CN108225809A - Unmanned plane during flying performance on-ground tests system - Google Patents
Unmanned plane during flying performance on-ground tests system Download PDFInfo
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- CN108225809A CN108225809A CN201711492825.XA CN201711492825A CN108225809A CN 108225809 A CN108225809 A CN 108225809A CN 201711492825 A CN201711492825 A CN 201711492825A CN 108225809 A CN108225809 A CN 108225809A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/005—Testing of complete machines, e.g. washing-machines or mobile phones
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
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Abstract
The present invention provides a kind of unmanned plane during flying performance on-ground test system, the device for measuring properties being connect including two-axis platcform test device and with the two-axis platcform test device；The two-axis platcform test device includes turning table control mechanism and the turntable mechanism being connect with the turning table control mechanism, and the turntable mechanism is used to drive rotor wing unmanned aerial vehicle while the turning table control mechanism is additionally operable to control rotor wing unmanned aerial vehicle；The device for measuring properties includes the unmanned plane information measurement sensor being set on rotor wing unmanned aerial vehicle and the equipment data acquisition analyzing being connect with the unmanned plane information measurement sensor.Unmanned plane during flying performance on-ground provided by the invention tests system, and for the test platform that small-sized rotor wing unmanned aerial vehicle is designed, simple system, production cost is relatively low.
Description
Technical field
The present invention relates to unmanned plane technical field of measurement and test, more particularly to a kind of unmanned plane during flying performance on-ground test system.
Background technology
Small drone has the characteristics that low noise, target are small, efficiency-cost ratio is high, radar signal is weak, mobility strong, to landing
Condition limitation is small, is particularly suitable for using in particular circumstances.Wherein rotor wing unmanned aerial vehicle is even more to have obtained extensive concern and application.
For rotor wing unmanned aerial vehicle, its flying quality how is tested, it is particularly significant.
It is dangerous larger and limited by the field due to verifying that flying quality cost is higher directly on unmanned plane so that
The ground test experiment of unmanned plane is widely applied.During unmanned plane during flying being simulated by ground testing system
Various parameters, so as to be simulated to the state of flight of unmanned plane.But the ground test platform in traditional technology is mostly system
Complexity, the higher large artificial platform of production cost, there is no the experiments that the feature for small-sized rotor wing unmanned aerial vehicle is designed to put down
Platform.
Invention content
Based on this, to solve the above problems, the present invention provides a kind of unmanned plane during flying performance on-ground test system, for small
The test platform that type rotor wing unmanned aerial vehicle is designed, simple system, production cost are relatively low.
Its technical solution is as follows：
A kind of unmanned plane during flying performance on-ground tests system, including two-axis platcform test device and with two shaft rotation
The device for measuring properties of platform test device connection；
The two-axis platcform test device includes turning table control mechanism and the turntable being connect with the turning table control mechanism
Mechanism, the turntable mechanism is used to drive rotor wing unmanned aerial vehicle while the turning table control mechanism is additionally operable to control rotor wing unmanned aerial vehicle；
The device for measuring properties include being set to unmanned plane information measurement sensor on rotor wing unmanned aerial vehicle and with institute
State the equipment data acquisition analyzing of unmanned plane information measurement sensor connection.
By the way that rotor wing unmanned aerial vehicle is arranged in the two-axis platcform test device, the flight shape of rotor wing unmanned aerial vehicle is simulated
State, and the parameters of rotor wing unmanned aerial vehicle are detected and analyzed, and finally obtain rotor by the device for detecting performance
The performance of unmanned plane.Specifically, rotor wing unmanned aerial vehicle can be placed on the turntable mechanism of the two-axis platcform test device, and led to
It crosses the turning table control mechanism to control the turntable mechanism, the turntable mechanism is made to carry out two axis movements, so as to drive
Rotor wing unmanned aerial vehicle is moved, to realize the simulated flight to rotor wing unmanned aerial vehicle.In the process, the turntable control can also be passed through
Mechanism processed controls rotor wing unmanned aerial vehicle, is located at the position angle of demand.Moreover, it is set on rotor wing unmanned aerial vehicle simultaneously
A variety of unmanned plane information measurement sensors are detected the various performance parameters of the rotor wing unmanned aerial vehicle of simulated flight, and will inspection
Measurement information passes to the equipment data acquisition analyzing, and the parameters of rotor wing unmanned aerial vehicle are collected and analyzed, final
Go out the performance of rotor wing unmanned aerial vehicle.
