Aviation permanent magnet generator voltage stabilization control method and system

Abstract

The invention provides a voltage stabilization control method and system for an aviation permanent magnet generator, and the method comprises the steps: enabling a result obtained after the difference value between a given voltage and a collected feedback voltage u passes through a PI controller to serve as the input of an inner ring given current calculation module, and enabling the inner ring given current calculation module to output a q-axis given current and a d-axis given current, performing Clarke and Park conversion to obtain a dq rotating coordinate system sum, using the dq rotating coordinate system sum as a feedback value of an iq current loop, using the dq rotating coordinate system sum as a feedback value of an id current loop, subtracting the q-axis given current from the feedback value of the iq current loop to obtain a first result, and subtracting the d-axis given current from the feedback value of the id current loop to obtain a second result; a first result is output through the current PI controller, a second result is output through the current PI controller, a sum is obtained through Park inverse transformation, and six paths of control signals are output through the SVPWM module to drive an inverter to work, so that a generator outputs given voltage. And voltage stabilization control of the aviation permanent magnet power generation system can be realized.

Description

Technical Field

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

[0002] 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.

[0003] As a key technology in modern aviation energy systems, permanent magnet synchronous generator (PMSG) technology's high efficiency, high power-to-weight ratio, high reliability, and compact structure have expanded its application scope and provided important support for the clean energy transition in the context of carbon neutrality. Under constant speed conditions, the output voltage of a PMSG generator is stable, but it decreases with increasing load. Furthermore, the magnetic properties of the permanent magnet material are affected by temperature, leading to fluctuations in the generator's output voltage and impacting its application.

[0004] The existing voltage regulation control methods for permanent magnet generators mainly include: 1. Adjusting the generator speed; 2. Adding a DC / DC module (the generator output becomes DC power after passing through the controller). These two methods increase costs and limit the application of permanent magnet generators. Summary of the Invention

[0005] To address the problems of high cost and limited application of existing voltage regulation control methods for permanent magnet generators, this invention provides a voltage regulation control method and system for aircraft permanent magnet generators. The technical solution is as follows: Firstly, a voltage regulation 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 a voltage loop, and the inner loop consists of current loops id and iq. The method is used for closed-loop power generation control in a voltage regulation power generation control state. The method includes: Step 1: Set the given voltage With the collected feedback voltage u The difference, after being processed by the PI controller, is used as the input to the inner loop given current calculation module. The inner loop current calculation module outputs the q-axis current. and d-axis given current , Step 2: Sample the two-phase current using a phase current detection circuit, and obtain the current in the dq rotating coordinate system through Clarke and Park transformations. and ,Will As the feedback value of the iq current loop, As the feedback value of the id current loop, the q-axis given current Subtracting the first result, the d-axis given current Subtracting the second result; Step 3, the first result is output through the current PI controller , and the second result is output through the current PI controller Through Park inverse transformation, the and are obtained Six control signals are output through the SVPWM module to drive the inverter to work, so that the generator outputs the given voltage .

[0006] The core of the aviation permanent magnet power generation control algorithm is to control the stable output of the voltage. The two-phase current in the three-phase generator and the output bus voltage are sampled. The rotor position and speed of the generator are sampled. The outer voltage loop and the inner current loop are used to realize the output of the target voltage of the generator.

[0007] Optionally, the inner loop given current calculation module calculates the q-axis given current and the d-axis given current based on the output of the outer loop voltage loop. The formula is:

[0008]

[0009] Where, the flux of the generator is , the inductance of the d-axis and q-axis of the generator is .

[0010] Optionally, the power generation control state further includes open-loop power generation control, and the open-loop power generation control is divided into open-loop control 1 and open-loop control 2. After the generator controller receives the power generation enable signal of the upper computer, it is transferred from the static state to the power generation control state, and starts to perform the voltage stabilization power generation control. In the open-loop control 1 state, that is, before time t1, the values of n and calculated by the speed and voltage formula calculation module under the current speed are taken as the output ​​​​​​​​​​​Within the range, open-loop control state 1 switches to open-loop control state 2, and the duration of open-loop control state 2 is... At this time, the output of the inner current loop For closed-loop control output The output of the inner current loop The output of the speed-voltage formula calculation module value, Starting at time t2, the open-loop control 2 state switches to voltage-stabilized dual-closed-loop control, executing steps 1 to 3. .

