CN109305389A - Power grid unmanned plane aerodynamic system detection platform - Google Patents
Power grid unmanned plane aerodynamic system detection platform Download PDFInfo
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- CN109305389A CN109305389A CN201811068144.5A CN201811068144A CN109305389A CN 109305389 A CN109305389 A CN 109305389A CN 201811068144 A CN201811068144 A CN 201811068144A CN 109305389 A CN109305389 A CN 109305389A
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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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Abstract
The invention discloses a kind of power grid unmanned plane aerodynamic system detection platforms, the platform includes host, display module and testboard bay, the aerodynamic system is mounted on testboard bay and controls it by host and runs according to setup parameter, the laser sensor of the revolving speed for obtaining propeller and the shock sensor of the vibration coefficient for obtaining the aerodynamic system are installed on the testboard bay, it further include the weight sensor of the pulling force for obtaining aerodynamic system generation or thrust and the temperature sensor of the temperature for obtaining the aerodynamic system, the laser sensor, shock sensor, weight sensor and temperature sensor are all connected with host；Host obtains test data by each sensor, handles and obtain the properties of the aerodynamic system.Unmanned plane aerodynamic system test platform of the present invention integrates a variety of test functions, and test operation is simple, safe, more automation, intelligence.
Description
Technical field
The present invention relates to a kind of power grid unmanned plane aerodynamic system detection platforms.
Background technique
Common flight device dynamical system detection platform is mostly integral type, easy mutual shadow between each equipment therein and sensor
It rings and forms error, process is complicated when failure is difficult to clear failure point, maintenance is torn open group.
In the industry now until be all using the raw mode of DC power supply and electronic scale test dynamical system, this test side
There is only the problems such as complicated for operation, reading is unstable, testing efficiency is low for formula, but also threaten and operate in default of preventive means
The personal safety of personnel.
Secondly, the matching of the dynamical system of unmanned plane and aviation model field is always to perplex numerous practitioners and fan
Primary problem.
Summary of the invention
The present invention provides a kind of power grid unmanned plane aerodynamic system detection platforms, and which overcome described in background technique
The deficiencies in the prior art.
The technical solution adopted by the present invention to solve the technical problems is:
Power grid unmanned plane aerodynamic system detection platform, the aerodynamic system include the mechanical, electrical tune of electricity, propeller and confession
Power supply；It is characterized by: the platform includes host, display module and testboard bay, which is mounted on test
On rack and it is controlled by host to run according to setup parameter, and the revolving speed for obtaining propeller is installed on the testboard bay
The shock sensor of laser sensor and the vibration coefficient for obtaining the aerodynamic system, cuts laser by propeller
The laser beam that sensor issues obtains the revolving speed of propeller, further includes pulling force for obtaining aerodynamic system generation or pushes away
The temperature sensor of the weight sensor of power and the temperature for obtaining the aerodynamic system, the laser sensor, vibration pass
Sensor, weight sensor and temperature sensor are all connected with host；Host obtains test data by each sensor, handles and obtains
The properties of the aerodynamic system out.
Among one embodiment: the host is equipped with the quasi- test module of electric adjustment, is arranged by the quasi- test module of the electricity adjustment defeated
The duration that voltage, the electric punctual full throttle of adjustment export out, realizes that electricity is adjusted at the duration of the electric punctual zero throttle output of adjustment
Calibration.
Among one embodiment: the host is equipped with throttle test module, and test voltage, defeated is arranged by the throttle test module
The testing time of the throttle terminal of throttle starting point, output out, throttle step value and each throttle point, and then it is dynamic to obtain the air
The characteristic curve of parameters of the Force system within the scope of the setting throttle under the test voltage point.
Among one embodiment: the host is equipped with voltage test module, and test throttle, defeated is arranged by the voltage test module
The testing time of the voltage terminal of voltage starting point, output out, voltage steps value and each electrical voltage point, and then it is dynamic to obtain the air
The characteristic curve of Force system parameters in the full voltage range under the test throttle point.
Among one embodiment: the host is equipped with distance test module, passes through the fixed survey of distance test module setting one
Try voltage, a fixed test throttle, apart from starting point, apart from step value, the testing time apart from terminal and each range points, into
And obtain in coaxial system the characteristic curve of parameters when different distance between two motors.
Among one embodiment: the host is equipped with manual test module, which includes regulated power supply and remote control
Device, manually adjusts output voltage by the regulated power supply, manually adjusts output throttle by remote controler.
