CN117833728A - Aviation two-stage starting power generation system topological structure containing feedback excitation and method - Google Patents
Aviation two-stage starting power generation system topological structure containing feedback excitation and method Download PDFInfo
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- CN117833728A CN117833728A CN202311740112.6A CN202311740112A CN117833728A CN 117833728 A CN117833728 A CN 117833728A CN 202311740112 A CN202311740112 A CN 202311740112A CN 117833728 A CN117833728 A CN 117833728A
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Abstract
The invention relates to a topology structure and a method of an aviation two-stage starting power generation system containing feedback excitation. The exciter, the rotary rectifier and the main motor are coaxially arranged, the input of the rotary rectifier is connected with the rotor winding of the exciter, and the output of the rotary rectifier is connected with the rotor winding of the main motor; the starting controller comprises a direct-current power supply, an exciter control power circuit and a main motor control power circuit; the power generation controller consists of an uncontrolled rectifying power circuit and an H-bridge chopper circuit. The invention reduces the weight of the permanent magnet auxiliary exciter and the corresponding structural members for installation and fixation, and does not have dead weight which does not participate in the starting work in the starting stage, thereby improving the power density; the permanent magnet with demagnetizing risk under special conditions such as high altitude, high temperature and the like is removed, and the reliability of the system is improved; the three-motor structure is changed into a two-motor structure, so that the axial length of the motor body is shortened, the structure is simplified, and the motor is easier to install.
Description
Technical Field
The invention belongs to the field of motor systems, and relates to an aviation two-stage starting power generation system topology structure containing feedback excitation and a method thereof.
Background
The integrated technology of starting and generating enables the aero-generator to have the capability of starting the aero-main engine, thereby omitting a set of special starting mechanism on the traditional aircraft, effectively reducing the volume and weight of the system and improving the reliability of the system. The three-stage starting power generation system mainly comprises a permanent magnet auxiliary exciter, an exciter, a rotary rectifier, a main motor, a starting controller and a power generation controller. The permanent magnet auxiliary exciter, the rotary rectifier, the exciter and the main motor are connected through a rotating shaft, and the exciter provides direct current excitation for the main motor through the rotary rectifier arranged on the rotor side. The aviation three-stage starting power generation system adopts a brushless structure, solves the problems of abrasion of an electric brush and a slip ring and possible electric spark generation, and is convenient and adjustable in excitation of a main motor.
In the starting stage of the three-stage starting power generation system, the starting controller provides excitation for the exciter and controls the main motor to operate in an electric state to output torque to drive the aero-engine to start. As the engine speed increases, the three-stage system will complete state switching and enter the power generation stage. In the power generation stage, the permanent magnet auxiliary exciter provides direct current excitation for the exciter through the adjustment of the power generation controller, the rotor of the exciter provides next-stage direct current excitation for the main motor through the rotary rectifier, the main motor operates in a power generation state, and three-phase alternating current is generated in the stator winding of the main motor. The closed-loop excitation adjustment of the power generation controller takes the output voltage of the stator of the main motor as a feedback value, and adjusts the excitation size of the exciter in real time, so that the output voltage of the main motor is stable.
The three-stage starting power generation system has the advantages of stable excitation, convenience and easy adjustment, and has great potential for aviation application, but the following problems still exist: 1) The three-motor system consisting of the permanent magnet auxiliary exciter, the main exciter and the main motor has complex structure, large volume and heavy weight and long installation shaft; 2) The permanent magnet auxiliary exciter does not participate in engine starting in the starting stage, and the system power density is low; 3) The permanent magnet auxiliary exciter adopts permanent magnet excitation, and has the characteristics of relative weakness and easy failure, and influences the reliability of the system.
The traditional aviation three-stage starting power generation system relies on a permanent magnet auxiliary exciter to provide direct current excitation, and the system fault risk is increased due to a complex topological structure and the use of the permanent magnet auxiliary exciter; and the permanent magnet auxiliary exciter does not participate in the engine starting in the starting stage, and acts as dead weight to reduce the power density of the system.
