Multiplexing type three-level starting power generation controller

Abstract

The embodiment of the invention discloses a multiplex type three-stage starting power generation controller, and relates to the technical field of aviation three-stage starting power generators. In the starting stage, an H-bridge inverter in the starting power generation controller provides single-phase alternating-current exciting current for a main exciter stator exciting winding through SPWM modulation so as to establish a pulsating magnetic field to provide exciting current for a main motor, and a three-phase full-bridge inverter provides armature current for a main motor stator armature winding through SVPWM modulation. In a power generation stage, an anti-parallel diode of the three-phase full-bridge inverter is used as a rectification circuit of the auxiliary exciter, and the H-bridge inverter adopts a PWM chopping mode to operate as an asymmetric half-bridge circuit. A power generation controller and a starting controller are integrated into a whole, and by changing the modulation mode of a hardware circuit, the control function of the three-stage starting generator at different stages can be realized by only one controller, so that the structure of the starting power generation controller is simplified, the system integration degree of the three-stage starting generator is improved, and the volume and the weight of the system are reduced.

Description

Technical Field

[0001] This invention relates to the field of aviation three-stage starter generator technology, and more particularly to a multiplexed three-stage starter generator controller. Background Technology

[0002] Three-stage starter generators are widely used in the aviation industry as both main power sources and starter motors for aircraft. The starter generator controller, as the core of the three-stage starter generator system, regulates the generator output voltage and starting output torque. Traditional starter generator controllers consist of two independent controllers: a starter controller and a generator controller. In starter mode, the starter controller operates independently, providing single-phase AC excitation current to the main exciter stator through its H-bridge inverter and three-phase AC current to the main generator stator through its three-phase full-bridge inverter. In generator mode, the starter controller is inactive, and the generator controller operates independently, providing DC excitation current to the main exciter stator through its three-phase full-bridge rectifier and asymmetrical half-bridge circuit.

[0003] However, with the development of aircraft electrification, the requirements for the integration level of aviation electrical systems are becoming increasingly higher, necessitating more integrated aviation generator controllers. Among these, how to improve traditional starter-generator controllers to achieve a higher degree of integration, thereby further reducing the size and weight of aviation three-stage starter-generators, has become a topic that requires in-depth research. Summary of the Invention

[0004] The embodiments of the present invention provide a reusable three-stage starter-generator controller that integrates the generator controller and the starter controller into one unit. This eliminates the need to deploy separate generator controllers and starter controllers, enabling control of single-phase AC excitation starting and DC excitation generation of the aircraft three-stage starter-generator, thereby further reducing the size and weight of the aircraft three-stage starter-generator.

[0005] To achieve the above objectives, the embodiments of the present invention adopt the following technical solutions:

[0006] A multi-functional three-stage starter-generator controller integrates the starter controller function and the generator controller function into the starter-generator controller to realize the starter and generator control of a three-stage brushless synchronous motor. The specific integrated structure includes: the aircraft electrical load (6) is connected to the three-stage brushless synchronous motor in sequence through the load generator control contactor (11) and the starter-generator control contactor (10); the structure of the three-stage brushless synchronous motor includes: a secondary exciter (1), a main exciter (2), a rotating rectifier (3) and a main motor (4), and the three-stage brushless synchronous motor is connected to the aircraft engine (5); the starting power supply (7) is connected to the starter-generator controller (8) through the starter control contactor (12); the starter-generator controller (8) is connected to the generator control contactor (9) and the starter-generator control contactor (10); the main circuit of the starter-generator controller (8) is composed of an H-bridge inverter (81), a three-phase full-bridge inverter (82) and a bus capacitor cascaded together; the operating modes of the starter-generator controller (8) include the start-up mode and the generator mode.

