CN207036971U - A kind of Electric aircraft dynamical system integrated tester - Google Patents
A kind of Electric aircraft dynamical system integrated tester Download PDFInfo
- Publication number
- CN207036971U CN207036971U CN201720427955.4U CN201720427955U CN207036971U CN 207036971 U CN207036971 U CN 207036971U CN 201720427955 U CN201720427955 U CN 201720427955U CN 207036971 U CN207036971 U CN 207036971U
- Authority
- CN
- China
- Prior art keywords
- sensor
- interface
- dynamical system
- controller
- pulling force
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Arrangements For Transmission Of Measured Signals (AREA)
- Testing Or Calibration Of Command Recording Devices (AREA)
Abstract
The utility model discloses a kind of Electric aircraft dynamical system integrated tester.Including：Controller, pulling force amplification D/A converter module, moment of torsion amplification D/A converter module, wireless data transfer module, pulling force sensor, voltage sensor, current sensor, speed probe, speed of incoming flow sensor, torque sensor, throttle position acquisition interface, motor temperature sensor, environment temperature sensor and Throttle Opening Control output interface.Dynamical system efficiency relevant parameter can be tested comprehensively, can be analyzed by these parameters and the power system parameters such as electric efficiency, dynamical system efficiency, motor force effect, dynamical system power effect, propeller force effect, propeller efficiency are calculated.User is allowd intuitively to draw the indices of dynamical system, convenient use person matches motor and propeller.For wireless transport module relative to there is farther transmission range in the past, test job is safer.
Description
Technical field
Dynamical system testing field is the utility model is related to, more specifically to a kind of Electric aircraft dynamical system
Integrated tester.
Background technology
At present, with the development of Miniature brushless motor, brushless speed regulator and lithium battery, the dynamical system using electric power as the energy
System by it is miniature, SUAV aircraft is widely used.It it is also proposed higher requirement to dynamical system.Systematically to analyze
Dynamical system, at least needs six physical quantitys, and known Electric aircraft dynamical system tester is only capable of doing letter to dynamical system
Single test, test parameter is not complete, analyzable data are limited, it is impossible to Systematic Analysis is done to dynamical system, to dynamical system
Test it is excessively general, it is impossible to independent testing of electric motors, propeller performance, the dynamic pulling force and efficiency of propeller can not be tested,
It not can know that whether motor matches with propeller, the meaning of measurement result is very limited.Due to existing Electric aircraft power
System test uses airborne indicator display data or data line transfer data, tester must near testboard work
Make, bear huge noise and risk.
The content of the invention
The utility model mainly solving the technical problems that：A kind of Electric aircraft dynamical system combined test stand is provided to use
Oil electric mixed dynamic system, six major parameters of dynamical system can be gathered：Supply voltage, supply current, Motor torque, electricity
Machine rotating speed, dynamical system pulling force, speed of incoming flow, and the auxiliary such as throttle position, motor temperature, environment temperature ginseng can be gathered
Number.It can be analyzed by these parameters and electric efficiency, dynamical system efficiency, motor force effect, dynamical system power effect, spiral shell is calculated
Revolve the power system parameters such as oar power effect, propeller efficiency.User is allowd intuitively to draw the indices of dynamical system, side
Just user matches motor and propeller.Using wireless way for transmitting data, relative to there is farther transmission range in the past, survey
Examination personnel can test of the time to dynamical system in away from the smaller and safe environment of testboard noise.
In order to achieve the above object, the technical solution adopted in the present invention is：The utility model includes three big components:Core
Observing and controlling component, indispensable sensor, apolegamy sensor.Core control component includes：The special amplification digital-to-analogue conversion mould of controller, dynamometry
Block, wireless data transfer module, indispensable sensor include：Voltage sensor, current sensor, torque sensor, revolution speed sensing
Device, pulling force sensor, speed of incoming flow sensor, apolegamy sensor include：Throttle position acquisition interface motor temperature sensor, ring
Border temperature sensor and Throttle Opening Control output interface.
As the further optimization of the technical program, the utility model apolegamy sensor can be increased and decreased as needed.
As the further optimization of the technical program, it can also be more that sensor described in the utility model, which can be one,
It is individual.
As the further optimization of the technical program, the unlimited Dingan County's dress stand mechanical structure of the utility model tester can
To install as needed on the stand with different structure.
