CN208704862U - A kind of UAV system weight test device - Google Patents
A kind of UAV system weight test device Download PDFInfo
- Publication number
- CN208704862U CN208704862U CN201821329176.1U CN201821329176U CN208704862U CN 208704862 U CN208704862 U CN 208704862U CN 201821329176 U CN201821329176 U CN 201821329176U CN 208704862 U CN208704862 U CN 208704862U
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- CN
- China
- Prior art keywords
- load cell
- uav system
- test device
- support base
- system weight
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Abstract
The utility model discloses a kind of UAV system weight test devices, including check weighing block, load cell and fixed plate, the fixed plate fixes on the ground, there are two support bases for setting above the fixed plate, and two support bases are oppositely arranged in sickle, are provided with mounting groove in the middle part of two support bases, and the load cell can be made to be placed among two support bases, it is provided on the support base and holds out against component, the load cell can held out against from side.Beneficial effect is: can be realized the quick test to UAV system weight, and test data accuracy is high；It can be applicable in the loading capacity test of different model unmanned plane, and easy to operate.
Description
Technical field
The utility model relates to unmanned plane fields, and in particular to a kind of UAV system weight test device.
Background technique
The application field of unmanned plane includes military operation, geological exploration, logistics transportation, agricultural application, video display bat at present
It takes the photograph, fire-fighting is combated a natural disaster and rescues the numerous areas such as inspection.It is required to carry constant weight when unmanned plane uses in these areas
Article, especially agricultural, in fire-fighting and logistics and transportation industry, article loading capacity entrained by unmanned plane is often heavier, therefore
Unmanned plane is both needed to carry out loading capacity test to it before factory, to ensure its lifting capacity.
Applicants have discovered that at least there is following technical problem in the prior art: existing UAV system, which resurveys examination, to be had one by one
Replacement test block is detected, therefore labor workload is larger, and detection data accuracy rate is lower.
Utility model content
The purpose of this utility model is that solve the above-mentioned problems and provides a kind of UAV system weight test device, with
It solves during UAV system resurveys examination in the prior art, labor workload is larger, and the more low technology of detection data accuracy rate
Problem.Preferred technical solution, which includes, in many technical solutions provided by the utility model can fast and accurately measure nothing
Man-machine loading capacity, and the technical effects such as labor workload is small, elaboration as detailed below.
To achieve the above object, the utility model provides following technical scheme:
The utility model provides a kind of UAV system weight test device, including check weighing block, load cell and fixed plate,
The fixed plate fixes on the ground, and there are two support bases for setting above the fixed plate, and two support bases are in reaping hook
Type is oppositely arranged, and is provided with mounting groove in the middle part of two support bases, and the load cell can be made to be placed on two institutes
It states among support base, is provided on the support base and holds out against component, the load cell can be held out against from side；
The upper surface of the load cell is higher than the upper surface of the support base, and the check weighing block is placed on the dynamometry
On sensor, traction rope is connected with above the check weighing block.
Using a kind of above-mentioned UAV system weight test device, the other end of the traction rope is fixed on uav bottom, institute
The specification of the weight and the load cell of stating check weighing block can be matched according to the model of unmanned plane, wherein the check weighing block
For unmanned plane manufacturer's maximum payload, and the load cell is electrically connected by signal wire with monitoring client, after the completion of apolegamy, general
The load cell is placed on the middle position of the mounting groove, using holding out against component described in two sides to the force-measuring sensing
Device is held out against, then the check weighing block is placed on above the load cell, and the test can be started, the load cell
Primary data be the check weighing block total weight, unmanned plane applies the check weighing block by the traction rope in test process
Lifting power upwards, to make the detection data of the load cell be gradually reduced, when the detection numerical value of the load cell
After stabilization, reduction amount is the loading capacity of unmanned plane, so tests the detection stability for being greatly improved test device.
Preferably, the fixed plate is fixed on the ground by expansion bolt, the support base is welded on the fixation
Plate.
Preferably, the component that holds out against includes top-fastening rod and jacking block, the top-fastening rod is horizontally disposed, and is pacified by screw thread
On the support base, one end of the top-fastening rod is protruded into the mounting groove, and end is provided with connector, the jacking block
It is fixedly mounted on the connector.
Preferably, the jacking block is formed using rubber processing.
Preferably, the opening width between two mounting grooves is greater than the length of the load cell.
Preferably, the load cell is two-direction pull press sensor, and the bottom of the load cell is equipped with
The anticreep hanging plate of two L-types, the L-type bending direction of two anticreep hanging plates stretch to the bottom of the support base of two sides respectively
Face.
Preferably, be provided with lifting component on the check weighing block, the lifting component includes side arm and lifting rod, described
Side arm shares two, U-shaped structure is collectively formed with the lifting rod, and two side arms are separately mounted to the check weighing block
On front-rear side walls, the lifting rod is located at the lower section of the load cell, and the lifting rod is removably pacified by bolt
On the side arm.
