CN205193510U - Novel aircraft electrical power generating system tests platform device - Google Patents
Novel aircraft electrical power generating system tests platform device Download PDFInfo
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- CN205193510U CN205193510U CN201520934655.6U CN201520934655U CN205193510U CN 205193510 U CN205193510 U CN 205193510U CN 201520934655 U CN201520934655 U CN 201520934655U CN 205193510 U CN205193510 U CN 205193510U
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Abstract
The utility model provides a novel aircraft electrical power generating system tests platform device, hold host computer, dc -to -ac converter and aircraft battery including motor timing control system, generator excitation control system, PC. The utility model discloses the rotor rotates required power when using motor timing control system to replace the aeroengine system to provide the electricity generation as alternator, and the DSP timing control utensils in the motor timing control system come the rotational speed of regulating motor, STM32 excitation control ware in the generator excitation control system makes dynamo output's terminal voltage invariable through control alternator's excitation winding's excitation current. PC serves a machine and is the required 200V115V of aviation alternating load, 400Hz's alternating current in the data parameter of control with two systems of demonstration, dc -to -ac converter with the contravariant of 28V direct current. This device has very positive effect for the research of aircraft electrical power generating system's theoretical aspect provides the platform that can verify to the popularization of experiment platform and present generation aircraft electrical power generating system's research and development.
Description
Technical field
The utility model belongs to technical field of electric control, particularly relates to aircraft power system experiment platform device.
Background technology
Along with contemporary type aircraft is fast-developing towards many electricity, electric aircraft direction, also more and more higher to the requirement of aircraft power system, its power supply quality and reliability have become the key factor affecting aeroplane performance, its research are also day by day become to the focus of aeronautical chart.
Aircraft power system mainly comprises the conversion fraction of synchronous generator power generation part, excitation controller regulable control part and electric energy.Because airborne consumer various on aircraft is very high to the quality requirements of electric energy, this electric energy just meaning that aircraft generator exports must reach the performance index of every regulation, little, the frequency-invariant of voltage fluctuation etc. during as stable in terminal voltage, load changing.If the terminal voltage that generator exports is in the non-steady state that fluctuated, frequency is suddenly big or suddenly small, so not only each airborne consumer can suffer damage in various degree, also likely affects the normal flight of aircraft and threatens the safety of aircraft and staff.
Due to confidentiality and the singularity of aircraft power system, be difficult on the market buy the experiment porch that basic equipment is perfect, performance is ripe, moderate at present.Therefore design the experiment porch of an aircraft power system, the analysis for various performance index during aircraft power system real work provides the support of True Data.Normally run and ruuning situation and each term system energy index in the process such as load change by detecting whole power-supply system in aircraft power system experiment porch, and contrast the result of theoretical research, the problem that simulated aircraft power-supply system that can be more detailed and true to nature may run in various working flight also finds solution in time, effectively can prevent the generation of all kinds of aircraft accidents caused because of power system problems, have very positive function and significance to the development of present generation aircraft power-supply system.
Utility model content
The purpose of this utility model is that providing a kind of is suitable for practical type aircraft power-supply system experiment platform device, and the theoretical research for aircraft power system provides the platform of checking.
To achieve these goals, the utility model adopts following technical scheme:
A kind of type aircraft power-supply system experiment platform device, comprises motor speed adjusting control system, Excitation Controller, PC holds host computer, inverter and aircraft battery;
The output terminal of motor speed governing system is connected to the input end of Excitation Controller, the output terminal of Excitation Controller is connected in DC voltage bus, and motor speed adjusting control system and Excitation Controller are held host computer to carry out two-way communication to be connected respectively with PC; The input end of aircraft battery is connected in DC voltage bus, and the output terminal of aircraft battery is connected to the respective input of Excitation Controller; The input end of inverter is connected in DC voltage bus, and the output terminal of inverter is connected in alternating voltage bus;
Motor speed adjusting control system has the permasyn morot and DSP speed setting controller that are connected, Excitation Controller has the alternator and three phase rectifier that are connected, the rotating speed of permasyn morot is regulated by DSP speed setting controller, be power when alternator provides generating required for rotor turns by permasyn morot, the three-phase alternating current that alternator exports exports 28V direct current, by the alternating current of inverter by 200V/115V, 400Hz required for aviation AC load of 28V DC inverter after three phase rectifier.
