CN208360517U - A kind of aircraft rotor component test device - Google Patents
A kind of aircraft rotor component test device Download PDFInfo
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- CN208360517U CN208360517U CN201821017861.0U CN201821017861U CN208360517U CN 208360517 U CN208360517 U CN 208360517U CN 201821017861 U CN201821017861 U CN 201821017861U CN 208360517 U CN208360517 U CN 208360517U
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- rack
- rotor component
- test device
- aircraft rotor
- component test
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Abstract
The utility model 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 under the driving of slide assemblies along planned orbit；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 utility model has many advantages, such as that structure is simple, convenient for disassembly and assembly, test is easy.
Description
Technical field
The utility model relates generally to vehicle technology field, refers in particular to a kind of aircraft rotor component test device.
Background technique
Currently, small aircraft is widely used in every field, various measuring instruments (such as camera) can be carried and carry out height
Sky detection can be used for the throwing of high-altitude object, 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 to be no longer satisfied 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.Every kind 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.
Utility model content
The technical problems to be solved in the utility model is that for technical problem of the existing technology, this is practical new
Type provides the aircraft rotor component test device that a kind of structure is simple, convenient for disassembly and assembly.
In order to solve the above technical problems, the utility model proposes technical solution are as follows:
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 making at its
In in perpendicular；
The rack is installed on the slide assemblies, and is slided under the driving of slide assemblies along planned orbit；
The test suite is installed on the rack or slide assemblies, for the rotor assemblies on suspension assembly into
Row test.
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 fasten on the rack,
In perpendicular and it is parallel to each other；One or more perpendicular guide rail is then slidably arranged on cross rail and is parallel to each other；It is described
Sliding is provided with the fastening unit for fastening the rotor assemblies on perpendicular guide rail.
Sliding slot is provided 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 and is 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, is fastened on the rack on the rack and by fastener for hooking
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 slides 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 utility model are:
Rotor assemblies are suspended on rack by suspension assembly by the aircraft rotor component test device of the utility model
On, then by slide assemblies driving housing slide, test suite is facilitated to survey the various performance parameters of rotor assemblies in real time
Examination, ensures the reliability of product；Specific structure is simple, installs convenient test and is easily achieved.The aircraft of the utility model revolves
Wing component test device, suspension assembly structure is simple, convenient for disassembly and assembly, and the rotor assemblies that can be adapted for different size specification are surveyed
Examination.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model.
Fig. 2 is one of the structural schematic diagram of the utility model in specific application.
Fig. 3 is the second structural representation of the utility model 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 embodiment
The utility model is further described below in conjunction with Figure of description and specific embodiment.
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(includes 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 in rack 1 by bolt and nut, 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 under the driving of dynamic component 3 along planned orbit；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.The aircraft rotor component test device of the utility model is hanged rotor assemblies 5 by suspension assembly 2
It hangs in rack 1, then drives rack 1 to slide by slide assemblies 3, test suite 4 is facilitated to join the properties of rotor assemblies 5
Number carries out real-time testing, ensures the reliability of product；Specific 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 parallel to each other；It is 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 after 202 end and the sliding slot of cross rail 201 with nut thread, guide rail 202 is erected in cross by the elastic realization to nut
Sliding or fastening on guide rail 201；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 and is 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, positioned 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, measured with the vibration to rotor assemblies 5；Thrust pickup 402 then be located at sliding rail 301 one end, and with rack 1
Pedestal is opposite, measures 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, revolving speed, vibration, function
Rate-speed curves etc.) outside, it can also be in the case where engine be constant, the propeller quantity of testing flying vehicle wing (is cutd 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. of paddle is revolved, in order to play the maximum function of rotor assemblies 5 in actually manipulation.
In test, sliding rail 301 is fixedly mounted on level ground or construction platform, has it 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 is 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.
Above are merely preferred embodiments of the utility model, the protection scope of the utility model is not limited merely to above-mentioned
Embodiment, technical solution belonging to the idea of the present invention belong to the protection scope of the utility model.It should be pointed out that pair
For those skilled in the art, several improvements and modifications without departing from the principle of the utility model,
It should be regarded as the protection scope of the utility model.
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), is installed on the rack (1), for fixing aircraft rotor component (5) to be tested and making
It is in perpendicular；
The rack (1), is installed on the slide assemblies (3), and sliding along planned orbit under the driving of slide assemblies (3)
It is dynamic；
The test suite (4) is installed on the rack (1) or slide assemblies (3), for the rotation on suspension assembly (2)
Wing component (5) is tested.
2. aircraft rotor component test device according to claim 1, which is characterized in that suspension assembly (2) packet
Include the perpendicular guide rail (202) of more cross rails (201) and one or more；More cross rails (201) are fastened on rack (1), are located at
In perpendicular and it is parallel to each other；One or more perpendicular guide rail (202) is then slidably arranged on cross rail (201) and mutually puts down
Row；Sliding is provided with the fastening unit (203) for fastening the rotor assemblies (5) on the perpendicular guide rail (202).
3. aircraft rotor component test device according to claim 2, which is characterized in that on the perpendicular guide rail (202)
It is provided with sliding slot；The fastening unit (203) includes the first bolt (2031) and the first nut (2032), first bolt
(2031) one end is connected with the rotor assemblies (5), and the other end passes through the sliding slot and is connected with the first nut (2032) fastening.
4. aircraft rotor component test device according to claim 2, which is characterized in that the cross rail (201)
Quantity is two, and the quantity of the perpendicular guide rail (202) is three；The both ends of each perpendicular guide rail (202) are slidedly arranged on two respectively
On cross rail (201).
5. aircraft rotor component test device as claimed in any of claims 2 to 4, which is characterized in that described
Hang part (204) are provided on cross rail (201), for being hooked on rack (1) and being fastened on by fastener (205) described
In rack (1).
6. aircraft rotor component test device according to claim 5, which is characterized in that the fastener (205) is
Second bolt (2051) and 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) include sliding rail (301) and pulley (302)；The pulley (302) is installed on the bottom of rack (1) and in sliding rail
(301) sliding in.
8. aircraft rotor component test device as claimed in any of claims 1 to 4, which is characterized in that described
Test suite (4) includes thrust pickup (402), is installed on one end of slide assemblies (3).
9. aircraft rotor component test device according to claim 3, which is characterized in that test suite (4) packet
Vibrating sensor (401) are included, are sheathed on first bolt (2031).
10. aircraft rotor component test device as claimed in any of claims 1 to 4, which is characterized in that described
Rack (1) is the rack of steel sectional material frame structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821017861.0U CN208360517U (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 |
|---|---|---|---|
| CN201821017861.0U CN208360517U (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft rotor component test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208360517U true CN208360517U (en) | 2019-01-11 |
Family
ID=64927650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821017861.0U Active CN208360517U (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft rotor component test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208360517U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639379A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft rotor component test device |
| CN111516903A (en) * | 2020-05-15 | 2020-08-11 | 蜂巢航宇科技（北京）有限公司 | Test bench for tilt rotor unmanned aerial vehicle |
-
2018
- 2018-06-29 CN CN201821017861.0U patent/CN208360517U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639379A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft rotor component test device |
| CN111516903A (en) * | 2020-05-15 | 2020-08-11 | 蜂巢航宇科技（北京）有限公司 | Test bench for tilt rotor unmanned aerial vehicle |
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