Aviation permanent magnet generator power control system and method

Abstract

The invention provides an aviation permanent magnet generator power control system and method, and the method comprises the steps: enabling a result obtained after the difference value between a given rotating speed and feedback power from a power calculation module passes through a PI controller to serve as the input of a current loop control signal, and enabling an output value of a modulation ratio weak magnetic module to serve as the input of the current loop control signal, two-phase current sampling is carried out through a phase current detection circuit, a dq rotating coordinate system is obtained through Clarke and Park conversion, a first result is obtained through subtracting an input and a feedback value of a current loop, a second result is obtained through subtracting the input and the feedback value of the current loop, and the first result is output through a current PI controller. And a second result is output through a current PI controller, a sum is obtained through Park inverse transformation, six paths of control signals are output through an SVPWM module to drive an inverter to work, and a generator outputs target power. The method can be used for power control of any aviation permanent magnet power generation control system.

Description

Technical Field

[0001] This invention belongs to the field of aviation motor control technology, and particularly relates to an aviation permanent magnet generator power control system and method. Background Technology

[0002] As a key technology for modern aviation energy systems, aviation permanent magnet synchronous power generation technology has expanded its application scope due to its high efficiency, high power-to-weight ratio, high reliability, and compact structure. It also provides important support for the transition to clean energy in the context of carbon neutrality.

[0003] Existing aviation synchronous generators mainly rely on electric excitation systems. Electric excitation requires a continuous external power supply, and excitation losses account for 15%-20% of the total generator losses. In particular, efficiency drops significantly under low load. At the same time, traditional synchronous generators have complex structures, high maintenance costs, and poor dynamic response.

[0004] The development of power electronics technology has accelerated the development of aviation permanent magnet synchronous power generation technology. Meanwhile, aviation permanent magnet generator controllers and aviation permanent magnet synchronous motors, as the carriers of this technology, play a crucial role in its development and application. Existing constant power output control methods for permanent magnet generators include: 1. adjusting load power; 2. adjusting motor magnetic field strength; 3. adjusting generator speed. Method 1 has high load requirements, method 2 is complex to operate, and method 3 is limited by the rated speed of the motor. Therefore, providing an aviation permanent magnet generator power control system and method is of great significance. Summary of the Invention

[0005] To address the problems of high load requirements, complex operation, and limitation by the rated speed of the motor in existing constant power output control methods for permanent magnet generators, this invention provides a power control system and method for aircraft permanent magnet generators. The technical solution is as follows: Firstly, a power control method for an aircraft permanent magnet generator is provided. The control strategy includes two control loops: an inner loop and an outer loop. The outer loop is the power loop, and the inner loop is... and Current loop, the method includes: Given rotation speed Feedback power from the power calculation module The difference obtained after passing through the PI controller is used as the result. Input of current loop control signal The output value of the modulation ratio field weakening module is used as Input of current loop control signal , Two-phase currents are sampled using a phase current detection circuit, and then transformed using Clarke and Park transformations to obtain the current in the dq rotating coordinate system. and ,Will As The feedback value of the current loop will As The feedback value of the current loop will be input. and The difference is used to obtain the first result; the input will then be... and The difference yields the second result. The first result is output via a current PI controller. The second result is output via a current PI controller. , and Obtained by inverse Park transform and The inverter is driven by six control signals output from the SVPWM module, enabling the generator to output the target power. .

[0006] Among them, the electric angle of the motor is used in the Park transform and inverse Park transform processes. Calculations are performed on the electric angle of the motor. Data collected by a position sensor.

[0007] The power calculation module is based on the motor speed. Calculate power P and motor speed Data collected by a position sensor.

[0008] The formula for calculating power P by the power calculation module is as follows:

[0009] Wherein, the generator speed is n, and the number of pole pairs is The magnetic flux of the generator is The inductance of the generator along the d-axis and q-axis is... , .

[0010] Among them, the modulation ratio weakening module calculates The process is as follows: Calculate the modulation ratio Determine the modulation ratio TZB Is it greater than the preset threshold? d When the modulation ratio TZB is greater than a preset threshold, make When the modulation ratio TZB When it is not greater than the preset threshold, make , in, The controller outputs bus voltage. The initial given value is 0. KThis is the magnetic weakening coefficient, which can be adjusted according to the experimental results. When the modulation ratio is greater than a preset threshold... d hour, Weakening of the magnetic field is required when the modulation ratio is less than a preset threshold. d hour, It remains unchanged.