Described motor speed governing system also comprises rectification circuit, three-phase inverting circuit, auxiliary power circuit, optical coupling isolation circuit, current detection circuit and photoelectric encoder interface circuit;
In motor speed adjusting control system, the connection of each several part is as follows:
The input end of rectification circuit is connected to civil power 220V interface, and the output terminal of rectification circuit is connected respectively to the input end of three-phase inverting circuit, auxiliary power circuit;
The input end of three-phase inverting circuit is connected respectively to the output terminal of rectification circuit, optical coupling isolation circuit, and the output terminal of three-phase inverting circuit is connected respectively to the input end of current detection circuit, permasyn morot;
The input end of auxiliary power circuit is connected to the output terminal of rectification circuit, and the output terminal of auxiliary power circuit is connected respectively to the respective input of optical coupling isolation circuit, DSP speed setting controller;
The input end of optical coupling isolation circuit is connected respectively to the output terminal of PWM module in auxiliary power circuit, DSP speed setting controller, and the output terminal of optical coupling isolation circuit is connected to the input end of three-phase inverting circuit;
The input end of current detection circuit is connected to the output terminal of three-phase inverting circuit, and the output terminal of electric current electrical measurement circuit is connected to the input end of A/D module in DSP speed setting controller;
The input end of permasyn morot is connected to the output terminal of three-phase inverting circuit, the output terminal of permasyn morot is connected to the input end of photoelectric encoder interface circuit, and the output terminal of photoelectric encoder interface circuit is connected to the input end of QEP module in DSP speed setting controller.
Described Excitation Controller also comprises excitation main circuit, driving circuit, exciting current sample circuit, voltage sampling circuit, current sampling circuit and STM32 excitation controller;
In Excitation Controller, the connection of each several part is as follows:
Alternator exports three-phase alternating current, after three phase rectifier rectification, exports 28V direct current in DC voltage bus;
The input end of excitation main circuit connects the output terminal of driving circuit, aircraft battery respectively, and the output terminal of excitation main circuit connects the input end of the field copper of alternator, exciting current sample circuit respectively;
The input end of driving circuit connects the output terminal of timer in STM32 excitation controller, and the output terminal of driving circuit connects the input end of excitation main circuit;
The input end of exciting current sample circuit connects the output terminal of excitation main circuit, and the output terminal of exciting current sample circuit connects the input end of an ADC module in STM32 excitation controller;
The input end of voltage sampling circuit is connected in DC voltage bus, and the output terminal of voltage sampling circuit is connected to the input end of the 2nd ADC module in STM32 excitation controller;
The input end of current sampling circuit is connected in DC voltage bus, and the output terminal of current sampling circuit is connected to the input end of the 3rd ADC module in STM32 excitation controller.
Described motor speed governing system also comprises keyboard and display panel, and DSP speed setting controller is bi-directionally connected by its digital I/O interface and keyboard and display panel.
After adopting such scheme, a kind of type aircraft power-supply system experiment platform device of the present utility model, design motor speed adjusting control system replaces aeromotor for power when alternator provides generating required for rotor turns, DSP speed setting controller in motor speed adjusting control system is then used for regulating the rotating speed of permasyn morot, such as aircraft is in rising, cruise, during lower other situations of degradation, rotating speed needs to change according to actual needs, now DSP speed setting controller just can carry out the adjustment of rotating speed as required to permasyn morot, and the rotating speed of motor and the electric current of motor winding are sampled, the rotating speed of motor is precisely controlled by FEEDBACK CONTROL.
The three-phase alternating current that alternator exports, directly by three phase rectifier, exports 28V direct current.The terminal voltage that STM32 excitation controller makes generator export by the exciting current of the field copper controlling alternator is constant.By real-time exciting current, output voltage sampling, and undertaken by excitation controller processing the exciting current controlling alternator, make the 28V voltage of generator voltage all-the-time stable needed for power-supply system.
PC holds the function that mainly realizes of host computer to be divided into two aspects: be the rotating speed by the display permasyn morot in real time of communicate with DSP speed setting controller on the interface that PC holds host computer and exciting current on the one hand, and directly can carry out the startup and shutdown of the setting of communication port parameter, the setting of Permanent Magnet Synchronous Motor and DSP speed setting controller at the interface of PC end host computer.Be by the general power showing the output voltage of alternator, the exciting current of field copper and power-supply system on the interface that PC holds host computer in real time that communicates with STM32 excitation controller on the other hand, can also hold host computer that the switching on and shutting down of communication port parameter and STM32 excitation controller are directly set at PC.
