment table, it comprises an experimental provision, and this experimental provision comprises variable-frequency motor, shaft coupling A, first order speed reduction unit, shaft coupling B, second level speed reduction unit, shaft coupling C, detent, bearing; Described variable-frequency motor 1 is through shaft coupling A and first order speed reduction unit level connection joint, and second level speed reduction unit is vertically connected with first order speed reduction unit through shaft coupling B; Detent is connected with second level speed reduction unit through shaft coupling C; Variable-frequency motor, first order speed reduction unit, second level speed reduction unit and detent order is fixed on bearing.
For realizing structure, effect optimization, its further measure: first order speed reduction unit (3) comprises the spiral bevel gear pair that pair of intersecting axis is 90 °, the master and slave moving axis of spiral bevel gear pair is respectively by cylinder rolling bearing D cantilever support, the sun gear of second level speed reduction unit is by cylinder rolling bearing E cantilever support, planetary gear is connected on disk planet carrier through needle bearing, and disk planet carrier supports through angular contact bearing.
The ring gear of second level speed reduction unit is fixed, and sun gear inputs, and disk planet carrier exports.
Input speed continuously adjustabe within the scope of 0 ~ 6000r/min of variable-frequency motor, the moment of torsion of detent is 0 ~ 8 × 10
5adjustable within the scope of Nm.
The ratio of gear of first order speed reduction unit is 4.76, and the ratio of gear of second level speed reduction unit is 4.65.
Sun gear in spiral bevel gear in first order speed reduction unit and second level speed reduction unit, planetary gear replace the fault gear of dissimilar, Injured level, different operating position respectively, and described fault type is spot corrosion, wearing and tearing, broken teeth, crackle, gummed.
Cylinder rolling bearing D in first order speed reduction unit and the cylinder rolling bearing E in the speed reduction unit of the second level, needle bearing, angular contact bearing replace the fault gear of dissimilar, Injured level, different operating position respectively, and described fault type is spot corrosion, wearing and tearing, broken teeth, crackle, gummed.
The position of variable-frequency motor height adjustable and detent is adjustable, is biased fault for simulating axle.
Also involving vibrations acceleration transducer, vibration displacement sensor, foil gauge, is arranged on experiment table bearing or gear, and vibration acceleration sensor, vibration displacement sensor, foil gauge transfer to computing machine through data acquisition unit connection.
Experimental provision is built-in a kind of Helicopter Main driving unit fault simulation software, can emulate the various dissimilar fault of main transmission.
The utility model Helicopter Main driving unit fault diagnosis comprehensive experiment table, it comprises an experimental provision, and this experimental provision comprises variable-frequency motor, shaft coupling A, first order speed reduction unit, shaft coupling B, second level speed reduction unit, shaft coupling C, detent, bearing; Described variable-frequency motor 1 is through shaft coupling A and first order speed reduction unit level connection joint, and second level speed reduction unit is vertically connected with first order speed reduction unit through shaft coupling B; Detent is connected with second level speed reduction unit through shaft coupling C; Variable-frequency motor, first order speed reduction unit, second level speed reduction unit and detent order is fixed on the technical scheme on bearing; Can be used for the independent or combined failure of helicopter simulating main transmission bevel gear, planetary gear, sun gear, bearing, the condition monitoring and fault diagnosis for Helicopter Main kinematic train provides theoretical foundation and technological guidance.
The utility model has the advantages that:
I. the second level speed reduction unit planet circular system in the utility model adopts horizontal structure, and consistent with the structure of actual Helicopter Main kinematic train, simulated experiment tallies with the actual situation more;
Ii. the utility model utilizes a pair spiral bevel gear and planet circular system helicopter simulating main transmission structure, is the simplification to the actual main transmission structure of typical case, but can simulates main transmission typical fault state, relatively simple and comprehensive;
Iii. the first speed reduction unit and the second speed reduction unit split, and are easy to the bearing of the different installation site of research Helicopter Main kinematic train, gear typical fault feature and micromechanism of damage, are convenient to identify separately or combined failure;
Iv. the master and slave moving axis of first stage decelerator adopts cantilever support, simple and reliable for structure, easy for installation;
V. can the variable-speed operation state of helicopter simulating main transmission by the output speed of stepless control drive motor 0 ~ 6000 r/min, for research under variable speed, Helicopter Main kinematic train state monitoring method and failure evolution mechanism;
Vi. 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 Helicopter Main kinematic train condition monitoring and fault diagnosis technique study;
Vii. by built-in a kind of Helicopter Main driving unit 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 Helicopter Main kinematic train condition monitoring and fault diagnosis technique study.
