CN208360518U - A kind of aircraft lift test device - Google Patents
A kind of aircraft lift test device Download PDFInfo
- Publication number
- CN208360518U CN208360518U CN201821017869.7U CN201821017869U CN208360518U CN 208360518 U CN208360518 U CN 208360518U CN 201821017869 U CN201821017869 U CN 201821017869U CN 208360518 U CN208360518 U CN 208360518U
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- aircraft
- pedestal
- plate
- lever
- test device
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- 238000012360 testing method Methods 0.000 title claims abstract description 61
- 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 claims abstract description 67
- 239000000203 mixture Substances 0.000 claims description 15
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 10
- 229910052742 iron Inorganic materials 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims description 3
- 239000007790 solid phase Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 description 4
- 238000003466 welding Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000012956 testing procedure Methods 0.000 description 1
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model discloses a kind of aircraft lift test devices, including pedestal, test cell, multiple clamping units and multiple pilot units；Multiple clamping units are installed on the pulley on the pedestal and with aircraft and correspond, for clamping carry-on pulley so that aircraft to be fixed on the base；Multiple pilot units are installed on the lower section of the pedestal, vertically moving for limiting the pedestal；Test cell is fixedly installed in the lower section of the pedestal, for connecting aircraft and measuring to the lift of aircraft.The aircraft lift test device of the utility model has many advantages, such as that structure is simple, test is reliable.
Description
Technical field
The utility model relates generally to vehicle technology field, refers in particular to a kind of aircraft lift 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.
It for the needs of various tests, develops that various test platforms are particularly significant, first ensures the safety of tester, two
To reduce aircraft impaired in testing as much as possible and bring economic cost, ensures follow-up test on schedule, smoothly
Ground carries out.
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 that a kind of structure is simple, the reliable aircraft lift test device of test.
In order to solve the above technical problems, the utility model proposes technical solution are as follows:
A kind of aircraft lift test device, including pedestal, test cell, multiple clamping units and multiple pilot units；
Multiple clamping units are installed on the pulley on the pedestal and with aircraft and correspond, winged for clamping
Pulley on row device is aircraft to be fixed on the base；
Multiple pilot units are installed on the lower section of the pedestal, vertically moving for limiting the pedestal；
Test cell is fixedly installed in the lower section of the pedestal, for connecting aircraft and carrying out to the lift of aircraft
Measurement.
As a further improvement of the above technical scheme:
The clamping unit includes mounting plate, limit plate, movable plate, pull rod and driving assembly；The mounting plate is installed on
On the pedestal, the limit plate is perpendicularly fixed on mounting plate, the movable plate be located at the side of the limit plate and with limit
Position plate is set side by side；One end of the pull rod passes through the limit plate and connect with the movable plate, the other end of the pull rod
It is connected with driving assembly, the pull rod pulls the movable plate close to or far from limit plate to clamp under the driving of driving assembly
Or unclamp pulley.
One end of the pull rod sequentially passes through the limit plate and movable plate, one end end of the pull rod and movable plate it
Between be provided with the first compressed spring.
The driving component includes lever and fixture block；The other end of one end of the fixture block and the pull rod is rotatablely connected,
The middle section of the other end and the lever is rotatablely connected；One end of the lever is rotatablely installed on the mounting plate, and the other end is set
It is equipped with locating part, when in lever rotation, driving fixture block, pull rod and movable plate movement successively to clamp pulley, to lever position
It sets and is limited to keep clamped condition.
Mounting hole is provided in the middle part of the lever；The locating part includes blend stop, one end of the blend stop and the thick stick
The second compressed spring is provided between the other end of bar, the other end of the blend stop is rotatablely installed in the mounting hole of the lever
Interior, the blend stop is rotated by second compressed spring, makes side phase of the other end of blend stop with the mounting plate
To be limited to lever.
The lower section of the mounting plate is equipped with clamping plate, and the mounting plate and clamping plate are located at the two sides of the pedestal and pass through fastening
Part fastening is connected.
The pilot unit includes guide rod and guide sleeve, and one end of the guide sleeve and the pedestal fasten, the other end
It is sheathed in the guide rod and along guide rod oscilaltion.
The test cell is tensiometer.
The pedestal is the reticular structure being made of fashioned iron.