Further, DSP speed setting controller is connected with keyboard and display panel, also can not set easily by the digital keys of keyboard and display panel and LCDs and observe the rotating speed of motor by host computer.
The utility model is compared with other aircraft power system experiment platform device, its effect is actively with obvious, solve the problem being difficult on the market buy the aircraft power system experiment porch that basic equipment is perfect, performance is ripe, moderate, and devise design motor speed adjusting control system and replace aeromotor for power when alternator provides generating required for rotor turns, and Excitation Controller, host computer, inverter etc.This device is that the research of the theoretical side of aircraft power system provides the platform that can verify, and equipment record, superior performance, moderate cost, there is very positive effect to the popularization of experiment porch and the research and development of present generation aircraft power-supply system.
Accompanying drawing explanation
Fig. 1 is the overall construction drawing of the utility model aircraft power system experiment platform device.
Fig. 2 is the schematic block circuit diagram of the utility model motor speed adjusting control system.
Fig. 3 is the schematic block circuit diagram of the utility model Excitation Controller.
Fig. 4 is the functional block diagram that in the utility model, PC holds host computer to realize.
Embodiment
Be described in detail below in conjunction with the embodiment of accompanying drawing to the utility model aircraft power supply experiment platform device.
As shown in Figure 1, a kind of type aircraft power supply experiment platform device of the present utility model, comprises motor speed adjusting control system 100, Excitation Controller 200, PC holds host computer 300, inverter 400 and aircraft battery 500.The output terminal of motor speed governing system 100 is connected to the input end of Excitation Controller 200, the output terminal of Excitation Controller 200 is connected in DC voltage bus (DCBUS), and motor speed adjusting control system 100 and Excitation Controller 200 are held host computer 300 to carry out two-way communication to be connected respectively with PC; The input end of aircraft battery 500 is connected in DC voltage bus, and the output terminal of aircraft battery 500 is connected to the respective input of Excitation Controller 200; The input end of inverter 400 is connected in DC voltage bus, and the output terminal of inverter 400 is connected in alternating voltage bus (ACBUS).
In the utility model, replace aeromotor for power when alternator provides generating required for rotor turns with motor speed-adjusting and control system 100, Excitation Controller 200 is by regulating the exciting current size of alternator field copper, and the alternating current that generator is exported is by exporting the 28V direct current of the high quality of power supply after rectifier.PC end host computer 300 passes through a good human-computer interaction interface, directly controls motor speed adjusting control system 100 and Excitation Controller 200, and shows their data parameters in real time.Inverter 400 carries out DC-AC conversion, by the alternating current of 200V/115V, 400Hz required for aviation AC load of 28V DC inverter.
Concrete, as shown in Figure 2, motor speed governing system 100 comprises rectification circuit 11, three-phase inverting circuit 12, auxiliary power circuit 13, optical coupling isolation circuit 14, current detection circuit 15, permasyn morot (PMSM) 16, photoelectric encoder interface circuit 17, DSP speed setting controller 18 and keyboard and display panel 19.
In motor speed adjusting control system 100, the connection of each several part is as follows:
The input end of rectification circuit 11 is connected to civil power 220V interface, and the output terminal of rectification circuit 11 is connected respectively to the input end of three-phase inverting circuit 12, auxiliary power circuit 13;
The input end of three-phase inverting circuit 12 is connected respectively to the output terminal of rectification circuit 11 and optical coupling isolation circuit 14, and the output terminal of three-phase inverting circuit 12 is connected respectively to the input end of current detection circuit 15 and permasyn morot 16;
The input end of auxiliary power circuit 13 is connected to the output terminal of rectification circuit 11, and the output terminal of auxiliary power circuit 13 is connected respectively to the respective input of optical coupling isolation circuit 14 and DSP speed setting controller 18;
The input end of optical coupling isolation circuit 14 is connected respectively to the output terminal of PWM module in auxiliary power circuit 13, DSP speed setting controller 18, and the output terminal of optical coupling isolation circuit 14 is connected to the input end of three-phase inverting circuit 12;
The input end of current detection circuit 15 is connected to the output terminal of three-phase inverting circuit 12, and the output terminal of electric current electrical measurement circuit 15 is connected to the input end of A/D module in DSP speed setting controller 18;
The input end of permasyn morot 16 is connected to the output terminal of three-phase inverting circuit 12, the output terminal of permasyn morot 16 is connected to the input end of photoelectric encoder interface circuit 17, and the output terminal of photoelectric encoder interface circuit 17 is connected to the input end of QEP module in DSP speed setting controller 18.
