CN108639379A - A kind of aircraft rotor component test device - Google Patents
A kind of aircraft rotor component test device Download PDFInfo
- Publication number
- CN108639379A CN108639379A CN201810695485.9A CN201810695485A CN108639379A CN 108639379 A CN108639379 A CN 108639379A CN 201810695485 A CN201810695485 A CN 201810695485A CN 108639379 A CN108639379 A CN 108639379A
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- China
- Prior art keywords
- rack
- rotor component
- test device
- aircraft rotor
- component test
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- 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.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 62
- 230000000712 assembly Effects 0.000 claims abstract description 52
- 238000000429 assembly Methods 0.000 claims abstract description 52
- 239000000725 suspension Substances 0.000 claims abstract description 21
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000012956 testing procedure Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a kind of aircraft rotor component test devices, including rack, suspension assembly, slide assemblies and test suite；The suspension assembly is installed in the rack, for fixing aircraft rotor component to be tested and being in perpendicular；The rack is installed on the slide assemblies, and is slided along planned orbit under the driving of slide assemblies；The test suite is installed on the rack or slide assemblies, for testing the rotor assemblies on suspension assembly.The aircraft rotor component test device of the present invention has many advantages, such as that simple in structure, convenient for disassembly and assembly, test is easy.
Description
Technical field
The invention mainly relates to vehicle technology fields, refer in particular to a kind of aircraft rotor component test device.
Background technology
Currently, small aircraft is widely used in every field, various measuring instruments can be carried（Such as camera）It carries out high
Sky detection can be used for high-altitude object and throw, and can also be applied to agricultural, detection, meteorological, hazard forecasting and rescue etc..
With the development of the times, it is more and more diversified cannot to have met people for Fixed Wing AirVehicle and rotor craft
Demand, each aircraft and Aircraft Company are also stepping up to develop new aircraft type with adaptation to market variations.Each is newly developed
Model aircraft before introducing to the market, all need by various tests, including part testing, unit test, system test；Ground
Face test, aerial test, durability test etc..Each testing procedure needs to stand the test, the product being sent in client's hand
It is only safe, reliable qualified products.
Invention content
The technical problem to be solved in the present invention is that：For technical problem of the existing technology, the present invention provides one
Kind aircraft rotor component test device simple in structure, convenient for disassembly and assembly.
In order to solve the above technical problems, technical solution proposed by the present invention is：
A kind of aircraft rotor component test device, including rack, suspension assembly, slide assemblies and test suite；
The suspension assembly is installed in the rack, for fixing aircraft rotor component to be tested and being at perpendicular
In straight plane；
The rack is installed on the slide assemblies, and is slided along planned orbit under the driving of slide assemblies；
The test suite is installed on the rack or slide assemblies, for being surveyed to the rotor assemblies on suspension assembly
Examination.
As a further improvement of the above technical scheme：
The suspension assembly includes the perpendicular guide rail of more cross rails and one or more；More cross rails are fastened in rack, are located at
In perpendicular and it is mutually parallel；One or more perpendicular guide rail is then slidably arranged on cross rail and is mutually parallel；Described erect is led
Sliding is provided with the fastening unit for fastening the rotor assemblies on rail.
It is provided with sliding slot on the perpendicular guide rail；The fastening unit includes the first bolt and the first nut, first spiral shell
One end of bolt is connected with the rotor assemblies, and the other end passes through the sliding slot to be connected with the fastening of the first nut.
The quantity of the cross rail is two, and the quantity of the perpendicular guide rail is three；Distinguish at the both ends of each perpendicular guide rail
It is slidedly arranged on two cross rails.
It is provided with hang part on the cross rail, for being hooked in rack and being fastened on the rack by fastener
On.
The fastener is the second bolt and the second nut.
The slide assemblies include sliding rail and pulley；The pulley is installed on the bottom of rack and is slided in sliding rail.
The test suite includes thrust pickup, is installed on one end of slide assemblies.
The test suite includes vibrating sensor, is sheathed on first bolt.
The rack is the rack of steel sectional material frame structure.
Compared with the prior art, the advantages of the present invention are as follows：
Rotor assemblies, are suspended in rack, then pass through by the aircraft rotor component test device of the present invention by suspension assembly
Slide assemblies drive housing slide, facilitate test suite to carry out real-time testing to the various performance parameters of rotor assemblies, ensure production
The reliability of product；Concrete structure is simple, installs convenient test and is easily achieved.The aircraft rotor module testing dress of the present invention
It sets, suspension assembly is simple in structure, convenient for disassembly and assembly, can be adapted for the rotor assemblies test of different size specification.