The utility model is extensively adapted to supporting the use of Helicopter Main driving unit fault simulated experiment.
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is outside drawing of the present utility model.
Fig. 3 is the cut-open view of the utility model first stage decelerator.
Fig. 4 is the cut-open view of the utility model two stage reducer.
Fig. 5 is the arrangenent diagram of vibration acceleration sensor of the present utility model and vibration displacement sensor.
Fig. 6 is the arrangenent diagram of the foil gauge of the utility model gear.
In figure: 1. variable-frequency motor, 2. shaft coupling A, 3. first order speed reduction unit, 4. shaft coupling B, 5. second level speed reduction unit, 6. shaft coupling C, 7. detent, 8. bearing, 9. vibration displacement sensor, 10. vibration acceleration sensor, 11. foil gauges, 31. cylinder rolling bearing D, 51. cylinder rolling bearing E, 52. sun gears, 53. ring gears, 54. disk planet carriers, 55. angular contact bearings, 56. needle bearings, 57. planetary gears.
concrete embodiment
As shown in Figure 1: Helicopter Main driving unit fault diagnosis comprehensive experiment table; it is characterized in that it comprises an experimental provision, this experimental provision comprises: variable-frequency motor 1, shaft coupling A2, first order speed reduction unit 3, shaft coupling B4, second level speed reduction unit 5, shaft coupling C6, detent 7, bearing 8; Described variable-frequency motor 1 is through shaft coupling A2 and first order speed reduction unit 3 level connection joint, and second level speed reduction unit 5 is vertically connected with first order speed reduction unit 3 through shaft coupling B4; Detent 7 is connected with second level speed reduction unit 5 through shaft coupling C6.Variable-frequency motor 1, first order speed reduction unit 3, second level speed reduction unit 5 and detent 7 order is fixed on bearing 8.
With reference to accompanying drawing, its installation requirement is: first order speed reduction unit 3 comprises the spiral bevel gear pair that pair of intersecting axis is 90 °, the master and slave moving axis of spiral bevel gear pair is respectively by cylinder rolling bearing D31 cantilever support, the sun gear 52 of second level speed reduction unit 5 is by cylinder rolling bearing E51 cantilever support, planetary gear 57 is connected on disk planet carrier 54 through needle bearing 56, disk planet carrier 54 supports through angular contact bearing 55, and this is simple and reliable for structure, easy for installation; The ring gear 53 of second level speed reduction unit 5 is fixed, and sun gear 52 inputs, and disk planet carrier 54 exports; Input speed continuously adjustabe within the scope of 0 ~ 6000r/min of variable-frequency motor 1, the moment of torsion of detent 7 is 0 ~ 8 × 10
5adjustable within the scope of Nm; Ratio of gear in first order speed reduction unit 3 is 4.76, and the ratio of gear of second level speed reduction unit 5 is 4.65; Sun gear 52 in spiral bevel gear in first order speed reduction unit 3 and second level speed reduction unit 5, planetary gear 57 replace the fault gear of dissimilar, Injured level, different operating position respectively, and described fault type is spot corrosion, wearing and tearing, broken teeth, crackle, gummed; Cylinder rolling bearing D31 in first order speed reduction unit 3 and the cylinder rolling bearing E51 in second level speed reduction unit 5, needle bearing 56, angular contact bearing 55 replace the fault gear of dissimilar, Injured level, different operating position respectively, and described fault type is spot corrosion, wearing and tearing, broken teeth, crackle, gummed; The position of variable-frequency motor 1 height adjustable and detent 7 is adjustable, is biased fault for simulating axle; The utility model is involving vibrations acceleration transducer 10, vibration displacement sensor 9, foil gauge 11 also, be arranged on experiment table bearing or gear, vibration acceleration sensor 10, vibration displacement sensor 9, foil gauge 11 transfer to computing machine through data acquisition unit connection; Experimental provision is built-in a kind of Helicopter Main driving unit fault simulation software, can emulate the various dissimilar fault of main transmission.