Among one embodiment: the host is equipped with integration test module, and test voltage, oil is arranged by the integration test module
The testing time of door starting point 0%, the throttle terminal 100% of output, throttle step value and each throttle point, and then obtain the air
The characteristic curve of parameters of the dynamical system within the scope of the full throttle under the test voltage point.
Among one embodiment: the host is equipped with vibration test module, which is obtained by the shock sensor
The aerodynamic system X-axis, the vibration data of Y-axis and Z axis, calculate separately in data area X axis, Y-axis and Z axis
The dispersion degree of vibration data, so that vibration coefficient of the entire unmanned plane dynamical system respectively on X axis, Y-axis and Z axis is obtained,
Total vibration coefficient of the unmanned plane dynamical system is obtained after vibration coefficient summation on X-axis, Y-axis and Z axis is averaged.
Among one embodiment: the host is equipped with optimum efficiency test module, and the optimum efficiency test module is empty by control
The throttle of pneumatic power system is from starting point 0% to throttle terminal 100%, to measure the pulling force of aerodynamic system and the function of motor
Rate is calculated the power effect of unmanned plane, using the data of aerodynamic system throttle as abscissa, draws out respectively in same plane
Power effect and two curves of pulling force, the point of intersection of two curves is the best efficiency point of the aerodynamic system.
Among one embodiment: the host is equipped with optimal combination test module, which passes through fixed electricity
Machine and electricity adjust model, measure respectively different model propeller arrange in pairs or groups the motor and electricity adjust, under different throttle supply values should
The pulling force that aerodynamic system generates, to show that the mechanical, electrical best applications for reconciling propeller of electricity combine.
Among one embodiment: the host is equipped with conformity testing module, which passes through test same motor, electricity
Adjust, the aerodynamic system of propeller is under equal-wattage, whether the thrust deflexion that motor positive and inverse generates is more than given threshold
It is whether qualified to screen the aerodynamic system.
Among one embodiment: including two temperatures sensor, one temperature sensor is used to obtain the real time temperature of electricity tune, separately
One temperature sensor is used to obtain the real time temperature of motor.
The technical program compared with the background art, it has the following advantages:
1, with Split module, (each sensor is independently installed on testboard bay, and the survey that will respectively obtain respectively
Trial signal is sent to host) assembling test platform, it avoids interacting and overhaul difficulty between integration apparatus.
2, revolving speed is tested in such a way that propeller cuts laser rays, equipment attrition, sensor sensitivity difference is avoided to make
At test error.
3, weight sensor and Shock inductor are directly connected with testboard bay, test and miss caused by avoiding compartment from conducting
Difference.
4, temperature sensor is added, the variation of real-time monitoring running temperature, is conducive to assessment equipment situation and protection test is flat
Platform promotes security performance.
5, aerodynamic system is controlled by host to run according to setup parameter, then test number is obtained by each sensor
According to, and be sent on host and handle, then shown by display module, the test operation simplicity, stable reading, testing efficiency
Height, and personnel safety of the entire test process without personnel close to unmanned plane aerodynamic system, when guarantee is tested.
6, this test platform passes through the throttle for controlling aerodynamic system from starting point 0% to throttle terminal 100%, to measure
The power effect of unmanned plane is calculated, with the data of aerodynamic system throttle in the pulling force of aerodynamic system and the power of motor
For abscissa, power output effect and two curves of pulling force are drawn in same plane respectively, the point of intersection for obtaining two curves as should
The best efficiency point of aerodynamic system；The model adjusted by fixed motor and electricity, the propeller for measuring different model respectively are taken
It is adjusted with the motor and electricity, the pulling force that the aerodynamic system generates under different throttle supply values, obtains the mechanical, electrical reconciliation spiral of electricity
The best applications of paddle combine；Realize the matching test of unmanned plane dynamical system.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and examples.
Fig. 1 is the structural schematic diagram of power grid unmanned plane aerodynamic system detection platform described in the present embodiment.
Fig. 2 is the system block diagram of power grid unmanned plane aerodynamic system detection platform described in the present embodiment.
Fig. 3 is in a preferred embodiments, and optimum efficiency test module carries out the power effect and pull-up curve figure that test obtains.
Fig. 4 is the power graph of motor in each combination that optimal combination test module obtains in a specific application example.
Fig. 5 is the aerodynamic system thrust respectively combined that optimal combination test module obtains in a specific application example
Curve graph.