Disclosure of Invention
Technical problem to be solved
In order to avoid the defects of the prior art, the invention provides a topological structure and a method of an aviation two-stage starting power generation system with feedback excitation, which are used for improving the reliability and the power density of the starting power generation system, and redesigning the structural topology and the control strategy of the traditional three-stage starting power generation system, so that the requirements of high power density and high reliability in aviation application can be better met.
Technical proposal
An aviation two-stage starting power generation system topological structure containing feedback excitation is characterized by comprising a two-stage starting power generator, a starting controller, a power generation controller and a change-over switch; the two-stage starting generator comprises an exciter, a rotary rectifier and a main motor which are coaxially arranged; the connection of the topological structure is as follows: the input of the rotary rectifier is connected with the exciter rotor winding, and the output of the rotary rectifier is connected with the main motor rotor winding; two output ends of the starting controller are connected with a stator winding of the exciter through a normally closed contact of the K1 change-over switch, and three output ends are connected with the stator winding of the main motor through a normally closed contact of the K2 change-over switch; two output ends of the power generation controller are connected with a stator winding of the exciter through a normally open contact of the K1 change-over switch, and three output ends are connected with the stator winding of the main motor through a normally open contact of the K2 change-over switch; the three input ends of the airborne load are connected with the stator winding of the main motor through the normally open contact of the K2 change-over switch, and form a parallel structure with the three output ends of the power generation controller.
In the starting stage of the topological structure, the starting controller outputs electromagnetic torque and drags the two-stage motor to start running; the starting controller comprises a direct-current power supply, an exciter control power circuit sharing a direct-current bus and a main motor control power circuit, wherein the output of the exciter control power circuit is connected with an exciter stator winding, and the output of the main motor control power circuit is connected with the main motor stator winding.
In the power generation stage, the power generation controller operates and provides excitation for the two-stage starting power generation system; the input of the power generation controller is connected with the stator winding of the main motor, and the output of the power generation controller is connected with the stator winding of the exciter; the K1 change-over switch and the K2 change-over switch control the connection state of the starting controller and the power generation controller. The starting stage K1 change-over switch and the K2 change-over switch are connected with two ends of the starting controller, and the system works in the starting stage; the power generation stage K1 change-over switch and the K2 change-over switch are connected with two ends of the power generation controller, and the system works in the power generation stage.
The K1 change-over switch and the K2 change-over switch are double-throw switches, and are used for controlling the connection or disconnection of the starting controller and the power generation controller.
The starting controller comprises a direct-current power supply, an exciter control power circuit and a main motor control power circuit; the exciter control power circuit and the main motor control power circuit are connected in parallel with a direct-current power supply; the output of the exciter control power circuit is connected with an exciter stator winding; and the output of the main motor control power circuit is connected with the stator winding of the main motor.
The power generation controller comprises an uncontrolled rectifying power circuit and an H-bridge chopper circuit which are connected in parallel; the uncontrolled rectifying circuit is used as an input end of the power generation controller and is connected with a main motor stator winding; the H-bridge chopper circuit is used as the output end of the power generation controller and is connected with the stator winding of the exciter.
The feedback excitation method for realizing the aviation two-stage starting power generation system by utilizing the topological structure is characterized by comprising the following steps of:
step 1, starting: the normally closed contacts of the K1 change-over switch and the K2 change-over switch are connected with a starting controller, and a direct current power supply arranged in the starting controller is connected into the system; the starting controller outputs alternating current or direct current to provide excitation for an excitation winding of the exciter through the exciter control power circuit, and simultaneously provides alternating current for a main motor through the main motor control power circuit, and the main motor generates enough electromagnetic torque to drive an aeroengine to start under the energy supply of two ends;
step 2: the rotating speed of the aero-engine is gradually increased under the drive of the main motor, when the rotating speed reaches the set disengaging rotating speed, the K2 change-over switch acts, the normally closed contact is opened, so that the stator winding of the main motor is disconnected with the starting controller, and the normally open contact is closed, and the stator winding of the main motor is connected with the input end of the power generation controller; the power supply built in the starting controller only provides excitation for the exciter control power circuit through the K1 change-over switch, and no electric energy is provided for the main motor; in the transition stage, the two-stage starting power generation system completes power generation and voltage establishment under the excitation of a power supply, and generates three-phase alternating current at the output end of a main generator;
step 3: when the system reaches the power generation rotating speed, the normally closed contact of the K1 change-over switch is disconnected, the exciter is disconnected with the starting controller, and the normally open contact is connected with the output end of the power generation controller; at this time, the output of the main motor is connected with the input end of the power generation controller, and the output of the power generation controller is connected with the input end of the exciter; the two-stage starting power generation system enters a power generation state, and partial energy generated by the two-stage starting power generation system provides excitation for the exciter, and the excitation mode forms feedback excitation; in the generating state, the voltage output to the on-board power system is kept at a nominal value by the excitation voltage regulation of the exciter.
