CN207737516U - A kind of helicopter tail rotor swing seal tightness test platform - Google Patents
A kind of helicopter tail rotor swing seal tightness test platform Download PDFInfo
- Publication number
- CN207737516U CN207737516U CN201721640443.2U CN201721640443U CN207737516U CN 207737516 U CN207737516 U CN 207737516U CN 201721640443 U CN201721640443 U CN 201721640443U CN 207737516 U CN207737516 U CN 207737516U
- Authority
- CN
- China
- Prior art keywords
- main shaft
- pressure gauge
- test platform
- tail rotor
- swings
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model provides a kind of helicopter tail rotor swing seal tightness test platform, including stage body, main shaft, eccentric wheel, variable-frequency motor, control cabinet and sealing test device；Main shaft is vertically fixedly installed on stage body, and main shaft is equipped with pendulous device, and tail-rotor is detachably set on pendulous device；Pendulous device is sequentially connected by connecting rod and eccentric wheel, and eccentric wheel is sequentially connected with variable-frequency motor；Control cabinet is electrically connected with variable-frequency motor, and control variable-frequency motor drives pendulous device to do and up and down reciprocatingly runs；By using above technical scheme, swing test can be carried out with tail-rotor hub sleeve sealing, test leakproofness at its swing, it is ensured that Flight Safety；Scenario-frame provided by the utility model is simple, easily operated, improves detection efficiency and accuracy of detection；It is promoted suitable for mass detection.
Description
Technical field
The utility model belongs to helicopter tail rotor technical field of measurement and test, and in particular to a kind of helicopter tail rotor swing leakproofness
Testing stand.
Background technology
After existing helicopter tail rotor hub manufacture or repair, need for sealing detection at its tail-rotor swing, if without
Overtesting, if there is oil leakage phenomenon in flight course, will seriously affect aircraft flight peace by with the presence of oil leak hidden danger at sealing
Entirely；Experiment needs the amplitude of fluctuation by pressing technology requirement（±30°）, hunting frequency（60 times/min）, duration of oscillation
（30min）Carry out swing test, it is ensured that sealing performance is intact；It is existing not specifically for the test equipment of tail-rotor hub, cause
Testing efficiency is extremely low, and safety detection is not accurate enough.
Based on technical problem present in the test of above-mentioned helicopter tail rotor, there has been no relevant solutions；Therefore urgent
It needs to seek effective scheme to solve the above problems.
Invention content
The purpose of this utility model be in view of the above technology present in shortcoming, propose that a kind of helicopter tail rotor is swung
Seal tightness test platform carries out swing leakage test, it is ensured that airplane tail after the repair of helicopter tail rotor hub to tail-rotor hub axle set
Propeller hub is working properly.
The utility model provides a kind of helicopter tail rotor swing seal tightness test platform, including stage body, main shaft, eccentric wheel, change
Frequency motor, control cabinet and sealing test device；Main shaft is vertically fixedly installed on stage body, and main shaft is equipped with to swing and fill
It sets, tail-rotor is detachably set on pendulous device；Pendulous device is sequentially connected by connecting rod and eccentric wheel, eccentric wheel and variable-frequency electric
Machine is sequentially connected；Frequency converter is equipped in control cabinet, frequency converter is electrically connected with variable-frequency motor, and control variable-frequency motor, which drives, swings dress
It sets to do and up and down reciprocatingly run.
Further, pendulous device includes five fork bearings and five fork guide sleeves；Five fork bearings are sheathed on main shaft；Five forks are led
It is placed on main shaft, and positioned at five fork bearing upper ends；Five fork bearings are sequentially connected by connecting rod and eccentric wheel；Five fork bearings and
Five fork guide sleeves are connected by guide rod.
Further, pitch-change-link there are five being set on five fork bearings；It is opposite with pitch-change-link there are five being set on five fork guide sleeves
The lock box answered；Pitch-change-link and lock box interaction, to fix tail-rotor.
Further, pitch-change-link can be rotated upwardly and downwardly by hexagonal cylindrical head screw and is set on five fork bearings, and lock box is logical
It crosses hexagonal cylindrical head screw and can rotate upwardly and downwardly and be set on five fork guide sleeves.
