CN110282155A - Two-degree-of-freedom unmanned aerial vehicle power test system - Google Patents
Two-degree-of-freedom unmanned aerial vehicle power test system Download PDFInfo
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- CN110282155A CN110282155A CN201910594546.7A CN201910594546A CN110282155A CN 110282155 A CN110282155 A CN 110282155A CN 201910594546 A CN201910594546 A CN 201910594546A CN 110282155 A CN110282155 A CN 110282155A
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- unmanned plane
- sensor
- data acquisition
- dynamic test
- tension sensor
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- 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
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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a two-degree-of-freedom unmanned aerial vehicle power test system which comprises a power test unit, a data acquisition unit and an angle controller, wherein the power test unit and the data acquisition unit are installed on a supporting plate, the power test unit is used for testing the performance of an unmanned aerial vehicle, the angle controller is connected with the power test unit and used for controlling the tilting angle of the unmanned aerial vehicle, the data acquisition unit is used for acquiring test data of the unmanned aerial vehicle and uploading the test data to an upper computer, and the angle controller is used for controlling the tilting of the unmanned aerial vehicle at different angles and completing the test of multiple items of performance data at one time.
Description
Technical field
The present invention relates to unmanned plane dynamical system testing field, in particular to a kind of two degrees of freedom unmanned plane dynamic test system
System.
Background technique
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, is using radio robot and to provide for oneself
The not manned aircraft of presetting apparatus manipulation, or fully or intermittently automatically operated by car-mounted computer.
With the continuous development of unmanned air vehicle technique, every technology is constantly mature, promotes the performance of unmanned plane constantly to enhance, adds
Small drone have many advantages, such as it is of simple structure and low cost, easy to operate, maintenance it is simple.Unmanned plane is commonly used at present
In take photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster relief, observation wild animal, monitoring infectious disease, mapping, news
Report, electric inspection process, the disaster relief, movies-making etc. field.Heart of the unmanned plane dynamical system as unmanned plane is unmanned function
Enough normal basic guarantees for executing task, therefore possess a qualified, reliable, simple, safety unmanned plane dynamic test system
And integrated data acquisition system is just particularly important.
Currently there are unmanned plane dynamic test system, it is most of that can only to test out unmanned plane dynamical system single
The data of aspect, such as pulling force, cannot systematically measure cannot comprehensively reflect unmanned plane dynamical system geological measuring and performance, and
And unmanned plane dynamical system of the most test macro both for single-degree-of-freedom in the market.Such as Publication No.
CN108845256A, the patent of invention of entitled " unmanned plane dynamic test system ", which disclose a kind of unmanned mechanomotive forces
Test macro, including measurement and control instrument, the measurement and control instrument are connect with laser sensor, and the measurement and control instrument is mounted on dynamic test rack
On；Laser sensor is mounted on dynamic test rack front end, and is located at the unmanned electromechanics being mounted on the dynamic test rack
The lower end of machine, the laser sensor are used to acquire the testing number of corresponding unmanned plane motor speed.Two to be verted based on motor
The current still blank of the unmanned plane dynamic test system of freedom degree, particularly with tilting rotor wing unmanned aerial vehicle, motor different angle is inclined
Turn very big on aircraft stress condition and posture change influence, therefore the dynamical system of two degrees of freedom test is extremely important, only
Dynamical system is safe and reliable, can just UAV system be made to execute task with security and stability.
Summary of the invention
For technical problem of the existing technology, the present invention provides a kind of two degrees of freedom unmanned plane dynamic test system,
It realizes that control unmanned plane verts different angle by angle controller, and realizes that unmanned plane dynamical system carries out multinomial performance data
Test.
In order to solve the above technical problems, the invention adopts the following technical scheme:
A kind of two degrees of freedom unmanned plane dynamic test system, including dynamic test unit, data acquisition unit, angle controller,
On the supporting plate, the dynamic test unit is for testing unmanned plane for the dynamic test unit and data acquisition unit installation
Performance, the angle controller are connected with dynamic test unit, and for controlling the tilt angle of unmanned plane, the data acquisition is single
Member is uploaded to host computer for acquiring unmanned plane test data.