Specific embodiment
Fig. 1 and Fig. 2, power grid unmanned plane aerodynamic system detection platform are please referred to, which includes electricity
Machine 10, electricity adjust 20, propeller 30 and power supply；The platform includes host 101, display module 102 and testboard bay 103, is somebody's turn to do
Aerodynamic system is mounted on testboard bay 103 and controls it by host 101 and runs according to setup parameter, the testboard bay
The laser sensor 104 of the revolving speed for obtaining propeller 30 and the shake for obtaining the aerodynamic system are installed on 103
The shock sensor 105 of dynamic coefficient cuts the laser beam that laser sensor 104 issues by propeller 30 to obtain propeller
30 revolving speed, further include for obtain the aerodynamic system generation pulling force or thrust weight sensor 106 and for obtaining
The temperature sensor 107 of the temperature of the aerodynamic system is taken, the laser sensor 104, shock sensor 105, weight sensing
Device 106 and temperature sensor 107 are all connected with host；Host 101 obtains test data by each sensor, handles and obtains
The properties of the aerodynamic system.
In the present embodiment, including two temperatures sensor, one temperature sensor is used to obtain the real time temperature of electricity tune, another
Temperature sensor is used to obtain the real time temperature of motor；The shock sensor 105 is located at the lower part of testboard bay 103, the weight
Sensor 107 is set on the electrode, which is liquid crystal display.
101 machine of master is equipped with the quasi- test module of electric adjustment, output voltage is arranged by the quasi- test module of the electricity adjustment, electricity is adjusted
The duration that full throttle exports when calibration, realizes that electric adjustment is quasi- at the duration of the electric punctual zero throttle output of adjustment." electricity is adjusted
The effect of calibration " is to adjust stroke to be calibrated to full throttle section electricity to have preferable response.It calibrates effect and depends on electricity tune itself
Characteristic, the quasi- effect of the electric adjustment of each brand or model can be variant.
Display module 102 is equipped with the parameter input window of electric adjustment standard, input window comprising voltage, high level time and
Three kinds of low level time: the voltage of window refers to the output voltage of the punctual equipment of electric adjustment, generally electric with the power supply of real system
Press identical, for example, by using the power supply system of 6S, which is just set as 22.2V；The high level time of window refers to electric tune
It the duration that full throttle exports when calibration, is typically chosen 3 seconds, but the time required for the electricity tune of each model, there is differences
Different, should specifically inquire the offer of electricity Tiao manufacturer illustrates document；The low level time of window refers to that punctual zero throttle of electric adjustment is defeated
It is duration out, general to select 3 seconds, but each model electricity tune required time there are variant, should specifically inquire electricity
That adjusts manufacturer's offer illustrates document.The parameters such as voltage, high level and low level are being set, and are guaranteeing system hardware connection just
It, can " RUN " button in window after really errorless.
The host 101 is equipped with throttle test module, and a test voltage (fixed voltage is arranged by the throttle test module
Point), the throttle starting point of output, the throttle terminal of output, throttle step value and each throttle point testing time, and then be somebody's turn to do
The characteristic curve of parameters of the aerodynamic system within the scope of the setting throttle under the test voltage point.
Display module 102 is equipped with the parameter input window of throttle test module, and input window includes voltage, throttle
The time of point, throttle terminal, throttle stepping and single-point: voltage is the test voltage tested under " throttle test " mode,
Such as the voltage of 6S power supply system may be configured as 22.2V, while can also in system power supply voltage range the several voltages of more options
Point does multiple test；The throttle starting point of equipment output when throttle starting point is throttle test；Equipment when throttle terminal is throttle test
The throttle terminal of output pays particular attention to the power limit that whether can exceed system under test (SUT) when inputting this parameter, therefore can be with
It first carries out manual test and measures limit throttle value of the system under test (SUT) under current voltage, is i.e. throttle tests end point values；Throttle stepping
The throttle step value of equipment output when being throttle test, this numerical value is smaller, and it is more accurate to test resulting result；The single-point time is oil
In the testing time of each throttle point when gate test, this numerical value is smaller, and it is more accurate to test resulting result.Ensuring data input
START button is clicked after the connection of errorless and system hardware is correct to be tested.
The host 101 is equipped with voltage test module, and a test throttle (fixed throttle is arranged by the voltage test module
Point), the voltage starting point of output, the voltage terminal of output, voltage steps value and each electrical voltage point testing time, and then be somebody's turn to do
The characteristic curve of aerodynamic system parameters in the full voltage range under the test throttle point.