A kind of Electric aircraft dynamical system integrated tester of the utility model has the beneficial effect that：
A kind of Electric aircraft dynamical system integrated tester of the utility model, can test dynamical system efficiency phase comprehensively
Related parameter, it can be analyzed by these parameters and electric efficiency, dynamical system efficiency, motor force effect, dynamical system power is calculated
The power system parameter such as effect, propeller force effect, propeller efficiency.User is allowd intuitively to show that the items of dynamical system refer to
Mark, convenient use person match motor and propeller.Using wireless way for transmitting data, relative to there is farther transmission distance in the past
From tester can test of the time to dynamical system in away from the smaller and safe environment of testboard noise.
Brief description of the drawings
The utility model is described in more detail with specific implementation method below in conjunction with the accompanying drawings.
Fig. 1 is a kind of logical construction schematic diagram of Electric aircraft dynamical system integrated tester of the utility model.
Fig. 2 is a kind of Electric aircraft dynamical system integrated tester circuit total figure schematic diagram of the utility model.
Fig. 3 is a kind of Electric aircraft dynamical system integrated tester voltage sensor circuit connection principle of the utility model
Figure.
Fig. 4 be a kind of Electric aircraft dynamical system integrated tester current sensor of the utility model, speed probe,
Speed of incoming flow sensor circuit elementary diagram.
Fig. 5 is a kind of Electric aircraft dynamical system integrated tester pulling force of the utility model, moment of torsion acquisition module circuit
Elementary diagram.
Fig. 6 is a kind of Electric aircraft dynamical system integrated tester throttle acquisition interface of the utility model, throttle output
Interface circuit elementary diagram.
Fig. 7 is that a kind of Electric aircraft dynamical system integrated tester temperature collect module wireless data of the utility model passes
Defeated modular circuit elementary diagram.
In figure：2 core observing and controlling components, 1 indispensable sensor, 3 apolegamy sensor/interfaces, 4 pulling force sensors, 5 voltage sensors
Device, 6 current sensors, 7 speed probes, 8 speed of incoming flow sensors, 9 torque sensors, 10 pulling force amplification digital-to-analogue conversion mould
Block, 11 controllers, 12 moments of torsion amplification D/A converter module, 13 wireless data transfer modules, 14 throttle position acquisition interfaces, 15 electricity
Machine temperature sensor, the sensor of environment temperature 16,17 Throttle Opening Control output interfaces.
Embodiment
Embodiment one：
Illustrate present embodiment with reference to Fig. 1 ~ 7.A kind of Electric aircraft dynamical system integration test of the utility model
Device, including three big components:Core observing and controlling component 2, indispensable sensor 1, apolegamy sensor/interface 3.Core control component 2 includes：
Controller 11, pulling force amplification D/A converter module 10, moment of torsion amplification D/A converter module 12, wireless data transfer module 13, must
Standby sensor 1 includes：Pulling force sensor 4, voltage sensor 5, current sensor 6, speed probe 7, speed of incoming flow sensor
8th, torque sensor 9, apolegamy sensor/interface 3 include：Throttle position acquisition interface 14, motor temperature sensor 15, environment temperature
Degree sensor 16 and Throttle Opening Control output interface 17 are formed.User is allowd intuitively to show that the items of dynamical system refer to
Mark, convenient use person match motor and propeller.
Indispensable sensor 1 is the sensor that tester must carry, wherein pulling force sensor 4 and pulling force amplification digital-to-analogue conversion
Module 10 is connected, the digital interface of pulling force amplification D/A converter module connection power supply and controller 11；Torque sensor 9 connects
Moment of torsion amplifies D/A converter module 12, and moment of torsion amplification D/A converter module is connected to the digital interface of controller 11；Revolution speed sensing
One digital interface of the output end access controller 11 of device 7；Voltage sensor 5 divides for reference voltage source and collection voltages circuit,
Reference voltage source both positive and negative polarity accesses power supply, and an A/D translation interface of output end access controller, Acquisition Circuit is a partial pressure
Circuit, the both positive and negative polarity of input termination dynamical system input power, an A/D translation interface of output end access controller 11；Electricity
The both positive and negative polarity of pressure sensor 5 accesses power supply, an A/D translation interface of output end access controller 11；The electricity of speed of incoming flow sensor 8
Acquisition module both positive and negative polarity access power supply is flowed, output end accesses an A/D translation interface into controller 11；Throttle Opening Control output connects
Mouth 17 is made up of signal wire and ground wire, and signal wire connects a digital interface of controller 11, and the interface requirement can export PWM
Ripple；Throttle position acquisition interface 14 is made up of signal wire and ground wire, and signal wire connects a digital interface of controller 11；Motor temperature
Degree sensor 15 and environment temperature sensor 16 are encapsulated in a module, both positive and negative polarity access power supply, export access controller
11 two digital interfaces.The both positive and negative polarity of wireless data transfer module 13 connects power supply, and Data Input Interface connection controller 11 counts
According to output interface, its data output interface connects the Data Input Interface of controller 11.