Advantageous effects
The invention provides a topology structure and a method of an aviation two-stage starting power generation system with feedback excitation. The exciter, the rotary rectifier and the main motor are coaxially arranged, the input of the rotary rectifier is connected with the rotor winding of the exciter, and the output of the rotary rectifier is connected with the rotor winding of the main motor; the starting controller comprises a direct-current power supply, an exciter control power circuit and a main motor control power circuit; the power generation controller consists of an uncontrolled rectifying power circuit and an H-bridge chopper circuit.
The feedback excitation topological structure of the aviation two-stage starting power generation system eliminates a permanent magnet auxiliary exciter in the traditional three-stage starting power generation system, and brings the advantages that: 1) The weight of the permanent magnet auxiliary exciter and the corresponding structural members for installation and fixation is directly reduced, dead weight which does not participate in starting work is avoided in the starting stage, and the power density is improved; 2) The permanent magnet with demagnetizing risk under special conditions such as high altitude, high temperature and the like is removed, and the reliability of the system is improved; 3) The three-motor structure is changed into a two-motor structure, so that the axial length of the motor body is shortened, the structure is simplified, and the motor is easier to install.
Drawings
FIG. 1 is a schematic diagram of an aviation two-stage starter-generator system topology;
FIG. 2 is a schematic diagram of a start controller configuration;
FIG. 3 is a schematic diagram of a power generation controller;
FIG. 4 is a schematic diagram of feedback excitation topology of an aviation two-stage starting power generation system;
fig. 5 is a schematic flow chart of feedback excitation control strategy of the aviation two-stage starting power generation system.
Detailed Description
The invention will now be further described with reference to examples, figures:
the topological structure schematic diagram of the aviation two-stage starting power generation system is shown in fig. 1. The system consists of a starting/generator, a starting controller, a power generation controller, a K1 change-over switch and a K2 change-over switch, wherein the starting/generator comprises an exciter, a rotary rectifier and a main motor. The exciter, the rotary rectifier and the main motor are coaxially arranged, the input of the rotary rectifier is connected with the rotor winding of the exciter, and the output of the rotary rectifier is connected with the rotor winding of the main motor; the starting controller is structurally schematically shown in fig. 2, and comprises a direct-current power supply, an exciter control power circuit and a main motor control power circuit, wherein the output of the exciter control power circuit is connected with an exciter stator winding, and the output of the main motor control power circuit is connected with a main motor stator winding; the structure schematic diagram of the power generation controller is shown in fig. 3, and the power generation controller consists of an uncontrolled rectifying power circuit and an H-bridge chopper circuit. The output end of the H-bridge chopper circuit serving as the power generation controller is connected with the stator winding of the exciter. The K1 change-over switch and the K2 change-over switch are double-throw switches, and are used for controlling the connection or disconnection of the starting controller and the power generation controller.
When the system is in a starting stage, the K1 change-over switch and the K2 change-over switch are connected with a starting controller, and at the moment, the direct-current power supply provides electromagnetic torque for the exciter and the main motor through the exciter control power circuit and the main motor control power circuit. When the system is in a transition stage, the K1 change-over switch is connected with the starting controller, the K2 change-over switch is connected with the power generation controller, the starting controller is internally provided with a direct current power supply to provide excitation for the exciter, and the initial power generation and voltage establishment are completed. When the system is in a power generation stage, the K1 change-over switch and the K2 change-over switch are connected with a power generation controller, and partial electric power output by the main motor provides direct current excitation for the exciter through uncontrolled rectification and an H-bridge chopper circuit. At this time, the output of the main motor provides excitation to the exciter, the input of the exciter ultimately producing the output of the main motor, such excitation being referred to as "feedback excitation".
