CN106017914A - Research and testing platform for vibration noises of helicopter transmission system - Google Patents
Research and testing platform for vibration noises of helicopter transmission system Download PDFInfo
- Publication number
- CN106017914A CN106017914A CN201610307788.XA CN201610307788A CN106017914A CN 106017914 A CN106017914 A CN 106017914A CN 201610307788 A CN201610307788 A CN 201610307788A CN 106017914 A CN106017914 A CN 106017914A
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- drive system
- transmission
- main rotor
- tail
- transmission system
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/028—Acoustic or vibration analysis
Abstract
The invention provides a research and testing platform for vibration noises of a helicopter transmission system. The platform comprises a transmission system, a drive system, a security protection net, a main rotor loading system, a tail transmission loading system, a measuring and control system, and a fixed pedestal. Te drive system and the transmission system are in engagement connection by a gear wheel and are arranged on the fixed pedestal. The transmission system is installed on the fixed pedestal in a suspension mode by a three-point support hanger. The main rotor loading system and the tail transmission loading system are connected with the transmission system by a main rotor shaft and a tail transmission shaft. The security protection net arranged on the fixed pedestal is used for protecting the transmission system, the main rotor loading system and the tail transmission loading system. According to the platform, on the basis of three-point suspension positioning for the transmission system and reasonable setting of all systems, a defect of expensive testing platform can be overcome; and a scientific basis is provided for analyzing the dynamics and vibration noises of the helicopter transmission system and guaranteeing safety and high-efficiency operation of the transmission system. The platform is widely applied to vibration noise control and operation state evaluation research of the transmission system.
Description
Technical field
The present invention relates to Helicopter Technology field, particularly relate to a kind of Helicopter Transmission System Vibration Noise Study test platform.
Background technology
Helicopter Transmission System is one of three big critical components of helicopter, is that turboshaft engine power exports indispensable biography
Defeated parts, are also unique delivering paths；The performance of helicopter is largely determined by the performance of drive system, and vibration is made an uproar
Sound is the major criterion that reflection Helicopter Transmission System performance is good and bad, and vibration and noise signals has contained Helicopter Transmission System simultaneously
Important running state information, based on vibration noise analysis can realize helicopter malfunction prediction, it is ensured that helicopter power train
The safe operation of system.
Helicopter Transmission System mechanical vibration and noise are closely connected and intercouple impact, on the one hand may impact systemic
Can, cause system parts premature fatigue, even lost efficacy；On the other hand drive system also goes straight up to cabin internal vibration noise
Main source, directly has a negative impact to helicopter crew；Helicopter Transmission System vibration noise performance study is to guarantee
Systematic function, improves security of system and reliability and occupant comfort aspect important in inhibiting, therefore builds a kind of straight
Rise the needs that machine driveline vibrations noise development test platform is scientific development；And the examination of existing research Helicopter Transmission System
Test platform cost sufficiently expensive, and colleges and universities and the test platform of the typically no this costliness of academy, thus hinder helicopter
The research of development.
Summary of the invention
For above-mentioned situation, it is an object of the invention to provide a kind of Helicopter Transmission System Vibration Noise Study test platform,
It uses rationally setting systems such as drive system trifilar suspension location and the driving of double frequency conversion motor, main rotor and tail transmission loadings
Put and existing Helicopter Transmission System test platform and practical structures difference can be overcome big and expensive defect, and overall knot
Structure is scientific and reasonable, simple installation, low cost of manufacture, can effectively simulate the loading of different flight state, convenient research helicopter
The dynamics and vibration noiseproof feature of drive system, the improvement for Helicopter Transmission System provides scientific basis, thus realizes passing
Dynamic security of system Effec-tive Function.
For realizing above-mentioned task, a kind of Helicopter Transmission System Vibration Noise Study test platform, it includes drive system, drives
Dynamic system, safety guard net, main rotor loading system, tail transmission loading system, TT&C system and firm banking；Described drive
Dynamic system is connected with drive system through gear engagement and is arranged on firm banking, and this drive system hangs through three-point support hanger
It is installed on firm banking；Described main rotor loading system and tail transmission loading system respectively through main rotor shaft and tail transmission shaft with
Drive system connect, described safety guard net be arranged on firm banking for protect drive system, main rotor loading system and
Tail transmission loading system.