Beneficial effect is: 1, the utility model can be realized the quick test to UAV system weight, and test data
Accuracy is high；
2, it can be applicable in the loading capacity test of different model unmanned plane, and easy to operate.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is some embodiments of the utility model, for those of ordinary skill in the art, in the premise not made the creative labor
Under, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is the structural schematic diagram of the utility model；
Fig. 2 is the front view of the utility model；
Fig. 3 is that the utility model holds out against modular construction enlarged drawing.
The reference numerals are as follows:
1, check weighing block；2, support base；201, mounting groove；3, load cell；301, anticreep hanging plate；4, component is held out against；
401, top-fastening rod；4011, connector；402, jacking block；5, fixed plate；6, component is lifted；601, side arm；602, lifting rod；7, it leads
Messenger.
Specific embodiment
To keep the purpose of this utility model, technical solution and advantage clearer, below by the technology to the utility model
Scheme is described in detail.Obviously, the described embodiments are only a part of the embodiments of the utility model, rather than all
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are not before making creative work
Obtained all other embodiment is put, the range that the utility model is protected is belonged to.
Shown in referring to figures 1-3, the utility model provides a kind of UAV system weight test device, including check weighing block 1, survey
Force snesor 3 and fixed plate 5, the fixed plate 5 fix on the ground, support base 2 there are two settings above the fixed plate 5,
And two support bases 2 are oppositely arranged in sickle, the middle part of two support bases 2 is provided with mounting groove 201, can make
The load cell 3 is placed among two support bases 2, is provided on the support base 2 and is held out against component 4, Neng Goucong
Side holds out against the load cell 3；
The upper surface of the load cell 3 is higher than the upper surface of the support base 2, and the check weighing block 1 is placed on described
On load cell 3, traction rope 7 is connected with above the check weighing block 1.
Preferably, the fixed plate 5 is fixed on the ground by expansion bolt, the support base 2 is welded on described solid
Fixed board 5, so set, convenient for fixed plate 5 and support base 2 are fixed.
The component 4 that holds out against includes top-fastening rod 401 and jacking block 402, and the top-fastening rod 401 is horizontally disposed, and passes through screw thread
It is mounted on the support base 2, one end of the top-fastening rod 401 is protruded into the mounting groove 201, and end is provided with connector
4011, the jacking block 402 is fixedly mounted on the connector 4011, so set, making convenient for by rotation top-fastening rod 401
Top-fastening rod 401 drives jacking block 402 to hold out against or loosen load cell 3.
The jacking block 402 is formed using rubber processing, so set, convenient for improving between jacking block 402 and load cell 3
Frictional force, to improve pressure, while preventing jacking block 402 really up to the mark, load cell 3 pushed up bad.
Opening width between two mounting grooves 201 is greater than the length of the load cell 3, so set, side
Just the installation of load cell 3, while the load cell 3 of different size, force-measuring sensing can be needed replacing according to actual test
Device 3 is connected to power supply by power supply line.
The load cell 3 is two-direction pull press sensor, and there are two L-types for the bottom installation of the load cell 3
Anticreep hanging plate 301, the L-type bending direction of two anticreep hanging plates 301 stretches to the bottom of the support base 2 of two sides respectively
Face.
Lifting component 6 is provided on the check weighing block 1, the lifting component 6 includes side arm 601 and lifting rod 602, described
Side arm 601 shares two, U-shaped structure is collectively formed with the lifting rod 602, and two side arms 601 are separately mounted to institute
On the front-rear side walls for stating check weighing block 1, the lifting rod 602 is located at the lower section of the load cell 3, and the lifting rod 602
It is detachably arranged on the side arm 601 by bolt, so set, when convenient for carrying out overload test to unmanned plane, in nothing
It is man-machine the check weighing block 1 is lifted up after, upward lifting power is applied to load cell 3 by lifting rod 602, to make
Pressure of the load cell 3 by opposite direction, and then quickly obtain the maximum loading amount of unmanned plane overload, while in lifting component
When 6 lifting that load cell 3 is upward, if the disengaging of load cell 3 holds out against when holding out against of component 4, anticreep hanging plate can be passed through
301 are still secured to load cell 3 on support base 2, to guarantee the accuracy of test data.