Compared with the prior art, the advantages of the utility model are:
The aircraft lift test device of the utility model, using multiple clamping units being distributed on pedestal to pulley into
Row clamps, so that aircraft be made to be fastened on pedestal, and limits the aircraft on pedestal and pedestal along perpendicular by pilot unit
Histogram guarantees that aircraft is connected when carrying out lift test with pedestal fastening to lifting, and goes up and down along the vertical direction, to guarantee
Test is reliably gone on smoothly.
The aircraft lift test device of the utility model, clamping unit are removably mounted on pedestal, and convenient for disassembly and assembly,
To be suitable for different model, the performance test of different size aircraft.And clamping unit structure is simple, easy to operate and folder
Tight effect is good.
The aircraft lift test device of the utility model, pedestal fenestral fabric made of fashioned iron welding；Not only
Pedestal intensity is only improved, while also mitigating the weight of pedestal, reduces its influence to measuring accuracy to the greatest extent.
Detailed description of the invention
Fig. 1 is the three-dimensional structure diagram of utility model device in specific application.
Fig. 2 is the schematic perspective view of utility model device.
Fig. 3 is the three-dimensional structure diagram of the clamping unit in utility model device.
Fig. 4 is the test method flow chart of the utility model.
Figure label indicates: 1, pedestal；2, clamping unit；201, mounting plate；202, limit plate；203, movable plate；204,
Pull rod；205, the first compressed spring；206, driving assembly；2061, lever；2062, fixture block；2063, locating part；20631, it keeps off
Item；20632, the second compressed spring；207, clamping plate；3, pilot unit；301, guide rod；302, guide sleeve；4, test cell；5,
Aircraft；501, pulley.
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 lift test device of the present embodiment, aircraft are rotorcycle or other nothings
People's aircraft etc. specifically includes latticed pedestal 1, test cell 4, multiple clamping units 2 and multiple pilot units 3；It is multiple
Clamping unit 2, quantity is consistent with 501 quantity of pulley of aircraft 5, be installed on pedestal 1 and with the pulley of aircraft 5 501 1
One is corresponding, for clamping the pulley 501 on aircraft 5 so that aircraft 5 is fixed on pedestal 1；Multiple pilot units 3, installation
It is vertically moving with aircraft 5 for limiting pedestal 1 in the lower section of pedestal 1；Test cell 4 is fixedly installed in pedestal 1
On the ground of lower section, for connecting aircraft 5 and being measured to the lift of aircraft 5.The aircraft lift of the utility model
Test device is clamped pulley 501 using multiple clamping units 2 being distributed on pedestal 1, so that aircraft 5 be made to fasten
On pedestal 1, and the aircraft 5 on pedestal 1 and pedestal 1 is limited by pilot unit 3 and is gone up and down along the vertical direction, guarantees flight
Device 5 is connected when carrying out lift test with the fastening of pedestal 1, and goes up and down along the vertical direction, thus guarantee that test is reliably gone on smoothly,
The cooperation of pedestal 1 and pilot unit 3 simultaneously, can limit the flight path of aircraft 5, ensure the personal safety of tester,
And reduce by 5 damaged risk of aircraft.
As shown in figure 3, the quantity of clamping unit 2 is three in the present embodiment；The specific structure of clamping unit 2 includes peace
Loading board 201, limit plate 202, movable plate 203, pull rod 204 and driving assembly 206；The lower section of mounting plate 201 is provided with clamping plate
207, it is connected between mounting plate 201 and clamping plate 207 by bolt and nut fastening, so that clamping unit 2 is fixed on pedestal 1；
Due to being connected using bolt and nut removably, it is suitable for different size of so as to carry out clamping unit 2 mobile
Aircraft 5 is tested.Limit plate 202 is perpendicularly fixed on mounting plate 201, movable plate 203 then positioned at limit plate 202 side and with
Limit plate 202 is set side by side, i.e., is arranged in parallel between limit plate 202 and movable plate 203, and centre forms the sky for accommodating pulley 501
Between, it is wherein bolted between limit plate 202 and movable plate 203, is mainly used for limiting the activity trajectory of movable plate 203,
Certainly, in other embodiments, movable plate 203 can also be slideably positioned on the track of mounting plate 201；Wherein limit plate
202 and the middle part of movable plate 203 be provided with through-hole, one end of pull rod 204 sequentially passes through limit plate 202 and movable plate 203
Through-hole is provided with stopper section in one end of pull rod 204, is arranged with first on the pull rod 204 between stopper section and movable plate 203
Compressed spring 205；The other end of pull rod 204 is then connected with driving assembly 206, and pull rod 204 is done under the driving of driving assembly 206
It is axially moved, to pull movable plate 203 close to or far from limit plate 202 with clamp or release pulley 501；By in pull rod
204 one end is arranged with the first compressed spring 205, can guarantee between limit plate 202 and movable plate 203 to the bullet of pulley 501
Property clamp, avoid the damage to pulley 501.Certainly, in other embodiments, one end of pull rod 204 can also be straight with movable plate 203
It connects fastening to be connected, such as be threadedly coupled, welding etc., but should be noted the size of clamping force, in case the hardness to pulley 501 is damaged.This
2 structure of clamping unit of utility model is simple, easy to operate and clamping effect is good.