For realizing present configuration, effect optimization, its further step: described drive system include one-level cylindric spiral gear,
Deuterostrophies bevel gear and three grades of pinion gear systems.
Described drive system includes two driving motors and sliding bottom, and described two driving motors connect fixing through sliding bottom
Base.
Two driving motors of described drive system converter of connecting respectively is then parallelly connected with same branch road.
Described three-point support hanger includes supporting seat and hound, and this support seat is three and by 90 ° of radial distribution of difference angle
In same level.
Described three-point support hanger symmetrical two support seats carry out vertical and longitudinal register respectively to drive system, another
Support seat and drive system is carried out located lateral.
Described main rotor loading system includes main rotor shaft, the second shaft coupling and main rotor loading disc, this main rotor loading disc warp
Second shaft coupling is connected with main rotor shaft.
Described tail transmission loading system includes tail transmission shaft, tail loading disc and the first shaft coupling, and this tail loading disc is through the first shaft coupling
Device is connected with tail transmission shaft.
Described TT&C system includes detection and control terminal and noise transducer, displacement transducer and acceleration transducer, described acceleration
Sensor is respectively arranged on three support seats of three-point support hanger and on the outer wall of drive system, and displacement transducer is arranged
On the power shaft and output shaft of drive system, noise transducer is arranged on drive system side.
Four acceleration transducers, the power shaft of described drive system and output shaft it is uniformly distributed on the outer wall of described drive system
On be respectively provided with two displacement transducers radially becoming 90 degree.
The present invention provides a kind of Helicopter Transmission System Vibration Noise Study test platform, it include drive system, drive system,
Safety guard net, main rotor loading system, tail transmission loading system, TT&C system and firm banking；Described drive system with
Drive system connects through gear engagement and is arranged on firm banking, and this drive system hangs through three-point support hanger and is installed on admittedly
Determine on base；Described main rotor loading system and tail transmission loading system are respectively through main rotor shaft and tail transmission shaft and drive system
Connecting, described safety guard net is arranged on firm banking for protecting drive system, main rotor loading system and tail transmission to add
The technical scheme of loading system；It uses drive system trifilar suspension location and the driving of double frequency conversion motor, main rotor and tail transmission
Existing Helicopter Transmission System test platform and practical structures difference can be overcome big for the rationally setting of the systems such as loading and price is held high
The defect of your costliness, for analyzing the dynamics and vibration noise of Helicopter Transmission System, it is ensured that drive system safe and highly efficient operation
Thering is provided scientific basis, and overall structure is scientific and reasonable, simple installation, low cost of manufacture, have significant economic benefit and
Social benefit, wide market, it is simple to promote the use of.
The present invention produced beneficial effect compared to existing technology:
I, the present invention uses and arranges main rotor loading system and tail transmission loading system, it is simple to helicopter simulating difference flight appearance
The stressing conditions of state lower transmission system, makes test data more conform to truth, for guaranteeing drive system safe and highly efficient operation
Scientific basis is provided；
II, the present invention uses and arranges main rotor loading system and tail transmission loading system, it is simple to more fully carry out helicopter biography
The dynamic failure evolution mechanism of system, signal characteristic extracting methods, Incipient Fault Diagnosis method, health maintenance method are ground with strategy
Study carefully；
III, the present invention uses and arranges displacement transducer and noise transducer drive system critical component is carried out vibration noise survey
Examination, the Research on Dynamic Characteristic for Helicopter Transmission System provides good experiment condition；
IV, the present invention uses the high-performance vector frequency converter arranging two VC5000 to control to drive rotating speed and the power of motor,
It is conveniently used for studying the new power shunt type gear transmission system of gear " point torsion car "；
V, the present invention uses and arranges main rotor loading system and tail transmission loading system, convenient research Helicopter Transmission System
Noise and vibration characteristic and the transmission power research of main deceleration two-output impulse generator；
VI, the drive system of the present invention preferably employs the most retired Helicopter Transmission System, it is simple to ensure structural integrity and
Precision, reduces laboratory table cost.
The present invention is widely used in Noise and Vibration Control and the running status evaluation studies of Helicopter Transmission System.
Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
Fig. 1 is the horizontal layout schematic diagram of the present invention.
Fig. 2 is the structural representation of drive system in the present invention.
Fig. 3 is the integral installation structural representation of the present invention.
Fig. 4 is the distribution schematic diagram of sensor in the present invention.