[0011] Secondly, an aviation permanent magnet generator power control system is provided, comprising: a permanent magnet synchronous generator, a generator controller, a host computer, a drive platform, and a load. The permanent magnet synchronous generator is connected to the drive platform and generator controller. The generator controller is connected to the host computer and the load. The generator controller receives control commands sent by the host computer and controls the output of the permanent magnet synchronous generator to provide DC power to the load. The generator controller is used for: Given rotation speed The difference between the feedback power P from the power calculation module and the current loop control signal iq is obtained by passing the result through a PI controller. The output value of the modulation ratio field weakening module is used as the input of the id current loop control signal. , Two-phase currents are sampled using a phase current detection circuit, and then transformed using Clarke and Park transformations to obtain the current in the dq rotating coordinate system. and ,Will As the feedback value of the iq current loop, As the feedback value of the id current loop, the input will and The difference is used to obtain the first result; the input will then be... and The difference yields the second result. The first result is output via a current PI controller. The second result is output via a current PI controller. , and Obtained by inverse Park transform and The inverter is driven by six control signals output from the SVPWM module, enabling the generator to output the target power. .

[0012] The generator controller includes: a main control unit, a data acquisition and conditioning circuit, a position detection module, a temperature detection module, a voltage and current detection module, a drive module, an inverter drive circuit, and a DC / DC module. The DC / DC module is connected to the main control unit, drive module, and position detection module. The external 28VDC is converted by the DC / DC module to provide DC power to the main control unit, drive module, and position detection module. The voltage and current detection module is connected to the inverter drive circuit to detect the DC voltage output by the inverter drive circuit and to detect the current of the three-phase output of the inverter drive circuit. The data acquisition and conditioning circuit is connected to the position detection module, temperature detection module, and voltage and current detection module. The voltage and current detection module detects the bus voltage, A-phase current, and B-phase current signals of the permanent magnet synchronous generator and transmits them to the main control unit via the data acquisition and conditioning circuit. The temperature detection module detects the winding temperature signal of the permanent magnet synchronous generator and transmits it to the main control unit via the data acquisition and conditioning circuit. The position detection module detects the rotor position signal and rotor speed signal of the permanent magnet synchronous generator and transmits them to the main control unit. The main control unit controls the power of the permanent magnet generator. It outputs a PWM control signal to the drive module, which in turn connects the drive module to the permanent magnet synchronous generator. The drive inverter circuit then applies the PWM signal from the drive module to the permanent magnet synchronous generator to achieve the target power output. Control; The main control unit monitors the drive module for faults in real time. When a fault signal is detected, the main control unit takes protective actions for the drive module. The drive inverter circuit is connected to the DC load, and the drive inverter circuit provides the target power to the DC load. .

[0013] The generator controller and the host computer communicate with each other via a CAN communication bus.

[0014] The beneficial effects of this invention are at least as follows: This invention provides a power control system and method for an aircraft permanent magnet generator. The architecture of the aircraft permanent magnet generator control system is described; the hardware architecture of the aircraft permanent magnet generator control system is described, and a hardware architecture for the control system is designed under the condition of minimum sampling (high power-to-weight ratio); the software architecture of the aircraft permanent magnet generator control system is designed, with each functional module cooperating to achieve the target power control of the aircraft permanent magnet generator system; and an aircraft permanent magnet generator control algorithm is designed, which can be used for power control of any aircraft permanent magnet generator control system. Attached Figure Description

[0015] Figure 1 It is a system architecture diagram; Figure 2 This is a hardware architecture diagram of the control system; Figure 3 It is a software functional architecture diagram; Figure 4 This is the main flowchart of the software; Figure 5 This is a schematic diagram of the control strategy. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0017] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0018] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited from each other.

[0019] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0020] This invention proposes an aviation permanent magnet power generation control system and method, mainly comprising an aviation permanent magnet power generation system architecture module, an aviation permanent magnet power generation control system hardware architecture module, an aviation permanent magnet power generation control system software architecture module, and an aviation permanent magnet power generation control algorithm module. The specific implementation design is shown below: 1) Architecture of aviation permanent magnet power generation system The aviation permanent magnet power generation control system includes an aviation permanent magnet generator and generator controller, a host computer, a drive platform, and a load. The system framework is as follows: Figure 1 As shown.

[0021] Driven by the drive platform, the generator operates. The host computer controls the generator controller to start power generation, converting the three-phase AC power generated by the generator into DC power for the load. The generator controller and the host computer exchange data via CAN communication, controlling the 28VDC power supply. The drive platform drives the generator, with a maximum speed of 20,000 rpm.

