CN113928590A - Electric aircraft propulsion system test platform based on modular permanent magnet synchronous motor - Google Patents
Electric aircraft propulsion system test platform based on modular permanent magnet synchronous motor Download PDFInfo
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- CN113928590A CN113928590A CN202111199917.5A CN202111199917A CN113928590A CN 113928590 A CN113928590 A CN 113928590A CN 202111199917 A CN202111199917 A CN 202111199917A CN 113928590 A CN113928590 A CN 113928590A
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- 238000012360 testing method Methods 0.000 title claims abstract description 55
- 230000001360 synchronised effect Effects 0.000 title claims abstract description 44
- 238000004088 simulation Methods 0.000 claims abstract description 35
- 238000004891 communication Methods 0.000 claims abstract description 4
- 238000005259 measurement Methods 0.000 claims description 12
- 238000001816 cooling Methods 0.000 claims description 11
- 238000004804 winding Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
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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
Abstract
Electric aircraft propulsion system test platform based on modularization PMSM relates to electric aircraft test technical field. The platform comprises a modularized permanent magnet synchronous motor and an upper computer; the platform also comprises a modular voltage source inverter, a propeller testing platform and a power electronic semi-physical simulation platform; the modularized voltage source inverter is used for driving the modularized permanent magnet synchronous motor and outputting voltage, current and temperature; the propeller testing platform is driven by the modularized permanent magnet synchronous motor and outputs rotating speed, torque and pulling force; the power electronic semi-physical simulation platform is used for acquiring voltage, current and temperature output by the modular voltage source inverter, acquiring rotating speed, torque and pulling force output by the propeller test platform and performing two-way communication with an upper computer. The invention solves the problem that the conventional aviation electric propulsion system based on the modular permanent magnet synchronous motor is lack of a ground test platform.
Description
Technical Field
The invention relates to the technical field of electric airplane testing.
Background
Compared with the traditional airplane, the electric airplane is an important measure for the aviation industry to carry out green aviation and meet global environmental challenges, and is an inevitable choice for achieving the goal of reducing carbon emission. The motor, as the power source and the core component in the electric aircraft, receives more and more attention, is arousing a new round of energy revolution. In an electric aircraft, in order to improve the fault-tolerant capability of a motor and reduce the current borne by an inverter, the motor windings are often designed in a multi-phase or modular manner. Modular Permanent Magnet Synchronous Machines (PMSM) have gained wide attention with their advantages of high reliability, fault-tolerant capability, high power density, and high control accuracy. The modularized permanent magnet synchronous motor needs to be designed into a plurality of three-phase module units, and each module unit is independently controlled by an independent three-phase voltage source inverter. The structure has high reliable fault-tolerant capability on one hand, and can reduce the current borne by a winding and an inverter power device and prolong the service life of a motor system on the other hand. However, the aviation electric propulsion system based on the modular permanent magnet synchronous motor needs to be tested in the ground in an early stage, so that a set of ground test platform needs to be built.
Disclosure of Invention
The invention aims to solve the problem that the conventional aviation electric propulsion system based on a modular permanent magnet synchronous motor is lack of a ground test platform, and provides a propulsion system test platform of an electric aircraft based on the modular permanent magnet synchronous motor, so that the performance of the propulsion system of the electric aircraft can be tested, and the aim of early-stage ground debugging is fulfilled.
The technical scheme of the invention is as follows:
the electric airplane propulsion system test platform based on the modular permanent magnet synchronous motor comprises a modular permanent magnet synchronous motor 3 and an upper computer 6;
the platform also comprises a modular voltage source inverter 2, a propeller testing platform 4 and a power electronic semi-physical simulation platform 5;
the modular voltage source inverter 2 is used for driving the modular permanent magnet synchronous motor 3 and outputting voltage, current and temperature;
the propeller testing platform 4 is driven by the modularized permanent magnet synchronous motor 3 and outputs rotating speed, torque and pulling force;
the power electronic semi-physical simulation platform 5 is used for collecting the voltage, the current and the temperature output by the modular voltage source inverter 2, collecting the rotating speed, the torque and the pulling force output by the propeller test platform 4 and carrying out two-way communication with the upper computer 6.
Preferably, the platform further comprises a dc power supply/battery 1, the dc power supply/battery 1 being adapted to provide electrical power to the modular voltage source inverter 2.
