CN-121984389-A - Excitation circuit control device and method suitable for three-stage power generation system of airplane

CN121984389ACN 121984389 ACN121984389 ACN 121984389ACN-121984389-A

Abstract

The invention relates to an excitation circuit control device and method suitable for an aircraft three-stage power generation system, comprising a double BUCK circuit, a power operational amplifier and a control module, wherein the aircraft three-stage power generation system comprises a permanent magnet auxiliary exciter, a main exciter and a main generator; the double BUCK circuit is connected with the stator winding of the permanent magnet auxiliary exciter and the power operational amplifier, the power operational amplifier is also connected with the control module and the exciting winding of the main exciter, and the control module is connected with the double BUCK circuit, the power operational amplifier and the stator winding of the main generator. The double BUCK circuit outputs positive and negative direct current voltages to be supplied to the power operational amplifier, and the power operational amplifier converts the positive and negative direct current voltages into output voltages to be transmitted to the excitation winding of the main exciter, so that the generator outputs stable voltages. The invention can be used for excitation control of an aviation three-stage alternating current power generation system, can effectively solve the excitation dynamic adjustment problem when the wide rotating speed and the heavy load change, and improves the quality and the stability of the output power supply of the power generation system.

Inventors

QIN YANAN
SHI CHAO
LIU WEIFANG
ZHANG JING

Assignees

中国商用飞机有限责任公司北京民用飞机技术研究中心
中国商用飞机有限责任公司

Dates

Publication Date: 20260505
Application Date: 20251224

Claims (10)

1. The excitation circuit control device suitable for the three-stage power generation system of the airplane is characterized by comprising a double BUCK circuit, a power operational amplifier and a control module, wherein the three-stage power generation system of the airplane comprises a permanent magnet auxiliary exciter, a main exciter and a main generator; The double BUCK circuit is connected with a stator winding of the permanent magnet auxiliary exciter and the power operational amplifier and is used for providing positive and negative direct current voltages; The power operational amplifier is also connected with the control module and the exciting winding of the main exciter at the same time and is used for converting the received positive and negative direct current voltage into exciting voltage and outputting the exciting voltage to the stator winding of the main exciter under the control action of the control module; The control module is connected with the BUCK circuit, the power operational amplifier and the stator winding of the main generator at the same time and used for controlling the BUCK circuit and the power operational amplifier.
2. The device according to claim 1, wherein the double BUCK circuit comprises a three-phase uncontrolled rectifying circuit, a regulated capacitor and a two-way anti-parallel traditional BUCK circuit which are connected in sequence.
3. The device according to claim 2, wherein the three-phase uncontrolled rectifying circuit is connected to a stator winding of the permanent magnet auxiliary exciter, and outputs direct current to a two-way anti-parallel conventional BUCK circuit after passing through a voltage stabilizing capacitor, and the two-way anti-parallel conventional BUCK circuit outputs positive and negative direct current voltages to the power operational amplifier.
4. The apparatus of claim 1, wherein the control module comprises a control board and a PWM circuit interface, an SPI interface, an i abc sampling circuit, and a v abc sampling circuit connected thereto.
5. The apparatus of claim 4, further comprising a drive circuit connecting the dual BUCK circuit and PWM circuit interface.
6. The apparatus of claim 4, further comprising a D/a module connecting the power op-amp and the SPI interface.
7. The apparatus of claim 4, wherein the stator windings of the main generator are connected to the i abc and v abc sampling circuits, respectively.
8. The apparatus of claim 7, wherein the v abc sampling circuit collects the output voltage signal of the main generator, compares the output voltage signal with the voltage signal expected to be output to obtain the expected excitation voltage output signal, and the i abc sampling circuit collects the current signal of the main generator.
9. S1, monitoring whether a startup state is normal or not after starting, S2 is carried out if the startup state is normal, and if the startup state is abnormal, the failure state is reported to be treated and the step is returned to after the failure state is reported to be treated; S2, detecting whether the output voltage, the current value, the exciting voltage value and the output voltage value of the double BUCK circuit are normal or not, and if so, performing the next step; s3, regulating the output voltage of the generator by adopting a set reference voltage to obtain a regulating voltage, and carrying out the steps S4 and S5 in parallel; S4, the regulated voltage is output to the D/A module through SPI interface communication, the D/A module inputs the regulated voltage to the power operational amplifier, the power operational amplifier is further controlled to amplify the regulated voltage to generate output voltage to the generator, and the regulated voltage returns to S2; S5, calculating the set value and the output value of the regulating voltage and the positive and negative direct current voltage of the double BUCK circuits to obtain PWM duty ratios of the positive circuit and the negative circuit respectively, and returning to S2.
10. The method of claim 9, wherein if S2 is abnormal, reporting the fault condition for waiting processing, and returning to S1.