A kind of operation principle of unmanned vehicle oil electric mixed dynamic system of the utility model：
Electric efficiency, dynamical system efficiency, dynamical system power effect, propeller force effect, propeller efficiency are to be related to dynamical system
The system most important several parameters of efficiency.
Electric aircraft dynamical system is made up of three critical pieces:Propeller, motor, electron speed regulator.Electronics is adjusted
Fast device is used for regulation motor rotating speed, power, ultrahigh in efficiency under normal operation, does not consider its loss typically.Motor is by electricity
The mechanical energy of rotation status can be converted into and exported the mechanical energy from motor is converted into thrust to propeller, propeller.It is dynamic
The product of Force system input voltage and input current is the input power of dynamical system, because electron speed regulator loss seldom can be with
Ignore, therefore be also power input to a machine, motor speed and motor output torque product are output power of motor, spiral
The product of oar pulling force and speed of incoming flow is propeller power output, and the power output of whole dynamical system.Dynamical system
Efficiency is equal to dynamical system power output divided by dynamical system input power, and electric efficiency is equal to output power of motor divided by power
System input power, propeller efficiency are equal to propeller power output divided by output power of motor, and dynamical system power effect is equal to dynamic
Force system pulling force divided by dynamical system input power, propeller force effect are equal to dynamical system pulling force divided by propeller input power.
Therefore supply voltage is measured using voltage sensor 5, current sensor 6 measures supply current, torque sensor 9 measures motor torsion
Square, speed probe 7 measure motor speed, pulling force sensor 4 measures dynamical system pulling force, speed of incoming flow sensor 8 is measured and
Flow velocity degree can be calculated electric efficiency, dynamical system efficiency, dynamical system power effect, propeller force effect, propeller efficiency this 5
The individual main efficiency parameters of dynamical system.
Voltage sensor 5 is made up of reference voltage source and collection voltages circuit, and voltage collection circuit is bleeder circuit, due to
The voltage that controller 11 can input is often below dynamical system supply voltage, so needing partial pressure to measure；Reference voltage source exports
Be high-precision burning voltage, the A/D conversion mouths that the voltage collected is sent into controller with reference voltage are converted to digital letter
High-precision collection voltages value can be drawn by number carrying out contrast.
Current sensor 6 is analog signal sensors, and after accessing power supply, output is analog signal, is sent into controller 11
A/D conversion mouth be converted to data signal.
Speed of incoming flow sensor 8 is analog signal sensors, and after accessing power supply, output is analog signal, is sent into control
The A/D conversion mouths of device 11 are converted to data signal.
Speed probe 7 export for data signal, the digital interface of input controller 11.
Speed probe 7 by detect motor commutation frequency or propeller rotational frequency to be converted into frequency signal defeated
Deliver to the analog interface of controller 11.
Pulling force sensor 4, torque sensor 9 are using strain variant sensor, and its output signal is analog voltage signal, phase
The model intensity that can gather for controller 11 is too weak directly to be gathered, therefore is respectively connected to pulling force amplification D/A converter module
10th, moment of torsion amplification D/A converter module 12.Signal is amplified and is converted to data signal, then is transported to controller 11.
In order that a kind of integrated tester of Electric aircraft dynamical system of the utility model is more preferably practical, increase some choosings
Use sensor.
Because Electric aircraft dynamical system is to control throttle position, therefore throttle position acquisition interface by PWM ripples
14 collection PWM ripples can draw throttle currency further according to its respective function relation；Similarly, Throttle Opening Control output interface 17 uses it
The throttle value of needs can be converted to PWM ripples so as to control dynamical system throttle by respective function relation.
Electric aircraft dynamical system often uses outer rotor brushless motor, and formula survey is inconveniently contacted in operation process
Amount, therefore, motor temperature carry out non-contact capture using infrared temperature sensor.Environment temperature is sensed using contact temperature
Device, it also can be used for the part of the accessible measurements such as measurement electron speed regulator.
Data from sensor are changed, filtered and transmitted to wireless according to certain functional relation by controller 11
Data transmission module 13, is transmitted to computer, meanwhile, computer throttle signal is transmitted to control by wireless data transfer module 13
Device 11 processed, be converted to pwm signal and be transported to Throttle Opening Control output interface 17 for controlling dynamical system throttle.