Display module 102 is equipped with the parameter input window of voltage test module, and input window includes input throttle, voltage
Five parameters such as starting point, voltage terminal, voltage steps and single-point time, wherein throttle refers to the test oil for the fixation tested
Door, can do multiple test by the several throttle points of more options in system power allowed band；Voltage starting point is set when referring to voltage tester
The voltage starting point of standby output；The voltage terminal that equipment exports when voltage terminal refers to voltage tester, needs spy when inputting this parameter
It is not noticed that whether that the power limit of system under test (SUT) can be exceeded, therefore can first carry out manual test and measure system under test (SUT) in current oil
Extreme voltage values under door, i.e. voltage tester end point values；The voltage steps value that equipment exports when voltage steps refer to voltage tester,
This numerical value is smaller, and it is more accurate to test resulting result；In the testing time of each test point when the single-point time refers to voltage tester,
This numerical value is smaller, and it is more accurate to test resulting result.
The host 101 be equipped with integration test module, by the integration test module be arranged test voltage, throttle starting point 0%,
The testing time of the throttle terminal 100% of output, throttle step value and each throttle point, and then obtain the aerodynamic system and exist
The characteristic curve of the parameters within the scope of full throttle under the test voltage point.
The host 101 is equipped with distance test module, is consolidated by the fixed test voltage of distance test module setting one, one
Fixed test throttle, apart from starting point, apart from step value, the testing time apart from terminal and each range points, and then obtain coaxial
In system between two motors when different distance parameters characteristic curve.
Wherein the several test voltages of more options multiple test can be done in system power supply voltage range；It can also be in system function
The several test throttles of more options do multiple test in rate allowed band, pay particular attention to the power that whether can exceed system under test (SUT)
The limit；Refer to the distance test starting point between two motors apart from starting point；Refer to the distance test terminal between two motors apart from terminal,
Need to pay special attention to whether first system can be gone out with dipstick metering beyond equipment apart from stroke when parameter input window inputs this parameter
Available travel after used again using this numerical value as apart from end point values；The distance of equipment output when referring to distance test apart from stepping
Step value, general minimum select 5mm or so, this value is smaller, and test result is more accurate.Testing time value per each range points is bigger,
Test result is more accurate.
The host is equipped with manual test module, which includes regulated power supply and remote controler, adjustable by this
Power supply manually adjusts output voltage, manually adjusts output throttle by remote controler, to obtain the items of the aerodynamic system
Performance parameter.
The host 101 is equipped with vibration test module, and the most important vibration source of high-tension line unmanned plane comes from as driving
The motor in source, the structure of rack and propeller.When the motor rotates, vibration is generated due to unbalance dynamic.It should be noted that
It is that each motor and propeller have fine distinction, therefore at work, the revolving speed of each motor of multi-rotor unmanned aerial vehicle also has
Fine distinction.The vibration of different motors can be overlapped mutually on more rotors, and the distance between adjacent two-arm motor is smaller, holds very much
It is also easy to produce interplane interference.Different multi-rotor unmanned aerial vehicle architectural differences is larger, and the material that uses, motor, load are also different,
The general Theory of Vibration being all suitable for all structures is substantially absent.Therefore the structure different for every kind of unmanned plane is needed
Feature makees independent analysis.
The vibration coefficient data table of all types of dynamical systems of table 1 combination
The vibration test module obtains the vibration number of the aerodynamic system X-axis, Y-axis and Z axis by the shock sensor
According to the dispersion degree of the vibration data of X-axis, Y-axis and Z axis in the data area being calculated separately, to obtain entire unmanned plane
Vibration coefficient summation on X-axis, Y axis and Z axis is averaged by the dynamical system vibration coefficient on X-axis, Y-axis and Z axis respectively
Total vibration coefficient of the unmanned plane dynamical system is obtained after value.
The selection of the unmanned plane aerodynamic system composite type of the table 1 be according to control unitary variant obtained from, than
The mechanical, electrical tune of electricity of such as fixed same type, changes the model of propeller, then compares the vibration coefficient of this group, obtains vibration system
The smallest dynamical system matched combined of number.It is available from table 1: to be that grace road 5008 and electricity adjust model in fixed motor model
HW50A, can get the smallest vibration coefficient when changing the blast 1660 of propeller model is 0.0327；With the spiral of blast 1660
The electricity of paddle type number and HW50A adjust model, and the smallest vibration coefficient can be obtained after motor model is T-MOTOR5212 by, which changing, is
0.132；With the propeller model of blast 1660 and the motor model of T-MOTOR5212, change the model that electricity is adjusted, it is final to obtain most
The electricity that smaller tremors coefficient is 0.0132 adjusts model HW50A.