Further, DSP speed setting controller 18 has also been bi-directionally connected keyboard and display panel 19 by its digital I/O interface.
The single-phase full bridge rectifier bridge that rectification circuit 11 is made up of four commutation diodes, three-phase inverting circuit 12 is traditional three phase full bridge topological structure, and the IGBT model of employing is FGA25N120.
The alternating current of 220V input obtains direct current through rectification circuit 11, then obtains two-way direct current by auxiliary power circuit 13, and a road supply DSP speed setting controller 18, another road then supplies optical coupling isolation circuit 14.
Optical coupling isolation circuit 14, the light current in digitial controller is affected in order to avoid the forceful electric power in main circuit, adopt 6N137 photo-coupler to carry out Phototube Coupling to the six road pwm control signals that DSP speed setting controller 18 produces, then deliver to the IGBT driving chip IR2110S of three-phase inverting circuit 12.
Current detection circuit 15, in motor speed adjusting control system 100, the adjustment of electric current loop can directly affect the electromagnetic torque of permasyn morot 16, so need the value knowing actual current in motor winding promptly and accurately, this just needs to carry out current detecting.By common method in AC servo drive system, namely detect the size of current of electric with the Hall element of electromagnetic isolation.The Hall current sensor model that this device is selected is CS010GT conventional in current detection circuit.
Photoelectric encoder interface circuit 17, adopts photoelectric encoder as the detecting sensor of motor position and speed, is used for the rotor-position of detection permasyn morot 16 and speed.Adopt four road differential line receiver AM26LS32ACD to receive the differential signal of photoelectric encoder in circuit, and two groups of signals use identical interface circuit.
DSP speed setting controller 18 adopts the high-performance processor TMS320F28335 of TI company, and this chip has powerful analog to digital converter ADC module and PWM ripple control module.
Keyboard and display panel 19, can be set by digital keys and LCDs and observe the rotating speed of permasyn morot 16 easily.
In the utility model, the function of motor speed adjusting control system 100 is for replacing aeromotor for power when alternator provides generating required for rotor turns, DSP speed setting controller 18 is used for regulating the rotating speed of permasyn morot 16, such as aircraft is in rising, cruise, during lower other situations of degradation, rotating speed needs to change according to actual needs, now DSP speed setting controller 18 just can carry out the adjustment of rotating speed as required to permasyn morot 16, and the rotating speed of permasyn morot 16 and the electric current of motor winding are sampled, the rotating speed of permasyn morot 16 is precisely controlled by FEEDBACK CONTROL.
As shown in Figure 3, Excitation Controller 200 comprises alternator 21, three phase rectifier 22, excitation main circuit 23, driving circuit 24, exciting current sample circuit 25, voltage sampling circuit 26, current sampling circuit 27 and STM32 excitation controller 28.
In Excitation Controller 200, the connection of each several part is as follows:
Alternator 21 exports three-phase alternating current, after three phase rectifier 22 rectification, exports 28V direct current in DC voltage bus (DCBUS);
The input end of excitation main circuit 23 connects the output terminal of driving circuit 24 and aircraft battery 500 respectively, and the output terminal of excitation main circuit 23 connects the field copper of alternator 21 and the input end of exciting current sample circuit 25 respectively;
The input end of driving circuit 24 connects the output terminal of timer in STM32 excitation controller 28, and the output terminal of driving circuit 24 connects the input end of excitation main circuit 23;
The input end of exciting current sample circuit 25 connects the output terminal of excitation main circuit 23, and the output terminal of exciting current sample circuit 25 connects the input end of an ADC module in STM32 excitation controller 28;
The input end of voltage sampling circuit 26 is connected on DCBUS, and the output terminal of voltage sampling circuit 26 is connected to the input end of the 2nd ADC module in STM32 excitation controller 28;
The input end of current sampling circuit 27 is connected on DCBUS, and the output terminal of current sampling circuit 27 is connected to the input end of the 3rd ADC module in STM32 excitation controller 28.