Embodiment two：
Illustrate present embodiment with reference to Fig. 1 ~ 7, present embodiment is described further to embodiment one, described
Speed of incoming flow sensor 8 can be that analog signal sensors can also be digital signal sensors.
Embodiment three：
Illustrate present embodiment with reference to Fig. 1 ~ 7, present embodiment is described further to embodiment one, described
Controller 11 can be that single-chip microcomputer can also be PLC, FPGA.
The maximum innovation of the utility model is that acquiring input voltage, input current, moment of torsion, motor simultaneously turns
Speed, dynamical system pulling force, speed of incoming flow so that tester can be with system, the efficiency of comprehensive analysis dynamical system each several part.
And can increase detection motor temperature, environment temperature, throttle collection and control on apolegamy sensor/interface as needed
System.Unmanned plane dynamical system tester with function above is the scope of this patent protection.Certainly, described above is not to this
The limitation of utility model, the utility model are also not limited to the example above, and those skilled in the art are in this practicality
The variations, modifications, additions or substitutions made in new essential scope, fall within the scope of protection of the utility model.
Claims (3)
1. a kind of Electric aircraft dynamical system integrated tester, it is characterised in that include three big components:Core observing and controlling component
(2), indispensable sensor (1), apolegamy sensor/interface (3);Core control component (2) includes：Controller (11), pulling force amplification
D/A converter module (10), moment of torsion amplification D/A converter module (12), wireless data transfer module (13), indispensable sensor (1)
Comprising：Pulling force sensor (4), voltage sensor (5), current sensor (6), speed probe (7), speed of incoming flow sensor
(8), torque sensor (9), apolegamy sensor/interface (3) include：Throttle position acquisition interface (14), motor temperature sensor
(15), environment temperature sensor (16) and Throttle Opening Control output interface (17) are formed；Indispensable sensor (1) is that tester is necessary
The sensor of carrying, wherein pulling force sensor (4) are connected with pulling force amplification D/A converter module (10), pulling force amplification digital-to-analogue conversion
Module connects the digital interface of power supply and controller (11)；Torque sensor (9) connection moment of torsion amplification D/A converter module
(12), moment of torsion amplification D/A converter module is connected to the digital interface of controller (11)；The access control of speed probe (7) output end
One digital interface of device (11) processed；Voltage sensor (5) is divided into reference voltage source and collection voltages circuit, and reference voltage source is just
Negative pole accesses power supply, and an A/D translation interface of output end access controller, Acquisition Circuit is a bleeder circuit, input
Connect the both positive and negative polarity of dynamical system input power, an A/D translation interface of output end access controller (11)；Voltage sensor
(5) both positive and negative polarity access power supply, an A/D translation interface of output end access controller (11)；Speed of incoming flow sensor (8) electric current
Acquisition module both positive and negative polarity accesses power supply, an A/D translation interface of output end access controller (11)；Throttle Opening Control output interface
(17) it is made up of signal wire and ground wire, signal wire connects a digital interface of controller (11), the exportable PWM ripples of the interface；Oil
Door station acquisition interface (14) is made up of signal wire and ground wire, and signal wire connects a digital interface of controller (11)；Motor temperature
Degree sensor (15) and environment temperature sensor (16) are encapsulated in a module, both positive and negative polarity access power supply, output access control
Two digital interfaces of device (11) processed, wireless data transfer module (13) both positive and negative polarity connection power supply, Data Input Interface connection control
Device (11) data output interface processed, the Data Input Interface of its data output interface connection controller (11).
2. a kind of Electric aircraft dynamical system integrated tester according to claim 1, it is characterised in that be integrated with drawing
Force snesor, voltage sensor, current sensor, speed probe, speed of incoming flow sensor, torque sensor.