Further technical solution is illustrated below：
Further, the electricity that the unmanned plane information measurement sensor includes being set on rotor wing unmanned aerial vehicle adjusts input electricity
Stream, voltage, motor speed measurement sensor, sextuple torque sensor and acceleration transducer.
Further, the turntable mechanism include U-shaped rack, be set on the U-shaped rack for place rotor without
Man-machine turn table body and the two axis driving mechanisms for driving the turn table body, the two axis driving mechanism with it is described
Turning table control mechanism connects.
Further, the turn table body includes the turret base being set on the U-shaped rack and is set to described
The horizontal revolving stage for being used to place rotor wing unmanned aerial vehicle in turret base；
The two axis driving mechanism includes the X-axis for being set on the U-shaped rack and being connect with turret base driving
Motor and the Y-axis driving motor for being set in the turret base and being connect with the horizontal revolving stage, the X-axis driving electricity
Machine and Y-axis driving motor are connect with the turning table control mechanism.
Further, the turntable mechanism further includes the first brake being set on the U-shaped rack and the second braking
Device, first brake is corresponding with the X-axis driving motor, and the second brake is corresponding with the Y-axis driving motor.
Further, environmental test chamber is further included, the turntable mechanism is set in the environmental test chamber.
Further, the environmental test chamber is set as blowing environmental test chamber of drenching with rain, and the turntable is accommodated including being used for
The babinet of mechanism, the spray equipment for being set to the top of the box and the blowing device for being set to the body side, it is described
Spray equipment and blowing device are corresponding with the turntable mechanism.
Further, the environmental test chamber is set as temperature humidity high integrity environmental test chamber, is accommodated including being used for
The babinet of the turntable mechanism, the height regulating frame for being used to support the turntable mechanism for being set to the bottom of box and
The temperature humidity regulating mechanism being set in the babinet.
Further, the adjusting control panel being connect with the height regulating frame and temperature humidity regulating mechanism is further included.
Further, the environmental test chamber is set as the blowing environment examination of drenching with rain with temperature humidity height adjusting function
Tryoff accommodates the babinet of the turntable mechanism, is set to the spray equipment of the top of the box and is set to institute including being used for
State the blowing device of body side, the height regulating frame for being used to support the turntable mechanism for being set to the bottom of box, with
And be set to the temperature humidity regulating mechanism in the babinet, the spray equipment and blowing device with the turntable mechanism pair
It should.
The present invention has the advantages that：Due to the centre symmetry of rotor wing unmanned aerial vehicle, pitching and rolling posture are basic
It is consistent, therefore present applicant proposes two-axis platcform test devices, compared to three-axle table test structure, can reduce equipment
Complexity, and reduce the quantity of acquisition signal, while will not be impacted again to result of the test；During to the man-machine flight of no rotor
Six-dimensional force and the data such as torque, Current Voltage measured and acquired, calculate the flight power of rotor wing unmanned aerial vehicle, so as to point
Analysis obtains the flying quality of rotor wing unmanned aerial vehicle；In addition it increases and use environment is considered, environmental test is incorporated, realize
Test under simulation use environment to unmanned plane during flying performance.
Description of the drawings
Fig. 1 is the structural schematic block diagram of the test system of unmanned plane during flying performance on-ground described in the embodiment of the present invention；
Fig. 2 be unmanned plane during flying performance on-ground described in the embodiment of the present invention test system (when setting drench with rain blowing environment
During chamber) structural schematic block diagram；
Fig. 3 is that unmanned plane during flying performance on-ground described in the embodiment of the present invention tests system (when set temperature, humidity, height
Spend combined environment test case when) structural schematic block diagram.