Description of the drawings
Fig. 1 is the structural diagram of the present invention.
Fig. 2 is one of the structural schematic diagram of the present invention in specific application.
Fig. 3 is the second structural representation of the present invention in specific application.
Figure label indicates：1, rack；2, suspension assembly；201, cross rail；202, guide rail is erected；203, fastening unit；
2031, the first bolt；2032, the first nut；204, hang part；205, fastener；2051, the second bolt；2052, the second spiral shell
It is female；3, slide assemblies；301, sliding rail；302, pulley；4, test suite；401, vibrating sensor；402, thrust pickup；5, it revolves
Wing component.
Specific implementation mode
Below in conjunction with Figure of description and specific embodiment, the invention will be further described.
As shown in Figure 1 to Figure 3, the aircraft rotor component test device of the present embodiment, for the rotor in aircraft
Component 5（Including rotor and engine etc.）Various performance parameters measure；Specifically include the machine of steel sectional material frame structure
Frame 1, suspension assembly 2, slide assemblies 3 and test suite 4；Suspension assembly 2 is fastened on by bolt and nut in rack 1, for solid
Fixed aircraft rotor component 5 to be tested is simultaneously in perpendicular；Rack 1 is installed on slide assemblies 3, and in cunning
It is slided along planned orbit under the driving of dynamic component 3；Test suite 4 is installed on rack 1 or slide assemblies 3 or rotor assemblies 5
On, for testing the rotor assemblies 5 on suspension assembly 2, specific test includes vibration, power curve, noise, thrust etc.
The test of performance parameter.Rotor assemblies 5, are suspended on by the aircraft rotor component test device of the present invention by suspension assembly 2
In rack 1, then drive rack 1 to slide by slide assemblies 3, facilitate test suite 4 to the various performance parameters of rotor assemblies 5 into
Row real-time testing ensures the reliability of product；Concrete structure is simple, installs convenient test and is easily achieved.
In the present embodiment, suspension assembly 2 includes two cross rails 201 and three perpendicular guide rails 202；Wherein two cross rails
201 are fastened in rack 1, in perpendicular and are mutually parallel；It is both provided with sliding slot on cross rail 201 and perpendicular guide rail 202,
The both ends of each perpendicular guide rail 202 are slidedly arranged on respectively in the sliding slot of cross rail 201, and one end of specially screw rod sequentially passes through perpendicular guide rail
It is connect with nut thread after 202 end and the sliding slot of cross rail 201, by erecting guide rail 202 in cross to the elastic realization of nut
Sliding on guide rail 201 or fastening；It should be noted that not limiting herein the quantity of cross rail 201 and perpendicular guide rail 202
It is fixed；In addition, in other embodiments, two perpendicular guide rails 202, cunning of the cross rail 201 in perpendicular guide rail 202 can also be fixedly installed
It is slided in slot.In the present embodiment, the fastening unit being provided in the sliding slot of guide rail 202 for fastening rotor assemblies 5 is erected
203.Fastening unit 203 includes the first bolt 2031 and the first nut 2032, one end and 5 phase of rotor assemblies of the first bolt 2031
Even, the other end passes through sliding slot to be connected with the fastening of the first nut 2032, to realize the fastening to rotor assemblies 5.In the present embodiment
Suspension assembly 2, different size can be suitable for, different size of rotor assemblies 5 are installed, and convenient for disassembly and assembly and be easy to real
It is existing.
In the present embodiment, hang part 204 is provided on cross rail 201, for being hooked in rack 1 and passing through fastener
205 are fastened in rack 1.Wherein fastener 205 includes the second bolt 2051 and the second nut 2052, passes through the second bolt 2051
Cooperation with the second nut 2052 fastens rotor assemblies 5.
As shown in Figure 1 to Figure 3, in the present embodiment, slide assemblies 3 include sliding rail 301 and pulley 302；Pulley 302 is installed on
The bottom of rack 1, particular number are four, are located at the four corners of rack 1, and can be slided along sliding rail 301, consequently facilitating test group
Part 4 tests its performance parameter in 5 operational process of rotor assemblies.
