CN205593748U - Helicopter transmission system vibration noise comprehensive test platform - Google Patents
Helicopter transmission system vibration noise comprehensive test platform Download PDFInfo
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- CN205593748U CN205593748U CN201620421845.2U CN201620421845U CN205593748U CN 205593748 U CN205593748 U CN 205593748U CN 201620421845 U CN201620421845 U CN 201620421845U CN 205593748 U CN205593748 U CN 205593748U
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- loading
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Abstract
Helicopter transmission system vibration noise comprehensive test platform, it includes transmission system, actuating system, safety protection net, main rotor loading system, tail transmission loading system, observing and controlling system and unable adjustment base, the actuating system is connected and is set up on unable adjustment base through gear engagement with transmission system, and this transmission system hangs through 3 supporting stores pylons and installs on unable adjustment base, main rotor loading system and tail transmission loading system are connected with transmission system through main rotor shaft and tail transmission shaft respectively, and safety protection net sets up and be used for protecting transmission system, main rotor loading system and tail transmission loading system on unable adjustment base, it adopts and can overcome the current dear defect of test platform to the reasonable setting of transmission system three point suspension location and each system, for analysis helicopter transmission system's dynamics and vibration noise, ensures that transmission system safe and high -efficiency operation provides the scientific basis, vibration noise control and running state that it extensively was applicable to transmission system evaluate research.
Description
Technical field
This utility model relates to Helicopter Technology field, particularly relates to Helicopter Transmission System vibration noise multi-function test stand.
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 helicopter
Driveline vibrations noise synthesis testing stand is the needs of scientific development；And the test platform of existing research Helicopter Transmission System
Cost is sufficiently expensive, and colleges and universities and the test platform of the typically no this costliness of academy, thus hinders Helicopter Development
Research.
Summary of the invention
For above-mentioned situation, the purpose of this utility model is to provide Helicopter Transmission System vibration noise multi-function test stand, it
Use the reasonable setting to systems such as drive system trifilar suspension location and the driving of double frequency conversion motor, main rotor and tail transmission loadings
Existing Helicopter Transmission System test platform and practical structures difference can be overcome big and expensive defect, and overall structure
Scientific and reasonable, simple installation, low cost of manufacture, can effectively simulate the loading of different flight state, convenient research helicopter passes
The dynamics and vibration noiseproof feature of dynamic system, the improvement for Helicopter Transmission System provides scientific basis, thus realizes transmission
Security of system Effec-tive Function.
For realizing above-mentioned task, Helicopter Transmission System vibration noise multi-function test stand, 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
Loading system.
For realizing this utility model structure, effect optimization, its further step: described drive system includes that one-level cylinder is oblique
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.
This utility model provide Helicopter Transmission System vibration noise multi-function test stand, 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.
This utility model produced beneficial effect compared to existing technology:
I, this utility model uses and arranges main rotor loading system and tail transmission loading system, it is simple to helicopter simulating difference flies
The stressing conditions of row attitude lower transmission system, makes test data more conform to truth, for guaranteeing that drive system is safe and efficient
Run and scientific basis is provided；
II, this utility model uses and arranges main rotor loading system and tail transmission loading system, it is simple to more fully go straight up to
The failure evolution mechanism of machine drive system, signal characteristic extracting methods, Incipient Fault Diagnosis method, health maintenance method and plan
Slightly study；
III, this utility model uses and arranges displacement transducer and noise transducer drive system critical component is carried out vibration noise
Test, the Research on Dynamic Characteristic for Helicopter Transmission System provides good experiment condition；
IV, this utility model uses the high-performance vector frequency converter arranging two VC5000 to control to drive rotating speed and the merit of motor
Rate, is conveniently used for studying the new power shunt type gear transmission system of gear " point torsion car "；
V, this utility model uses and arranges main rotor loading system and tail transmission loading system, convenient research helicopter power train
The noise and vibration characteristic of system and the transmission power research of main deceleration two-output impulse generator；
VI, drive system of the present utility model preferably employs the most retired Helicopter Transmission System, it is simple to ensure that structure is consistent
Property and precision, reduce laboratory table cost.
This utility model is widely used in Noise and Vibration Control and the running status evaluation studies of Helicopter Transmission System.
Below with reference to figure, this utility model is described in further detail.
Accompanying drawing explanation
Fig. 1 is horizontal layout schematic diagram of the present utility model.
Fig. 2 is the structural representation of drive system in this utility model.
Fig. 3 is integral installation structural representation of the present utility model.
Fig. 4 is the distribution schematic diagram of sensor in this utility model.
Fig. 5 is the top view of Fig. 4.
Fig. 6 is the process schematic diagram of this utility model TT&C system.
Fig. 7 is the control circuit figure of this utility model drive system.
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, this utility model is achieved in that Helicopter Transmission System vibration noise multi-function test stand, and it includes
Drive system, drive system, safety guard net 13, main rotor loading system, tail transmission loading system, TT&C system and solid
Determine base 1；Described drive system is connected with drive system and is arranged on firm banking 1, and this drive system is through three-point support
Hanger 2 hangs and is installed on firm banking 1；Described main rotor loading system and tail transmission loading system are respectively through main rotor shaft
7 and tail transmission shaft 3 be connected with drive system, described safety guard net 13 is arranged on firm banking 1 for protecting transmission
System, main rotor loading system and tail transmission loading system.
As in figure 2 it is shown, transmission principle of the present utility model is: on the one hand the driving motor 10 of drive system exports power warp
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
Impart power to main rotor shaft 7, and drive main rotor loading disc 8 to rotate through the second shaft coupling 9；On the other hand drivetrain
The driving motor 10 of system exports power and changes through one-level cylindric spiral gear Z1 and Z2 car, deuterostrophies bevel gear Z3 and Z4
To and three grades of spiral bevel gear Z11 impart power to tail transmission shaft 3, and drive tail loading disc 4 through the first shaft coupling 5
Rotate；The power transmission point two ways of described three grades of pinion gear system Z5-Z10: 1. gear Z5 output power is through differential row
Star 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, ring gear Z7 and external toothing Z pass to fixed gear Z9, in finally power being passed to be connected with main rotor shaft 7
Gear ring Z10；Described drive system preferably employs the most retired Helicopter Transmission System, it is simple to ensure structural integrity and essence
Degree, reduces laboratory table cost.
As it is shown on figure 3, drive system of the present utility model includes two driving motors 10 and sliding bottom 12, described two
Drive motor 10 to be connected on firm banking 1 through sliding bottom 12 slidingtype, use slidingtype easy to connect to gear engagement
Gap adjust, ensure that drive train power output is reliable and stable and improves service life of equipment；Described main rotor loads system
System includes main rotor shaft the 7, second shaft coupling 9 and main rotor loading disc 8, and this main rotor loading disc 8 is through the second shaft coupling 9
It is connected with main rotor shaft 7；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, acceleration transducer 14 of the present utility model is respectively arranged at three supports of three-point support hanger 2
On seat and on the outer wall of drive system 6, the outer wall of this drive system 6 is uniformly distributed four acceleration transducers 14, should
On the outer wall that sun gear ring gear that four acceleration transducers 14 are perfectly even distributed in drive system 6 is corresponding；Displacement passes
Sensor 15 is arranged on power shaft 11 and the output shaft of drive system 6, the power shaft 11 of described drive system 6 and output
Being respectively provided with two displacement transducers 15 radially becoming 90 degree on axle, this structure arranges and facilitates Real-time Collection signal, and favorably
In test drive system 6 power shaft 11 and circular radial the jumpings degree of output shaft, for analyze Helicopter Transmission System kinetics and
Vibration noise and drive system safe and highly efficient operation provide scientific basis.
As it is shown in figure 5, three-point support hanger 2 of the present utility model includes supporting seat and hound, this support seat be three and
By 90 ° of radial distribution of difference angle in same level；Two support seats difference that described three-point support hanger 2 is symmetrical
Drive system 6 carries out vertical and longitudinal register, and another supports seat for drive system 6 is carried out located lateral；This knot
Structure can ensure that drive system is solid and reliable, and is conducive to ensureing the precision of testing research.
As shown in Figure 6, TT&C system of the present utility model includes sensor and detection and control terminal, this detection and control terminal include wave filter,
Control system 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 this utility model drive system 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 and converter respectively
2 energisings or disconnection, this converter 1 and converter 2 also can be simultaneously by Terminal controls, to ensure two driving motors 10
Use with power and synchronous working；Circuit control principle is: when the switch that switches on power, and presses A.C. contactor KM1 and connects
Power 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, embodiment one of the present utility model: the dynamic characteristic of research Helicopter Transmission System, first start two
Drive motor 10, then utilize two high-performance vector frequency converters of VC5000 to control the rotating speed of two driving motors 10 respectively
Keep consistent with power, through gear engagement transmission power to Helicopter Transmission System 6, Helicopter Transmission System 6 respectively will
Power passes to main rotor shaft loading disc 8 and tail loading disc 4；Then proceed by loading, loaded by main rotor shaft respectively
Helicopter Transmission System is loaded by dish 8 and tail loading disc 4；Sensor acquisition is utilized to count accordingly during loading
According to, and input control system after data filtering is processed, finally by display, data are shown；By changing loading side
Formula or change two drive the speed of motors 10, available many groups to test data, and these data are passed through network cable transmission to meter
Calculation machine data acquisition software, by being analyzed the signal gathered, it is possible to analyze the vibration of Helicopter Transmission System
Characteristic and research vibration control strategy.
In conjunction with accompanying drawing, real row two of the present utility model: the new power shunting gear of research gear " point torsion car "
The vibration characteristics of drive system, first starts two driving motors 10, then utilizes two high performance vector of VC 5000 to become
Frequently device controls the rotating speed of two driving motors 10 respectively and keeps consistent with power, through gear engagement transmission power to helicopter biography
Dynamic system 6, is imparted power to main rotor shaft loading disc 8 and tail loading disc 4 respectively by Helicopter Transmission System 6；Then
Proceed by loading, by main rotor shaft loading disc 8 and tail loading disc 4, Helicopter Transmission System is loaded respectively；?
Utilize the corresponding data of sensor acquisition during loading, and input control system after data filtering is processed, finally by showing
Show that data are shown by device；Different capacity difference or the speed discrepancy of two driving motors 10 is changed by regulation, available many
Group test data, and by these data by network cable transmission to computer data acquiring software, by the signal gathered is carried out
Relative analysis, it is possible to the vibration of the new power shunt type gear transmission system of analysis and research gear " point torsion car " is special
Property.
The foregoing is only preferred embodiment of the present utility model, be not limited to this utility model, for this area
Technical staff for, this utility model can have various modifications and variations；It is all within spirit of the present utility model and principle,
Any modification, equivalent substitution and improvement etc. made, within should be included in protection domain of the present utility model.
Claims (10)
1. Helicopter Transmission System vibration noise multi-function test stand, 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.
Helicopter Transmission System vibration noise multi-function test stand 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.
Helicopter Transmission System vibration noise multi-function test stand 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.
Helicopter Transmission System vibration noise multi-function test stand 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.
Helicopter Transmission System vibration noise multi-function test stand 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.
Helicopter Transmission System vibration noise multi-function test stand 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.
Helicopter Transmission System vibration noise multi-function test stand 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.
Helicopter Transmission System vibration noise multi-function test stand 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.
Helicopter Transmission System vibration noise multi-function test stand 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.
Helicopter Transmission System vibration noise multi-function test stand 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620421845.2U CN205593748U (en) | 2016-05-11 | 2016-05-11 | Helicopter transmission system vibration noise comprehensive test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620421845.2U CN205593748U (en) | 2016-05-11 | 2016-05-11 | Helicopter transmission system vibration noise comprehensive test platform |
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| Publication Number | Publication Date |
|---|---|
| CN205593748U true CN205593748U (en) | 2016-09-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620421845.2U Expired - Fee Related CN205593748U (en) | 2016-05-11 | 2016-05-11 | Helicopter transmission system vibration noise comprehensive test platform |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017914A (en) * | 2016-05-11 | 2016-10-12 | 湖南科技大学 | Research and testing platform for vibration noises of helicopter transmission system |
| CN108896302A (en) * | 2018-06-15 | 2018-11-27 | 西安工业大学 | A kind of warship face gear retarder closing noise detection apparatus |
| CN111532450A (en) * | 2020-04-30 | 2020-08-14 | 中国航发哈尔滨东安发动机有限公司 | Mechanical closed transmission device for main reducing test bed of coaxial double-propeller helicopter |
| CN111855201A (en) * | 2020-09-01 | 2020-10-30 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
-
2016
- 2016-05-11 CN CN201620421845.2U patent/CN205593748U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017914A (en) * | 2016-05-11 | 2016-10-12 | 湖南科技大学 | Research and testing platform for vibration noises of helicopter transmission system |
| 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 |
| CN108896302A (en) * | 2018-06-15 | 2018-11-27 | 西安工业大学 | A kind of warship face gear retarder closing noise detection apparatus |
| CN111532450A (en) * | 2020-04-30 | 2020-08-14 | 中国航发哈尔滨东安发动机有限公司 | Mechanical closed transmission device for main reducing test bed of coaxial double-propeller helicopter |
| CN111532450B (en) * | 2020-04-30 | 2023-09-15 | 中国航发哈尔滨东安发动机有限公司 | Mechanical closed transmission device for main test-reducing platform of coaxial double-oar helicopter |
| CN111855201A (en) * | 2020-09-01 | 2020-10-30 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
| CN111855201B (en) * | 2020-09-01 | 2022-03-22 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
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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: 20160921 Termination date: 20190511 |
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| CF01 | Termination of patent right due to non-payment of annual fee |