In the utility model; excitation main circuit 23 regulates the size of the field copper input exciting current of alternator 21 by the time turned on and off controlling a power tube; make circuit structure simple; stable and reliable operation; field suppression protection loop during generator operation fault can also be added, in order to improve security during generator operation.
Driving circuit 23 adopts the special driver module EXB841 of IGBT, adopt photoelectrical coupler isolate as signal, and there is overcurrent protection, volume is little, performance good and high reliability.
The output current of exciting current sample circuit 25, alternator 21 all selects the Hall element with electromagnetic isolation to detect, the Hall current sensor model selected is CS010GT conventional in current detection circuit, sends into the corresponding A/D C module of STM32 excitation controller 28 after modulate circuit.
Output voltage sampling circuit 26 selects Hall voltage sensor, and model is CHV-25P, and sensor output voltage sends into the corresponding A/D C module of STM32 excitation controller 28 after modulate circuit.
That STM32 excitation controller 28 adopts is high-performance processor STM32F103ZE based on Contex-M3 kernel, and this chip has the feature of high-performance, low cost, low-power consumption, and possesses powerful analog to digital converter ADC module and timer module.In addition, the power supply of STM32 excitation controller 28 is provided by accessory power supply 13.
Further, in Excitation Controller 200, the terminal voltage that STM32 excitation controller 28 makes alternator 21 export by the exciting current of the field copper controlling alternator 21 is constant.By real-time exciting current, output voltage sampling, and undertaken processing the exciting current controlling alternator 21 by STM32 excitation controller 28, make the 28V voltage of alternator 21 terminal voltage all-the-time stable needed for power-supply system.
As shown in Figure 4, in the utility model, held the parameters of serial ports and each controller serial ports by design PC, make PC hold host computer 300 and each controller to carry out communication, after successful communication, PC holds the communication pilot lamp on host computer 300 interface to brighten.The each control knob on host computer 300 control panel is held to realize the transmission whole aircraft power system experimental provision being carried out to monitor data display and steering order by PC.
Inverter is by the conversion of DC-AC, and the alternating current of 200V/115V, 400Hz required for aviation AC load of 28V DC inverter, on supply aircraft, various AC load uses.
The above embodiment further describes embodiment of the present utility model, can not assert that embodiment of the present utility model is confined to these explanations.It should be pointed out that for the person of ordinary skill of the art, without departing from the concept of the premise utility, some distortion and improvement can also be made, and character or purposes identical, these all belong to the protection domain of utility model.Therefore, the protection domain of the utility model patent should be as the criterion with claims.
Claims (4)
1. a type aircraft power-supply system experiment platform device, is characterized in that: comprise motor speed adjusting control system, Excitation Controller, PC hold host computer, inverter and aircraft battery;
The output terminal of motor speed governing system is connected to the input end of Excitation Controller, the output terminal of Excitation Controller is connected in DC voltage bus, and motor speed adjusting control system and Excitation Controller are held host computer to carry out two-way communication to be connected respectively with PC; The input end of aircraft battery is connected in DC voltage bus, and the output terminal of aircraft battery is connected to the respective input of Excitation Controller; The input end of inverter is connected in DC voltage bus, and the output terminal of inverter is connected in alternating voltage bus;
Motor speed adjusting control system has the permasyn morot and DSP speed setting controller that are connected, Excitation Controller has the alternator and three phase rectifier that are connected, the rotating speed of permasyn morot is regulated by DSP speed setting controller, be power when alternator provides generating required for rotor turns by permasyn morot, the three-phase alternating current that alternator exports exports 28V direct current, by the alternating current of inverter by 200V/115V, 400Hz required for aviation AC load of 28V DC inverter after three phase rectifier.