Preferably, the propeller test platform 4 comprises a propeller, a rotating speed sensor, a torque sensor and a tension sensor; the modularized permanent magnet synchronous motor 3 drives the propeller to rotate, the rotating speed sensor measures the rotating speed of the propeller and outputs the rotating speed to the power electronic semi-physical simulation platform 5, the torque sensor measures the torque of the propeller and outputs the torque to the power electronic semi-physical simulation platform 5, and the tension sensor measures the rotating speed of the propeller and outputs the rotating speed to the power electronic semi-physical simulation platform 5.
Preferably, the modular voltage source inverter 2 comprises a three-phase current measuring circuit board I2-4, a three-phase current measuring circuit board II 2-5, a three-phase current measuring circuit board III 2-6, a voltage source inverter I2-7, a voltage source inverter II 2-8, a voltage source inverter III 2-9, a three-phase voltage measuring circuit board I2-10, a three-phase voltage measuring circuit board II 2-11, a three-phase voltage measuring circuit board III 2-12, a thermocouple temperature sensor I2-13, a thermocouple temperature sensor II 2-14 and a thermocouple temperature sensor III 2-15;
the direct current power supply/battery 1 is used for supplying power to the first voltage source inverter No. 2-7, the second voltage source inverter No. 2-8 and the third voltage source inverter No. 2-9;
the three-phase current measuring circuit board I2-4, the three-phase voltage measuring circuit board I2-10 and the thermocouple temperature sensor I2-13 are used for respectively collecting the current, the voltage and the temperature of the voltage source inverter I2-7 and sending the collected current, the voltage and the temperature of the voltage source inverter I2-7 to the power electronic semi-physical simulation platform 5;
the second three-phase current measuring circuit board 2-5, the second three-phase voltage measuring circuit board 2-11 and the second thermocouple temperature sensor 2-14 respectively collect the current, voltage and temperature of the second voltage source inverter 2-8 and send the collected current, voltage and temperature of the first voltage source inverter 2-7 to the power electronic semi-physical simulation platform 5;
the third three-phase current measuring circuit board 2-6 and the third three-phase voltage measuring circuit board 2-12 are provided with thermocouple temperature sensors 2-15 which respectively collect the current, the voltage and the temperature of the third voltage source inverter 2-9 and send the collected current, the voltage and the temperature of the first voltage source inverter 2-7 to the power electronic semi-physical simulation platform 5.
Preferably, the platform further comprises an auxiliary power supply 24V2-1, wherein the auxiliary power supply 24V2-1 is used for supplying power to the first three-phase current measuring circuit board 2-4, the second three-phase current measuring circuit board 2-5, the third three-phase current measuring circuit board 2-6, the first three-phase voltage measuring circuit board 2-10, the second three-phase voltage measuring circuit board 2-11 and the third three-phase voltage measuring circuit board 2-12 in the modular voltage source inverter 2.
Preferably, the platform further comprises an auxiliary power supply 12V2-2 and a cooling fan 2-3; the auxiliary power supply 12V2-2 is used for driving the cooling fan 2-3 to rotate; the cooling fan 2-3 is used for cooling the first voltage source inverter 2-7, the second voltage source inverter 2-8 and the third voltage source inverter 2-9 in the modular voltage source inverter 2.
Has the advantages that: the direct current power supply/battery in the platform provides power for the modular voltage source inverter, the modular permanent magnet synchronous motor is driven to rotate by the modular voltage source inverter, the propeller test platform is driven by the modular permanent magnet synchronous motor, the voltage, the current and the temperature output by the modular voltage source inverter are completed by data transmission between the power electronic semi-physical simulation platform and the upper computer, the rotating speed, the torque and the pulling force output by the propeller test platform are monitored in real time, a motor control core algorithm is burnt into the power electronic semi-physical simulation platform by the upper computer, the modular permanent magnet synchronous motor is controlled, the ground test of an electric propulsion system of the electric airplane is realized, and the performance parameters of the propulsion system are obtained in real time. Meanwhile, the multiple module driving motors adopt a redundancy driving scheme, so that the reliability of the electric propulsion system is improved, and the scheme has wide application prospect and high popularization value.
Drawings
FIG. 1 is a schematic diagram of the platform of the present invention;
FIG. 2 is a schematic diagram of the components of a modular voltage source inverter in the platform of the present invention;
FIG. 3 is a schematic diagram of a portion of the platform of the present invention;
fig. 4 is a distribution diagram of the winding of the modular permanent magnet synchronous motor body.