A kind of 3. Electric aircraft dynamical system integrated tester according to claim 1, it is characterised in that every kind of sensing
It can also be multiple that device quantity, which can be one,.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720427955.4U CN207036971U (en) | 2017-04-22 | 2017-04-22 | A kind of Electric aircraft dynamical system integrated tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720427955.4U CN207036971U (en) | 2017-04-22 | 2017-04-22 | A kind of Electric aircraft dynamical system integrated tester |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207036971U true CN207036971U (en) | 2018-02-23 |
Family
ID=61479141
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720427955.4U Expired - Fee Related CN207036971U (en) | 2017-04-22 | 2017-04-22 | A kind of Electric aircraft dynamical system integrated tester |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207036971U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791819A (en) * | 2018-07-06 | 2018-11-13 | 陈俊胤 | A kind of automatic pitch propeller device and its control method, aircraft |
| CN109556878A (en) * | 2018-12-21 | 2019-04-02 | 沈阳航空航天大学 | A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus and method |
| CN110371320A (en) * | 2019-08-07 | 2019-10-25 | 山东交通学院 | A kind of device, method and application for testing revolution speed of propeller, lift and noise |
| CN113093002A (en) * | 2020-01-08 | 2021-07-09 | 灵翼飞航（天津）科技有限公司 | Factory calibration method for unmanned aerial vehicle power test board |
| CN113252933A (en) * | 2021-05-12 | 2021-08-13 | 北京航空航天大学 | Propeller incoming flow speed detection device and method |
| CN116184098A (en) * | 2023-04-26 | 2023-05-30 | 深圳市好盈科技股份有限公司 | Power system test platform |
-
2017
- 2017-04-22 CN CN201720427955.4U patent/CN207036971U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791819A (en) * | 2018-07-06 | 2018-11-13 | 陈俊胤 | A kind of automatic pitch propeller device and its control method, aircraft |
| CN108791819B (en) * | 2018-07-06 | 2024-01-05 | 陈俊胤 | Automatic variable-pitch propeller device, control method thereof and aircraft |
| CN109556878A (en) * | 2018-12-21 | 2019-04-02 | 沈阳航空航天大学 | A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus and method |
| CN109556878B (en) * | 2018-12-21 | 2024-03-22 | 沈阳航空航天大学 | Synchronous measurement device and method for pneumatic performance and efficiency of electric propeller system |
| CN110371320A (en) * | 2019-08-07 | 2019-10-25 | 山东交通学院 | A kind of device, method and application for testing revolution speed of propeller, lift and noise |
| CN110371320B (en) * | 2019-08-07 | 2021-04-23 | 山东交通学院 | Device and method for testing rotating speed, lift force and noise of propeller and application |
| CN113093002A (en) * | 2020-01-08 | 2021-07-09 | 灵翼飞航（天津）科技有限公司 | Factory calibration method for unmanned aerial vehicle power test board |
| CN113252933A (en) * | 2021-05-12 | 2021-08-13 | 北京航空航天大学 | Propeller incoming flow speed detection device and method |
| CN113252933B (en) * | 2021-05-12 | 2022-03-11 | 北京航空航天大学 | Propeller incoming flow speed detection device and method |
| CN116184098A (en) * | 2023-04-26 | 2023-05-30 | 深圳市好盈科技股份有限公司 | Power system test platform |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207036971U (en) | A kind of Electric aircraft dynamical system integrated tester | |
| CN206161814U (en) | Servo motor reliability testing system | |
| CN103076565B (en) | Phase asynchronous high-voltage electric machine overhauling health status check and evaluation system | |
| CN207181562U (en) | Electric automobile charging pile movable type detection platform | |
| CN203250001U (en) | Motor performance test platform | |
| CN107677959A (en) | Unmanned plane induction machine combined test stand and method of testing | |
| CN102621491A (en) | Motor parameter detector | |
| CN202075392U (en) | Electromotor comprehensive state monitoring system | |
| CN108799014B (en) | The detection system of data sampling sensor and pitch-controlled system, method and apparatus | |
| CN109708893A (en) | A kind of aero-engine alternative electric generation type power-measuring system | |
| CN104316333B (en) | The test system of system is put in a kind of moped | |
| CN109470470A (en) | One kind carrying out gearbox mechanical efficiency test macro and test method on vehicle | |
| CN206281953U (en) | A kind of electric automobile motor drive system test device | |
| CN108438250A (en) | Serial mixed power aircraft power system testboard bay | |
| CN106768287A (en) | A kind of test device for multi-rotor unmanned aerial vehicle mount vibration situation | |
| CN105372537B (en) | Frequency converter intelligence test platform based on Labview/PDA | |
| CN205157637U (en) | Generator carbon brush current distribution monitoring system | |
| CN201984109U (en) | Eddy current dynamometric system | |
| CN201163778Y (en) | Server management monitoring apparatus | |
| CN203745076U (en) | Portable vibration-testing device for gear case of double-feed wind turbine generation set of wireless communication type | |
| CN201322753Y (en) | Rotating-speed measuring device | |
| CN202002938U (en) | Wireless wind speed detector | |
| CN208420240U (en) | A kind of real-time vehicle load measurement system of electric efficiency based on pure electric automobile | |
| CN205427155U (en) | Dc motor test platform based on labVIEW | |
| CN207675855U (en) | A kind of test system of frequency converter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180223 Termination date: 20210422 |