Further, sealing test device includes fuel tank, hand pump, pressure gauge and multiple interfaces arranged side by side；
Fuel tank is connect with hand pump, and hand pump connection is connect with multiple interfaces；Pressure gauge is set between hand pump and the interface.
Further, further include filter and air filter；Air filter is set on fuel tank；Filter be set to hand pump and
Between interface.
Further, further include multiple hand-operated valves；Multiple hand-operated valves are respectively arranged at the branch road of multiple interfaces.
Further, pressure gauge includes first pressure gauge and second pressure gauge；First pressure gauge and second pressure gauge are side by side
It is set between hand pump and interface；Second pressure gauge connection branch road is additionally provided with hand-operated valve；First pressure gauge test scope is 0
To 1MPa；Second pressure gauge test scope is 0 to 0.16MPa.
Further, further include having bottom plate；Bottom plate is fixedly installed on by hexagonal cylindrical head screw on stage body；Main shaft passes through
Hex head screw is fixedly installed on bottom plate.
Further, further include upper tapered sleeve and lower tapered sleeve；Epicone set is set to spindle top, between upper tapered sleeve and main shaft also
Equipped with gasket；Lower tapered sleeve is set between five fork guide sleeves and main shaft；It is lower to have washer between tapered sleeve and main shaft system.
By using above technical scheme, swing test can be carried out with tail-rotor hub sleeve sealing, test at its swing and seal
Property, it is ensured that Flight Safety；Scenario-frame provided by the utility model is simple, easily operated, improves detection efficiency and detection
Precision；It is promoted suitable for mass detection.
Description of the drawings
Utility model will be further described in detail below with reference to the attached drawings and specific embodiments.
Below with reference to attached drawing, the utility model is described in further detail：
Fig. 1 is that a kind of helicopter tail rotor of the utility model swings seal tightness test platform stereogram；
Fig. 2 is that a kind of helicopter tail rotor of the utility model swings seal tightness test platform front view；
Fig. 3 is the utility model sealing test device schematic diagram.
In figure：1, stage body；2, bottom plate；3, main shaft；4, five fork bearing；6, upper tapered sleeve；7, lower tapered sleeve；9, bearing；10, even
Bar；11, needle bearing；12, guide rod；13, eccentric wheel；17, nut；18, five fork guide sleeve；19, pitch-change-link；20, lock box；
21, hexagonal cylindrical head screw；22, hex head screw；23, hex head screw；25, hex nut；27, hexagonal cylindrical head screw；
30, hexagonal cylindrical head screw；31, hexagonal cylindrical head screw；32, control cabinet；33, variable-frequency motor.
Specific implementation mode
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The utility model will be described in detail below with reference to the accompanying drawings and embodiments.
As shown in Figure 1 to Figure 3, the utility model provides a kind of helicopter tail rotor swing seal tightness test platform, including stage body
1, main shaft 3, eccentric wheel 13, variable-frequency motor 33, control cabinet 32 and sealing test device；Main shaft 3 is vertically fixedly installed
In on stage body 1, main shaft 3 is equipped with pendulous device, and tail-rotor is detachably set on pendulous device；To keep swing stable, platform
1 bottom of body uses cast；Pendulous device is sequentially connected by connecting rod 10 and eccentric wheel 13, and eccentric wheel 13 is passed with variable-frequency motor 33
Dynamic connection；Frequency converter is equipped in control cabinet 32, frequency converter is electrically connected with variable-frequency motor 33, and control variable-frequency motor 33, which drives, to be swung
Device, which is done, up and down reciprocatingly to be run, and is swung and is used eccentric wheel structure, i.e., variable-frequency motor band movable eccentric wheel rotates, the connecting rod on eccentric wheel
Connection pendulous device drives tail-rotor hub to pump；Variable-frequency motor 33 is by Frequency Converter Control, it is ensured that stable and fast
Degree is continuously adjustable；Using the above scheme, to ensure Flight Safety, pressuring shaft set pendulum is carried out after tail-rotor hub is manufactured or repaired
Dynamic sealing is tested, by the amplitude of fluctuation of pressing technology requirement（±30°）, hunting frequency（80 times/min）, duration of oscillation
（120min）Carry out swing test, it is ensured that sealing performance is intact, eliminates oil leak hidden danger at sealing and exists and leaked in flight course
The generation of oily phenomenon, it is ensured that Flight Safety.