In the present embodiment, test suite 4 can specifically include vibrating sensor 401, thrust pickup 402, noise sensing
Device etc.；Wherein vibrating sensor 401 can be installed on 5 surface of rotor assemblies, the spiral shell that can also be sheathed in fastening unit 203
On bar, to be measured to the vibration of rotor assemblies 5；Thrust pickup 402 then be located at sliding rail 301 one end, and with rack 1
Pedestal is opposite, is measured convenient for the thrust to rotor assemblies 5；Noise transducer can then be located in rack 1, to rotor assemblies
5 noise is tested.The test device of the present embodiment is in addition to test engine performance parameter（Such as thrust, rotating speed, vibration, work(
Rate-speed curves etc.）It outside, can also be the propeller quantity of testing flying vehicle, wing in the case where engine is constant（It cuts open
Face）, radius, foline angle, area, the influence of the parameters to motor power size such as wing-tip shape；In addition displacement spiral shell can also be tested
The performance curve etc. for revolving paddle, in order to play the maximum function of rotor assemblies 5 in actually manipulating.
In test, sliding rail 301 is fixedly mounted on level ground or construction platform, so that it is had sufficiently stable, sufficient
Bearing capacity, will not move or turn on one's side.It is different according to 5 model of rotor assemblies and hanging position, by each perpendicular guide rail 202 adjust to
Suitable position, and rotor assemblies 5 are fixed, then by suspension assembly 2 and the whole hooking of rotor assemblies 5 and be fixed in rack 1,
Then each sensor is placed, connects data acquisition line and be connected to computer, start rotor assemblies 5, tests the phase of rotor assemblies 5
Close data, such as thrust, vibration, power curve and noise.
The above is only the preferred embodiment of the present invention, protection scope of the present invention is not limited merely to above-described embodiment,
All technical solutions belonged under thinking of the present invention all belong to the scope of protection of the present invention.It should be pointed out that for the art
For those of ordinary skill, several improvements and modifications without departing from the principles of the present invention should be regarded as the protection of the present invention
Range.
Claims (10)
1. a kind of aircraft rotor component test device, which is characterized in that including rack（1）, suspension assembly（2）, slide assemblies
（3）And test suite（4）；
The suspension assembly（2）, it is installed on the rack（1）On, for fixing aircraft rotor component to be tested（5）And make
It is in perpendicular；
The rack（1）, it is installed on the slide assemblies（3）On, and in slide assemblies（3）Driving under along planned orbit slide
It is dynamic；
The test suite（4）, it is installed on the rack（1）Or slide assemblies（3）On, for suspension assembly（2）On rotation
Wing component（5）It is tested.
2. aircraft rotor component test device according to claim 1, which is characterized in that the suspension assembly（2）Packet
Include more cross rails（201）With one or more perpendicular guide rail（202）；More cross rails（201）It is fastened on rack（1）On, it is located at
In perpendicular and it is mutually parallel；One or more perpendicular guide rail（202）Then it is slidably arranged in cross rail（201）It is upper and mutually flat
Row；The perpendicular guide rail（202）Upper sliding is provided with for fastening the rotor assemblies（5）Fastening unit（203）.
3. aircraft rotor component test device according to claim 2, which is characterized in that the perpendicular guide rail（202）On
It is provided with sliding slot；The fastening unit（203）Including the first bolt（2031）With the first nut（2032）, first bolt
（2031）One end and the rotor assemblies（5）It is connected, the other end passes through the sliding slot and the first nut（2032）Fastening is connected.
4. aircraft rotor component test device according to claim 2, which is characterized in that the cross rail（201）'s
Quantity is two, the perpendicular guide rail（202）Quantity be three；Each perpendicular guide rail（202）Both ends be slidedly arranged on two respectively
Cross rail（201）On.
5. aircraft rotor component test device as claimed in any of claims 2 to 4, which is characterized in that described
Cross rail（201）On be provided with hang part（204）, for being hooked on rack（1）It goes up and passes through fastener（205）It is fastened on described
Rack（1）On.
6. aircraft rotor component test device according to claim 5, which is characterized in that the fastener（205）For
Second bolt（2051）With the second nut（2052）.
7. aircraft rotor component test device as claimed in any of claims 1 to 4, which is characterized in that described
Slide assemblies（3）Including sliding rail（301）And pulley（302）；The pulley（302）It is installed on rack（1）Bottom and in sliding rail
（301）Interior sliding.
8. aircraft rotor component test device as claimed in any of claims 1 to 4, which is characterized in that described
Test suite（4）Including thrust pickup（402）, it is installed on slide assemblies（3）One end.
9. aircraft rotor component test device according to claim 3, which is characterized in that the test suite（4）Packet
Include vibrating sensor（401）, it is sheathed on first bolt（2031）On.