[0011] An aircraft permanent magnet generator produces three-phase alternating current driven by an engine. After uncontrolled rectification by a controller, it outputs direct current. This state is a static state. In this static state, the controller cannot achieve voltage stability. During the transition from static to generator mode, the momentary PWM activation of the drive transistor causes extremely large voltage and current pulses in the generator system. These pulses can cause overvoltage and overcurrent breakdown of the drive transistor, resulting in damage. The voltage and current surge suppression algorithm provided in this invention effectively solves this problem.

[0012] Optionally, the speed-voltage formula calculation module calculates the current speed. n Below The formula is: (1); Calculate the current speed n The formula is: (2).

[0013] Optionally, formulas (1) and (2) are obtained through low-speed no-load test of the aircraft permanent magnet power generation system.

[0014] Optionally, during low-speed no-load testing of the aircraft permanent magnet power generation system, the power generation control state is limited to closed-loop power generation control. After receiving the power generation enable signal from the host computer, the generator controller transitions from a static state to the power generation control state. The power generation state is stable, and the current speed and closed-loop output are recorded. and If the rated speed of the motor is N, record the speed. Speeds up to N / 2 and their corresponding speeds and The obtained rotational speed and its corresponding speed and The data points were fitted to obtain The linear relationship between rotational speed and speed, and The linear relationship between the rotational speed and the rotational speed. The formula for the linear relationship between rotational speed and rotational speed is formula (1). And the linear straight line of the rotation speed is formula (2).

[0015] Optionally, when the generator controller output voltage fluctuates in the range of ± V, it is determined that the power generation state of the generator controller is stable.

[0016] In a second aspect, a stable voltage control system of an aviation permanent magnet generator is provided, comprising: a permanent magnet synchronous generator, a generator controller, an upper computer, a drag table and a load, The permanent magnet synchronous generator is connected with the drag table and the generator controller, the generator controller is connected with the upper computer and the load, the generator controller receives the control instruction sent by the upper computer, controls the output of the permanent magnet synchronous generator, and provides direct current for the load; The generator controller is used for: The difference between the given voltage And the feedback voltage u collected is taken as the input of the inner loop given current calculation module after PI controller The inner loop given current calculation module outputs q-axis given current And d-axis given current , Two-phase current sampling is carried out through a phase current detection circuit, and dq rotating coordinate system And Are obtained through Clarke and Park transformation conversion As the feedback value of the iq current loop, and As the feedback value of the id current loop, q-axis given current And The first result is obtained by subtracting d-axis given current And The second result is obtained by subtracting The first result is outputted through a current PI controller The second result is outputted through a current PI controller , And Park inverse transformation is carried out to obtain And Six-way control signals are outputted through an SVPWM module to drive the inverter to work, so that the generator outputs given voltage

[0017] The present application has at least the following advantages: The application provides an aviation permanent magnet generator voltage stabilization control method and system, and the aviation permanent magnet generator system architecture is described; the aviation permanent magnet generator control system hardware architecture is described, including sampling, control, communication, driving output and the like; the aviation permanent magnet generator control software architecture is designed, and various function modules are cooperated to realize the aviation permanent magnet generator system voltage stabilization control; the aviation permanent magnet generator voltage stabilization control algorithm is designed, and the voltage and current double closed loop control algorithm can be used for the voltage stabilization control of any aviation permanent magnet generator control system; the aviation permanent magnet generator voltage and current impact suppression method is designed, and the voltage and current pulse when the generator controller is switched from the static state to the power generation state is effectively suppressed. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 is a system architecture diagram; Figure 2 is a control system hardware architecture diagram; Figure 3 is a software function architecture diagram; Figure 4 is a software main flow diagram; Figure 5 is a voltage stabilization double closed loop control strategy principle diagram; Figure 6 is a static and power generation state switching flow diagram; Figure 7 is a static and power generation state switching time diagram. DETAILED DESCRIPTION

[0019] To make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described below in connection with the drawings of the embodiments of the present application. Obviously, the described embodiments are some of the embodiments of the present application, but not all the embodiments of the present application. Based on the embodiments in the present application, any other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0020] The features and illustrative embodiments of various aspects of the present application will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, it will be apparent to one of ordinary skill in the art that the present application can be practiced without some of these specific details. The description of the embodiments below is merely intended to provide a better understanding of the present application by showing examples of the present application. The present application is by no means limited to any specific settings and methods presented below, but covers any improvements, replacements and modifications of structures, methods and devices without departing from the spirit of the present application. In the drawings and the following description, well-known structures and technologies are not shown to avoid unnecessary obscuring of the present application.