By reference to the accompanying drawings, installation steps of the present utility model are as follows:
A) first the slide rail of two stage reducer 5 casing along bearing 8 is slided into, be then screwed;
B) detent 7 is fixed on bearing 8, axle remains on vertical direction, cover upper coupling C6;
C) planet circular system is assembled in two stage reducer 5 casing, sun wheel shaft is overlapped upper coupling B4;
D) bevel gear to being assembled in the casing of first stage decelerator 3;
E) first stage decelerator 3 is fixed on bearing 8;
F) variable-frequency motor 1 is connected by shaft coupling A2.
Fault simulation experiment of the present utility model comprises following several:
A. the fault of bearing, type has: cylinder rolling bearing D(31), cylinder rolling bearing E(51), the inner ring of needle bearing (56), angular contact bearing (55), outer ring, rolling body spot corrosion, peel off, wear and tear, crackle, gummed fault;
B. the fault of gear, type has: the spot corrosion of spiral bevel gear, sun gear 52, planetary gear 57, peel off, wear and tear, crackle, hypodontia fault;
C. rotor deflection fault;
D. regulate the rotating speed of variable-frequency motor 1 and the moment of torsion of detent 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 is hyperphoric: 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;
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 cylinder rolling bearing fault is simulated
By the first speed reduction unit driving wheel support cylinder rolling bearing D(31) be replaced into respectively and there is inner ring pitting fault, outer ring pitting fault, the faulty bearings of ball pitting fault, start and drive variable-frequency motor 1, setting input turns cylinder rolling bearing D(31) speed is for 1800r/min, gather this vibration of bearings signal for faster, obtain a series of sample signal, extract its time domain statistical characteristic value, to normal bearing, inner ring fault, outer ring fault, the Time-domain Statistics feature of ball fault is analyzed, in Table, find to there are mapping relations between fault signature and fault type.
。
Claims (10)
1. Helicopter Main driving unit fault diagnosis comprehensive experiment table, it is characterized in that it comprises an experimental provision, this experimental provision comprises: variable-frequency motor (1), shaft coupling A(2), first order speed reduction unit (3), shaft coupling B(4), second level speed reduction unit (5), shaft coupling C(6), detent (7), bearing (8); Described variable-frequency motor (1) is through shaft coupling A(2) and first order speed reduction unit (3) level connection joint, second level speed reduction unit (5) is through shaft coupling B(4) be vertically connected with first order speed reduction unit (3); Detent (7) is through shaft coupling C(6) be connected with second level speed reduction unit (5); Variable-frequency motor (1), first order speed reduction unit (3), second level speed reduction unit (5) and detent (7) order is fixed on bearing (8).
2. Helicopter Main driving unit fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that first order speed reduction unit (3) comprises the spiral bevel gear pair that pair of intersecting axis is 90 °, the master and slave moving axis of spiral bevel gear pair is respectively by cylinder rolling bearing D(31) cantilever support.
3. Helicopter Main driving unit fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that the sun gear (52) of second level speed reduction unit (5) is by cylinder rolling bearing E(51) cantilever support, planetary gear (57) is connected on disk planet carrier (54) through needle bearing (56), and disk planet carrier (54) supports through angular contact bearing (55); Ring gear (53) is fixed, and sun gear (52) inputs, and disk planet carrier (54) exports.
4. Helicopter Main driving unit fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that input speed continuously adjustabe within the scope of 0 ~ 6000r/min of variable-frequency motor (1), the moment of torsion of detent (7) is 0 ~ 8 × 10
5adjustable within the scope of Nm.