Description

Excitation circuit control device and method suitable for three-stage power generation system of airplane Technical Field The invention belongs to the technical field of alternating current power supply systems, and particularly relates to an excitation circuit control device and method suitable for an aircraft three-level power generation system. Background Currently, the importance of aviation power supplies in airplanes is increasing, and three-stage brushless synchronous motors are used as the most commonly used aviation motors, and the technology is mature. The aviation three-stage synchronous generator consists of a permanent magnet auxiliary exciter, a rotary armature synchronous generator, a main exciter, a rotary magnetic pole synchronous generator and a main generator. The output of the permanent magnet auxiliary exciter is rectified and filtered to obtain direct current voltage in a certain range, and the direct current voltage is used as a working power supply of the controller and is also an excitation source of the main exciter. The main exciter outputs three-phase alternating-current voltage, and the direct-current voltage rectified by the three-phase full-bridge rotary rectifier is applied to the exciting winding of the main generator. The excitation current of the main generator is indirectly controlled by controlling the excitation current of the main exciter, so that the output voltage of the main generator is regulated. The exciting circuit mainly comprises a three-phase full-bridge uncontrolled rectifying circuit, a voltage regulating power circuit and a related driving circuit, and as shown in fig. 1, the main function is to rectify three-phase alternating current output by the auxiliary exciter and then supply the rectified three-phase alternating current to the main exciter and the controller, and the voltage regulating function is realized by regulating the power tube. The exciting current regulating circuit commonly used in the existing three-stage power generation system is shown in fig. 2. The asymmetric half-bridge circuit T1 is in a normally-on state when working normally, and the output voltage is stabilized by adjusting the T2 tube. By comparing the two exciting current regulating circuits, when the output voltage suddenly rises due to the unloading of the generator and the like, the asymmetric half-bridge circuit turns off the T1 and the T2, and the direction of the current changes due to the existence of the diode, so that the voltage directions at the two ends of the exciting winding are reversed, the output voltage can be quickly reduced, and the dynamic response speed of the system is improved. However, the direct-current voltage rectified by the permanent magnet auxiliary exciter is changed in a wider range due to the change of the rotating speed, so that the power switch tube cannot be adjusted in a following way due to the overlarge duty ratio or the small duty ratio, and the dynamic performance of the generator is difficult to meet the requirement or the steady-state error is larger. As is known from the search literature, most of research on excitation control of aviation three-stage synchronous generators is focused on the aspects of automatic voltage regulation control flow, automatic voltage regulation control method and the like. The prior literature, such as JP6563378B2, discloses an automatic voltage regulator, an automatic voltage regulating method, an automatic voltage regulating program, a generator excitation system and a power generation system, and introduces a power generation voltage controller, a composition structure and a control flow, thereby reducing maintenance and management cost and improving the continuity of the power generation system. As CN202411779827.7 discloses an excitation control circuit with multiple de-excitation loops for aviation three-stage power generation system, which aims at the problems that the flywheel diode added between excitation voltages in the existing asymmetric excitation circuit cannot consume the energy of magnetic field and the de-excitation speed is slower, and the excitation circuit with the de-excitation loops is invented based on the original excitation circuit. A step-down type excitation circuit based on a single-tube IGBT is provided as CN103746622B 'three-stage brushless generator power supply control device and method based on the single-tube IGBT'. In the circuit, the IGBT requires larger voltage stabilizing devices such as inductance, capacitance and the like due to the limitation of the switching speed, and particularly has poor voltage stabilizing capability and response speed when the duty ratio is lower. Mathematical model of permanent magnet generator: The parameters of the traditional permanent magnet generator are mutually coupled under a three-phase coordinate system, and the analysis is relatively complex, so that the mathematical model of the permanent magnet generator after Park conversion c