[0021] It should be noted that the features in the embodiments and the embodiments can be combined with each other without conflict, and each embodiment can be mutually referred to and quoted.

[0022] The application will be described in detail below with reference to the drawings and specific embodiments.

[0023] The application proposes an aviation permanent magnet generator voltage stabilization control method and system, which comprises 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, an aviation permanent magnet power generation voltage stabilization control method module, and an aviation permanent magnet power generation voltage and current impact suppression method module. The specific implementation design is as follows: 1) Aviation permanent magnet power generation system architecture The aviation permanent magnet power generation control system comprises an aviation permanent magnet generator, a generator controller, an upper computer, an aviation engine, and a direct current load. The aviation engine is mechanically connected to the generator through a speed reducer. The aviation engine drives the generator to operate. The three-phase alternating current generated by the generator is controlled by the generator controller to output direct current for the load. The generator controller and the upper computer exchange data through CAN communication. The system framework is as shown in Figure 1 .

[0024] 2) Aviation permanent magnet power generation control system hardware architecture The generator controller comprises control hardware and control software. The control hardware comprises 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 driving module, an inverter driving circuit, and a DC / DC module.

[0025] The DC / DC module is connected to the main control unit, the driving module, and the position detection module. The external 28VDC is converted into direct current by the DC / DC module to provide power for the main control unit, the driving module, and the position detection module.

[0026] The voltage and current detection module is connected to the inverter driving circuit. The direct current voltage output by the inverter driving circuit needs to be detected, and the three-phase output of the inverter driving circuit needs to be current detected.

[0027] The data acquisition and conditioning circuit is connected to the position detection module, the temperature detection module, and the voltage and current detection module. The voltage and current detection module detects the bus voltage, the A-phase current, and the B-phase current signals of the permanent magnet synchronous generator and transmits them to the main control unit through 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 through the data acquisition and conditioning circuit. The position detection module detects the rotor position signal and the rotor speed signal of the permanent magnet synchronous generator and transmits them to the main control unit.

[0028] The main control unit carries out the permanent magnet generator voltage stabilization control according to the method, outputs a PWM control signal to the driving module, and drives the inverter circuit connected with the driving module and the permanent magnet synchronous generator, so that the PWM signal of the driving module is finally output to the permanent magnet synchronous generator to realize the voltage stabilization control of the motor target voltage.

[0029] The main control unit detects whether the driving module is faulty in real time, and outputs a protection action to the driving module when a fault signal is detected.

[0030] The driving inverter circuit module is connected with the DC load, and the driving inverter circuit module provides a target voltage for the DC load .

[0031] 3) Software architecture of the aviation permanent magnet power generation control system The software of the aviation permanent magnet power generation control system mainly comprises a state conversion program, a main cycle control program and a CAN receiving interrupt program. The software architecture diagram of the control system is as Figure 3 .

[0032] The state conversion program mainly completes the conversion among the three states of the system, i.e. static state, power generation state and fault state. After the system is powered on, it is in the static state. When the generator controller receives the power generation instruction from the upper computer, the system enters the power generation state. When the system detects a fault, the system enters the fault state.

[0033] The main cycle control program completes the sampling of voltage, current and position signals, the voltage stabilization power generation control, the sending of the state information update of the upper computer, the fault detection and protection function.

[0034] The CAN receiving interrupt program mainly completes the reception of the instructions sent by the upper computer. The instructions sent by the upper computer include enable, target voltage, PI parameter and the like.

[0035] The main cycle control program is realized in the ePWM1 interrupt service program, and the implementation flowchart is as shown in Figure 4 .