5. Helicopter Main driving unit fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that the ratio of gear of first order speed reduction unit (3) is 4.76, the ratio of gear of second level speed reduction unit (5) is 4.65.
6. Helicopter Main driving unit fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that the spiral bevel gear in first order speed reduction unit (3) and the sun gear (52) in second level speed reduction unit (5), planetary gear (57) replace the fault gear of dissimilar, Injured level, different operating position respectively, described fault type is spot corrosion, wearing and tearing, broken teeth, crackle, gummed.
7. Helicopter Main driving unit fault diagnosis comprehensive experiment table according to claim 1, it is characterized in that the cylinder rolling bearing D(31 in first order speed reduction unit (3)) and second level speed reduction unit (5) in cylinder rolling bearing E(51), needle bearing (56), angular contact bearing (55) replace the fault gear of dissimilar, Injured level, different operating position respectively, described fault type is spot corrosion, wearing and tearing, broken teeth, crackle, gummed.
8. Helicopter Main driving unit fault diagnosis comprehensive experiment table according to claim 1, is characterized in that the position of variable-frequency motor (1) height adjustable and detent (7) is adjustable, being biased fault for simulating axle.
9. Helicopter Main driving unit fault diagnosis comprehensive experiment table according to claim 1, characterized by further comprising vibration acceleration sensor (10), vibration displacement sensor (9), foil gauge (11), be arranged on experiment table bearing or gear, vibration acceleration sensor (10), vibration displacement sensor (9), foil gauge (11) transfer to computing machine through data acquisition unit connection.
10. Helicopter Main driving unit fault according to claim 1 diagnosis comprehensive experiment table, is characterized in that the built-in a kind of Helicopter Main driving unit fault simulation software of experimental provision, can emulate the various dissimilar fault of main transmission.
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| CN201420804464.3U CN204269367U (en) | 2014-12-19 | 2014-12-19 | Helicopter Main driving unit fault diagnosis comprehensive experiment table |
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| CN201420804464.3U CN204269367U (en) | 2014-12-19 | 2014-12-19 | Helicopter Main driving unit fault diagnosis comprehensive experiment table |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104502094A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation device for helicopter main transmission system |
| CN105650449A (en) * | 2016-03-21 | 2016-06-08 | 哈尔滨东安发动机（集团）有限公司 | Positioning method for low pressure fault cause of main oil cavity of helicopter main reducing gear |
| CN105840978A (en) * | 2016-03-21 | 2016-08-10 | 哈尔滨东安发动机（集团）有限公司 | Positioning method for main oil cavity high-pressure failure cause of helicopter main reducing gear |
| CN110304229A (en) * | 2019-07-18 | 2019-10-08 | 重庆大学 | A kind of steering engine for ship of two-stage mechanical transmission structure |
| 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 |
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2014
- 2014-12-19 CN CN201420804464.3U patent/CN204269367U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104502094A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation device for helicopter main transmission system |
| CN104502094B (en) * | 2014-12-19 | 2017-10-20 | 湖南科技大学 | A kind of Helicopter Main driving unit fault analogue means |
| CN105650449A (en) * | 2016-03-21 | 2016-06-08 | 哈尔滨东安发动机（集团）有限公司 | Positioning method for low pressure fault cause of main oil cavity of helicopter main reducing gear |
| CN105840978A (en) * | 2016-03-21 | 2016-08-10 | 哈尔滨东安发动机（集团）有限公司 | Positioning method for main oil cavity high-pressure failure cause of helicopter main reducing gear |
| CN110304229A (en) * | 2019-07-18 | 2019-10-08 | 重庆大学 | A kind of steering engine for ship of two-stage mechanical transmission structure |
| CN110304229B (en) * | 2019-07-18 | 2021-04-16 | 重庆大学 | Marine steering engine with two-stage mechanical transmission structure |
| 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 |
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| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20171219 |
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| CF01 | Termination of patent right due to non-payment of annual fee |