[0007] In the three-phase full-bridge inverter (82), the midpoints of the three bridge arms are respectively connected to the generator control contactor (9) and the starting generator control contactor (10) connected to the stator three-phase armature winding end of the auxiliary exciter (1). In the three-phase full-bridge inverter (82), the main circuit consists of 6 IGBTs and 6 diodes, with each IGBT connected in reverse parallel to a diode; the emitter of Q3 (821) is connected to the collector of Q8 (822) to form the first bridge arm of the three-phase full-bridge inverter (82), the collector of Q3 (821) is connected to the positive terminal of the starting contactor (12), and the emitter of Q8 (822) is connected to the negative terminal of the starting contactor (12); the emitter of Q4 (825) is connected to the collector of Q9 (826) to form the second bridge arm of the three-phase full-bridge inverter (82), the collector of Q4 (825) is connected to the positive terminal of the starting contactor (12), and the emitter of Q9 (826) is connected to the negative terminal of the starting contactor (12); the emitter of Q5 (829 ... 10 (8210) The collectors are connected to form the third arm of the three-phase full-bridge inverter (82), and the collector of Q5 (829) is connected to the positive terminal of the starting contactor (12). 10 The emitter of (8210) is connected to the negative terminal of the starting contactor (12).

[0008] Specifically, in the H-bridge inverter (81), the midpoints of the two bridge arms are connected to the end of the single-phase excitation winding of the stator of the main exciter (2) and the starting and generating control contactor (10), respectively. In the H-bridge inverter (81), the main circuit consists of 4 IGBTs and 4 diodes, with each IGBT connected in reverse parallel to a diode; the emitter of Q1 (811) is connected to the collector of Q6 (812) to form the first bridge arm of the H-bridge inverter (81), the collector of Q1 (811) is connected to the positive terminal of the starting contactor (12), and the emitter of Q6 (812) is connected to the negative terminal of the starting contactor (12); the emitter of Q2 (815) is connected to the collector of Q7 (816) to form the second bridge arm of the H-bridge inverter (81), the collector of Q2 (815) is connected to the positive terminal of the starting contactor (12), and the emitter of Q7 (816) is connected to the negative terminal of the starting contactor (12).

[0009] In this embodiment, the single-phase AC excitation current of the main exciter (2) is provided by the H-bridge inverter (81) in the start-generator controller (8), and SPWM modulation is used. The armature current supplied to the stator armature winding of the main motor (4) is provided by the three-phase full-bridge inverter (82) in the start-generator controller (8), and SVPWM modulation is used. The starting mode includes: the single-phase AC excitation current of the main exciter (2) is provided by the H-bridge inverter (81) in the start-generator controller (8); the armature current supplied to the stator armature winding of the main motor (4) is provided by the three-phase full-bridge inverter (82) in the start-generator controller (8).

[0010] For example: In the starting mode, the generator control contactor (9) is open, the starting control contactor (12) is closed, the starting generator control contactor (10) is closed, and the starting power supply (7) is connected to the starting generator controller (8). At this time, the H-bridge inverter (81) in the starting generator controller provides single-phase AC excitation current to the stator excitation winding of the main exciter (2) through SPWM modulation to establish a pulsating magnetic field to provide excitation current to the main motor; the three-phase full-bridge inverter (82) provides armature current to the stator armature winding of the main motor (4) through SVPWM modulation. In the starting mode, the rotor side of the main exciter (2) generates an induced electromotive force, thereby providing excitation current to the main motor (4).

[0011] In this embodiment, the power generation mode includes: the three-phase AC power generated by the auxiliary exciter (1) is rectified by the three-phase full-bridge uncontrolled rectifier circuit, and then chopped by the asymmetrical half-bridge to provide an adjustable DC excitation current to the main exciter (2).

[0012] For example: In the power generation mode, the load power generation control contactor (11) and the power generation control contactor (9) are closed, the starter controller contactor (12) is open, the stator winding of the main motor (4) is connected to the aircraft electrical load (6), the anti-parallel diode of the three-phase full-bridge inverter (82) is used as the rectifier circuit of the auxiliary exciter (1), and the H-bridge inverter (81) is operated as an asymmetrical half-bridge circuit using PWM chopping. During the power generation process, the aircraft engine (5) drives the motor to rotate, and the AC power generated by the auxiliary exciter (1) is rectified and chopped by the starter power generation controller (8) to provide DC excitation current to the main exciter (2).