Preferably, in conjunction with said program, as shown in Figure 1 to Figure 2, in the present embodiment, pendulous device includes five fork bearings
4 and five pitch guide sleeve 18；Five fork bearings 4 are sheathed on main shaft 3, and can up and down reciprocatingly be run along main shaft 3；Five fork guide sleeves 18 are placed on
It can be run on main shaft 1 and up and down reciprocatingly along main shaft 3, five fork guide sleeves 18 are located at five 4 upper ends of fork bearing；Five fork bearings 4 pass through connecting rod
10 are sequentially connected with eccentric wheel 13；Five fork bearings 4 and five are pitched guide sleeve 18 and are connected by guide rod 12.
Preferably, in conjunction with said program, as shown in Figure 1 to Figure 2, in the present embodiment, five fork bearings 4 on set there are five become
Away from pull rod 19；Lock box corresponding with pitch-change-link 19 20 there are five being set on five fork guide sleeves 18；20 phase of pitch-change-link 19 and lock box
Interaction, to fix tail-rotor；Further, lock box 20 is square frame structure, and square frame structure passes through hexagonal cylindrical
Head screw is fixed；Square frame structure is that axle sleeve fixes anchor ear quick-release type structure, and axle sleeve is convenient for disassembly and assembly, and lock box 20, which is equipped with, to be adjusted
Handle is saved, can be adjusted simultaneously to clamping tail-rotor hub.
Preferably, in conjunction with said program, as shown in Figure 1 to Figure 2, in the present embodiment, in the present embodiment, pitch-change-link 19
It can be rotated upwardly and downwardly and be set on five fork bearings 4 by hexagonal cylindrical head screw 27, lock box 20 can by hexagonal cylindrical head screw 30
It rotates upwardly and downwardly and is set on five fork guide sleeves 18.
Preferably, in conjunction with said program, as shown in figure 3, in the present embodiment, sealing test device includes fuel tank A, hand
Pump M, pressure gauge and multiple interfaces arranged side by side；Further, interface includes six（D1、D2、D3、D4、D5、D6）,
In five interfaces correspond to five fork guide sleeves 18 and five respectively and pitch bearings 4, remain next interface for spare；Fuel tank A connects with hand pump M
It connects, hand pump M connections are connect with multiple interfaces；Pressure gauge is set between hand pump M and interface；When test, interface is fixed
It is oil-filled by hand pump in the position of tail-rotor hub axle set, the indicating value variation of pressure gauge is observed, to judge to seal situation.
Preferably, further include filter G and air filter KQ as shown in figure 3, in the present embodiment in conjunction with said program；Air filter
Device KQ is set on fuel tank A, for filtering sundries；Filter G is set between hand pump M and interface, for filtering sundries.
Preferably, further include multiple hand-operated valves as shown in figure 3, in the present embodiment in conjunction with said program（K1、K2、K3、
K4、K5、K6）；Multiple hand-operated valves are respectively arranged at the branch road of multiple interfaces, for individually controlling each interface；Further,
Oil extraction branch is additionally provided on the branch road of hand pump and interface, oil extraction branch road is additionally provided with hand-operated valve K8.
Preferably, in conjunction with said program, as shown in figure 3, in the present embodiment, pressure gauge includes first pressure gauge P1 and second
Pressure gauge P2；First pressure gauge P1 and second pressure gauge P2 are arranged side by side between hand pump M and interface；Second pressure gauge P2 connects
It connects branch road and is additionally provided with hand-operated valve K7；First pressure gauge P1 test scopes are 0 to 1MPa；Second pressure gauge P2 test scopes are 0
To 0.16MPa.
Preferably, further include having bottom plate 2 in the present embodiment as shown in Figure 1 to Figure 2 in conjunction with said program；Bottom plate 2 passes through
Hexagonal cylindrical head screw 21 is fixedly installed on stage body 1；Main shaft 3 is fixedly installed on by hex head screw 22 on bottom plate 2.