Reference sign：
100- two-axis platcform test devices, 110- turntable mechanisms, 112-U type racks, 113- turret bases, 114-X axis drive
Dynamic motor, 116-Y axis driving motors, the first brakes of 115-, 117- horizontal revolving stages, 120- turning table controls mechanism, 200- performances
Measuring device, 210- electricity tune input current, voltage, motor speed measurement sensor, 220- 6 DOF torque sensors, 230- accelerate
Spend sensor, 240- equipment data acquisition analyzings, 300- environmental test chambers, 302- height regulating frames, 310- spray equipments, 320-
Blowing device, 330- temperature humidity regulating mechanisms, 340- adjusting control panels.
Specific embodiment
The embodiment of the present invention is described below in detail, the example of the embodiment is shown in the drawings, wherein phase in each figure
With the identical part of label expression.The embodiments described below with reference to the accompanying drawings are exemplary, is only used for explaining this hair
It is bright, and it is not understood to limitation of the present invention.
As shown in Figure 1, the present invention proposes a kind of unmanned plane during flying performance on-ground test system, test and fill including two-axis platcform
Put 100 and the device for measuring properties 200 being connect with the two-axis platcform test device 100.By the way that rotor wing unmanned aerial vehicle is set
In the two-axis platcform test device 100, the state of flight of rotor wing unmanned aerial vehicle is simulated, and passes through the device for detecting performance
The parameters of 200 pairs of rotor wing unmanned aerial vehicles are detected and analyzed, and finally obtain the performance of rotor wing unmanned aerial vehicle.Moreover, because
The centre symmetry of rotor wing unmanned aerial vehicle, pitching and rolling posture are substantially coincident, therefore three axis (X-axis, the Y of rotor wing unmanned aerial vehicle
Axis, Z axis) movement can be reduced to two axis (X-axis, Y-axis) movement, therefore can set two-axis platcform test device to rotor nobody
Machine is tested, and can greatly simplify test device and test process.
Specifically, the two-axis platcform test device 100 include turning table control mechanism 120 and with the turning table control
The turntable mechanism 110 that mechanism 120 connects, the turntable mechanism 120 are used to drive rotor wing unmanned aerial vehicle while the turning table control machine
Structure 120 is additionally operable to control rotor wing unmanned aerial vehicle, and the turning table control mechanism 120 can be used for controlling the posture of the turntable mechanism 110
With the motor rotary speed of rotor wing unmanned aerial vehicle.Moreover, the device for measuring properties 200 includes the nothing being set on rotor wing unmanned aerial vehicle
Man-machine information measurement sensor and the equipment data acquisition analyzing 240 being connect with the unmanned plane information measurement sensor.I.e.
Rotor wing unmanned aerial vehicle can be placed on the turntable mechanism 110 of the two-axis platcform test device 100, and pass through the turning table control
Mechanism 120 controls the turntable mechanism 110, and the turntable mechanism 110 is made to carry out two axis movements (i.e. to the turntable machine
The posture of structure 110 is adjusted), rotor wing unmanned aerial vehicle can also be controlled by the turning table control mechanism 120 in the process
The rotating speed of demand is made, reached, can thus rotor wing unmanned aerial vehicle be driven to be moved, to realize the mould to rotor wing unmanned aerial vehicle
Intend flight.Moreover, a variety of unmanned plane information measurement sensors are set on rotor wing unmanned aerial vehicle simultaneously, to the rotor of simulated flight without
Man-machine various performance parameters are detected, and detection information is passed to the equipment data acquisition analyzing 240, to rotor without
Man-machine parameters are collected and analyze, and finally obtain the performance of rotor wing unmanned aerial vehicle.
