CN108639377A - A kind of aircraft lift test device and method - Google Patents
A kind of aircraft lift test device and method Download PDFInfo
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- CN108639377A CN108639377A CN201810695034.5A CN201810695034A CN108639377A CN 108639377 A CN108639377 A CN 108639377A CN 201810695034 A CN201810695034 A CN 201810695034A CN 108639377 A CN108639377 A CN 108639377A
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- 238000012360 testing method Methods 0.000 title claims abstract description 77
- 238000000034 method Methods 0.000 title 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 claims abstract description 62
- 238000010998 test method Methods 0.000 claims abstract description 6
- 239000000203 mixture Substances 0.000 claims description 15
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims description 3
- 239000007790 solid phase Substances 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
- 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
- 235000013399 edible fruits Nutrition 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000005259 measurement Methods 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
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)
- Force Measurement Appropriate To Specific Purposes (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a kind of aircraft lift test devices, including pedestal, test cell, multiple clamping units and multiple pilot units；Multiple clamping units, for clamping carry-on pulley so that aircraft to be fixed on the base；Multiple pilot units, it is vertically moving for limiting pedestal；Test cell, for connecting aircraft and being measured to the lift of aircraft.The test device of the present invention has many advantages, such as that simple in structure, test is reliable.The invention also discloses a kind of test methods, include the following steps：S01, aircraft is placed on chassis, and is clamped the pulley of aircraft by clamping unit, aircraft is made to be fixed on the base；S02, test cell is connected with aircraft, lift test is carried out to aircraft, aircraft is vertically moved up or down under the guiding role of pilot unit with pedestal, is measured to the real-time lift of aircraft by test cell.The test method of the present invention has many advantages, such as that easy to operate, testing efficiency is high.
Description
Technical field
The invention mainly relates to vehicle technology field, a kind of aircraft lift test device and method are refered in particular to.
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.
It for the needs of various tests, develops that various test platforms are particularly significant, first ensures the safety of tester, two
The economic cost to reduce the impaired of aircraft in testing as much as possible and brought, ensures follow-up test on schedule, smoothly
Ground carries out.
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 is simple in structure, tests reliable aircraft lift test device, and accordingly provides a kind of survey easy to operate, testing efficiency is high
Method for testing.
In order to solve the above technical problems, technical solution proposed by the present invention is：
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, for clamping aircraft
On pulley 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 being measured to the lift of aircraft.
As a further improvement of the above technical scheme：
The clamping unit includes mounting plate, limiting plate, movable plate, pull rod and drive component；The mounting plate is installed on described
On pedestal, the limiting plate is perpendicularly fixed on mounting plate, and the movable plate is located at the side of the limiting plate and and limiting plate
It is set up in parallel；One end of the pull rod passes through the limiting plate and is connect with the movable plate, the other end of the pull rod and drive
Dynamic component is connected, and the pull rod pulls the movable plate closer or far from limiting plate to clamp or pine under the driving of drive component
Open pulley.
One end of the pull rod sequentially passes through the limiting plate and movable plate, one end end and movable plate of the pull rod it
Between be provided with the first compressed spring.
The driving component includes lever and fixture block；One end of the fixture block and the other end of the pull rod are rotatablely connected,
The stage casing 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.
It is provided with mounting hole 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 the other end of blend stop with the side phase of the mounting plate
To be limited to lever.
The lower section of the mounting plate is equipped with clamping plate, and the mounting plate is located at the both sides of the pedestal and passes through fastening with clamping plate
Part fastening is connected.
The pilot unit includes guide rod and guide sleeve, and one end of the guide sleeve is fastened with the pedestal, 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 shaped steel.
The invention also discloses a kind of test method based on aircraft lift test device as described above, including it is following
Step：
S01, the aircraft is placed on the pedestal, and is clamped the pulley of aircraft by clamping unit, make aircraft
It is fixed on the base；
S02, test cell is connected with the aircraft, lift test is carried out to aircraft, aircraft is being oriented to list with pedestal
It is vertically moved up or down under the guiding role of member, the real-time lift of aircraft is measured by test cell.
Compared with the prior art, the advantages of the present invention are as follows：
The aircraft lift test device of the present invention, is clamped pulley using multiple clamping units being distributed on pedestal,
To make aircraft be fastened on pedestal, and the aircraft on pedestal and pedestal is limited by pilot unit and is vertically risen
Drop ensures that aircraft is fastened when carrying out lift test with pedestal and is connected, and vertically lift, to ensure to test can
By being smoothed out.
The aircraft lift test device of the present invention, clamping unit are removably mounted on pedestal, and convenient for disassembly and assembly, to
Suitable for different model, the performance test of different size aircraft.And clamping unit is simple in structure, easy to operate and clamping effect
Fruit is good.