The host 101 is equipped with optimum efficiency test module, because the power effect of unmanned plane is bigger, corresponding efficiency is got over
Height, therefore the best efficiency point for finding unmanned plane dynamical system needs to know power effect (g/W) data of unmanned plane.The best effective
Rate test module passes through the throttle of control aerodynamic system from starting point 0% to throttle terminal 100%, to measure air force
The power effect of unmanned plane is calculated in the pulling force of system and the power of motor, using the data of aerodynamic system throttle as abscissa,
Power output effect and two curves of pulling force are drawn in same plane respectively, the point of intersection of two curves is the aerodynamic system
Best efficiency point.
By a preferred embodiments analyze, obtain Fig. 3 power effect and pull-up curve figure, can obtain: power effect curve be first in sharply on
The trend of liter, it is 12.52 (g/W) that highest point is reached when throttle is 38%, occurs gentle downward trend later.Therefore, if
When unmanned plane will obtain maximum efficiency, it should take throttle when 38%.But pass through an other curve -- pulling force
(g) curve is can be found that: under identical throttle parameter, the pulling force of unmanned plane still belongs to reduced levels, only 384 (g) at this time,
Whole unmanned plane can not be even set to take off.So parameter set by throttle is unable to satisfy requirement at this time, even if unmanned plane at this time
Efficiency reach maximum, but unmanned plane can not take off.By Fig. 3 can look for obtain power imitate curve and pull-up curve throttle about
An intersection point is produced when being 77%.Power effect at this time is 8.48 (g/W), pulling force is 1966 (g), in the drone status of the point
, pulling force higher in efficiency is enough a series of state for supporting whole unmanned plane to carry out aerial operations.
To sum up, the best efficiency point of unmanned plane dynamical system appearance when controlling throttle (%) parameter and being about 77%.
The host 101 is equipped with optimal combination test module, when seeking the optimal combination of the mechanical, electrical tune of electricity and propeller,
The optimal combination test module passes through the model that fixed motor and electricity are adjusted, and the propeller for measuring different model respectively is arranged in pairs or groups the motor
It is adjusted with electricity, the pulling force that the aerodynamic system generates under different throttle supply values, to obtain the mechanical, electrical reconciliation propeller of electricity
Best applications combination.
In one specific application example, then the model that fixed motor and electricity are adjusted selects the propeller of different model, including mad
The propeller of 5 models such as wind 1450, blast 1555, blast 1660, blast 1760 and blast 1865 is tested, and is tested
The power of motor and the dynamical system thrust of the combination are obtained as shown in Fig. 4, Fig. 5.
At this point, if the power of fixed motor is 100W, can be obtained in Fig. 4 propeller model blast 1450,
Unmanned plane throttle value under blast 1555, blast 1660, blast 1760 and blast 1865 respectively may be about 73%, 61%, 55%,
52% and 51%, the thrust that can get the corresponding generation of unmanned plane dynamical system from Fig. 5 is 870g, 963g, 996g, 1079g
And 1119g.
It can analyze to obtain according to the data of specific throttle and thrust under above-mentioned figure and same power: propeller
The throttle value of unmanned plane required for the dynamical system of model blast 1865 combines is minimum and the thrust that generates reaches maximum,
Therefore same motor can be obtained and electricity is adjusted, the group of the unmanned plane aerodynamic system of propeller model blast 1865 is combined into most
Good combination.
The host 101 is equipped with conformity testing module, which passes through test same motor, electricity tune, propeller
Aerodynamic system under equal-wattage, motor positive and inverse generate thrust deflexion whether be more than given threshold to screen the sky
Whether pneumatic power system is qualified, if deviation indicates qualified without departing from given threshold, conversely, indicating unqualified.
It is above-mentioned be related to test parameter setting and analysis result curve, chart respectively can be inputted by the parameter of display module
Window setting is shown with window as the result is shown, simple and clear.
Unmanned plane aerodynamic system test platform of the present invention integrates a variety of test functions, test operation letter
Single, safety, more automation, intelligence.
The above is only the preferred embodiment of the present invention, the range implemented of the present invention that therefore, it cannot be limited according to, i.e., according to
Equivalent changes and modifications made by the invention patent range and description, should still be within the scope of the present invention.