Fig. 5 is the top view of Fig. 4.
Fig. 6 is the process schematic diagram of TT&C system of the present invention.
Fig. 7 is the control circuit figure of drive system of the present invention.
In figure: 1-firm banking, 2-three-point support hanger, 3-tail transmission shaft, 4-tail loading disc, 5-the first shaft coupling, 6-
Drive system, 7-main rotor shaft, 8-main rotor loading disc, 9-the second shaft coupling, 10-drives motor, 11-power shaft, 12-
Sliding bottom, 13-safety guard net, 14-acceleration transducer, 15-displacement transducer.
Detailed description of the invention
Referring to the drawings, the present invention is achieved in that a kind of Helicopter Transmission System Vibration Noise Study test platform, its bag
Include drive system, drive system, safety guard net 13, main rotor loading system, tail transmission loading system, TT&C system and
Firm banking 1；Described drive system is connected with drive system and is arranged on firm banking 1, and this drive system is through 3
Hold hanger 2 suspension to be installed on firm banking 1；Described main rotor loading system and tail transmission loading system are respectively through main rotor
Axle 7 and tail transmission shaft 3 are connected with drive system, and described safety guard net 13 is arranged on firm banking 1 for protecting biography
Dynamic system, main rotor loading system and tail transmission loading system.
As in figure 2 it is shown, the transmission principle of the present invention is: on the one hand the driving motor 10 of drive system exports power through one-level
Cylindric spiral gear Z1 and Z2 car, deuterostrophies bevel gear Z3 and Z4 commutation and three grades of pinion gear system Z5-Z10 will
Power passes to main rotor shaft 7, and drives main rotor loading disc 8 to rotate through the second shaft coupling 9；On the other hand drive system
Driving motor 10 export power through one-level cylindric spiral gear Z1 and Z2 car, deuterostrophies bevel gear Z3 and Z4 commutation,
And three grades of spiral bevel gear Z11 impart power to tail transmission shaft 3, and tail loading disc 4 is driven to rotate through the first shaft coupling 5；
The power transmission point two ways of described three grades of pinion gear system Z5-Z10: 1. gear Z5 output power is through differential planet gear
Z6 is directly passed to the ring gear Z10 fixed with planet carrier；2. gear Z5 output power is through differential planet gear Z6, interior
Gear ring Z7 and external toothing Z passes to fixed gear Z9, finally power is passed to the ring gear Z10 being connected with main rotor shaft 7；
Described drive system preferably employs the most retired Helicopter Transmission System, it is simple to ensure structural integrity and precision, reduces real
Test platform cost.
As it is shown on figure 3, the drive system of the present invention includes two driving motors 10 and sliding bottom 12, described two drivings
Motor 10 is connected on firm banking 1 through sliding bottom 12 slidingtype, between using slidingtype easy to connect to gear engagement
Gap adjusts, and ensures that drive train power output is reliable and stable and improves the service life of equipment；Described main rotor loading system bag
Including main rotor shaft the 7, second shaft coupling 9 and main rotor loading disc 8, this main rotor loading disc 8 is through the second shaft coupling 9 and master
Rotor shaft 7 connects；Described tail transmission loading system includes tail transmission shaft 3, tail loading disc 4 and the first shaft coupling 5, this tail
Loading disc 4 is connected with tail transmission shaft 3 through the first shaft coupling 5.
As shown in Figure 4, the acceleration transducer 14 of the present invention is respectively arranged on three support seats of three-point support hanger 2
And on the outer wall of drive system 6, the outer wall of this drive system 6 is uniformly distributed four acceleration transducers 14, these four
Acceleration transducer 14 is perfectly even distributed on the outer wall that the sun gear ring gear of drive system 6 is corresponding；Displacement transducer
On 15 power shafts 11 being arranged at drive system 6 and output shaft, the power shaft 11 of described drive system 6 and output shaft divide
Not arranging two displacement transducers 15 radially becoming 90 degree, this structure arranges and facilitates Real-time Collection signal, and is conducive to test
The circular radial jumping degree of drive system 6 power shaft 11 and output shaft, makes an uproar for analyzing the dynamics and vibration of Helicopter Transmission System
Sound and drive system safe and highly efficient operation provide scientific basis.
