CN208576735U - A kind of clamping device for aircraft lift test - Google Patents
A kind of clamping device for aircraft lift test Download PDFInfo
- Publication number
- CN208576735U CN208576735U CN201821018005.7U CN201821018005U CN208576735U CN 208576735 U CN208576735 U CN 208576735U CN 201821018005 U CN201821018005 U CN 201821018005U CN 208576735 U CN208576735 U CN 208576735U
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- China
- Prior art keywords
- plate
- pull rod
- lever
- movable plate
- limit plate
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- 238000012360 testing method Methods 0.000 title claims abstract description 30
- 239000000203 mixture Substances 0.000 claims description 15
- 238000009434 installation Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 5
- 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 3
- 238000001514 detection method Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000001771 impaired effect Effects 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
- 239000007787 solid Substances 0.000 description 1
- 238000012956 testing procedure Methods 0.000 description 1
- 238000003466 welding 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 clamping devices for aircraft lift test, including mounting plate, limit plate, movable plate, pull rod and driving assembly；The limit plate is perpendicularly fixed on mounting plate, and the movable plate is located at the side of the limit plate and is set side by side with limit plate；One end of the pull rod passes through the limit plate and connect with the movable plate, and the other end of the pull rod is connected with driving assembly, and the pull rod pulls the movable plate close to or far from limit plate with the pulley of clamp or release aircraft under the driving of driving assembly.The clamping device for aircraft lift test of the utility model has many advantages, such as that structure is simple, easy to operate and clamping effect is good.
Description
Technical field
The utility model relates generally to vehicle technology field, refers in particular to a kind of clamping dress for aircraft lift test
It sets.
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.For the needs of various tests, it is particularly significant to develop various test platforms, first protects
Hinder the safety of tester, two can reduce aircraft impaired and bring economic cost in testing as much as possible, protect
Barrier follow-up test on schedule, successfully 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 the clamping device for aircraft lift test that a kind of structure is simple, easy to operate, clamping effect is good.
In order to solve the above technical problems, the utility model proposes technical solution are as follows:
A kind of clamping device for aircraft lift test, including mounting plate, limit plate, movable plate, pull rod and driving
Component；The limit plate is perpendicularly fixed on mounting plate, the movable plate be located at the side of the limit plate and with limit plate simultaneously
Column setting；One end of the pull rod passes through the limit plate and connect with the movable plate, the other end of the pull rod and driving
Component is connected, and the pull rod pulls the movable plate close to or far from limit plate with clamp or release under the driving of driving assembly
The pulley of aircraft.
As a further improvement of the above technical scheme:
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, and the other end of blend stop and the side of the pedestal is made to offset
To be limited to lever.
The lower section of the mounting plate is equipped with clamping plate, and the mounting plate is connected with clamping plate by fastener fastening solid with sandwiched
It is fixed.
Compared with the prior art, the advantages of the utility model are:
The clamping device for aircraft lift test of the utility model, passes through the mutual cooperation of limit plate and movable plate
It realizes the clamping and release to aircraft pulley, to realize the fixation to aircraft, guarantees going on smoothly for test, structure letter
It is single, easy to operate, and clamping effect is good.
Detailed description of the invention
Fig. 1 is the schematic perspective view of the utility model.
Figure label indicates: 1, mounting plate；2, limit plate；3, movable plate；4, pull rod；5, the first compressed spring；6, it drives
Component；61, lever；62, fixture block；63, locating part；631, blend stop；632, the second compressed spring；7, clamping plate.
Specific embodiment
The utility model is further described below in conjunction with Figure of description and specific embodiment.
As shown in Figure 1, the clamping device for aircraft lift test of the present embodiment, wherein aircraft is rotorcycle
Pulley is arranged in the lower section of equal manned vehicles, rotorcycle；Clamping device specifically include mounting plate 1, limit plate 2, movable plate 3,
Pull rod 4 and driving assembly 6；The lower section of mounting plate 1 is provided with clamping plate 7, is fastened between mounting plate 1 and clamping plate 7 by bolt and nut
It is connected, so that mounting plate 1 is fixed on the pedestal (such as latticed web plate) of test platform；Due to detachable using bolt and nut
Mode connects, and is suitable for different size of Aerospace vehicle test so as to be carried out mobile.Limit plate 2 is perpendicularly fixed at peace
In loading board 1, movable plate 3 is then set side by side positioned at the side of limit plate 2 and with limit plate 2, i.e., between limit plate 2 and movable plate 3
Parallel arrangement, centre form the space for accommodating the pulley of aircraft, are wherein bolted between limit plate 2 and movable plate 3,
Movable plate 3 in other embodiments, can also be slideably positioned in peace certainly by the activity trajectory for being mainly used for limiting movable plate 3
On the track of loading board 1；Wherein the middle part of limit plate 2 and movable plate 3 is provided with through-hole, and one end of pull rod 4 sequentially passes through limit
The through-hole of plate 2 and movable plate 3 is provided with stopper section in one end of pull rod 4, covers on the pull rod 4 between stopper section and movable plate 3
Equipped with the first compressed spring 5；The other end of pull rod 4 is then connected with driving assembly 6, and pull rod 4 does axis under the driving of driving assembly 6
To movement, to pull movable plate 3 close to or far from limit plate 2 with clamp or release pulley；By being arranged in one end of pull rod 4
There is the first compressed spring 5, can guarantee the elastic clamping between limit plate 2 and movable plate 3 to pulley, avoids the damage to pulley
Wound.Certainly, in other embodiments, one end of pull rod 4 can also directly fasten with movable plate 3 and be connected, and such as be threadedly coupled, welding
Deng, but should be noted the size of clamping force, in case the hardness to pulley is damaged.The utility model is used for what aircraft lift was tested
Clamping device structure is simple, easy to operate and clamping effect is good.
