Voltage buildup circuit of low-voltage direct-current starting power generation system of aero-engine

Abstract

The invention belongs to the technical field of aero-engine low-voltage direct-current starting power generation system voltage buildup design, and particularly relates to an aero-engine low-voltage direct-current starting power generation system voltage buildup circuit which comprises a controller, a controller power supply and a power generation switch. A generator terminal voltage connecting terminal, a residual magnetism voltage building anti-reverse circuit and a magnetizing circuit are arranged in the controller, and the generator terminal voltage connecting terminal is connected with the residual magnetism voltage building anti-reverse circuit and is connected with a generator excitation positive end through a power generation switch; the magnetizing circuit comprises an electronic switch, a magnetizing anti-reverse circuit and a magnetizing control module, and the electronic switch is connected with the controller power supply, is connected with the magnetizing anti-reverse circuit and is connected with the excitation positive end of the generator through the power generation switch; the magnetizing control module is connected with the power generation switch and controls the electronic switch to be switched on when receiving the magnetizing control signal; and the magnetizing control signal is generated by the controller after the power generation switch is closed.

Description

Technical Field

[0001] The present application belongs to the technical field of voltage building design of a low-voltage DC starting and generating system of an aircraft engine, and specifically relates to a voltage building circuit of a low-voltage DC starting and generating system of an aircraft engine. Background Art

[0002] After the aviation low-voltage DC starting and generating system is started, it mainly relies on the residual magnetic voltage of the DC starting generator in the system at a low speed to complete voltage building and power generation. This voltage building method is prone to voltage building failure when the properties of the punching sheet materials in the generator pole assembly are dispersed and the residual magnetic voltage is low, thereby reducing mission reliability.

[0003] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0004] The purpose of the present application is to provide a voltage building circuit for a low-voltage DC starting and generating system of an aircraft engine, so as to overcome or alleviate at least one aspect of the known technical defects.

[0005] The technical solution of this application is:

[0006] A voltage building circuit for a low-voltage DC starting power generation system of an aircraft engine, comprising a controller, a controller power supply, and a power generation switch;

[0007] The controller is provided with a generator terminal voltage connection terminal, a residual magnetic voltage build-up anti-reverse circuit, and a magnetizing circuit, wherein the generator terminal voltage connection terminal is connected to the residual magnetic voltage build-up anti-reverse circuit, and is connected to the generator excitation positive terminal through a generating switch;

[0008] The magnetization circuit includes an electronic switch, a magnetization anti-reverse circuit, and a magnetization control module, wherein the electronic switch is connected to the controller power supply, and the magnetization anti-reverse circuit, and is connected to the positive excitation terminal of the generator through the power generation switch; the magnetization control module is connected to the power generation switch, and controls the electronic switch to be turned on when receiving the magnetization control signal;

[0009] The magnetization control signal is generated by the controller after the generator switch is closed.

[0010] According to at least one embodiment of the present application, in the voltage building circuit of the above-mentioned aircraft engine low-voltage DC starting and generating system, the magnetization control signal lasts for 100 to 500 ms.

[0011] According to at least one embodiment of the present application, in the voltage building circuit of the above-mentioned aircraft engine low-voltage DC starting and generating system, the negative terminal of the generator excitation and the negative terminal of the controller power supply are connected to the electrical ground.

[0012] According to at least one embodiment of the present application, in the voltage building circuit of the above-mentioned aircraft engine low-voltage DC starting and generating system, the residual magnetic voltage building anti-reverse circuit adopts an anti-reverse diode V1;

[0013] The magnetizing anti-reverse circuit uses an anti-reverse diode V2;

[0014] The electronic switch uses a photo MOS tube field effect tube or a triode.

[0015] According to at least one embodiment of the present application, in the voltage building circuit of the above-mentioned aircraft engine low-voltage DC starting and generating system, the magnetization control module includes a resistor R1 and a resistor R2, wherein one end of the resistor R1 can be connected to the magnetization control signal, and the other end is connected to the positive control terminal of the electronic switch; one end of the resistor R2 is connected to the negative control terminal of the electronic switch, and the other end is connected to the line between the resistor R1 and the positive control terminal of the electronic switch.

[0016] This application has at least the following beneficial technical effects:

[0017] A voltage building circuit for a low-voltage DC starting and generating system of an aircraft engine is provided. When the circuit is working, the power supply of a controller is used to instantaneously magnetize the excitation winding of the generator, so that the low-voltage DC starting and generating system of the aircraft engine can overcome the problem of low residual magnetic voltage, achieve smooth and successful voltage building, and improve the working reliability of the low-voltage DC starting and generating system of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the topological structure of the voltage building circuit of the aircraft engine low-voltage DC starting and generating system provided in the embodiment of the present application;

[0019] Figure 2 It is a schematic diagram of the voltage building circuit structure of the aircraft engine low-voltage DC starting and generating system provided in the embodiment of the present application.

[0020] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0021] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0022] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0023] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0024] In actual engineering applications, it is difficult to troubleshoot the problem that the power generation system cannot build voltage and generate electricity due to low residual magnetic voltage, and the characteristics of the generator pole assembly are not easy to adjust and control, so it is difficult to solve the problem by adjusting the generator characteristics. In this regard, the embodiment of the present application provides a voltage building circuit for a low-voltage DC starting power generation system of an aircraft engine, and its topological structure is as follows: Figure 1 As shown, at the beginning of voltage building, the positive end of the generator excitation can be instantaneously magnetized to assist voltage building, so that the aircraft engine low-voltage DC starting and generating system can reliably build voltage and generate electricity under the condition of low residual magnetism of the generator, which can more fully meet the use requirements of the aviation low-voltage DC starting and generating system.