Moreover, the turntable mechanism 110 includes U-shaped rack 112, it is set to being revolved for placing on the U-shaped rack 112
The turn table body of wing unmanned plane and the two axis driving mechanisms for driving the turn table body, the two axis driving mechanism with
The turning table control mechanism 120 connects.The two axis driving mechanism can be driven by the turning table control mechanism 120, so as to
The turn table body is driven to do two shaft rotations to move, so that the rotor wing unmanned aerial vehicle being placed on the turn table body does two axis fortune
It is dynamic, to simulate the state of flight of rotor wing unmanned aerial vehicle.
Further, the turn table body includes the turret base 113 being set on the U-shaped rack 112 and setting
In the horizontal revolving stage 117 for being used to place rotor wing unmanned aerial vehicle in the turret base 113.Moreover, the two axis driving mechanism packet
It includes the X-axis driving motor 114 for being set on the U-shaped rack 112 and being connect with the turret base 113 and is set to institute
The Y-axis driving motor 116 stated in turret base 113 and connect with the horizontal revolving stage 117, the X-axis driving motor 114 and Y
Axis driving motor 116 is connect with the turning table control mechanism 120.The X-axis driving motor 114 can drive the turret base
113 in X to rotation, so as to which the horizontal revolving stage 117 and rotor wing unmanned aerial vehicle be driven to be rotated in X axis, and the Y-axis driving motor
116 can drive the horizontal revolving stage 117 and rotor wing unmanned aerial vehicle to be rotated in Y-axis, so as to carry out two axis to rotor wing unmanned aerial vehicle
Driving.In addition, the turntable mechanism 110 further includes the first brake 115 being set on the U-shaped rack 112 and the second system
Dynamic device (not illustrated in figure), first brake is corresponding with the X-axis driving motor 114, the second brake and institute
Y-axis driving motor 116 is stated to correspond to.First brake can brake the X-axis driving motor 114, and described second
Brake can brake the Y-axis driving motor 116.
In addition, the electricity that the unmanned plane information measurement sensor includes being set on rotor wing unmanned aerial vehicle adjusts input current, electricity
Pressure, motor speed measurement sensor 210, sextuple torque sensor 220 and acceleration transducer 230.Pass through the unmanned plane
Information measurement sensor, can to unmanned plane electricity adjust input current, voltage, motor speed, unmanned plane generate six-dimensional force and
The parameters such as torque (lift), acceleration measure, and will measure the six-dimensional force obtained and torque, acceleration, electric current, voltage etc.
Data are transferred to the equipment data acquisition analyzing 240 and are handled and calculated, and the power of rotor wing unmanned aerial vehicle are obtained, according to power
To judge the performance of rotor wing unmanned aerial vehicle.
In addition, the unmanned plane during flying performance on-ground test system further includes environmental test chamber 300, the turntable mechanism
110 are set in the environmental test chamber 300.By setting the environmental test chamber 300, making the turntable mechanism 110 and putting
The rotor wing unmanned aerial vehicle on the turntable mechanism 110 is placed in be in the environmental test chamber 300, so as to simulate rotor nobody
Machine outdoors flight when environment so as to the test of rotor wing unmanned aerial vehicle more accurately and reliably.
Specifically, as shown in Fig. 2, in some embodiments, the environmental test chamber 300 may be configured as blowing environment of drenching with rain
Chamber, including be used to accommodating the babinet of the turntable mechanism 110, be set to the top of the box spray equipment 310 and
Be set to the blowing device 320 of the body side, the spray equipment 310 and blowing device 320 with the turntable mechanism
110 correspond to.The ambient weather that can be rained outside simulating chamber in the babinet by the shape spray 310, and filled by drying
Put 320 ambient weathers that can be blown outside simulating chamber in the babinet, thus can in the environmental test chamber 300 mould
Intend the weather blown that rains, facilitate performance of the test rotor wing unmanned aerial vehicle under this weather condition.