Using the above structure, the other end of the traction rope 7 is fixed on uav bottom, the weight of the check weighing block 1 and
The specification of the load cell 3 can be matched according to the model of unmanned plane, wherein the check weighing block 1 is that unmanned plane maximum is set
Loading capacity is counted, and the load cell 3 is electrically connected by signal wire with monitoring client, after the completion of apolegamy, by the force-measuring sensing
Device 3 is placed on the middle position of the mounting groove 201, is carried out using component 4 is held out against described in two sides to the load cell 3
It holds out against, then the check weighing block 1 is placed on 3 top of load cell, the test can be started, the load cell 3
Primary data is the total weight of the check weighing block 1, and unmanned plane applies the check weighing block 1 by the traction rope 7 in test process
Add lifting power upwards, to make the detection data of the load cell 3 be gradually reduced, when the detection of the load cell 3
After numerical stability, reduction amount is the loading capacity of unmanned plane, so tests the detection stability for being greatly improved test device.
Above description is only a specific implementation of the present invention, but the protection scope of the utility model is not limited to
In this, anyone skilled in the art within the technical scope disclosed by the utility model, can readily occur in variation
Or replacement, it should be covered within the scope of the utility model.Therefore, the protection scope of the utility model should be with the power
Subject to the protection scope that benefit requires.
Claims (7)
1. a kind of UAV system weight test device, it is characterised in that: including check weighing block (1), load cell (3) and fixed plate
(5), the fixed plate (5) fixes on the ground, and there are two support base (2) for setting above the fixed plate (5), and described in two
Support base (2) is oppositely arranged in sickle, is provided with mounting groove (201) in the middle part of two support bases (2), can be made described
Load cell (3) is placed among two support bases (2), is provided on the support base (2) and is held out against component (4), energy
It is enough that the load cell (3) is held out against from side；
The upper surface of the load cell (3) is higher than the upper surface of the support base (2), and the check weighing block (1) is placed on institute
It states on load cell (3), is connected with traction rope (7) above the check weighing block (1).
2. a kind of UAV system weight test device according to claim 1, it is characterised in that: the fixed plate (5) passes through swollen
Swollen bolt fixes on the ground, and the support base (2) is welded on the fixed plate (5).
3. a kind of UAV system weight test device according to claim 1, it is characterised in that: the component (4) that holds out against includes
Top-fastening rod (401) and jacking block (402), the top-fastening rod (401) is horizontally disposed, and by being threadably mounted at the support base (2)
On, one end of the top-fastening rod (401) is protruded into the mounting groove (201), and end is provided with connector (4011), the top
Block (402) is fixedly mounted on the connector (4011).
4. a kind of UAV system weight test device according to claim 3, it is characterised in that: the jacking block (402) uses rubber
Glue is process.
5. a kind of UAV system weight test device according to claim 1, it is characterised in that: two mounting grooves (201)
Between opening width be greater than the load cell (3) length.
6. a kind of UAV system weight test device according to claim 2, it is characterised in that: the load cell (3) is
Two-direction pull press sensor, and there are two the anticreep hanging plates (301) of L-type for the bottom installation of the load cell (3), described in two
The L-type bending direction of anticreep hanging plate (301) stretches to the bottom surface of the support base (2) of two sides respectively.
7. a kind of UAV system weight test device according to claim 6, it is characterised in that: be arranged on the check weighing block (1)
Have lifting component (6), the lifting component (6) includes side arm (601) and lifting rod (602), and the side arm (601) shares two
U-shaped structure is collectively formed with the lifting rod (602) in root, and two side arms (601) are separately mounted to the check weighing block
(1) on front-rear side walls, the lifting rod (602) is located at the lower section of the load cell (3), and the lifting rod (602)
It is detachably arranged on the side arm (601) by bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821329176.1U CN208704862U (en) | 2018-08-17 | 2018-08-17 | A kind of UAV system weight test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821329176.1U CN208704862U (en) | 2018-08-17 | 2018-08-17 | A kind of UAV system weight test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208704862U true CN208704862U (en) | 2019-04-05 |
Family
ID=65942483
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821329176.1U Expired - Fee Related CN208704862U (en) | 2018-08-17 | 2018-08-17 | A kind of UAV system weight test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208704862U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113218482A (en) * | 2021-06-11 | 2021-08-06 | 丰县森侠智能设备有限公司 | Unmanned aerial vehicle load capacity testboard for fire rescue |
| CN116750201A (en) * | 2023-04-25 | 2023-09-15 | 北京电子科技职业学院 | Unmanned aerial vehicle carries heavy ability testing arrangement |
-
2018
- 2018-08-17 CN CN201821329176.1U patent/CN208704862U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113218482A (en) * | 2021-06-11 | 2021-08-06 | 丰县森侠智能设备有限公司 | Unmanned aerial vehicle load capacity testboard for fire rescue |
| CN116750201A (en) * | 2023-04-25 | 2023-09-15 | 北京电子科技职业学院 | Unmanned aerial vehicle carries heavy ability testing arrangement |
| CN116750201B (en) * | 2023-04-25 | 2024-01-05 | 北京电子科技职业学院 | Unmanned aerial vehicle carries heavy ability testing arrangement |
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Legal Events
| 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: 20190405 Termination date: 20200817 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |