CN204928654U - High -power high -efficient PMSM servo controller of manned electronic aircraft - Google Patents
High -power high -efficient PMSM servo controller of manned electronic aircraft Download PDFInfo
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- CN204928654U CN204928654U CN201520500159.XU CN201520500159U CN204928654U CN 204928654 U CN204928654 U CN 204928654U CN 201520500159 U CN201520500159 U CN 201520500159U CN 204928654 U CN204928654 U CN 204928654U
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Abstract
The utility model provides a high -power high -efficient PMSM servo controller of manned electronic aircraft, includes circuit control unit and mechanical unit, wherein circuit control unit includes inside unit and outside unit, wherein inside unit includes electric capacity break plate B2, three -phase inverter main circuit, the main control panel, current sensor module, temperature sensor and direct current busbar voltage sampling unit, outside unit includes X1 interface, X2 interface, X3 interface, X4 interface, X5 interface and X6 interface, the beneficial effect of the utility model: this type PMSM servo controller has realized high reliability, light, big power output, low -cost technological achievement, and the technique of having filled high -power high -efficient permanent magnet synchronous motor (PMSM) the controller design of electronic aircraft is blank, has improved job stabilization nature, payload and the duration of electronic aircraft to the cost is reduced more does benefit to the upgrading and the convenient assembling of complete machine system.
Description
Technical field
The utility model belongs to technical field of servo control, particularly relates to a kind of manned electric airplane large power high efficiency permagnetic synchronous motor servo controller.
Background technology
At present, the adoptable power drive system of domestic manned electric airplane mainly includes brush DC motor system, induction motor system, switch magnetic-resistance motor system, brushless direct current motor system and PMSM Control System.Wherein permagnetic synchronous motor (PMSM) system has the highest efficiency, high power density and torque density, the preferably performance characteristics such as speed regulation capacity, lower vibration noise, has the optimal synthesis index that electric airplane drives.
At present, high-power PMSM controller major defect: cost is high, blockade on new techniques (equipment maintenance cost is high, and technical support difficulty is large, and the cycle is long), weight large (reducing the payload of aircraft), the reliability that works long hours is low.
At present, close with manned electric airplane PMSM servo controller product mainly electric automobile PMSM big power controller.Because this controller is used for electric automobile, the type of cooling mainly water-cooling pattern of controller, and weight is large, and nominal operation efficiency is low, and the reliability that works long hours is low.Therefore, the control system of manned electric airplane permagnetic synchronous motor is not suitable for.
Summary of the invention
The purpose of this utility model is to overcome above-mentioned deficiency, provides a kind of manned electric airplane large power high efficiency permagnetic synchronous motor servo controller.
The technical solution of the utility model is such: this type PMSM servo controller comprises circuit control unit and machine assembly;
Wherein circuit control unit comprises internal element and external unit; Wherein internal element comprises electric capacity distribution plate B2, three-phase inverter main circuit, master board, current sensor module, temperature sensor and DC bus-bar voltage sampling unit; External unit comprises X1 interface, X2 interface, X3 interface, X4 interface, X5 interface and X6 interface;
Described three-phase inverter main circuit comprises three groups of inverter bridges and drive plate;
Described current sensor module comprises three groups of AC current sensor and one group of DC current sensor;
Described temperature sensor comprises heatsink temperature sensor and controller temperature sensor;
Described X1 interface is responsible for electric control and fans drive in working power, buffering;
Described X2 interface is responsible for switching signal input and output and analog signal input;
Described X3 interface is responsible for two-way CAN and a road RS232 bus;
Described X4 interface is responsible for electromechanical transducer, a road photoelectric encoder, a road Hall element, three groups of motor internal winding temperature analog signals;
Described X5 interface is responsible for DC bus;
Described X6 interface is responsible for driver output;
Internal element connects: DC bus interface X5 adopts bus both positive and negative polarity copper bar to connect electric capacity distribution plate B2 through over-current sensor IS4, electric capacity distribution plate B2 adopts positive and negative soft copper to arrange connection three-phase inverter main circuit, three-phase inverter main circuit adopts three-phase soft copper row after three-phase current sensor, connect driver output interface X6 again, thus forms driving major loop.Current sensor IS4, busbar voltage, three-phase output current transducer IS1, IS2, IS3, heatsink temperature sensor T4, controller temperature sensor T5, drive plate output temperature signal and control signal adopt terminal to be connected master board B1 by signal conditioning circuit.Master board B1 adopts terminal to connect X1, X2, X3, X4 external connection terminals respectively through insulation blocking and signal conditioning circuit simultaneously.
External unit connects: external dc bus X5 interface adopts shielded type cable to connect DC bus major loop buffering power supply unit, external drive output interface X6 adopts shielded type cable to connect PMSM motor, X1 interface adopts shielded type cable to connect operate outside power supply 24V respectively, radiator fan, cushion power on unit relay and main circuit breaker, X2 interface connects exterior I O equipment and simulation speed control device respectively, X3 interface adopts shielded type cable to connect debugging host computer respectively, user's host computer and digital displaying meter, X4 interface adopts shielded type cable to connect the photoelectric encoder that motor is installed respectively, Hall element and temperature sensor.
Machine assembly comprises housing unit, control board support and heat sink assembly; Housing unit comprises housing KT and case lid KTG; Heat sink assembly comprises radiator SRQ, radiator protecting cover SRG and radiator fan.Case lid is arranged on housing tip, and radiator is arranged on housing lower end, and radiator protecting cover is arranged on radiator two ends and bottom, and radiator fan is arranged on the side of radiator, control board support installing in housing, radiator upper end.
Described master board is arranged on control board support;
Described housing unit, control board support and heat sink assembly all adopt lightweight aluminium to make.
The beneficial effects of the utility model:
This type PMSM servo controller achieves the technological achievement of high reliability (under rated condition complete machine 2 hours reliability services), lightweight (controller Weight control is within 10kg), high-power output (amount 50KW), low cost, fill up the technological gap of electric airplane large power high efficiency permanent magnet synchronous motor (PMSM) Controller gain variations, reach advanced level.This type PMSM servo controller improves the job stability of electric airplane, payload and flying power, and reduce cost, be more conducive to the upgrading of machine system and easy to assembly, for the production of this type controller and maintenance provide technical support, its practical significance and benefit fairly obvious.
Accompanying drawing illustrates:
Fig. 1 is PMSM motor servo controller functional block diagram;
Fig. 2 is PMSM motor servo controller device assembled front view;
Fig. 3 is PMSM motor servo controller device assembling plan view;
Fig. 4 is that PMSM motor servo controller device removes top cover mounted inside vertical view;
In figure: 1 housing, 2IGBT module, 3 connectors, 4 electric capacity distribution plates, 5 drive plates, 6 radiator fans, 7 AC current sensor, 8 bus positive pole copper bars, 9 three-phase soft copper rows 1, 10 three-phase soft copper rows 2, 11 negative soft copper rows 1, 12 positive soft copper rows 2, 13 DC current sensor, 14 radiators, 15 radiator protecting covers, 16 temperature sensors, 17 master boards, 18 aluminum studs, 19 case lid, 20 air plugs 1, 21 air plugs 2, 22 air plugs 3, 23 air plugs 4, 24 control board supports, 25 bus negative pole copper bars.
Embodiment
Below in conjunction with accompanying drawing and enforcement, the utility model is further described.
As Fig. 1,2, shown in 3 and 4, this type PMSM servo controller comprises circuit control unit and machine assembly;
Wherein circuit control unit comprises internal element and external unit; Wherein internal element comprises electric capacity distribution plate B2; Three-phase inverter main circuit (three groups of inverter bridges are often organized bridge and comprised: IGBT module M1, M2, M3 and drive plate QD1, QD2, QD3 are formed, and wherein IGBT module adopts FF600R07ME4, and drive plate adopts 2SP0115T); Master board B1 (DSP28335, as main control unit, realizes the functions such as analog-and digital-information gathering, space vector control algorithm, control logic, output, is arranged on control board support TJ1); Current sensor (three groups of AC current sensor HAH1DR400-S:IS1, IS2, IS3 and one group of DC current sensor HAH1DR200-S:IS4) and temperature sensor (heatsink temperature sensor: T4 and controller temperature sensor: T5); DC bus-bar voltage sampling unit.
External unit comprises: X1 interface (electric control in working power, buffering, fans drive: FAN1, FAN2 and FAN3); X2 interface (switching signal input and output and analog signal input); X3 interface (two-way CAN and a road RS232 bus); X4 interface (electromechanical transducer interface, road photoelectric encoder A, B, a Z, road Hall element U, V, a W, three groups of motor internal winding temperature analog signals: T1, T2, T3); X5 interface (DC bus 300-420V:X5-BUS+ and X5-BUS-); X6 interface (driver output: X6-U, X6-V and X6-W).
Internal element annexation is as follows: DC bus interface X5 adopts bus both positive and negative polarity copper bar to connect electric capacity distribution plate B2 through over-current sensor IS4, electric capacity distribution plate B2 adopts positive and negative soft copper to arrange connection three-phase inverter main circuit, three-phase inverter main circuit adopts three-phase soft copper row after three-phase current sensor, connect driver output interface X6 again, thus forms driving major loop.Current sensor IS4, busbar voltage, three-phase output current transducer IS1, IS2, IS3, heatsink temperature sensor T4, controller temperature sensor T5, drive plate output temperature signal and control signal adopt terminal to be connected master board B1 by signal conditioning circuit.Master board B1 adopts terminal to connect X1, X2, X3, X4 external connection terminals respectively through insulation blocking and signal conditioning circuit simultaneously.
External unit annexation is as follows: external dc bus X5 interface adopts shielded type cable to connect DC bus major loop buffering power supply unit (300-420V DC bus power supply), external drive output interface X6 adopts shielded type cable to connect PMSM motor, X1 interface adopts shielded type cable to connect operate outside power supply 24V respectively, radiator fan, cushion power on unit relay and main circuit breaker, X2 interface connects exterior I O equipment and simulation speed control device respectively, X3 interface adopts shielded type cable to connect debugging host computer respectively, user's host computer and digital displaying meter, X4 interface adopts shielded type cable to connect the photoelectric encoder that motor is installed respectively, Hall element and temperature sensor.
Machine assembly comprises housing unit, control board support 24 and heat sink assembly; Housing unit comprises housing 1KT and case lid 19KTG; Heat sink assembly comprises radiator 14SRQ, radiator protecting cover 15SRG and radiator fan 6.Case lid 19 is arranged on housing 1 top, and radiator 14 is arranged on housing 1 lower end, and radiator protecting cover 15 is arranged on radiator 14 two ends and bottom, and radiator fan 6 is arranged on the side of radiator 14, and control board support 24 is arranged in housing 1, radiator 14 upper end.
Housing unit, control board support 24 and heat sink assembly all adopt lightweight aluminium to design, design in strict accordance with national electromagnetic compatibility standard, simultaneously compatiblely consider intensity and weight and power consumption cooling requirements, especially fansink designs have employed the comprehensive Design that many flabellums large area adds fan, well meet power consumption requirements.Internal part space layout also designs in strict accordance with national electromagnetic compatibility standard, makes every effort to reliable, safe, reasonable, succinct.
Claims (4)
1. a manned electric airplane large power high efficiency permagnetic synchronous motor servo controller, is characterized in that: comprise circuit control unit and machine assembly;
Wherein circuit control unit comprises internal element and external unit; Wherein internal element comprises electric capacity distribution plate B2, three-phase inverter main circuit, master board, current sensor module, temperature sensor and DC bus-bar voltage sampling unit; External unit comprises X1 interface, X2 interface, X3 interface, X4 interface, X5 interface and X6 interface;
Described three-phase inverter main circuit comprises three groups of inverter bridges and drive plate;
Described current sensor module comprises three groups of AC current sensor and one group of DC current sensor;
Described temperature sensor comprises heatsink temperature sensor and controller temperature sensor;
Described X1 interface is responsible for electric control and fans drive in working power, buffering;
Described X2 interface is responsible for switching signal input and output and analog signal input;
Described X3 interface is responsible for two-way CAN and a road RS232 bus;
Described X4 interface is responsible for electromechanical transducer, a road photoelectric encoder, a road Hall element, three groups of motor internal winding temperature analog signals;
Described X5 interface is responsible for DC bus;
Described X6 interface is responsible for driver output;
Internal element connects: DC bus interface X5 adopts bus both positive and negative polarity copper bar to connect electric capacity distribution plate B2 through over-current sensor IS4, electric capacity distribution plate B2 adopts positive and negative soft copper to arrange connection three-phase inverter main circuit, three-phase inverter main circuit adopts three-phase soft copper row after three-phase current sensor, connect driver output interface X6 again, thus form driving major loop, current sensor IS4, busbar voltage, three-phase output current transducer IS1, IS2, IS3, heatsink temperature sensor T4, controller temperature sensor T5, drive plate output temperature signal adopts terminal to be connected master board B1 with control signal by signal conditioning circuit, master board B1 adopts terminal to connect X1 respectively through insulation blocking and signal conditioning circuit simultaneously, X2, X3, X4 external connection terminals, external unit connects: external dc bus X5 interface adopts shielded type cable to connect DC bus major loop buffering power supply unit, external drive output interface X6 adopts shielded type cable to connect PMSM motor, X1 interface adopts shielded type cable to connect operate outside power supply 24V respectively, radiator fan, cushion power on unit relay and main circuit breaker, X2 interface connects exterior I O equipment and simulation speed control device respectively, X3 interface adopts shielded type cable to connect debugging host computer respectively, user's host computer and digital displaying meter, X4 interface adopts shielded type cable to connect the photoelectric encoder that motor is installed respectively, Hall element and temperature sensor.
2. manned electric airplane large power high efficiency permagnetic synchronous motor servo controller according to claim 1, is characterized in that: machine assembly comprises housing unit, control board support and heat sink assembly; Housing unit comprises housing and case lid; Heat sink assembly comprises radiator, radiator protecting cover and radiator fan, case lid is arranged on housing tip, radiator is arranged on housing lower end, radiator protecting cover is arranged on radiator two ends and bottom, radiator fan is arranged on the side of radiator, control board support installing in housing, radiator upper end.
3. manned electric airplane large power high efficiency permagnetic synchronous motor servo controller according to claim 2, is characterized in that: described master board is arranged on control board support.
4. manned electric airplane large power high efficiency permagnetic synchronous motor servo controller according to claim 2, is characterized in that: described housing unit, control board support and heat sink assembly all adopt lightweight aluminium to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520500159.XU CN204928654U (en) | 2015-07-10 | 2015-07-10 | High -power high -efficient PMSM servo controller of manned electronic aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520500159.XU CN204928654U (en) | 2015-07-10 | 2015-07-10 | High -power high -efficient PMSM servo controller of manned electronic aircraft |
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| CN204928654U true CN204928654U (en) | 2015-12-30 |
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| CN201520500159.XU Expired - Fee Related CN204928654U (en) | 2015-07-10 | 2015-07-10 | High -power high -efficient PMSM servo controller of manned electronic aircraft |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105048911A (en) * | 2015-07-10 | 2015-11-11 | 沈阳航空航天大学 | Large power high efficiency PMSM (Permanent Magnet Synchronous Motor) servo controller for manned electric airplane |
| CN105897074A (en) * | 2016-06-14 | 2016-08-24 | 上海华铭智能终端设备股份有限公司 | Servo driver |
| CN106602968A (en) * | 2017-01-05 | 2017-04-26 | 四川埃姆克伺服科技有限公司 | Servo motor driving unit structure |
| CN111579850A (en) * | 2020-04-16 | 2020-08-25 | 南京金龙新能源汽车研究院有限公司 | System and method for improving anti-interference performance of motor rack system |
| CN111770671A (en) * | 2020-07-17 | 2020-10-13 | 辽宁通用航空研究院 | Radiator structure optimization method based on operation condition of electric aircraft |
| US20230079752A1 (en) * | 2020-05-27 | 2023-03-16 | Byd Company Limited | Motor controller and vehicle having same |
-
2015
- 2015-07-10 CN CN201520500159.XU patent/CN204928654U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105048911A (en) * | 2015-07-10 | 2015-11-11 | 沈阳航空航天大学 | Large power high efficiency PMSM (Permanent Magnet Synchronous Motor) servo controller for manned electric airplane |
| CN105897074A (en) * | 2016-06-14 | 2016-08-24 | 上海华铭智能终端设备股份有限公司 | Servo driver |
| CN105897074B (en) * | 2016-06-14 | 2019-09-27 | 上海华铭智能终端设备股份有限公司 | A kind of servo-driver |
| CN106602968A (en) * | 2017-01-05 | 2017-04-26 | 四川埃姆克伺服科技有限公司 | Servo motor driving unit structure |
| CN106602968B (en) * | 2017-01-05 | 2023-07-25 | 四川埃姆克伺服科技有限公司 | Servo motor driving unit structure |
| CN111579850A (en) * | 2020-04-16 | 2020-08-25 | 南京金龙新能源汽车研究院有限公司 | System and method for improving anti-interference performance of motor rack system |
| US20230079752A1 (en) * | 2020-05-27 | 2023-03-16 | Byd Company Limited | Motor controller and vehicle having same |
| CN111770671A (en) * | 2020-07-17 | 2020-10-13 | 辽宁通用航空研究院 | Radiator structure optimization method based on operation condition of electric aircraft |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151230 Termination date: 20180710 |
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| CF01 | Termination of patent right due to non-payment of annual fee |