[0022] 2) Hardware architecture of aviation permanent magnet power generation control system The hardware architecture of the aviation permanent magnet power generation control system mainly includes a main control unit, a data acquisition and conditioning circuit module, a DC / DC module, a drive module, a current detection module, a temperature detection module, a position detection module, an inverter drive circuit module, and a communication module. See the control system hardware architecture section for details. Figure 2 .

[0023] To improve the power-to-weight ratio of the aviation permanent magnet generator control system, the control system hardware should be as simple as possible, completing the system's functions with minimal sampling. Therefore, the control system hardware architecture includes two-phase currents from the generator's three phases, the generator's rotor position and speed, the controller's output bus voltage, and the motor's temperature signal. The host computer and controller exchange data via a CAN communication bus. 28VDC is converted by a DC / DC module to power the main control unit, drive module, and position detection module. The main control unit periodically detects and protects against drive module faults. The main control unit's PWM wave output is transmitted to the generator's three-phase AC power via the drive module and drive inverter circuit, controlling the target power of the inverter drive circuit. This enables the regulation of the generator's target power.

[0024] 3) Software architecture of aviation permanent magnet power generation control system The aviation permanent magnet generator control system software mainly consists of state transition programs, main loop control programs, and CAN receive interrupt programs. The control system software architecture diagram is shown below. Figure 3 .

[0025] The state transition program mainly handles the transitions between three system states: static, generating, and fault. After power-on, the system is in a static state. When the generator controller receives a generating command from the host computer, the system enters the generating state. When a fault is detected, the system transitions to a fault state.

[0026] The main loop control program completes voltage, current, and position signal sampling, power generation control, sending status information updates to the host computer, and fault detection and protection functions.

[0027] The CAN receive interrupt routine is mainly responsible for receiving commands sent by the host computer. Commands sent by the host computer include enable, target power, PI parameters, etc.

[0028] The main loop control program is implemented in the ePWM1 interrupt service routine, and its implementation flowchart is as follows: Figure 4 As shown.

[0029] First, the A-phase and B-phase currents, bus voltage, and rotor position of the motor are detected. After the data acquisition is completed, filtering is performed. Then, the outer power loop and inner loop are completed according to claim 1. and The current loop power generation control algorithm controls 6 PWM wave outputs to achieve the target power output.

[0030] 4) Aircraft permanent magnet power generation control algorithm The core of the aviation permanent magnet generator control algorithm of this invention is to control the output of a given power. It samples the current of two phases in the three phases of the generator and the output bus voltage, and samples the rotor position and speed of the generator. It uses an outer power loop, an inner current loop and a modulation ratio field weakening control to achieve the output of the generator target power.

[0031] The power control strategy for aircraft permanent magnet generators consists of two control loops: an inner loop (power loop) and an outer loop (id and iq current loops). The overall block diagram of the control strategy is shown below. Figure 5 As shown.

[0032] The electric angle of the motor is collected by a position sensor. Collect motor speed n Given power The deviation between the calculated feedback power P and the actual feedback power P is processed by a PI controller and used as the input to the iq current loop control signal. The modulation ratio field weakening module output value is the input of the id current loop control signal. The phase current detection circuit samples the two-phase current and transforms it using Clarke and Park transformations to obtain the current in the dq rotating coordinate system. and These are used as the feedback values ​​for the iq current loop and the id current loop, respectively, and their reference inputs. and The difference is calculated and output by the current PI controller. and The result obtained by inverse Park transform and The inverter is driven by six control signals output from the SVPWM module, enabling the generator to output the target power. .

[0033] Obtain real-time feedback power with minimal sampling P , P It is obtained from the following formula:

[0034] Wherein, the generator speed is n The extreme logarithm is The magnetic flux of the generator is The inductance of the generator is , .

[0035] The modulation ratio field weakening is obtained from the output of the modulation ratio field weakening module. The modulation ratio field weakening is calculated using the following formula:

[0036]

[0037] in, The controller outputs bus voltage. The initial given value is 0. TZB The modulation ratio, K This is the weak magnetic coefficient, which can be adjusted according to the experimental results. TZB When it is greater than 1.1, Weakening of the magnetic field is required when the modulation ratio is less than 1.1. It remains unchanged.

[0038] The above description merely illustrates embodiments of the present invention and is quite specific and detailed; however, it should not be construed as limiting the scope of the patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Furthermore, any parts of the present invention not described in detail are conventional techniques.