[0013] The multiplexed three-stage starter-generator controller provided in this invention is mainly used to control the starting and power generation of an aircraft three-stage starter-generator. During the starting phase, the H-bridge inverter in the starter-generator controller provides single-phase AC excitation current to the stator excitation winding of the main exciter via SPWM modulation to establish a pulsating magnetic field to provide excitation current to the main motor. The three-phase full-bridge inverter provides armature current to the stator armature winding of the main motor via SVPWM modulation. During the power generation phase, the anti-parallel diodes of the three-phase full-bridge inverter are used as the rectifier circuit for the auxiliary exciter, and the H-bridge inverter operates as an asymmetrical half-bridge circuit using PWM chopping. During power generation, the engine drives the motor to rotate, and the AC power generated by the auxiliary exciter is rectified and chopped by the starter-generator controller to provide an adjustable DC excitation current to the main exciter. This invention integrates the generator controller and the starter controller into one unit. By changing the modulation method of the hardware circuit, only one controller is needed to realize the control functions of different stages of the three-stage starter generator. This simplifies the starter generator controller architecture, improves the system integration of the three-stage starter generator, and helps to reduce the size and weight of the system. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram of the aviation three-stage starter generator system provided in an embodiment of the present invention;

[0016] Figure 2 This is an embodiment of the present invention illustrating the connection method of an aviation three-stage starter generator system in start-up mode;

[0017] Figure 3 This is a schematic diagram of the connection method of the aviation three-stage starter generator system in power generation mode provided by the embodiments of the present invention. Detailed Implementation

[0018] To enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. Embodiments of the present invention will be described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention. Those skilled in the art will understand that, unless specifically stated otherwise, the singular forms “a,” “an,” “the,” and “the” used herein may also include the plural forms. It should be further understood that the term “comprising” as used in the specification of the present invention means the presence of the stated features, integers, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. It should be understood that when we say an element is “connected” or “coupled” to another element, it can be directly connected or coupled to the other element, or there may be intermediate elements. Furthermore, “connected” or “coupled” as used herein can include wireless connections or couplings. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items. It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the meaning consistent with their meaning in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein.

[0019] This invention proposes a reusable three-stage starter-generator controller, which integrates the entire aviation three-stage starter-generator system as follows: Figure 1 As shown, it includes: auxiliary exciter (1), main exciter (2), rotating rectifier (3), main motor (4), aircraft engine (5), aircraft electrical load (6), starting power supply (7), starting generator controller (8), generator control contactor (9), starting generator control contactor (10), load generator control contactor (11), and starting control contactor (12).

[0020] Preferably, in the starter generator controller (8), the main circuit consists of a three-phase full-bridge inverter (82), an H-bridge inverter (81), and a bus capacitor cascaded together.

[0021] Preferably, in the three-phase full-bridge inverter (82), the main circuit consists of 6 IGBTs and 6 diodes, with each IGBT connected in reverse parallel to a diode;

[0022] The emitter of Q3 (821) is connected to the collector of Q8 (822) to form the first bridge arm. The collector of Q3 (821) is connected to the positive terminal of the starting contactor (12), and the emitter of Q8 (822) is connected to the negative terminal of the starting contactor (12). The emitter of Q4 (825) is connected to the collector of Q9 (826) to form the second bridge arm. The collector of Q4 (825) is connected to the positive terminal of the starting contactor (12), and the emitter of Q9 (826) is connected to the negative terminal of the starting contactor (12). The emitter of Q5 (829) is connected to the collector of Q8 (822) to form the second bridge arm. 10 (8210) The collectors are connected to form the third bridge arm, and the collector of Q5 (829) is connected to the positive terminal of the starting contactor (12). 10 The emitter of (8210) is connected to the negative terminal of the starting contactor (12).