In the present embodiment, driving assembly 6 includes lever 61 and fixture block 62；One end of fixture block 62 and the other end of pull rod 4 turn
The middle section of dynamic connection, the other end and lever 61 is rotatablely connected；One end of lever 61 is rotatablely installed on mounting plate 1, and the other end is set
It is equipped with locating part 63, for being rotated in lever 61, after successively fixture block 62, pull rod 4 and movable plate 3 being driven to move to clamp pulley,
61 position of lever is limited to keep clamped condition.In addition, blend stop 631 of the locating part 63 including bending, the one of blend stop 631
The second compressed spring 632 is provided between end and the other end of lever 61, the other end of blend stop 631 is rotatablely installed in lever 61
In the mounting hole of section；After being clamped to pulley, being rotated by the second compressed spring 632 of blend stop 631, makes to keep off at this time
The other end of item 631 and the side of pedestal 1 offset, to limit to lever 61, guarantee that pulley is in clamped condition.
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 (6)
1. a kind of clamping device for aircraft lift test, which is characterized in that including mounting plate (1), limit plate (2), live
Movable plate (3), pull rod (4) and driving assembly (6)；The limit plate (2) is perpendicularly fixed on mounting plate (1), the movable plate (3)
Positioned at the limit plate (2) side and be set side by side with limit plate (2)；One end of the pull rod (4) passes through the limit plate
(2) and with the movable plate (3) it connect, the other end of the pull rod (4) is connected with driving assembly (6), and the pull rod (4) is being driven
Pull the movable plate (3) close to or far from limit plate (2) with the cunning of clamp or release aircraft under the driving of dynamic component (6)
Wheel.
2. the clamping device according to claim 1 for aircraft lift test, which is characterized in that the pull rod (4)
One end sequentially pass through the limit plate (2) and movable plate (3), set between one end end and movable plate (3) of the pull rod (4)
It is equipped with the first compressed spring (5).
3. the clamping device according to claim 1 or 2 for aircraft lift test, which is characterized in that the driving
Component (6) includes lever (61) and fixture block (62)；One end of the fixture block (62) and the other end of the pull rod (4) rotate and connect
It connects, the middle section of the other end and the lever (61) is rotatablely connected；One end of the lever (61) is rotatablely installed in the mounting plate
(1) on, finite place piece (63) are arranged in the other end, for rotating, successively driving fixture block (62), pull rod (4) and living in lever (61)
When movable plate (3) movement is to clamp pulley, lever (61) position is limited to keep clamped condition.
4. the clamping device according to claim 3 for aircraft lift test, which is characterized in that the lever (61)
Middle part be provided with mounting hole；The locating part (63) includes blend stop (631), one end of the blend stop (631) and the lever
(61) it is provided between the other end the second compressed spring (632), the other end of the blend stop (631) is rotatablely installed in the thick stick
In the mounting hole of bar (61), blend stop (631) being rotated by the second compressed spring (632) makes blend stop (631)
The other end and the side of the mounting plate (1) offset to be limited to lever (61).
5. the clamping device according to claim 1 or 2 for aircraft lift test, which is characterized in that the installation
The lower section of plate (1) is equipped with clamping plate (7), and the mounting plate (1) is connected with clamping plate (7) by fastener fastening is fixed with sandwiched.
6. the clamping device according to claim 5 for aircraft lift test, which is characterized in that the fastener is
Bolt and nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821018005.7U CN208576735U (en) | 2018-06-29 | 2018-06-29 | A kind of clamping device for aircraft lift test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821018005.7U CN208576735U (en) | 2018-06-29 | 2018-06-29 | A kind of clamping device for aircraft lift test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208576735U true CN208576735U (en) | 2019-03-05 |
Family
ID=65509860
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821018005.7U Expired - Fee Related CN208576735U (en) | 2018-06-29 | 2018-06-29 | A kind of clamping device for aircraft lift test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208576735U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639378A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of clamping device for aircraft lift test |
-
2018
- 2018-06-29 CN CN201821018005.7U patent/CN208576735U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639378A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of clamping device for aircraft lift test |
| CN108639378B (en) * | 2018-06-29 | 2024-06-04 | 长沙市云智航科技有限公司 | Clamping device for lift force test 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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190305 |