Detailed Description
In a first embodiment, the first embodiment is specifically described with reference to fig. 1 to 4, and the electric aircraft propulsion system test platform based on the modular permanent magnet synchronous motor in the first embodiment includes a modular permanent magnet synchronous motor 3 and an upper computer 6;
the platform also comprises a modular voltage source inverter 2, a propeller testing platform 4 and a power electronic semi-physical simulation platform 5;
the modular voltage source inverter 2 is used for driving the modular permanent magnet synchronous motor 3 and outputting voltage, current and temperature;
the propeller testing platform 4 is driven by the modularized permanent magnet synchronous motor 3 and outputs rotating speed, torque and pulling force;
the power electronic semi-physical simulation platform 5 is used for collecting the voltage, the current and the temperature output by the modular voltage source inverter 2, collecting the rotating speed, the torque and the pulling force output by the propeller test platform 4 and carrying out two-way communication with the upper computer 6.
In this embodiment, the modular permanent magnet synchronous motor 3 adopts a three-module winding structure, and three sets of windings have a spatial phase difference of 120 degrees, thereby forming three unit motors. The motor structure is 36-slot 42-pole and is an outer rotor structure, as shown in fig. 4.
The modularized permanent magnet synchronous motor directly drives the propeller testing platform to enable the propeller testing platform to realize conversion of electric energy and mechanical energy, and therefore ground testing is completed.
The propeller test platform is provided with a rotating speed torque sensor and a tension sensor, and output signals need to be monitored in real time on the power electronic semi-physical simulation platform.
The power electronic semi-physical simulation platform is used for receiving a control signal of an upper computer and monitoring signals output by the modular voltage source inverter and the propeller test platform, and the output signals are voltage, current, temperature, rotating speed, torque and pulling force. The motor control core algorithm is programmed in the upper computer and is burnt into the power electronic semi-physical simulation platform, so that the modular permanent magnet synchronous motor can be controlled.
The invention discloses a modularized voltage source inverter, which realizes direct current-alternating current energy conversion and drives a motor (a modularized permanent magnet synchronous motor). The modularized voltage source inverter is also designed into a modularized structure because the motor is a modularized winding, and the modularized voltage source inverter takes a three-module permanent magnet synchronous motor as an example and has the specific composition as shown in figure 4.
The platform drives the modularized permanent magnet synchronous motor to rotate through the modularized voltage source inverter, then drives the propeller testing platform through the modularized permanent magnet synchronous motor, and completes the voltage, the current and the temperature output by the modularized voltage source inverter and the rotating speed, the torque and the tension output by the propeller testing platform through the data transmission between the power electronic semi-physical simulation platform and the upper computer. Meanwhile, the plurality of modules drive the motor, and a redundancy driving scheme is adopted, so that the reliability of the electric propulsion system is improved.
In a second embodiment, the test platform for the propulsion system of the electric aircraft based on the modular permanent magnet synchronous motor according to the first embodiment is further described, the test platform further includes a dc power supply/battery 1, and the dc power supply/battery 1 is used for supplying electric energy to the modular voltage source inverter 2.
The direct current power supply/battery supplies power for the test platform and simulates a direct current power supply system of the electric airplane.
In a third specific embodiment, the present embodiment is a further description of the test platform of the modular permanent magnet synchronous motor-based electric aircraft propulsion system described in the second embodiment, where the propeller test platform 4 includes a propeller, a rotation speed sensor, a torque sensor, and a tension sensor; the modularized permanent magnet synchronous motor 3 drives the propeller to rotate, the rotating speed sensor measures the rotating speed of the propeller and outputs the rotating speed to the power electronic semi-physical simulation platform 5, the torque sensor measures the torque of the propeller and outputs the torque to the power electronic semi-physical simulation platform 5, and the tension sensor measures the rotating speed of the propeller and outputs the rotating speed to the power electronic semi-physical simulation platform 5.
In the embodiment, the modularized permanent magnet synchronous motor directly drives the propeller in the propeller test platform to rotate the propeller in the propeller test platform, so that the conversion of electric energy and mechanical energy is realized, and the ground test is completed. Unlike the ordinary motor test, the load is not a dynamometer, but the air resistance of the propeller when rotating. The rotating speed, the torque and the tension obtained after the propeller rotates are monitored by the rotating speed sensor, the torque sensor and the tension sensor, and the monitored rotating speed, torque and tension are sent to the power electronic semi-physical simulation platform for real-time monitoring.