As it is shown in figure 5, the three-point support hanger 2 of the present invention includes supporting seat and hound, this support seat is three and by phase
90 ° of radial distribution of declinate degree are in same level；Described three-point support hanger 2 symmetrical two support seats are respectively to biography
Dynamic system 6 carries out vertical and longitudinal register, and another supports seat for drive system 6 is carried out located lateral；This structure can
Guarantee drive system is solid and reliable, and is conducive to ensureing the precision of testing research.
As shown in Figure 6, the TT&C system of the present invention includes sensor and detection and control terminal, and this detection and control terminal includes wave filter, control
System processed and display；Sensor for signals collecting and will be gathered signal filtered device filtering after output give control system
System, control system by processed signal preserve and export to display and show；By experimental data is acquired,
Analyzing and processing, can analyze the practical operation situation understanding Helicopter Transmission System, it is simple to more fully shake drive system
The problem such as dynamic is analyzed, and provides condition for vibration evolution mechanism, vibration control and status monitoring.
As it is shown in fig. 7, the two of drive system of the present invention driving motors 10 are connected respectively, a converter is then parallelly connected with same
Branch road, i.e. on and off switch control to be switched on or switched off, and catalyst KM1 and KM2 controls converter 1 respectively and converter 2 leads to
Electricity or disconnection, this converter 1 and converter 2 also can be simultaneously by Terminal controls, to ensure that two driving motors 10 are adopted
By same power and synchronous working；Circuit control principle is: when the switch that switches on power, and presses A.C. contactor KM1 and connects electricity
Source circuit is 1., it indicates that lamp 1 is bright and converter 1 is energized, and is adjusted converter 1 and just can control respective drive motor 10
Rotating speed or power；Or switch on power switch, press A.C. contactor KM2 and switch on power circuit 2., it indicates that lamp 2
Bright and converter 2 is energized, and is adjusted converter 2 and just can control rotating speed or the power of respective drive motor 10；Or connect
Energising source switch, presses A.C. contactor KM3 and switches on power circuit 3., it indicates that lamp 3 is bright and Frequency Converter Control terminal leads to
Electricity, is adjusted Frequency Converter Control terminal and just can control converter 1 and converter 2 simultaneously, thus control two drivings simultaneously
The rotating speed of motor 10 or power；Described converter preferably employs two VC5000 high-performance vector frequency converters for controlling respectively
Two driving motors 10.
In conjunction with accompanying drawing, embodiments of the invention one: the dynamic characteristic of research Helicopter Transmission System, first start two drivings
Motor 10, then utilizes two high-performance vector frequency converters of VC5000 to control rotating speed and the merit of two driving motors 10 respectively
Rate keeps consistent, through gear engagement transmission power to Helicopter Transmission System 6, by Helicopter Transmission System 6 respectively by power
Pass to main rotor shaft loading disc 8 and tail loading disc 4；Then loading is proceeded by, respectively by main rotor shaft loading disc 8
With tail loading disc 4, Helicopter Transmission System is loaded；The corresponding data of sensor acquisition are utilized during loading,
And input control system after data filtering is processed, finally by display, data are shown；By change load mode or
Change two speed driving motors 10, available many group test data, and these data are passed through network cable transmission to computer
Data acquisition software, by being analyzed the signal gathered, it is possible to analyze the vibration characteristics of Helicopter Transmission System
And research vibration control strategy.
In conjunction with accompanying drawing, the real row two of the present invention: the new power shunting gear drive of research gear " point torsion car "
The vibration characteristics of system, first starts two driving motors 10, then utilizes two high-performance vector frequency converters of VC 5000
The rotating speed controlling two driving motors 10 respectively keeps consistent with power, through gear engagement transmission power to helicopter power train
System 6, is imparted power to main rotor shaft loading disc 8 and tail loading disc 4 respectively by Helicopter Transmission System 6；Then start
Load, by main rotor shaft loading disc 8 and tail loading disc 4, Helicopter Transmission System is loaded respectively；Loading
During utilize the corresponding data of sensor acquisition, and input control system after data filtering is processed, finally by display
Data are shown；Changed different capacity difference or the speed discrepancy of two driving motors 10 by regulation, can get and organize survey more
Examination data, and by these data by network cable transmission to computer data acquiring software, by the signal gathered is contrasted
Analyze, it is possible to the vibration characteristics of the new power shunt type gear transmission system of analysis and research gear " point torsion car ".