For the feedback excitation topology structure of the aviation two-stage starting power generation system shown in fig. 4, the connection is as follows:
the input of the rotary rectifier is connected with the exciter rotor winding, and the output of the rotary rectifier is connected with the main motor rotor winding; two output ends of the starting controller are connected with a stator winding of the exciter through a normally closed contact of the K1 change-over switch, and three output ends are connected with the stator winding of the main motor through a normally closed contact of the K2 change-over switch; two output ends of the power generation controller are connected with a stator winding of the exciter through a normally open contact of the K1 change-over switch, and three output ends are connected with the stator winding of the main motor through a normally open contact of the K2 change-over switch; the three input ends of the airborne load are connected with the stator winding of the main motor through the normally open contact of the K2 change-over switch, and form a parallel structure with the three output ends of the power generation controller.
The flow chart of the adopted control strategy is shown in fig. 5, specifically:
(1) In the system starting stage, the switching switches K1 and K2 are connected with a starting controller. A direct current power supply arranged in the starting controller outputs 210V/200Hz single-phase alternating current through an exciter control power circuit to provide alternating current excitation for an exciter stator single-phase winding, and a vector control strategy is adopted by a main motor control power circuit to input variable-frequency alternating current to a main motor, so that the main motor generates electromagnetic torque to drive an aeroengine to start.
(2) After the starting power generation system drives the aero-engine to accelerate to 6000r/min, the aero-engine is started, and the two-stage starting power generation system enters a transition stage. The change-over switch K2 is shifted to the power generation controller by the starting controller, and the change-over switch K1 is still connected with the starting controller. In the transition stage, a built-in power supply of the starting controller provides initial excitation for the exciter, three-phase alternating voltage is induced in a stator winding of the main motor, the two-stage system completes initial power generation and voltage establishment, and the stator winding of the main motor is connected with the power generation controller through K2. The power generation controller measures the effective value of the output voltage of the main motor in real time, and adjusts the excitation size of the exciter by adopting a PI control strategy so that the effective value of the output voltage of the main motor is kept at 115V of the rated voltage value of the airborne power supply of the aviation.
(3) When the aero-engine drives the starting power generation system to accelerate to 8000r/min, the starting power generation system enters a power generation stage. The change-over switches K1 and K2 are connected with the power generation controller and the onboard load. In the power generation stage, the feedback excitation converts partial energy of the main motor into direct current through an uncontrolled rectifying circuit, and the direct current excitation is provided for the exciter after the feedback excitation is regulated through an H-bridge chopper circuit. The power generation controller adjusts the PWM signal duty ratio of the H-bridge chopper circuit at any time according to the effective value of the output voltage of the main motor, so that the voltage output by the main motor to the on-board load is kept at 115V of the rated voltage value of the aviation power supply.
Claims (7)
1. An aviation two-stage starting power generation system topological structure containing feedback excitation is characterized by comprising a two-stage starting power generator, a starting controller, a power generation controller and a change-over switch; the two-stage starting generator comprises an exciter, a rotary rectifier and a main motor which are coaxially arranged; the connection of the topological structure is as follows: the input of the rotary rectifier is connected with the exciter rotor winding, and the output of the rotary rectifier is connected with the main motor rotor winding; two output ends of the starting controller are connected with a stator winding of the exciter through a normally closed contact of the K1 change-over switch, and three output ends are connected with the stator winding of the main motor through a normally closed contact of the K2 change-over switch; two output ends of the power generation controller are connected with a stator winding of the exciter through a normally open contact of the K1 change-over switch, and three output ends are connected with the stator winding of the main motor through a normally open contact of the K2 change-over switch; the three input ends of the airborne load are connected with the stator winding of the main motor through the normally open contact of the K2 change-over switch, and form a parallel structure with the three output ends of the power generation controller.