A fourth embodiment is a further description of the test platform of the modular permanent magnet synchronous motor-based electric aircraft propulsion system described in the third embodiment, the modularized voltage source inverter 2 comprises a three-phase current measuring circuit board I2-4, a three-phase current measuring circuit board II 2-5, a three-phase current measuring circuit board III 2-6, a voltage source inverter I2-7, a voltage source inverter II 2-8, a voltage source inverter III 2-9, a three-phase voltage measuring circuit board I2-10, a three-phase voltage measuring circuit board II 2-11, a three-phase voltage measuring circuit board III 2-12, a thermocouple temperature sensor I2-13, a thermocouple temperature sensor II 2-14 and a thermocouple temperature sensor III 2-15;
the direct current power supply/battery 1 is used for supplying power to the first voltage source inverter No. 2-7, the second voltage source inverter No. 2-8 and the third voltage source inverter No. 2-9;
the three-phase current measuring circuit board I2-4, the three-phase voltage measuring circuit board I2-10 and the thermocouple temperature sensor I2-13 are used for respectively collecting the current, the voltage and the temperature of the voltage source inverter I2-7 and sending the collected current, the voltage and the temperature of the voltage source inverter I2-7 to the power electronic semi-physical simulation platform 5;
the second three-phase current measuring circuit board 2-5, the second three-phase voltage measuring circuit board 2-11 and the second thermocouple temperature sensor 2-14 respectively collect the current, voltage and temperature of the second voltage source inverter 2-8 and send the collected current, voltage and temperature of the first voltage source inverter 2-7 to the power electronic semi-physical simulation platform 5;
the third three-phase current measuring circuit board 2-6 and the third three-phase voltage measuring circuit board 2-12 are provided with thermocouple temperature sensors 2-15 which respectively collect the current, the voltage and the temperature of the third voltage source inverter 2-9 and send the collected current, the voltage and the temperature of the first voltage source inverter 2-7 to the power electronic semi-physical simulation platform 5.
In the present embodiment, three voltage source inverters (i.e., the first voltage source inverter 2-7, the second voltage source inverter 2-8, and the third voltage source inverter 2-9) are connected in parallel to a dc power source/battery (or a dc bus), and the dc input terminals of the three voltage source inverters may be connected to the same dc bus or different dc buses.
When the voltage source inverter works, the three-phase current measuring circuit board and the three-phase voltage measuring circuit board are needed to monitor the current and the voltage of the three-phase winding, and meanwhile, the three-phase current measuring circuit board and the three-phase voltage measuring circuit board transmit the acquired current and voltage to the power electronic semi-physical simulation platform, so that the current and voltage signals can be sampled and monitored in real time.
The number of the thermocouple temperature sensors is 3, the thermocouple temperature sensors are required to be placed on a power module of a voltage source inverter and used for monitoring the temperature, and meanwhile, temperature signals are output to a power electronic semi-physical simulation platform.
In a fifth specific embodiment, the fourth embodiment is further described with respect to the test platform of the modular permanent magnet synchronous motor-based electric aircraft propulsion system described in the fourth embodiment, where the platform further includes an auxiliary power supply 24V2-1, and the auxiliary power supply 24V2-1 is configured to supply power to the first three-phase current measurement circuit board 2-4, the second three-phase current measurement circuit board 2-5, the third three-phase current measurement circuit board 2-6, the first three-phase voltage measurement circuit board 2-10, the second three-phase voltage measurement circuit board 2-11, and the third three-phase voltage measurement circuit board 2-12 in the modular voltage source inverter 2.
A sixth specific embodiment is a further description of the test platform for the propulsion system of the electric aircraft based on the modular permanent magnet synchronous motor according to the fifth embodiment, and the test platform further comprises an auxiliary power supply 12V2-2 and a cooling fan 2-3; the auxiliary power supply 12V2-2 is used for driving the cooling fan 2-3 to rotate; the cooling fan 2-3 is used for cooling the first voltage source inverter 2-7, the second voltage source inverter 2-8 and the third voltage source inverter 2-9 in the modular voltage source inverter 2.
In the fifth and sixth embodiments, 220V ac power is connected to two power modules to form an auxiliary power supply, a 12V auxiliary power supply (auxiliary power supply 12V) drives a heat dissipation fan to dissipate heat of the whole inverter, and a 24V auxiliary power supply (auxiliary power supply 24V) drives a circuit board to provide electric energy for the circuit board to ensure normal operation of the circuit board.
Claims (6)
1. The electric airplane propulsion system testing platform based on the modularized permanent magnet synchronous motor comprises the modularized permanent magnet synchronous motor (3) and an upper computer (6);
the test platform is characterized by further comprising a modular voltage source inverter (2), a propeller test platform (4) and a power electronic semi-physical simulation platform (5);
the modularized voltage source inverter (2) is used for driving the modularized permanent magnet synchronous motor (3) and outputting voltage, current and temperature;
the propeller testing platform (4) is driven by the modularized permanent magnet synchronous motor (3) and outputs rotating speed, torque and pulling force;
the power electronic semi-physical simulation platform (5) is used for collecting the voltage, the current and the temperature output by the modular voltage source inverter (2), collecting the rotating speed, the torque and the pulling force output by the propeller testing platform (4) and carrying out two-way communication with the upper computer (6).