As a further improvement of the present invention: the dynamic test unit includes connecting plate, rotary shaft, slide plate, the first cunning
Dynamic component, the second slide assemblies, the first tension sensor and the second tension sensor, the connecting plate for connect unmanned plane and
Dynamic test unit, the connecting plate are connected with angle controller, and the connecting plate and angle controller are set in the rotation
On axis, the rotary shaft is installed on first slide assemblies, and first slide assemblies are slided by slide plate and described second
Dynamic component is connected, and first tension sensor one end is connect with the slide plate, the first tension sensor other end and institute
Rotary shaft is stated to be connected；Second tension sensor one end is connect with the slide plate, and the second tension sensor other end is logical
It crosses connector and the support plate is affixed.
As a further improvement of the present invention: first slide assemblies include the first sliding block and the first sliding rail, and described the
One sliding rail vertical symmetry is arranged on the slide plate, is equipped with the first sliding block on two first sliding rails, and described two first
Sliding block is connected by rotary shaft.
As a further improvement of the present invention: second slide assemblies include the second sliding block, the second sliding rail and sliding rail branch
Support, second sliding rail are arranged in the support plate by the slideway carriage Parallel Symmetric, two second cunnings
The second sliding block is equipped on rail, the slide plate is mounted on described two second sliding blocks.
As a further improvement of the present invention: the connector is connecting angle iron.
As a further improvement of the present invention: the data acquisition unit includes tension sensor amplifier and data acquisition
Plate, the tension sensor amplifier are connect with the first tension sensor and the second tension sensor, for receiving the first pulling force
Sensor and the electric signal of the second tension sensor are simultaneously delivered to data acquisition board after amplifying signal.
As a further improvement of the present invention: the data acquisition unit further includes first sensor, second sensor,
Three sensors, be respectively used to acquisition unmanned plane speed change when electric current, voltage and motor rotations test data.
As a further improvement of the present invention: the data acquisition board is arranged in the data acquisition unit, for adopting
Collection integrates the survey of first tension sensor, the second tension sensor, first sensor, second sensor, 3rd sensor
Examination data are simultaneously uploaded to host computer.
Compared with the prior art, the advantages of the present invention are as follows:
1, the present invention is the unmanned dynamic test system based on Unmanned Aerial Vehicle Powerplants two degrees of freedom, is applicable not only to single-degree-of-freedom
Unmanned plane, moreover it is possible to meet the power device performance test of rotor wing unmanned aerial vehicle, it is applied widely, it is real to pass through setting angle controller
The tilt angle control of existing Unmanned Aerial Vehicle Powerplants, more true simulation rotor wing unmanned aerial vehicle actual flight state, can more comprehensively, it is quasi-
Really, the performance of Unmanned Aerial Vehicle Powerplants is objectively tested out.
2, the present invention can disposably acquire pulling force, the electricity of power device by the way that multiple sensors, data acquisition unit is arranged
The multiple test datas of stream, voltage, revolving speed realize that unmanned plane dynamical system quality and performance are tested comprehensively, improve performance test
Reliability and comprehensive, it is ensured that power device is safe and reliable, improves the reliability and stability of entire unmanned plane during flying.
Detailed description of the invention
Fig. 1 is schematic perspective view of the present invention in concrete application embodiment；
Fig. 2 is the decomposition diagram of present invention data acquisition unit in concrete application embodiment；
Marginal data:
1, data acquisition unit；111, tension sensor amplifier；112, data acquisition board；113, first sensor；114,
Two sensors；2, angle controller；3, support plate；4, connecting plate；5, rotary shaft；6, slide plate；7, the first slide assemblies；71,
One sliding block；72, the first sliding rail；8, the second slide assemblies；81, the second sliding block；82, the second sliding rail；83, slideway carriage；9,
One tension sensor；10, the second tension sensor；11, connector.
Specific embodiment
The present invention is described in further details below with reference to Figure of description and specific embodiment.