2. The aviation two-stage starter-generator system topology including feedback excitation of claim 1, wherein: in the starting stage of the topological structure, the starting controller outputs electromagnetic torque and drags the two-stage motor to start running; the starting controller comprises a direct-current power supply, an exciter control power circuit sharing a direct-current bus and a main motor control power circuit, wherein the output of the exciter control power circuit is connected with an exciter stator winding, and the output of the main motor control power circuit is connected with the main motor stator winding.
3. The aviation two-stage starter-generator system topology including feedback excitation of claim 1, wherein: in the power generation stage, the power generation controller operates and provides excitation for the two-stage starting power generation system; the input of the power generation controller is connected with the stator winding of the main motor, and the output of the power generation controller is connected with the stator winding of the exciter; the K1 change-over switches K1 and K2 change-over switches control the connection states of the starting controller and the power generation controller. The starting stage K1 change-over switch and the K2 change-over switch are connected with two ends of the starting controller, and the system works in the starting stage; the power generation stage K1 change-over switch and the K2 change-over switch are connected with two ends of the power generation controller, and the system works in the power generation stage.
4. The aviation two-stage starter-generator system topology including feedback excitation of claim 1, wherein: the K1 change-over switch and the K2 change-over switch are double-throw switches, and are used for controlling the connection or disconnection of the starting controller and the power generation controller.
5. The aviation two-stage starter-generator system topology including feedback excitation of claim 1, wherein: the starting controller comprises a direct-current power supply, an exciter control power circuit and a main motor control power circuit; the exciter control power circuit and the main motor control power circuit are connected in parallel with a direct-current power supply; the output of the exciter control power circuit is connected with an exciter stator winding; and the output of the main motor control power circuit is connected with the stator winding of the main motor.
6. The aviation two-stage starter-generator system topology including feedback excitation of claim 1, wherein: the power generation controller comprises an uncontrolled rectifying power circuit and an H-bridge chopper circuit which are connected in parallel; the uncontrolled rectifying circuit is used as an input end of the power generation controller and is connected with a main motor stator winding; the H-bridge chopper circuit is used as the output end of the power generation controller and is connected with the stator winding of the exciter.
7. A method for realizing feedback excitation of an aviation two-stage starting power generation system by using the topological structure as claimed in any one of claims 1 to 6, which is characterized by comprising the following steps:
step 1, starting: the normally closed contacts of the K1 change-over switch and the K2 change-over switch are connected with a starting controller, and a direct current power supply arranged in the starting controller is connected into the system; the starting controller outputs alternating current or direct current to provide excitation for an excitation winding of the exciter through the exciter control power circuit, and simultaneously provides alternating current for a main motor through the main motor control power circuit, and the main motor generates enough electromagnetic torque to drive an aeroengine to start under the energy supply of two ends;
step 2: the rotating speed of the aero-engine is gradually increased under the drive of the main motor, when the rotating speed reaches the set disengaging rotating speed, the K2 change-over switch acts, the normally closed contact is opened, so that the stator winding of the main motor is disconnected with the starting controller, and the normally open contact is closed, and the stator winding of the main motor is connected with the input end of the power generation controller; the power supply built in the starting controller only provides excitation for the exciter control power circuit through the K1 change-over switch, and no electric energy is provided for the main motor; in the transition stage, the two-stage starting power generation system completes power generation and voltage establishment under the excitation of a power supply, and generates three-phase alternating current at the output end of a main generator;
step 3: when the system reaches the power generation rotating speed, the normally closed contact of the K1 change-over switch is disconnected, the exciter is disconnected with the starting controller, and the normally open contact is connected with the output end of the power generation controller; at this time, the output of the main motor is connected with the input end of the power generation controller, and the output of the power generation controller is connected with the input end of the exciter; the two-stage starting power generation system enters a power generation state, and partial energy generated by the two-stage starting power generation system provides excitation for the exciter, and the excitation mode forms feedback excitation; in the generating state, the voltage output to the on-board power system is kept at a nominal value by the excitation voltage regulation of the exciter.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311740112.6A CN117833728A (en) | 2023-12-18 | 2023-12-18 | Aviation two-stage starting power generation system topological structure containing feedback excitation and method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311740112.6A CN117833728A (en) | 2023-12-18 | 2023-12-18 | Aviation two-stage starting power generation system topological structure containing feedback excitation and method |
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