[0036] First, the motor A, B phase current, bus voltage and rotor position are detected, and after the collection is completed, the filtering processing is performed, and then the voltage loop, the inner loop and the current loop of the outer loop are completed according to claim 1 to complete the power generation control algorithm, and the control 6-way PWM wave output is realized to achieve the target voltage stable output.

[0037] 4) Aviation permanent magnet power generation control algorithm The voltage stabilization control strategy of the aviation permanent magnet power generation comprises two control loops, i.e. the outer loop and the inner loop. The outer loop is the voltage loop, the inner loop is the id and iq current loop, and the overall block diagram of the voltage stabilization double closed loop control strategy is as shown in Figure 5 . ​​​

[0038] Collecting motor electric angle by position sensor , collecting motor speed n , target voltage , deviation compared with feedback collected voltage u after PI controller as input of inner loop given current calculation module, output of inner loop given current calculation module as given input of inner loop iq and id; input of iq current loop control signal , input of id current loop control signal , two-phase current sampling by phase current detection circuit, Clarke and Park conversion to get and , respectively as feedback value of iq current loop and id current loop and its reference input and , difference compared with its reference input, output of current PI controller and , Park inverse conversion to get and , six-way control signal output by SVPWM module to drive inverter work, so that the generator stable output target voltage u .

[0039] Inner loop given current calculation module calculates given and and .

[0040]

[0041]

[0042] Flux of the generator is , inductance of the generator is , .

[0043] 5) Aviation permanent magnet generator voltage and current impact suppression method The switching moment of the generator controller from static state to generating state, the driving tube PWM moment opening will cause the generating system to produce a great voltage and current pulse, which will cause the overvoltage and overcurrent breakdown of the driving tube, causing damage to the driving tube. The generating control state is divided into open loop generating control and closed loop generating control, and the open loop generating control is divided into open loop control 1 and open loop control 2, which effectively suppresses the voltage and current impact and realizes the stable output of the aviation permanent magnet generator voltage.

[0044] The generator controller starts the voltage stabilization and power generation control after receiving the power generation enable signal from the upper computer, that is, the voltage and current surge suppression algorithm starts to run, and the algorithm implementation flowchart is shown in Figure 6 .

[0045] Figure 6 The calculation formula in the intermediate speed voltage formula calculation module is obtained through the low-speed no-load test of the aviation permanent magnet power generation system. During the test, the only power generation control state is closed-loop power generation control. The generator controller enters the power generation control state from the static state after receiving the power generation enable signal from the upper computer. After the power generation state is stable (the output voltage fluctuation of the generator controller is within ±5V), the current speed and the closed-loop output and are recorded. If the rated speed of the motor is N, the voltage and current surges of the power generation system at low speed will not damage the power tube of the generator controller, so the test records the test data from 500rpm to N / 2 (the speed increases by 500 each time). The obtained speed and its corresponding and data points are fitted to obtain the and speed linear line , and speed linear line . The linear formula is the calculation formula of and in the voltage formula calculation module.

[0046] When the open-loop control 1 state, that is, before time t1 in Figure 7 , the output and of the inner current loop is directly given as the and values of the current speed n output by the speed voltage formula calculation module. When the value output by the closed-loop running program enters the Figure 7 range to give uq , the open-loop control 1 state is switched to the open-loop control 2 state, and the duration of the open-loop control 2 state is . At this time, the output of the inner current loop is the output by the closed-loop control, and the output of the inner current loop is the value output by the speed voltage formula calculation module, after time t2, that is, at the beginning of , the open-loop control 2 state is switched to the voltage stabilization double closed-loop control, and the control is performed according to the voltage stabilization control strategy in claim 1.

[0047] The above merely expresses the embodiments of the present application, the description is more specific and detailed, but cannot be understood as the limitation of the patent scope. It should be noted that for ordinary skilled in the art, several modifications and improvements can be made without departing from the concept of the present application, which all belong to the protection scope of the present application. In addition, the unexplained part of the present application is all the routine technology.