Claims (12)
1. power grid unmanned plane aerodynamic system detection platform, which includes the mechanical, electrical tune of electricity, propeller and power supply
Power supply；It is characterized by: the platform includes host, display module and testboard bay, which is mounted on testboard
On frame and it is controlled by host to run according to setup parameter, and swashing for the revolving speed for obtaining propeller is installed on the testboard bay
The shock sensor of optical sensor and the vibration coefficient for obtaining the aerodynamic system, cuts laser sensing by propeller
The laser beam that device issues obtains the revolving speed of propeller, further includes pulling force or thrust for obtaining aerodynamic system generation
Weight sensor and the temperature for obtaining the aerodynamic system temperature sensor, the laser sensor, vibration-sensing
Device, weight sensor and temperature sensor are all connected with host；Host obtains test data by each sensor, handles and obtains
The properties of the aerodynamic system.
2. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is equipped with
The electric quasi- test module of adjustment is held by what the quasi- test module setting output voltage of the electricity adjustment, the electric punctual full throttle of adjustment exported
The continuous time, realizes that electric adjustment is quasi- at the duration of the electric punctual zero throttle output of adjustment.
3. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is equipped with
Throttle test module, by the throttle test module be arranged test voltage, the throttle starting point of output, output throttle terminal, oil
The testing time of door step value and each throttle point, and then obtain setting oil of the aerodynamic system under the test voltage point
The characteristic curve of parameters in door range.
4. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is equipped with
Voltage test module, by the voltage test module be arranged test throttle, the voltage starting point of output, output voltage terminal, electricity
The testing time of step value and each electrical voltage point is pressed, and then obtains full voltage of the aerodynamic system under the test throttle point
The characteristic curve of parameters in range.
5. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is equipped with
Distance test module is risen by the fixed test voltage of distance test module setting one, a fixed test throttle, distance
Point, apart from step value, the testing time apart from terminal and each range points, and then obtain different between two motors in coaxial system
Apart from when parameters characteristic curve.
6. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is equipped with
Manual test module, the manual test module include regulated power supply and remote controler, manually adjust output electricity by the regulated power supply
Pressure, manually adjusts output throttle by remote controler.
7. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is equipped with
Integration test module, by the integration test module be arranged test voltage, throttle starting point 0%, output throttle terminal 100%,
The testing time of throttle step value and each throttle point, and then obtain full oil of the aerodynamic system under the test voltage point
The characteristic curve of parameters in door range.
8. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is equipped with
Vibration test module, the vibration test module obtain the shake of the aerodynamic system X-axis, Y-axis and Z axis by the shock sensor
Dynamic data, calculate separately the dispersion degree of the vibration data of X-axis, Y-axis and Z axis in the data area, to obtain entire nothing
The man-machine dynamical system vibration coefficient on X-axis, Y-axis and Z axis respectively makes even the vibration coefficient summation on X-axis, Y-axis and Z axis
Total vibration coefficient of the unmanned plane dynamical system is obtained after mean value.
9. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is equipped with
Optimum efficiency test module, the optimum efficiency test module is by the throttle of control aerodynamic system from starting point 0% to throttle
The power effect of unmanned plane is calculated to measure the pulling force of aerodynamic system and the power of motor in terminal 100%, dynamic with air
The data of Force system throttle are abscissa, draw power output effect and two curves of pulling force in same plane respectively, two curves
Point of intersection is the best efficiency point of the aerodynamic system.
10. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is set
There is optimal combination test module, which passes through the model that fixed motor and electricity are adjusted, and measures different shaped respectively
Number propeller arrange in pairs or groups the motor and electricity adjust, under different throttle supply values the aerodynamic system generate pulling force, thus
The electric mechanical, electrical best applications for reconciling propeller combine out.
11. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: the host is set
There is conformity testing module, which is adjusted by test same motor, electricity, the aerodynamic system of propeller is identical
Under power, whether the thrust deflexion that motor positive and inverse generates is more than whether given threshold is qualified to screen the aerodynamic system.
12. power grid unmanned plane aerodynamic system detection platform according to claim 1, it is characterised in that: including two temperature
Sensor is spent, one temperature sensor is used to obtain the real time temperature of electricity tune, and another temperature sensor is used to obtain the reality of motor
Shi Wendu.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109774971A (en) * | 2019-03-07 | 2019-05-21 | 吉林大学 | A kind of unmanned plane propeller Testing Platform |
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| CN207556727U (en) * | 2017-12-22 | 2018-06-29 | 中南大学 | A kind of microminiature propeller pulling force and torque-measuring apparatus |
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| CN109774971B (en) * | 2019-03-07 | 2023-08-15 | 吉林大学 | Unmanned aerial vehicle screw aerodynamic performance test platform |
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