10. aircraft rotor component test device as claimed in any of claims 1 to 4, which is characterized in that described
Rack（1）For the rack of steel sectional material frame structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810695485.9A CN108639379A (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft rotor component test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810695485.9A CN108639379A (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft rotor component test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108639379A true CN108639379A (en) | 2018-10-12 |
Family
ID=63749894
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810695485.9A Pending CN108639379A (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft rotor component test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108639379A (en) |
Citations (16)
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|---|---|---|---|---|
| US5693896A (en) * | 1995-03-16 | 1997-12-02 | Eurocopter France | Test rig for rotors of gyrocraft |
| CN202511930U (en) * | 2012-02-23 | 2012-10-31 | 北京理工大学 | Device for measurement of thrust and torque of small-size propeller engine |
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| CN103940627A (en) * | 2014-04-11 | 2014-07-23 | 同济大学 | Bidirectional sliding device suitable for civil engineering space loading test |
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| CN106516160A (en) * | 2016-12-12 | 2017-03-22 | 哈尔滨理工大学 | Remote control testing device for rotor lift force parameters |
| CN206161812U (en) * | 2016-10-21 | 2017-05-10 | 中国民航大学 | Brushless motor and screw performance testing system |
| CN106705930A (en) * | 2017-03-21 | 2017-05-24 | 北方工业大学 | Reconfigurable tool for deformation test of thin-wall curved surface part |
| CN107117332A (en) * | 2017-07-13 | 2017-09-01 | 安徽工程大学 | A kind of test platform of small-sized multi-rotor unmanned aerial vehicle rotor power system |
| CN206601406U (en) * | 2016-11-30 | 2017-10-31 | 中国直升机设计研究所 | A kind of installs fixture for composite material structural member lightning test |
| CN206740391U (en) * | 2017-04-01 | 2017-12-12 | 昆山航理机载设备股份有限公司 | Aerial weapon equipment test bay |
| CN207066636U (en) * | 2017-03-31 | 2018-03-02 | 成都天府新区光启未来技术研究院 | Rotor thrust and force moment testing device |
| CN208360517U (en) * | 2018-06-29 | 2019-01-11 | 长沙市云智航科技有限公司 | A kind of aircraft rotor component test device |
-
2018
- 2018-06-29 CN CN201810695485.9A patent/CN108639379A/en active Pending
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5693896A (en) * | 1995-03-16 | 1997-12-02 | Eurocopter France | Test rig for rotors of gyrocraft |
| CN202511930U (en) * | 2012-02-23 | 2012-10-31 | 北京理工大学 | Device for measurement of thrust and torque of small-size propeller engine |
| CN202676446U (en) * | 2012-07-16 | 2013-01-16 | 芜湖市中兴机械技术开发有限公司 | MTS bench test power head fixing and adjusting device |
| CN103940627A (en) * | 2014-04-11 | 2014-07-23 | 同济大学 | Bidirectional sliding device suitable for civil engineering space loading test |
| CN104960673A (en) * | 2015-06-08 | 2015-10-07 | 上海交通大学 | Multi-functional extensible test platform applicable to biomimetic flapping-wing micro air vehicle |
| CN205898345U (en) * | 2015-12-23 | 2017-01-18 | 湖北三禾智翔无人机有限公司 | Plant protection unmanned aerial vehicle's power detecting system |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| CN106240843A (en) * | 2016-07-26 | 2016-12-21 | 江苏工程职业技术学院 | Many rotor wing unmanned aerial vehicles structured testing device and method based on reducing frame |
| CN206161812U (en) * | 2016-10-21 | 2017-05-10 | 中国民航大学 | Brushless motor and screw performance testing system |
| CN206601406U (en) * | 2016-11-30 | 2017-10-31 | 中国直升机设计研究所 | A kind of installs fixture for composite material structural member lightning test |
| CN106516160A (en) * | 2016-12-12 | 2017-03-22 | 哈尔滨理工大学 | Remote control testing device for rotor lift force parameters |
| CN106705930A (en) * | 2017-03-21 | 2017-05-24 | 北方工业大学 | Reconfigurable tool for deformation test of thin-wall curved surface part |
| CN207066636U (en) * | 2017-03-31 | 2018-03-02 | 成都天府新区光启未来技术研究院 | Rotor thrust and force moment testing device |
| CN206740391U (en) * | 2017-04-01 | 2017-12-12 | 昆山航理机载设备股份有限公司 | Aerial weapon equipment test bay |
| CN107117332A (en) * | 2017-07-13 | 2017-09-01 | 安徽工程大学 | A kind of test platform of small-sized multi-rotor unmanned aerial vehicle rotor power system |
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