As shown in Figure 1 and Figure 2, one of the present embodiment two degrees of freedom unmanned plane dynamic test system, including dynamic test
Unit, data acquisition unit 1 and angle controller 2, dynamic test unit and data acquisition unit 1 are mounted in support plate 3, are moved
Power test cell is used to test the performance of unmanned plane, and angle controller 2 is connected with dynamic test unit, for controlling unmanned plane
Tilt angle, data acquisition unit 1 are delivered to host computer for acquiring unmanned plane test data.Due to the difference of unmanned plane during flying
Angle verts to change aircraft stress condition and posture and influences greatly, to be able to achieve in the present embodiment by the way that angle controller 2 is arranged
Control rotor wing unmanned aerial vehicle vert at 0 °~90 °, more really simulation rotor wing unmanned aerial vehicle actual flight state, can more comprehensively,
Accurately, the performance of Unmanned Aerial Vehicle Powerplants is objectively tested out.
In the present embodiment, dynamic test unit includes connecting plate 4, rotary shaft 5, slide plate 6, the first slide assemblies 7, second cunning
Dynamic component 8, the first tension sensor 9 and the second tension sensor 10, connecting plate 4 is for connecting unmanned plane and dynamic test list
Member, connecting plate 4 are connected with angle controller 2, and connecting plate 4 and angle controller 2 are set in rotary shaft 5, and rotary shaft 5 is installed in
On first slide assemblies 7, the first slide assemblies 7 are connected by slide plate 6 with the second slide assemblies 8,9 one end of the first tension sensor
It is connect with slide plate 6,9 other end of the first tension sensor is connected with rotary shaft 5；Second tension sensor, 10 one end and slide plate 6 connect
It connects, 10 other end of the second tension sensor is affixed by connector 11 and support plate 3.
In preferred embodiments, the first slide assemblies 7 include the first sliding block 71 and the first sliding rail 72, and the first sliding rail 72 is vertical
It being symmetricly set on slide plate 6, the first sliding rail 72 is two, it is equipped with the first sliding block 71 on two first sliding rails 72, two first
Sliding block 71 is connected by rotary shaft 5；Second slide assemblies 8 include the second sliding block 81, the second sliding rail 82 and slideway carriage 83, the
Two sliding rails 82 are arranged in support plate 3 by 83 Parallel Symmetric of slideway carriage, and the second sliding rail 82 is two, two second sliding rails
The second sliding block 81 is equipped on 82, slide plate 6 is mounted on two the second sliding blocks 81；In a preferred embodiment, connector 11 is to connect
Connect angle bar.
When concrete application, when power device (such as motor or internal combustion engine) the rotation drive propeller rotational of unmanned plane, thus
Generation and power device axis pulling force in the same direction, since Unmanned Aerial Vehicle Powerplants are connect by connecting plate 4 with dynamic test unit, therefore
The pulling force of generation can be transmitted to connecting plate 4, and pulling force is decomposed into component vertically and horizontally, the component band of vertical direction
Dynamic rotary shaft 5 and the first sliding block 71 move straight up along the first sliding rail 72, so that the deformation of the first tension sensor 9 produces
A raw electric signal；Component drive slide plate 6, the second sliding block 81 of horizontal direction make the movement of horizontal direction along the second sliding rail 82,
So that the deformation of the second tension sensor 10 generates an electric signal；Two electric signals are exported to data acquisition unit 1, are led to
Host computer is uploaded to after crossing integration.
In the present embodiment, data acquisition unit 1 includes tension sensor amplifier 111 and data acquisition board 112, and pulling force passes
Sensor amplifier 111 is electrically connected with the first tension sensor 9 and the second tension sensor 10, for receiving the first tension sensor
9 and second tension sensor 10 electric signal and be delivered to data acquisition board 112 after amplifying signal.
In the present embodiment, data acquisition unit 1 further includes first sensor 113, second sensor 114 and third sensing
Device, be respectively used to acquisition unmanned plane speed change when electric current, voltage and motor rotations test data.
Data acquisition board 112 is arranged in data acquisition unit 1, when the first tension sensor 9 and the second tension sensor
When 10 deformation generate electric signal, it is transferred to data acquisition board 112, the first pull sensing of integration is acquired by data acquisition board 112
Device 9, the second tension sensor 10, first sensor 113, second sensor 114, the test data of 3rd sensor are simultaneously uploaded to
Host computer.Data acquisition unit 1 can disposably acquire the multiple test datas of pulling force, electric current, voltage, revolving speed of power device, real
Existing unmanned plane dynamical system quality and performance are tested comprehensively, improve the reliability of performance test and comprehensive, it is ensured that power dress
It sets securely and reliably, improves the reliability and stability of entire unmanned plane during flying.