Preferably, further include upper tapered sleeve 6 and lower tapered sleeve 7 in the present embodiment as shown in Figure 1 to Figure 2 in conjunction with said program；
Upper tapered sleeve 6 is set to 3 top of main shaft, and gasket is additionally provided between upper tapered sleeve 6 and main shaft 3；Lower tapered sleeve 7 is set to five fork guide sleeves, 18 He
Between main shaft 3；Washer is equipped between lower tapered sleeve 7 and main shaft 3.
By using above technical scheme, swing test can be carried out with tail-rotor hub sleeve sealing, test at its swing and seal
Property, it is ensured that Flight Safety；Scenario-frame provided by the utility model is simple, easily operated, improves detection efficiency and detection
Precision；It is promoted suitable for mass detection.
The above, the only preferred embodiment of the utility model, not do limit in any form to the utility model
System.Any technical person familiar with the field, in the case where not departing from technical solutions of the utility model ambit, all using above-mentioned
The technology contents make many possible changes and modifications to technical solutions of the utility model, or be revised as equivalent variations etc.
Imitate embodiment.Therefore, every content without departing from technical solutions of the utility model, the technology according to the utility model is to above real
Any change modification, equivalent variations and modification that example is made are applied, the protection domain of the technical program is belonged to.
Claims (10)
1. a kind of helicopter tail rotor swings seal tightness test platform, which is characterized in that including stage body, main shaft, eccentric wheel, variable-frequency electric
Machine, control cabinet and sealing test device；The main shaft is vertically fixedly installed on the stage body, is set on the main shaft
There are pendulous device, the tail-rotor to be detachably set on the pendulous device；The pendulous device passes through connecting rod and the bias
Wheel is sequentially connected, and the eccentric wheel is sequentially connected with the variable-frequency motor；Frequency converter, the frequency converter are equipped in the control cabinet
It is electrically connected with the variable-frequency motor, controls the variable-frequency motor pendulous device is driven to do and up and down reciprocatingly run.
2. helicopter tail rotor according to claim 1 swings seal tightness test platform, which is characterized in that the pendulous device packet
Five fork bearings and five fork guide sleeves are included；The five forks bearing is sheathed on the main shaft；The five forks guide sleeve is placed on main shaft,
And pitch bearing upper end positioned at described five；The five fork bearing is sequentially connected by the connecting rod and the eccentric wheel；Five fork
Bearing is connected with the five forks guide sleeve by guide rod.
3. helicopter tail rotor according to claim 2 swings seal tightness test platform, which is characterized in that on the five forks bearing
If there are five pitch-change-links；Lock box corresponding with the pitch-change-link there are five being set on the five forks guide sleeve；The displacement is drawn
Bar and lock box interaction, with the fixation tail-rotor.
4. helicopter tail rotor according to claim 3 swings seal tightness test platform, which is characterized in that the pitch-change-link is logical
Cross hexagonal cylindrical head screw can rotate upwardly and downwardly be set to it is described five fork bearing on, the lock box by hexagonal cylindrical head screw can on
Under be rotatably dispose in it is described five fork guide sleeve on.
5. helicopter tail rotor according to claim 1 swings seal tightness test platform, which is characterized in that the sealing test dress
Set includes fuel tank, hand pump, pressure gauge and multiple interfaces arranged side by side；The fuel tank is connect with the hand pump, institute
Hand pump connection is stated to connect with multiple interfaces；The pressure gauge is set between the hand pump and the interface.
6. helicopter tail rotor according to claim 5 swings seal tightness test platform, which is characterized in that further include filter and
Air filter；The air filter is set on the fuel tank；The filter is set between the hand pump and the interface.
7. helicopter tail rotor according to claim 5 swings seal tightness test platform, which is characterized in that further include multiple manual
Valve；Multiple hand-operated valves are respectively arranged at the branch road of multiple interfaces.
8. helicopter tail rotor according to claim 5 swings seal tightness test platform, which is characterized in that the pressure gauge includes
First pressure gauge and second pressure gauge；The first pressure gauge and the second pressure gauge are arranged side by side in the hand pump and institute
It states between interface；The second pressure gauge connection branch road is additionally provided with hand-operated valve；The first pressure gauge test scope be 0 to
1MPa；The second pressure gauge test scope is 0 to 0.16MPa.