[0023] Preferably, in the H-bridge inverter (81), the circuit consists of 4 IGBTs and 4 diodes, with each IGBT connected in reverse parallel to a diode;

[0024] The emitter of Q1 (811) is connected to the collector of Q6 (812) to form the first bridge arm. The collector of Q1 (811) is connected to the positive terminal of the starting contactor (12), and the emitter of Q6 (812) is connected to the negative terminal of the starting contactor (12). The emitter of Q2 (815) is connected to the collector of Q7 (816) to form the second bridge arm. The collector of Q2 (815) is connected to the positive terminal of the starting contactor (12), and the emitter of Q7 (816) is connected to the negative terminal of the starting contactor (12).

[0025] Preferably, the working principle of the starter generator controller (8) is as follows:

[0026] like Figure 2 As shown, during the starting phase, the generator control contactor (9) is disconnected, the starting control contactor (12) is closed, the starting generator control contactor (10) is closed, the starting power supply (7) is connected to the starting generator controller (8), the H-bridge inverter (81) in the starting generator controller provides single-phase AC excitation current to the stator excitation winding of the main exciter (2) through SPWM modulation, so as to establish a pulsating magnetic field to provide excitation current to the main motor, and the three-phase full-bridge inverter (82) provides armature current to the stator armature winding of the main motor (4) through SVPWM modulation. During the starting phase, the rotor side of the main exciter (2) generates an induced electromotive force, thereby providing excitation current to the main motor (4);

[0027] like Figure 3As shown, during the power generation stage, the load power generation control contactor (11) and the power generation control contactor (9) are closed, the starter controller contactor (12) is open, and the stator winding of the main motor (4) is connected to the aircraft electrical load (6). The anti-parallel diode of the three-phase full-bridge inverter (82) is used as the rectifier circuit of the auxiliary exciter, and the H-bridge inverter (81) operates as an asymmetrical half-bridge circuit using PWM chopping. During power generation, the aircraft engine (5) drives the motor to rotate, and the AC power generated by the auxiliary exciter (1) is rectified and chopped by the starter power generation controller (8) to provide an adjustable DC excitation current to the main exciter (2).

[0028] The reusable three-stage starter generator controller provided in this embodiment integrates the generator controller and the starter controller into one unit. By changing the modulation method of the hardware circuit, only one controller is needed to realize the control functions of different stages of the three-stage starter generator. This simplifies the starter generator controller architecture, improves the system integration of the three-stage starter generator, and helps to reduce the size and weight of the system.

[0029] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on its differences from other embodiments. In particular, the device embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments. The above descriptions are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A reusable three-stage starter-generator controller, characterized in that, The aircraft electrical load (6) is connected to the three-stage brushless synchronous motor in sequence through the load power generation control contactor (11) and the starting power generation control contactor (10); The structure of the three-stage brushless synchronous motor includes: an auxiliary exciter (1), a main exciter (2), a rotary rectifier (3) and a main motor (4), and the three-stage brushless synchronous motor is connected to the aircraft engine (5). The starting power supply (7) is connected to the starting generator controller (8) through the starting control contactor (12); The start-up generator controller (8) is connected to the generator control contactor (9) and the start-up generator control contactor (10). The main circuit of the generator starter controller (8) consists of an H-bridge inverter (81), a three-phase full-bridge inverter (82), and a bus capacitor cascaded together. The operating modes of the start-up and power generation controller (8) include start-up mode and power generation mode.

2. The multiplexed three-stage starter-generator controller according to claim 1, characterized in that, In the three-phase full-bridge inverter (82), the midpoints of the three bridge arms are respectively connected to the generator control contactor (9) and the starting generator control contactor (10) connected to the stator three-phase armature winding end of the auxiliary exciter (1).