The aircraft lift test device of the present invention, pedestal fenestral fabric made of shaped steel welding；Not only carry
High-base intensity, while the weight of pedestal is also mitigated, reduce its influence to measuring accuracy to the greatest extent.
The aircraft lift test method of the present invention, equally has the advantages that described in device as above, and easy to operate, easy
In realization and testing efficiency height.
Description of the drawings
Fig. 1 is the three-dimensional structure diagram of apparatus of the present invention in specific application.
Fig. 2 is the dimensional structure diagram of apparatus of the present invention.
Fig. 3 is the three-dimensional structure diagram of the clamping unit in apparatus of the present invention.
Fig. 4 is the test method flow chart of the present invention.
Figure label indicates：1, pedestal；2, clamping unit；201, mounting plate；202, limiting plate；203, movable plate；204、
Pull rod；205, the first compressed spring；206, drive component；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 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 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 corresponds to, 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 test of the present invention
Device is clamped pulley 501 using multiple clamping units 2 being distributed on pedestal 1, to make aircraft 5 be fastened on bottom
On seat 1, and the aircraft 5 on pedestal 1 and pedestal 1 is limited by pilot unit 3 and is vertically lifted, ensures aircraft 5
It is connected with the fastening of pedestal 1 when carrying out lift test, and vertically lifts, to ensure that test is reliably smoothed out, together
When pedestal 1 and pilot unit 3 cooperation, the flight path of aircraft 5 can be limited, ensure the personal safety of tester, with
And reduce by 5 damaged risk of aircraft.
As shown in figure 3, in the present embodiment, the quantity of clamping unit 2 is three；The concrete structure of clamping unit 2 includes peace
Loading board 201, limiting plate 202, movable plate 203, pull rod 204 and drive component 206；The lower section of mounting plate 201 is provided with clamping plate
207, it is connected by bolt and nut fastening between mounting plate 201 and clamping plate 207, to which clamping unit 2 to be 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.Limiting plate 202 is perpendicularly fixed on mounting plate 201, movable plate 203 then be located at limiting plate 202 side and with
Limiting plate 202 is set up in parallel, i.e., is arranged in parallel between limiting plate 202 and movable plate 203, and centre forms the sky for accommodating pulley 501
Between, it is wherein bolted between limiting plate 202 and movable plate 203, is mainly used for limiting the event trace of movable plate 203,
Certainly, in other embodiments, movable plate 203 can also be slideably positioned on the track of mounting plate 201；Wherein limiting plate
202 and the middle part of movable plate 203 be both provided with through-hole, one end of pull rod 204 sequentially passes through limiting plate 202 and movable plate 203
Through-hole is provided with stopper section in one end of pull rod 204, and first is arranged 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 drive component 206, and pull rod 204 is done under the driving of drive component 206
It is axially moved, to pull movable plate 203 closer or far from limiting plate 202 with clamp or release pulley 501；By in pull rod
204 one end is arranged with the first compressed spring 205, can ensure between limiting 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 also can 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
The clamping unit 2 of invention is simple in structure, easy to operate and clamping effect is good.
In the present embodiment, drive component 206 includes lever 2061 and fixture block 2062；One end of fixture block 2062 and pull rod 204
Other end rotation connection, the stage casing 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 being rotated in lever 2061, drives fixture block 2062,204 and of pull rod successively
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 and the other end of lever 2061 of blend stop 20631
The other end of spring 20632, blend stop 20631 is rotatablely installed in the mounting hole in 2061 stage casing 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, and to be limited to lever 2061, ensures 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 and the pedestal 1 of guide sleeve 302 fasten, and the other end is sheathed in guide rod 301 and edge
301 oscilaltion of guide rod ensures the reliability and accuracy of test to ensure that aircraft 5 vertically lifts.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 pressure stabilizer blade, to be suitable for non-level ground, by adjusting the height of hydraulic pressure stabilizer blade to ensure 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 shaped steel, by welding or being spirally connected between each shaped steel
Mode connects, and can not only ensure the fixing of pedestal 1, while can mitigate the weight of pedestal 1, minimize to test
It influences.In addition, test cell 4 is the measuring instruments, wherein tensiometer and host computer such as tensiometer（It is not shown in figure）It is connected, it 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 positioned over to the centre position of pedestal 1 again, clamping unit 2 is used in combination to clamp aircraft 5
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 present invention accordingly discloses a kind of test based on aircraft lift test device as described above
Method specifically includes following steps：
S01, pedestal 1 is fixedly installed on level ground first, aircraft 5 is placed on pedestal 1, and pass through clamping unit 2
The pulley 501 of aircraft 5 is clamped, aircraft 5 is made to be fixed on pedestal 1；
S02, test cell 4 is connected with aircraft 5, lift test is carried out to aircraft 5, made by the guiding of pilot unit 3
With making aircraft 5 be vertically moved up or down, then by test cell 4 the real-time lift of aircraft 5 is measured.