Claims

1. A method for stabilizing voltage control of an aviation permanent magnet generator, characterized in that, The control strategy comprises two control loops, i.e., an inner loop and an outer loop. The outer loop is a voltage loop, and the inner loop is an id and iq current loop. The method is used for closed-loop power generation control in a steady voltage power generation control state. The method comprises the following steps: Step 1, the given voltage the difference between the collected feedback voltage u and the result obtained after PI controller as the input of the inner loop given current calculation module The inner loop given current calculation module outputs q-axis given current and d-axis given current , Step 2, two-phase current sampling is carried out through a phase current detection circuit, and Clarke and Park transformation is carried out to obtain a first result in a dq rotating coordinate system and , and is taken as a feedback value of the iq current loop, and is taken as a feedback value of the id current loop, and q-axis given current is subtracted from to obtain the first result, and d-axis given current is subtracted from to obtain a second result; Step 3, the first result is output by a current PI controller , the second result is output by a current PI controller , and are obtained by Park inverse transformation and , six control signals are output by an SVPWM module to drive the inverter to work, so that the generator outputs a given voltage .

2. The method of claim 1, wherein, The inner loop given current calculation module is based on the output of the outer loop voltage loop The formula for calculating the q-axis given current And the d-axis given current Is: Wherein, the flux of the generator is , the inductance of the generator d-axis, q-axis is 、 .

3. The method of claim 1, wherein, The power generation control state further comprises open-loop power generation control, which is divided into open-loop control 1 and open-loop control 2. After receiving the power generation enable signal from the host computer, the generator controller transitions from a static state to a power generation control state and begins voltage stabilization control. In open-loop control state 1, i.e., before time t1, the current speed calculated by the speed-voltage formula calculation module is used. n Below and The value is used as the output of the inner current loop. and When the current PI controller outputs Value enters Within the range, open-loop control state 1 switches to open-loop control state 2, and the duration of open-loop control state 2 is... At this time, the output of the inner current loop For closed-loop control output The output of the inner current loop The output of the speed-voltage formula calculation module value, Starting at time t2, the open-loop control 2 state switches to voltage-stabilized dual-closed-loop control, executing steps 1 to 3. .

4. The method of claim 3, wherein, The rotational speed voltage formula calculation module calculates the current rotational speed n The formula is: The formula is: （1）； The formula for calculating the current rotational speed n is: The formula for calculating the current rotational speed n is: （2）。 5. The method of claim 4, wherein, Formulas (1) and (2) are obtained through low-speed no-load test of the aviation permanent magnet power generation system.

6. The method of claim 5, wherein, During low-speed no-load testing of the aircraft permanent magnet generator system, the generator control state is limited to closed-loop generator control. After receiving the generator enable signal from the host computer, the generator controller transitions from a static state to generator control state. The generator state remains stable, and the current speed and closed-loop output are recorded. and If the rated speed of the motor is N, record the speed. Speeds up to N / 2 and their corresponding speeds and The obtained rotational speed and its corresponding speed and The data points were fitted to obtain The linear relationship between the rotational speed and the rotational speed, and The linear relationship between the rotational speed and the rotational speed. The formula for the linear relationship between rotational speed and rotational speed is formula (1). The formula for the linear relationship between rotational speed and rotational speed is formula (2).

7. The method of claim 6, wherein, The generator controller output voltage is determined to be stable when the generator controller output voltage fluctuation is within ± V of the generator controller output voltage.

8. An aviation permanent magnet generator voltage stabilization control system, characterized in that, Comprise: A permanent magnet synchronous generator, a generator controller, an upper computer, a drag table and a load, The permanent magnet synchronous generator is connected with the drag table and the generator controller. The generator controller is connected with the upper computer and the load. The generator controller receives a control instruction sent by the upper computer, controls the output of the permanent magnet synchronous generator, and provides direct current for the load. The generator controller is used for: the given voltage the difference between the given voltage and the feedback voltage u is input to the inner loop current calculation module after being processed by a PI controller the inner loop current calculation module outputs the q-axis given current and the d-axis given current ​ Two-phase current sampling is performed by a phase current detection circuit, and Clarke and Park transformation is performed to obtain a dq rotating coordinate system and , as the feedback value of the iq current loop, and , as the feedback value of the id current loop, and the q-axis given current is subtracted from and to obtain a first result, and the d-axis given current is subtracted from to obtain a second result, The first result is output through a current PI controller The second result is output through a current PI controller , and are obtained through Park inverse transformation and Six control signals are output through an SVPWM module to drive the inverter to work, so that the generator outputs a given voltage .

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