In addition, as shown in figure 3, in further embodiments, it is comprehensive that the environmental test chamber 300 is set as temperature humidity height
Environmental test chamber is closed, the babinet of the turntable mechanism, to be set to being used to support for the bottom of box described including being used to accommodating
The height regulating frame 302 of turntable mechanism 110 and the temperature humidity regulating mechanism 330 being set in the babinet.By described
Height regulating frame 302 can be adjusted the height and position of the turntable mechanism 110 and rotor wing unmanned aerial vehicle 10, meet different
Height detection demand.And by the temperature humidity regulating mechanism 330, the temperature and humidity in the babinet can be adjusted
It is whole, meet the detection needs under different temperatures and humidity.It is adjusted in addition, the environmental test chamber 300 is further included with the height
The adjusting control panel 340 that frame 302 and temperature humidity regulating mechanism 330 connect, can be square by the adjusting control panel 340
Just the height regulating frame 302 and temperature humidity regulating mechanism 330 are adjusted.In addition, the temperature humidity adjusts machine
Structure can be arranged on the height regulating frame 302, can save space.
In addition, in further embodiments, the environmental test chamber 300 is set as with temperature humidity height adjusting function
Blowing environmental test chamber of drenching with rain, including the babinet for being used to accommodate the turntable mechanism 110, the spray that is set to the top of the box
Shower device 310 and be set to the blowing device 320 of the body side, be set to the bottom of box be used to support institute
The temperature humidity regulating mechanism 330 stated the height regulating frame 302 of turntable mechanism 110 and be set in the babinet, the spray
Shower device 310 and blowing device 320 are corresponding with the turntable mechanism 110.I.e. in the present embodiment, can simulate rotor nobody
Machine, which is located to rain, to be scraped in wind environment, while can also be simulated rotor wing unmanned aerial vehicle and be at different height position and in not equality of temperature
It spends in humidity environment, flying quality of the test unmanned plane under integrated environment meets a variety of detection demands.
A kind of unmanned plane during flying performance on-ground test system of the present invention, has two-axis platcform test device, compared to three axis
Turntable test structure, can reduce the complexity of equipment, and reduce the quantity of acquisition signal, while will not be made again to result of the test
Into influence；The data such as six-dimensional force and torque, Current Voltage during to the man-machine flight of no rotor are measured and have been acquired, and calculate rotation
The flight power of wing unmanned plane, so as to analyze to obtain the flying quality of rotor wing unmanned aerial vehicle；In addition it increases and use environment is examined
Amount, environmental test is incorporated, and realizes the test to unmanned plane during flying performance under simulation use environment.
In addition it is also necessary to understand, in the present embodiment, term " under ", " on ", "front", "rear", "left", "right",
" interior ", " outer ", " top ", " bottom ", " side ", " opposite side ", " one end ", " other end ", etc. indicated by position relationship be based on
Position relationship shown in the drawings；The terms such as " first ", " second " are to distinguish different structure members.These terms are only
Convenient for the description present invention and simplify description, it is impossible to be interpreted as limitation of the present invention.
Each technical characteristic of embodiment described above can be combined arbitrarily, to make description succinct, not to above-mentioned reality
It applies all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, it is all considered to be the range of this specification record.
Embodiment described above only expresses the several embodiments of the present invention, and description is more specific and detailed, but simultaneously
It cannot therefore be construed as limiting the scope of the patent.It should be pointed out that those of ordinary skill in the art are come
It says, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to the protection of the present invention
Range.Therefore, the protection domain of patent of the present invention should be determined by the appended claims.
Claims (10)
1. a kind of unmanned plane during flying performance on-ground tests system, which is characterized in that including two-axis platcform test device and with institute
State the device for measuring properties of two-axis platcform test device connection；
The two-axis platcform test device includes turning table control mechanism and the turntable machine being connect with the turning table control mechanism
Structure, the turntable mechanism is used to drive rotor wing unmanned aerial vehicle while the turning table control mechanism is additionally operable to control rotor wing unmanned aerial vehicle；
The device for measuring properties include being set to unmanned plane information measurement sensor on rotor wing unmanned aerial vehicle and with the nothing
The equipment data acquisition analyzing of man-machine information measurement sensor connection.