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 lift test device, which is characterized in that including pedestal（1）, test cell（4）, multiple clamping units
（2）With multiple pilot units（3）；
Multiple clamping units（2）, it is installed on the pedestal（1）Upper and and aircraft（5）Pulley（501）It corresponds,
For clamping aircraft（5）On pulley（501）With by aircraft（5）It is fixed on pedestal（1）On；
Multiple pilot units（3）, it is installed on the pedestal（1）Lower section, for limiting the pedestal（1）Vertically transport
It is dynamic；
Test cell（4）, it is fixedly installed in the pedestal（1）Lower section, for connecting aircraft（5）And to aircraft（5）'s
Lift measures.
2. aircraft lift test device according to claim 1, which is characterized in that the clamping unit（2）Including peace
Loading board（201）, limiting plate（202）, movable plate（203）, pull rod（204）And drive component（206）；The mounting plate（201）Peace
Loaded on the pedestal（1）On, the limiting plate（202）It is perpendicularly fixed at mounting plate（201）On, the movable plate（203）It is located at
The limiting plate（202）Side and and limiting plate（202）It is set up in parallel；The pull rod（204）One end pass through the limit
Plate（202）And with the movable plate（203）Connection, the pull rod（204）The other end and drive component（206）It is connected, it is described
Pull rod（204）In drive component（206）Driving under pull the movable plate（203）Closer or far from limiting plate（202）With folder
Tight or release pulley（501）.
3. aircraft lift test device according to claim 2, which is characterized in that the pull rod（204）One end according to
It is secondary to pass through the limiting plate（202）And movable plate（203）, the pull rod（204）The end of one end and movable plate（203）Between set
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）；The fixture block（2062）One end and the pull rod（204）The other end rotation connection,
The other end and the lever（2061）Stage casing rotation connection；The lever（2061）One end be rotatablely installed in the mounting plate
（201）On, finite place piece is arranged in the other end（2063）, in lever（2061）Rotation, drives fixture block successively（2062）, pull rod
（204）And movable plate（203）Movement is to clamp pulley（501）When, to lever（2061）Position is limited to keep clamping shape
State.
5. aircraft lift test device according to claim 4, which is characterized in that the lever（2061）Middle part set
It is equipped with mounting hole；The locating part（2063）Including blend stop（20631）, the blend stop（20631）One end and the lever
（2061）The other end between be provided with the second compressed spring（20632）, the blend stop（20631）The other end rotational installation in
The lever（2061）Mounting hole in, the blend stop（20631）In second compressed spring（20632）Lower turn of driving
It is dynamic, make blend stop（20631）The other end and the mounting plate（201）Side offset with to lever（2061）It is limited.
6. aircraft lift test device according to claim 2 or 3, which is characterized in that the mounting plate（201）Under
Side is equipped with clamping plate（207）, the mounting plate（201）With clamping plate（207）Positioned at the pedestal（1）Both sides and tight by fastener
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）, the guide sleeve（302）One end and the pedestal（1）Fastening, another end cap
Set on the guide rod（301）Above 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）It serves as reasons
The reticular structure that shaped steel is constituted.
10. a kind of test method based on the aircraft lift test device described in any one of claim 1 to 9, special
Sign is, includes the following steps：
S01, by the aircraft（5）It is placed in the pedestal（1）On, and pass through clamping unit（2）By aircraft（5）Pulley
（501）It clamps, makes aircraft（5）It is fixed on pedestal（1）On；
S02, by test cell（4）With the aircraft（5）It is connected, to aircraft（5）Carry out lift test, aircraft（5）With
Pedestal（1）In pilot unit（3）Guiding role under be vertically moved up or down, pass through test cell（4）To aircraft（5）Real-time lift
It measures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810695034.5A CN108639377B (en) | 2018-06-29 | 2018-06-29 | Device and method for testing lift force of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810695034.5A CN108639377B (en) | 2018-06-29 | 2018-06-29 | Device and method for testing lift force of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108639377A true CN108639377A (en) | 2018-10-12 |
| CN108639377B CN108639377B (en) | 2024-06-04 |
Family
ID=63749977
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810695034.5A Active CN108639377B (en) | 2018-06-29 | 2018-06-29 | Device and method for testing lift force of aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN108639377B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116184101A (en) * | 2023-04-27 | 2023-05-30 | 合肥航太电物理技术有限公司 | Lightning current sweep damage test device and system for aircraft |
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| CN116184101A (en) * | 2023-04-27 | 2023-05-30 | 合肥航太电物理技术有限公司 | Lightning current sweep damage test device and system for aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108639377B (en) | 2024-06-04 |
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