2. a kind of type aircraft power-supply system experiment platform device according to claim 1, is characterized in that: described motor speed governing system also comprises rectification circuit, three-phase inverting circuit, auxiliary power circuit, optical coupling isolation circuit, current detection circuit and photoelectric encoder interface circuit;
In motor speed adjusting control system, the connection of each several part is as follows:
The input end of rectification circuit is connected to civil power 220V interface, and the output terminal of rectification circuit is connected respectively to the input end of three-phase inverting circuit, auxiliary power circuit;
The input end of three-phase inverting circuit is connected respectively to the output terminal of rectification circuit, optical coupling isolation circuit, and the output terminal of three-phase inverting circuit is connected respectively to the input end of current detection circuit, permasyn morot;
The input end of auxiliary power circuit is connected to the output terminal of rectification circuit, and the output terminal of auxiliary power circuit is connected respectively to the respective input of optical coupling isolation circuit, DSP speed setting controller;
The input end of optical coupling isolation circuit is connected respectively to the output terminal of PWM module in auxiliary power circuit, DSP speed setting controller, and the output terminal of optical coupling isolation circuit is connected to the input end of three-phase inverting circuit;
The input end of current detection circuit is connected to the output terminal of three-phase inverting circuit, and the output terminal of electric current electrical measurement circuit is connected to the input end of A/D module in DSP speed setting controller;
The input end of permasyn morot is connected to the output terminal of three-phase inverting circuit, the output terminal of permasyn morot is connected to the input end of photoelectric encoder interface circuit, and the output terminal of photoelectric encoder interface circuit is connected to the input end of QEP module in DSP speed setting controller.
3. a kind of type aircraft power-supply system experiment platform device according to claim 1, is characterized in that: described Excitation Controller also comprises excitation main circuit, driving circuit, exciting current sample circuit, voltage sampling circuit, current sampling circuit and STM32 excitation controller;
In Excitation Controller, the connection of each several part is as follows:
Alternator exports three-phase alternating current, after three phase rectifier rectification, exports 28V direct current in DC voltage bus;
The input end of excitation main circuit connects the output terminal of driving circuit, aircraft battery respectively, and the output terminal of excitation main circuit connects the input end of the field copper of alternator, exciting current sample circuit respectively;
The input end of driving circuit connects the output terminal of timer in STM32 excitation controller, and the output terminal of driving circuit connects the input end of excitation main circuit;
The input end of exciting current sample circuit connects the output terminal of excitation main circuit, and the output terminal of exciting current sample circuit connects the input end of an ADC module in STM32 excitation controller;
The input end of voltage sampling circuit is connected in DC voltage bus, and the output terminal of voltage sampling circuit is connected to the input end of the 2nd ADC module in STM32 excitation controller;
The input end of current sampling circuit is connected in DC voltage bus, and the output terminal of current sampling circuit is connected to the input end of the 3rd ADC module in STM32 excitation controller.
4. a kind of type aircraft power-supply system experiment platform device according to any one of claim 1-3, it is characterized in that: described motor speed governing system also comprises keyboard and display panel, DSP speed setting controller is bi-directionally connected by its digital I/O interface and keyboard and display panel.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105353682A (en) * | 2015-11-20 | 2016-02-24 | 泉州装备制造研究所 | Airplane power supply system experiment platform device |
| CN105806200A (en) * | 2016-05-23 | 2016-07-27 | 桥弘数控科技（上海）有限公司 | Encoder parsing method |
| CN109708893A (en) * | 2018-10-29 | 2019-05-03 | 中国航发贵阳发动机设计研究所 | A kind of aero-engine alternative electric generation type power-measuring system |
| CN109959831A (en) * | 2019-04-17 | 2019-07-02 | 成都航空职业技术学院 | A kind of laboratory simulation unmanned plane power-supply system |
| CN111740660A (en) * | 2020-07-16 | 2020-10-02 | 瑞安市伏特佳电子有限公司 | Energy-saving generator set |
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2015
- 2015-11-20 CN CN201520934655.6U patent/CN205193510U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105353682A (en) * | 2015-11-20 | 2016-02-24 | 泉州装备制造研究所 | Airplane power supply system experiment platform device |
| CN105353682B (en) * | 2015-11-20 | 2018-03-06 | 泉州装备制造研究所 | Aircraft power system experiment platform device |
| CN105806200A (en) * | 2016-05-23 | 2016-07-27 | 桥弘数控科技（上海）有限公司 | Encoder parsing method |
| CN105806200B (en) * | 2016-05-23 | 2018-09-28 | 桥弘数控科技（上海）有限公司 | A kind of analytic method of encoder |
| CN109708893A (en) * | 2018-10-29 | 2019-05-03 | 中国航发贵阳发动机设计研究所 | A kind of aero-engine alternative electric generation type power-measuring system |
| CN109959831A (en) * | 2019-04-17 | 2019-07-02 | 成都航空职业技术学院 | A kind of laboratory simulation unmanned plane power-supply system |
| CN111740660A (en) * | 2020-07-16 | 2020-10-02 | 瑞安市伏特佳电子有限公司 | Energy-saving generator set |
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