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for those skilled in the art
For Yuan, the present invention can have various modifications and variations；All within the spirit and principles in the present invention, any amendment of being made,
Equivalent, improvement etc., should be included within the scope of the present invention.
Claims (10)
1. a Helicopter Transmission System Vibration Noise Study test platform, it is characterised in that include drive system, drive system, safety guard net, main rotor loading system, tail transmission loading system, TT&C system and firm banking；Described drive system is connected with drive system through gear engagement and is arranged on firm banking, and this drive system hangs through three-point support hanger and is installed on firm banking；Described main rotor loading system and tail transmission loading system are connected with drive system through main rotor shaft and tail transmission shaft respectively, and described safety guard net is arranged on firm banking for protecting drive system, main rotor loading system and tail transmission loading system.
A kind of Helicopter Transmission System Vibration Noise Study test platform the most according to claim 1, it is characterised in that described drive system includes one-level cylindric spiral gear, deuterostrophies bevel gear and three grades of pinion gear systems.
A kind of Helicopter Transmission System Vibration Noise Study test platform the most according to claim 1, it is characterised in that described drive system includes that two driving motors and sliding bottom, described two driving motors connect firm banking through sliding bottom.
A kind of Helicopter Transmission System Vibration Noise Study test platform the most according to claim 3, it is characterised in that two driving motors of described drive system converter of connecting respectively is then parallelly connected with same branch road.
A kind of Helicopter Transmission System Vibration Noise Study test platform the most according to claim 1, it is characterised in that described three-point support hanger includes supporting seat and hound, this support seat be three and by 90 ° of radial distribution of difference angle in same level.
A kind of Helicopter Transmission System Vibration Noise Study test platform the most according to claim 5, it is characterized in that described three-point support hanger symmetrical two support seats carry out vertical and longitudinal register respectively to drive system, another supports seat and drive system is carried out located lateral.
A kind of Helicopter Transmission System Vibration Noise Study test platform the most according to claim 1, it is characterized in that described main rotor loading system includes main rotor shaft, the second shaft coupling and main rotor loading disc, this main rotor loading disc is connected with main rotor shaft through the second shaft coupling.
A kind of Helicopter Transmission System Vibration Noise Study test platform the most according to claim 1, it is characterised in that described tail transmission loading system includes tail transmission shaft, tail loading disc and the first shaft coupling, and this tail loading disc is connected with tail transmission shaft through the first shaft coupling.
A kind of Helicopter Transmission System Vibration Noise Study test platform the most according to claim 1, it is characterized in that described TT&C system includes detection and control terminal and noise transducer, displacement transducer and acceleration transducer, described acceleration transducer is respectively arranged on three support seats of three-point support hanger and on the outer wall of drive system, displacement transducer is arranged on power shaft and the output shaft of drive system, and noise transducer is arranged on drive system side.
A kind of Helicopter Transmission System Vibration Noise Study test platform the most according to claim 9, it is characterized in that on the outer wall of described drive system, being uniformly distributed four acceleration transducers, the power shaft of described drive system be respectively provided with two displacement transducers radially becoming 90 degree on output shaft.
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| CN201610307788.XA CN106017914B (en) | 2016-05-11 | 2016-05-11 | A kind of Helicopter Transmission System Vibration Noise Study test platform |
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| CN201610307788.XA CN106017914B (en) | 2016-05-11 | 2016-05-11 | A kind of Helicopter Transmission System Vibration Noise Study test platform |
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| CN106017914B CN106017914B (en) | 2018-11-16 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428630A (en) * | 2016-12-06 | 2017-02-22 | 北京航空航天大学 | Rotation platform for helicopter rotor anti-icing/de-icing test in ice wind tunnel |
| CN110285942A (en) * | 2019-07-01 | 2019-09-27 | 中国人民解放军陆军装甲兵学院 | The method for measuring planet row vibration |
| CN110901951A (en) * | 2019-11-15 | 2020-03-24 | 哈尔滨飞机工业集团有限责任公司 | Multifunctional tail rotor test system |
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| CN110285942A (en) * | 2019-07-01 | 2019-09-27 | 中国人民解放军陆军装甲兵学院 | The method for measuring planet row vibration |
| CN110901951A (en) * | 2019-11-15 | 2020-03-24 | 哈尔滨飞机工业集团有限责任公司 | Multifunctional tail rotor test system |
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| Publication number | Publication date |
|---|---|
| CN106017914B (en) | 2018-11-16 |
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