9. helicopter tail rotor according to claim 1 swings seal tightness test platform, which is characterized in that further include having bottom plate；
The bottom plate is fixedly installed on by hexagonal cylindrical head screw on the stage body；The main shaft is fixedly installed by hex head screw
In on the bottom plate.
10. helicopter tail rotor according to claim 2 swings seal tightness test platform, which is characterized in that further include upper tapered sleeve
With lower tapered sleeve；The epicone set is set to the spindle top, and gasket is additionally provided between the upper tapered sleeve and the main shaft；It is described
Lower tapered sleeve is set between the five fork guide sleeve and the main shaft；There is washer between the lower tapered sleeve and the main shaft system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721640443.2U CN207737516U (en) | 2017-11-30 | 2017-11-30 | A kind of helicopter tail rotor swing seal tightness test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721640443.2U CN207737516U (en) | 2017-11-30 | 2017-11-30 | A kind of helicopter tail rotor swing seal tightness test platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207737516U true CN207737516U (en) | 2018-08-17 |
Family
ID=63116822
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721640443.2U Active CN207737516U (en) | 2017-11-30 | 2017-11-30 | A kind of helicopter tail rotor swing seal tightness test platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207737516U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110207912A (en) * | 2019-04-30 | 2019-09-06 | 武汉船用机械有限责任公司 | Propeller hub body pump pressure frock |
| CN110641735A (en) * | 2019-09-29 | 2020-01-03 | 中国直升机设计研究所 | Fatigue test loading device for tail rotor hub journal shaft sleeve assembly |
-
2017
- 2017-11-30 CN CN201721640443.2U patent/CN207737516U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110207912A (en) * | 2019-04-30 | 2019-09-06 | 武汉船用机械有限责任公司 | Propeller hub body pump pressure frock |
| CN110641735A (en) * | 2019-09-29 | 2020-01-03 | 中国直升机设计研究所 | Fatigue test loading device for tail rotor hub journal shaft sleeve assembly |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207737516U (en) | A kind of helicopter tail rotor swing seal tightness test platform | |
| CN104596905B (en) | Device and method for measuring permeability of rock in fracturing process | |
| CN202108718U (en) | Oil pump performance testing equipment | |
| CN208872473U (en) | Sebific duct air tightness test platform | |
| CN202305136U (en) | Sealed bearing simulation testing machine | |
| CN104390788B (en) | The method of oil feeding line and control oil feeding line for engine testsand | |
| CN105699011A (en) | Stand test system for simulating automobile tire rotation and internal pressure change | |
| CN203069340U (en) | Carbon tank performance detecting device | |
| CN204630716U (en) | One is " helicopter " screw propeller lift proving installation under water | |
| CN207798354U (en) | A kind of helicopter tail rotor support arm swing test platform | |
| CN205981569U (en) | Motor edge leakage investigation machine | |
| CN2898802Y (en) | Checker of pressure-releasing valve | |
| CN105043673B (en) | A kind of airplane starter rotor seal performance test frock | |
| CN202866796U (en) | Three-phase flow simulator of oil, gas, and water in oil well | |
| CN207020000U (en) | A kind of vacuum pressure experimental rig | |
| CN205953491U (en) | Two pass evacuation gravitional force filling pump device | |
| CN204881989U (en) | Aircraft starter armature sealing performance test fixture | |
| CN205691337U (en) | A kind of wheel set bearing fatigue life and fault detect testing stand | |
| CN204116060U (en) | Train pressurized cylinder test fixture | |
| CN206449348U (en) | Production trunk line is with pressure to change stop valve for pressure gauge device | |
| CN209326886U (en) | A kind of turbocharger turbine shell leak detector | |
| CN209296304U (en) | Valve body Turnover testing equipment | |
| CN106289997A (en) | A kind of pressure test detection device | |
| CN206057359U (en) | A kind of fluid pump battery saving arrangement | |
| CN205826223U (en) | Drag-line leak tightness test device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 315000 Xiyang village, Shiqi street, Haishu District, Ningbo City, Zhejiang Province Patentee after: Star Arrow Technology Co.,Ltd. Address before: Xiyang village, Shiqi street, Haishu District, Ningbo City, Zhejiang Province Patentee before: NINGBO XINGJIAN SPACE MACHINERY Co.,Ltd. |