In the present embodiment, driving assembly 206 includes lever 2061 and fixture block 2062；One end of fixture block 2062 and pull rod 204
Other end rotation connection, the middle section of the other end and lever 2061 is rotatablely connected；One end of lever 2061 is rotatablely installed in installation
On plate 201, finite place piece 2063 is arranged in the other end, for rotating in lever 2061, successively drives fixture block 2062,204 and of pull rod
When the movement of movable plate 203 is to clamp pulley 501,2061 position of lever is limited to keep clamped condition.In addition, locating part
2063 include the blend stop 20631 of bending, and the second compression bullet is provided between one end of blend stop 20631 and the other end of lever 2061
The other end of spring 20632, blend stop 20631 is rotatablely installed in the mounting hole in 2061 middle section of lever；It is clamped to pulley 501
Afterwards, being rotated by the second compressed spring 20632 of blend stop 20631 at this time, makes the other end and mounting plate of blend stop 20631
201 side offsets, to limit to lever 2061, guarantees that pulley 501 is in clamped condition.
As depicted in figs. 1 and 2, in the present embodiment, pilot unit 3 includes guide rod 301 and guide sleeve 302, wherein being oriented to
Bar 301 is fastened on ground, and one end of guide sleeve 302 and pedestal 1 fasten, and the other end is sheathed in guide rod 301 and edge
301 oscilaltion of guide rod guarantees the reliability and accuracy of test to guarantee that aircraft 5 is gone up and down along the vertical direction.Wherein
The quantity of pilot unit 3 is four, is distributed in the four corners of pedestal 1.Alternatively, it is also possible to be provided in the lower section of pilot unit 3
Height-adjustable hydraulic stabilizer blade, to be suitable for non-level ground, by adjusting the height of hydraulic stabilizer blade to guarantee pedestal 1
On aircraft 5 test when be in horizontality.
In the present embodiment, pedestal 1 is the rectangle reticular structure that is made of fashioned iron, by welding or is spirally connected between each fashioned iron
Mode connects, and can not only guarantee the fixing of pedestal 1, while can reduce the weight of pedestal 1, minimizes to test
It influences.In addition, test cell 4 is the measuring instruments such as tensiometer, wherein tensiometer is connected with host computer (not shown), can
The result of measurement is shown by host computer, is monitored in real time convenient for staff in order to test.
Workflow: pedestal 1 is fixed on level ground or building, it is enable to have sufficiently stable, sufficient carrying
Power will not move or turn on one's side；Aircraft 5 is placed in the middle position of pedestal 1 again, and is clamped aircraft 5 with clamping unit 2
On pedestal 1, relevant test is then carried out as desired and carries out the collecting work of data, after completing test, by pedestal 1
Clamping unit 2 unclamps, and aircraft 5 is moved to outside pedestal 1.
As shown in figure 4, the utility model accordingly disclose it is a kind of based on aircraft lift test device as described above
Test method, specifically includes the following steps:
S01, pedestal 1 is fixedly installed on level ground first, aircraft 5 is placed on pedestal 1, and is single by clamping
Member 2 clamps the pulley 501 of aircraft 5, is fixed on aircraft 5 on pedestal 1；
S02, test cell 4 is connected with aircraft 5, lift test is carried out to aircraft 5, passes through leading for pilot unit 3
It is vertically moved up or down aircraft 5 to effect, then is measured by real-time lift of the test cell 4 to aircraft 5.