2. Electric aircraft propulsion system test platform based on modular permanent magnet synchronous machines according to claim 1, characterized in that the platform further comprises a direct current power supply/battery (1), the direct current power supply/battery (1) being used to supply the modular voltage source inverter (2) with electrical energy.
3. The modular PMSM based electric aircraft propulsion system test platform according to claim 2, characterised in that the propeller test platform (4) comprises a propeller, a rotational speed sensor, a torque sensor and a tension sensor; the modularized permanent magnet synchronous motor (3) drives the propeller to rotate, the rotating speed sensor measures the rotating speed of the propeller and outputs the rotating speed to the power electronic semi-physical simulation platform (5), the torque sensor measures the torque of the propeller and outputs the torque to the power electronic semi-physical simulation platform (5), and the tension sensor measures the rotating speed of the propeller and outputs the rotating speed to the power electronic semi-physical simulation platform (5).
4. An electric aircraft propulsion system test platform based on modular PMSM according to claim 3, the modularized voltage source inverter (2) is characterized by comprising a three-phase current measuring circuit board I (2-4), a three-phase current measuring circuit board II (2-5), a three-phase current measuring circuit board III (2-6), a voltage source inverter I (2-7), a voltage source inverter II (2-8), a voltage source inverter III (2-9), a three-phase voltage measuring circuit board I (2-10), a three-phase voltage measuring circuit board II (2-11), a three-phase voltage measuring circuit board III (2-12), a thermocouple temperature sensor I (2-13), a thermocouple temperature sensor II (2-14) and a thermocouple temperature sensor III (2-15);
the direct current power supply/battery (1) is used for supplying power to the first voltage source inverter (2-7), the second voltage source inverter (2-8) and the third voltage source inverter (2-9);
the three-phase current measuring circuit board I (2-4), the three-phase voltage measuring circuit board I (2-10) and the thermocouple temperature sensor I (2-13) respectively collect the current, the voltage and the temperature of the voltage source inverter I (2-7), and send the collected current, the collected voltage and the collected temperature of the voltage source inverter I (2-7) to the power electronic semi-physical simulation platform (5);
the three-phase current measuring circuit board II (2-5), the three-phase voltage measuring circuit board II (2-11) and the thermocouple temperature sensor II (2-14) respectively collect the current, the voltage and the temperature of the voltage source inverter II (2-8), and send the collected current, the collected voltage and the collected temperature of the voltage source inverter I (2-7) to the power electronic semi-physical simulation platform (5);
the three-phase current measuring circuit board III (2-6) and the three-phase voltage measuring circuit board III (2-12) are connected with the thermocouple temperature sensor III (2-15) respectively, the current, the voltage and the temperature of the voltage source inverter III (2-9) are collected respectively, and the collected current, the collected voltage and the collected temperature of the voltage source inverter I (2-7) are sent to the power electronic semi-physical simulation platform (5).
5. The modular PMSM based electric aircraft propulsion system test platform of claim 4, further comprising an auxiliary power supply 24V (2-1), the auxiliary power supply 24V (2-1) being used to power a three-phase current measurement circuit board number one (2-4), a three-phase current measurement circuit board number two (2-5), a three-phase current measurement circuit board number three (2-6), a three-phase voltage measurement circuit board number one (2-10), a three-phase voltage measurement circuit board number two (2-11) and a three-phase voltage measurement circuit board number three (2-12) in the modular voltage source inverter (2).
6. An electric aircraft propulsion system test platform based on modular PMSM according to claim 5, characterized in that it further comprises an auxiliary power supply 12V (2-2) and a radiator fan (2-3); the auxiliary power supply 12V (2-2) is used for driving the cooling fan (2-3) to rotate; the cooling fan (2-3) is used for cooling a first voltage source inverter (2-7), a second voltage source inverter (2-8) and a third voltage source inverter (2-9) in the modular voltage source inverter (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111199917.5A CN113928590A (en) | 2021-10-14 | 2021-10-14 | Electric aircraft propulsion system test platform based on modular permanent magnet synchronous motor |
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| CN202111199917.5A CN113928590A (en) | 2021-10-14 | 2021-10-14 | Electric aircraft propulsion system test platform based on modular permanent magnet synchronous motor |
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