2. unmanned plane during flying performance on-ground according to claim 1 tests system, which is characterized in that the unmanned machine information
The electricity that measurement sensor includes being set on rotor wing unmanned aerial vehicle adjusts input current, voltage, motor speed measurement sensor, six-dimensional force
Square sensor and acceleration transducer.
3. unmanned plane during flying performance on-ground according to claim 1 tests system, which is characterized in that the turntable mechanism packet
U-shaped rack is included, is set to described for the turn table body of placing rotor wing unmanned aerial vehicle and for driving on the U-shaped rack
Two axis driving mechanisms of turn table body, the two axis driving mechanism are connect with the turning table control mechanism.
4. unmanned plane during flying performance on-ground according to claim 3 tests system, which is characterized in that the turn table body packet
Include the turret base being set on the U-shaped rack and be set in the turret base for placing rotor wing unmanned aerial vehicle
Horizontal revolving stage；
The two axis driving mechanism includes the X-axis driving motor for being set on the U-shaped rack and being connect with the turret base,
And the Y-axis driving motor for being set in the turret base and being connect with the horizontal revolving stage, the X-axis driving motor and Y
Axis driving motor is connect with the turning table control mechanism.
5. unmanned plane during flying performance on-ground according to claim 4 tests system, which is characterized in that the turntable mechanism is also
Including the first brake and second brake being set on the U-shaped rack, first brake and X-axis driving electricity
Machine corresponds to, and the second brake is corresponding with the Y-axis driving motor.
6. the unmanned plane during flying performance on-ground test system according to claim 1-5 any one, which is characterized in that also wrap
Environmental test chamber is included, the turntable mechanism is set in the environmental test chamber.
7. unmanned plane during flying performance on-ground according to claim 6 tests system, which is characterized in that the environmental test chamber
Blowing environmental test chamber of drenching with rain is set as, including being used to accommodate the babinet of the turntable mechanism, being set to the top of the box
Spray equipment and the blowing device for being set to the body side, the spray equipment and blowing device with the turntable
Mechanism corresponds to.
8. unmanned plane during flying performance on-ground according to claim 6 tests system, which is characterized in that the environmental test chamber
Temperature humidity high integrity environmental test chamber is set as, including being used to accommodate the babinet of the turntable mechanism, being set to the case
The height regulating frame for being used to support the turntable mechanism of body bottom and the temperature humidity being set in the babinet adjust machine
Structure.
9. unmanned plane during flying performance on-ground according to claim 7 tests system, which is characterized in that further includes and the height
Spend adjusting bracket and the adjusting control panel of temperature humidity regulating mechanism connection.
10. unmanned plane during flying performance on-ground according to claim 6 tests system, which is characterized in that the environmental test
Case is set as the blowing environmental test chamber of drenching with rain with temperature humidity height adjusting function, and the turntable mechanism is accommodated including being used for
Babinet, be set to the spray equipment of the top of the box and be set to the body side blowing device, be set to institute
The temperature humidity tune stated the height regulating frame for being used to support the turntable mechanism of the bottom of box and be set in the babinet
Mechanism is saved, the spray equipment and blowing device are corresponding with the turntable mechanism.
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| CN109398749A (en) * | 2018-10-16 | 2019-03-01 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | A kind of unmanned plane wind resistance rain test device |
| CN109459376A (en) * | 2018-12-17 | 2019-03-12 | 西北工业大学 | Unmanned plane surface property test device |
| CN109823567A (en) * | 2019-01-04 | 2019-05-31 | 上海自图新材料科技有限公司 | The experimental rig and method of dynamic analog aircraft windward side and rotor by environmental attack |
| CN111063056A (en) * | 2019-11-21 | 2020-04-24 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Aviation accident analysis method and device, computer equipment and storage medium |
| CN111650567A (en) * | 2020-04-30 | 2020-09-11 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Comprehensive simulation test system and method for actual working conditions of phase-sweeping radar |
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