Claims

1. A power control method for an aircraft permanent magnet generator, characterized in that, The control strategy consists of two control loops: an inner loop and an outer loop. The outer loop is the power loop, and the inner loop is... and Current loop, the method includes: Given power Feedback power from the power calculation module The difference obtained after passing through the PI controller is used as the result. Input of current loop control signal The output value of the modulation ratio field weakening module is used as Input of current loop control signal , Two-phase currents are sampled using a phase current detection circuit, and then transformed using Clarke and Park transformations to obtain the current in the dq rotating coordinate system. and ,Will As The feedback value of the current loop will As The feedback value of the current loop will be input. and The difference is used to obtain the first result; the input will then be... and The difference yields the second result. The first result is output via a current PI controller. The second result is output via a current PI controller. , and Obtained by inverse Park transform and The inverter is driven by six control signals output from the SVPWM module, enabling the generator to output the target power. .

2. The method according to claim 1, characterized in that, The electric angle of the motor is used in the Park transform and inverse Park transform processes. Calculations are performed on the electric angle of the motor. Data collected by a position sensor.

3. The method according to claim 1, characterized in that, The power calculation module is based on motor speed. Calculate power P and motor speed Data collected by a position sensor.

4. The method according to claim 1, characterized in that, The formula for calculating power P by the power calculation module is: Wherein, the generator speed is n, and the number of pole pairs is The magnetic flux of the generator is The inductance of the generator along the d-axis and q-axis is... , .

5. The method according to claim 1, characterized in that, Modulation ratio field weakening module calculation The process is as follows: Calculate the modulation ratio Determine the modulation ratio TZB Is it greater than the preset threshold? d When the modulation ratio TZB is greater than a preset threshold, make When the modulation ratio TZB When it is not greater than the preset threshold, make , in, The controller outputs bus voltage. The initial given value is 0. K This is the magnetic weakening coefficient, which can be adjusted according to the experimental results. When the modulation ratio is greater than a preset threshold... d hour, Weakening of the magnetic field is required when the modulation ratio is less than a preset threshold. d hour, It remains unchanged.

6. A power control system for an aircraft permanent magnet generator, characterized in that, include: Permanent magnet synchronous generator, generator controller, host computer, drive platform and load. The permanent magnet synchronous generator is connected to the drive platform and generator controller. The generator controller is connected to the host computer and the load. The generator controller receives control commands sent by the host computer and controls the output of the permanent magnet synchronous generator to provide DC power to the load. The generator controller is used for: Given power The difference between the feedback power P from the power calculation module and the current loop control signal iq is obtained by passing the result through a PI controller. The output value of the modulation ratio field weakening module is used as the input of the id current loop control signal. , Two-phase currents are sampled using a phase current detection circuit, and then transformed using Clarke and Park transformations to obtain the current in the dq rotating coordinate system. and ,Will As the feedback value of the iq current loop, As the feedback value of the id current loop, the input will and The difference is used to obtain the first result; the input will then be... and The difference yields the second result. The first result is output via a current PI controller. The second result is output via a current PI controller. , and Obtained by inverse Park transform and The inverter is driven by six control signals output from the SVPWM module, enabling the generator to output the target power. .

7. The system according to claim 6, characterized in that, The generator controller includes: a main control unit, a data acquisition and conditioning circuit, a position detection module, a temperature detection module, a voltage and current detection module, a drive module, an inverter drive circuit, and a DC / DC module. The DC / DC module is connected to the main control unit, drive module, and position detection module. The external 28VDC is converted by the DC / DC module to provide DC power to the main control unit, drive module, and position detection module. The voltage and current detection module is connected to the inverter drive circuit to detect the DC voltage output by the inverter drive circuit and to detect the current of the three-phase output of the inverter drive circuit. The data acquisition and conditioning circuit is connected to the position detection module, temperature detection module, and voltage and current detection module. The voltage and current detection module detects the bus voltage, A-phase current, and B-phase current signals of the permanent magnet synchronous generator and transmits them to the main control unit via the data acquisition and conditioning circuit. The temperature detection module detects the winding temperature signal of the permanent magnet synchronous generator and transmits it to the main control unit via the data acquisition and conditioning circuit. The position detection module detects the rotor position signal and rotor speed signal of the permanent magnet synchronous generator and transmits them to the main control unit. The main control unit controls the power of the permanent magnet generator. It outputs a PWM control signal to the drive module, which in turn connects the drive module to the permanent magnet synchronous generator. The drive inverter circuit then applies the PWM signal from the drive module to the permanent magnet synchronous generator to achieve the target power output. Control; The main control unit monitors the drive module for faults in real time. When a fault signal is detected, the main control unit takes protective actions for the drive module. The drive inverter circuit is connected to the DC load, and the drive inverter circuit provides the target power to the DC load. .

8. The system according to claim 6, characterized in that, The generator controller and the host computer exchange data via a CAN communication bus.

Images