3. The multiplexed three-stage starter-generator controller according to claim 1 or 2, characterized in that, In the three-phase full-bridge inverter (82), the main circuit consists of 6 IGBTs and 6 diodes, with each IGBT connected in reverse parallel to a diode; The emitter of Q3 (821) is connected to the collector of Q8 (822) to form the first bridge arm of the three-phase full-bridge inverter (82). The collector of Q3 (821) is connected to the positive terminal of the starting contactor (12), and the emitter of Q8 (822) is connected to the negative terminal of the starting contactor (12). The emitter of Q4 (825) is connected to the collector of Q9 (826) to form the second bridge arm of the three-phase full-bridge inverter (82). The collector of Q4 (825) is connected to the positive terminal of the starting contactor (12), and the emitter of Q9 (826) is connected to the negative terminal of the starting contactor (12). The emitter of Q5 (829) and Q 10 (8210) The collectors are connected to form the third arm of the three-phase full-bridge inverter (82). The collector of Q5 (829) is connected to the positive terminal of the starting contactor (12). 10 The emitter of (8210) is connected to the negative terminal of the starting contactor (12).

4. The multiplexed three-stage starter-generator controller according to claim 1, characterized in that, In the H-bridge inverter (81), the midpoints of the two bridge arms are connected to the end of the stator single-phase excitation winding of the main exciter (2) and the starting and generating control contactor (10), respectively.

5. The multiplexed three-stage starter-generator controller according to claim 1 or 4, characterized in that, In the H-bridge inverter (81), the main circuit consists of 4 IGBTs and 4 diodes, with each IGBT connected in reverse parallel to a diode; The emitter of Q1 (811) is connected to the collector of Q6 (812) to form the first bridge arm of the H-bridge inverter (81). The collector of Q1 (811) is connected to the positive terminal of the starting contactor (12), and the emitter of Q6 (812) is connected to the negative terminal of the starting contactor (12). The emitter of Q2 (815) is connected to the collector of Q7 (816) to form the second bridge arm of the H-bridge inverter (81). The collector of Q2 (815) is connected to the positive terminal of the starting contactor (12), and the emitter of Q7 (816) is connected to the negative terminal of the starting contactor (12).

6. The multiplexed three-stage starter-generator controller according to claim 1, characterized in that, The starting mode includes: the single-phase AC excitation current of the main exciter (2) is provided by the H-bridge inverter (81) in the starting generator controller (8); the armature current supplied to the stator armature winding of the main motor (4) is provided by the three-phase full-bridge inverter (82) in the starting generator controller (8).

7. The multiplexed three-stage starter-generator controller according to claim 1 or 6, characterized in that, In the starting mode, the generator control contactor (9) is open, the start control contactor (12) is closed, the start generator control contactor (10) is closed, and the starting power supply (7) is connected to the start generator controller (8). At this time, the H-bridge inverter (81) in the start generator controller provides single-phase AC excitation current to the stator excitation winding of the main exciter (2) through SPWM modulation to establish a pulsating magnetic field to provide excitation current to the main motor. The three-phase full-bridge inverter (82) provides armature current to the stator armature winding of the main motor (4) through SVPWM modulation. In the starting mode, the rotor side of the main exciter (2) generates induced electromotive force, thereby providing excitation current to the main motor (4).

8. The multiplexed three-stage starter-generator controller according to claim 1, characterized in that, The power generation mode includes: the three-phase AC power generated by the auxiliary exciter (1) is rectified by the three-phase full-bridge uncontrolled rectifier circuit, and then chopped by the asymmetrical half-bridge to provide an adjustable DC excitation current to the main exciter (2).

9. The multiplexed three-stage starter-generator controller according to claim 1 or 8, characterized in that, In the power generation mode, the load power generation control contactor (11) and the power generation control contactor (9) are closed, the starter controller contactor (12) is open, the stator winding of the main motor (4) is connected to the aircraft electrical load (6), the anti-parallel diode of the three-phase full-bridge inverter (82) is used as the rectifier circuit of the auxiliary exciter (1), and the H-bridge inverter (81) is operated as an asymmetrical half-bridge circuit using PWM chopping. During the power generation process, the aircraft engine (5) drives the motor to rotate, and the alternating current generated by the auxiliary exciter (1) is rectified and chopped by the starter generator controller (8) to provide DC excitation current to the main exciter (2).

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