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 (9)
1. a kind of aircraft lift test device, which is characterized in that including pedestal (1), test cell (4), multiple clamping units
(2) and multiple pilot units (3)；
Multiple clamping units (2) are installed on the pulley (501) on the pedestal (1) and with aircraft (5) and correspond,
For clamping the pulley (501) on aircraft (5) so that aircraft (5) is fixed on pedestal (1)；
Multiple pilot units (3), are installed on the lower section of the pedestal (1), transport along the vertical direction for limiting the pedestal (1)
It is dynamic；
Test cell (4), is fixedly installed in the lower section of the pedestal (1), for connecting aircraft (5) and to aircraft (5)
Lift measures.
2. aircraft lift test device according to claim 1, which is characterized in that the clamping unit (2) includes peace
Loading board (201), limit plate (202), movable plate (203), pull rod (204) and driving assembly (206)；Mounting plate (201) peace
Loaded on the pedestal (1), the limit plate (202) is perpendicularly fixed on mounting plate (201), and the movable plate (203) is located at
It the side of the limit plate (202) and is set side by side with limit plate (202)；One end of the pull rod (204) passes through the limit
Plate (202) is simultaneously connect with the movable plate (203), and the other end of the pull rod (204) is connected with driving assembly (206), described
Pull rod (204) pulls the movable plate (203) close to or far from limit plate (202) to press from both sides under the driving of driving assembly (206)
Tight or release pulley (501).
3. aircraft lift test device according to claim 2, which is characterized in that one end of the pull rod (204) according to
It is secondary to pass through the limit plate (202) and movable plate (203), it is set between the end and movable plate (203) of described pull rod (204) one end
It is equipped with the first compressed spring (205).
4. aircraft lift test device according to claim 2 or 3, which is characterized in that the driving component (206) packet
Include lever (2061) and fixture block (2062)；One end of the fixture block (2062) and the other end of the pull rod (204) are rotatablely connected,
The middle section of the other end and the lever (2061) is rotatablely connected；One end of the lever (2061) is rotatablely installed in the mounting plate
(201) on, finite place piece (2063) are arranged in the other end, for rotating in lever (2061), successively drive fixture block (2062), pull rod
(204) when and movable plate (203) movement is to clamp pulley (501), lever (2061) position is limited to keep clamping shape
State.
5. aircraft lift test device according to claim 4, which is characterized in that set in the middle part of the lever (2061)
It is equipped with mounting hole；The locating part (2063) includes blend stop (20631), one end of the blend stop (20631) and the lever
(2061) be provided between the other end the second compressed spring (20632), the rotational installation of the other end of the blend stop (20631) in
In the mounting hole of the lever (2061), the blend stop (20631) turns under the driving of second compressed spring (20632)
It is dynamic, so that the side of the other end of blend stop (20631) and the mounting plate (201) is offseted to limit to lever (2061).
6. aircraft lift test device according to claim 2 or 3, which is characterized in that under the mounting plate (201)
Side is equipped with clamping plate (207), and the mounting plate (201) and clamping plate (207) are located at the two sides of the pedestal (1) and to pass through fastener tight
Solid phase connects.
7. aircraft lift test device according to claim 1 or 2 or 3, which is characterized in that the pilot unit (3)
Including guide rod (301) and guide sleeve (302), one end and the pedestal (1) of the guide sleeve (302) are fastened, another end cap
On the guide rod (301) and along guide rod (301) oscilaltion.
8. aircraft lift test device according to claim 1 or 2 or 3, which is characterized in that the test cell (4)
For tensiometer.
9. aircraft lift test device according to claim 1 or 2 or 3, which is characterized in that the pedestal (1) is served as reasons
The reticular structure that fashioned iron is constituted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821017869.7U CN208360518U (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft lift test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821017869.7U CN208360518U (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft lift test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208360518U true CN208360518U (en) | 2019-01-11 |
Family
ID=64927610
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821017869.7U Expired - Fee Related CN208360518U (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft lift test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208360518U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639377A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft lift test device and method |
-
2018
- 2018-06-29 CN CN201821017869.7U patent/CN208360518U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639377A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft lift test device and method |
| CN108639377B (en) * | 2018-06-29 | 2024-06-04 | 长沙市云智航科技有限公司 | Device and method for testing lift force of aircraft |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190111 |