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 protection of the invention
Range.
Claims (8)
1. a kind of two degrees of freedom unmanned plane dynamic test system, which is characterized in that including dynamic test unit, data acquisition unit
(1) it is mounted on support plate (3) with angle controller (2), the dynamic test unit and data acquisition unit (1), it is described dynamic
Power test cell is used to test the performance of unmanned plane, and the angle controller (2) is connected with dynamic test unit, for controlling nothing
Man-machine tilt angle, the data acquisition unit (1) are uploaded to host computer for acquiring unmanned plane test data.
2. two degrees of freedom unmanned plane dynamic test system according to claim 1, which is characterized in that the dynamic test list
Member includes connecting plate (4), rotary shaft (5), slide plate (6), the first slide assemblies (7), the second slide assemblies (8), the first pulling force biography
Sensor (9) and the second tension sensor (10), the connecting plate (4) is for connecting unmanned plane and dynamic test unit, the company
Fishplate bar (4) is connected with angle controller (2), and the connecting plate (4) and angle controller (2) are set on the rotary shaft (5),
The rotary shaft (5) is installed on first slide assemblies (7), first slide assemblies (7) by slide plate (6) with it is described
Second slide assemblies (8) are connected, and described first tension sensor (9) one end is connect with the slide plate (6), and first pulling force passes
Sensor (9) other end is connected with the rotary shaft (5)；Described second tension sensor (10) one end is connect with the slide plate (6),
Second tension sensor (10) other end is connect by connector (11) with the support plate (3).
3. two degrees of freedom unmanned plane dynamic test system according to claim 2, which is characterized in that first Slide Group
Part (7) includes the first sliding block (71) and the first sliding rail (72), and the first sliding rail (72) vertical symmetry is arranged in the slide plate (6)
On, it is equipped with the first sliding block (71) on two first sliding rails (72), described two first sliding blocks (71) pass through rotary shaft (5)
It is connected.
4. two degrees of freedom unmanned plane dynamic test system according to claim 2, which is characterized in that second Slide Group
Part (8) includes that the second sliding block (81), the second sliding rail (82) and slideway carriage (83), second sliding rail (82) pass through the cunning
Rail support frame (83) Parallel Symmetric is arranged on the support plate (3), and it is sliding that second is equipped on two second sliding rails (82)
Block (81), the slide plate (6) are mounted on described two second sliding blocks (81).
5. two degrees of freedom unmanned plane dynamic test system according to claim 2, which is characterized in that the connector (11)
For connecting angle iron.
6. two degrees of freedom unmanned plane dynamic test system described in -5 any one according to claim 1, which is characterized in that described
Data acquisition unit (1) includes tension sensor amplifier (111) and data acquisition board (112), the tension sensor amplification
Device (111) is connect with the first tension sensor (9) and the second tension sensor (10), for receiving the first tension sensor (9)
Data acquisition board (112) are delivered to after amplifying with the electric signal of the second tension sensor (10) and by signal.
7. two degrees of freedom unmanned plane dynamic test system described in -5 any one according to claim 1, which is characterized in that described
Data acquisition unit (1) further includes first sensor (113), second sensor (114) and 3rd sensor, is respectively used to acquire
The test data of electric current, voltage and motor rotations when unmanned plane speed change.
8. two degrees of freedom unmanned plane dynamic test system according to claim 6, which is characterized in that the data acquisition board
(112) setting is in the data acquisition unit (1), and for acquiring integration first tension sensor (9), the second pulling force passes
Sensor (10), first sensor (113), second sensor (114), the test data of 3rd sensor are simultaneously uploaded to host computer.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910594546.7A CN110282155B (en) | 2019-07-03 | 2019-07-03 | Two-degree-of-freedom unmanned aerial vehicle power test system |
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| CN201910594546.7A CN110282155B (en) | 2019-07-03 | 2019-07-03 | Two-degree-of-freedom unmanned aerial vehicle power test system |
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| CN110282155A true CN110282155A (en) | 2019-09-27 |
| CN110282155B CN110282155B (en) | 2020-10-16 |
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| CN110282155B (en) | 2020-10-16 |
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