[0025] The voltage-building circuit of the aircraft engine low-voltage DC starting generator system includes a controller, a controller power supply, and a generator switch.

[0026] The controller is equipped with a generator terminal voltage connection terminal, a residual magnetic voltage buildup anti-reverse circuit, and a magnetizing circuit.

[0027] The generator end voltage connection terminal is connected to the residual magnetic voltage building and anti-reverse circuit, and is connected to the generator excitation positive terminal through the generating switch.

[0028] The magnetization circuit includes an electronic switch, a magnetization anti-reverse circuit, and a magnetization control module.

[0029] The electronic switch is connected to the controller power supply and the magnetizing anti-reverse circuit, and is connected to the generator excitation positive terminal through the generating switch.

[0030] The negative terminal of the generator excitation and the negative terminal of the controller power supply are connected to the electrical ground.

[0031] The magnetization control module is connected to the power generation switch, and controls the electronic switch to be turned on when receiving the magnetization control signal.

[0032] The magnetization control signal is generated by the controller using software or hardware circuits after the generator switch is closed and can last for 100 to 500 ms.

[0033] The voltage-building circuit of the aircraft engine low-voltage DC starting power generation system disclosed in the above embodiment adds a magnetizing circuit inside the controller, and the controller power supply is connected to the positive excitation terminal of the generator through the magnetizing circuit and the power generation switch. The magnetizing control module is used to control the on and off of the electronic switch to realize magnetic flash. The specific working process is as follows:

[0034] After the generator switch is closed, the controller generates a magnetization control signal, the magnetization control module controls the electronic switch to turn on, and the power supply acts on the positive excitation terminal of the generator through the electronic switch, the magnetization anti-reverse circuit, and the generator switch to magnetize the generator excitation winding. The magnetization control module controls the electronic switch to magnetize the motor excitation winding for a certain period of time and then disconnects to complete the magnetization. Subsequently, the generator-end voltage connection terminal continues to apply it to the excitation positive end through the residual magnetism voltage building anti-reverse circuit and the generator switch to complete the entire voltage building process. If the residual magnetism is sufficient, after the generator switch is closed, the generator-end voltage connection terminal will be applied to the excitation positive end at the same time through the residual magnetism voltage building circuit and the magnetization circuit.

[0035] The voltage building circuit of the aircraft engine low-voltage DC starting and generating system disclosed in the above embodiment, at the beginning of voltage building, the controller power supply is instantaneously applied to the generator excitation positive terminal through the internal magnetizing circuit of the controller to magnetize the generator excitation winding. The magnetizing time can be controlled by the controller to ensure smooth voltage building of the system, solve the problem of difficulty in voltage building when the residual magnetism is low, and improve the system working reliability. Among them, the introduced magnetizing control module is isolated from other functional circuits and has no effect on the starting and voltage regulation performance of the controller.

[0036] The voltage building circuit of the aircraft engine low voltage DC starting power generation system disclosed in the above embodiment can be specifically designed as follows: Figure 2 shown.

[0037] The residual magnetic voltage building and reverse protection circuit uses a reverse protection diode V1.

[0038] The magnetizing anti-reverse circuit uses an anti-reverse diode V2.

[0039] The electronic switch uses a photo MOS tube field effect tube or a triode.

[0040] The magnetization control module includes a resistor R1 and a resistor R2, wherein one end of the resistor R1 can be connected to the magnetization control signal, and the other end is connected to the positive control terminal of the electronic switch; one end of the resistor R2 is connected to the negative control terminal of the electronic switch, and the other end is connected to the line between the resistor R1 and the positive control terminal of the electronic switch.

[0041] After the generating switch is closed, the controller generates a magnetizing control signal. The magnetizing control module controls the electronic switch to be turned on through the voltage divider circuit composed of resistors R1 and R2. The power supply acts on the positive excitation terminal of the generator through the electronic switch, the anti-reverse diode V2, and the generating switch to magnetize the generator excitation winding. The magnetizing control module controls the electronic switch to magnetize the motor excitation winding for a certain period of time and then disconnect it to complete the magnetization. Subsequently, the generator terminal voltage connection terminal continues to be applied to the positive excitation terminal through the anti-reverse diode V1 and the generating switch to complete the entire voltage building process.

[0042] The voltage building circuit of the aircraft engine low-voltage DC starting and generating system disclosed in the above embodiment has been applied in the aircraft engine low-voltage DC starting and generating system. After a series of tests and assessments such as ground identification and installation test flight, the voltage building performance is good and stable.

[0043] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A voltage building circuit for a low voltage DC starting and generating system of an aircraft engine, characterized in that: Including controller, controller power supply, and power generation switch; The controller is provided with a generator terminal voltage connection terminal, a residual magnetic voltage build-up anti-reverse circuit, and a magnetizing circuit, wherein the generator terminal voltage connection terminal is connected to the residual magnetic voltage build-up anti-reverse circuit, and is connected to the generator excitation positive terminal through a generating switch; The magnetization circuit includes an electronic switch, a magnetization anti-reverse circuit, and a magnetization control module, wherein the electronic switch is connected to the controller power supply, and the magnetization anti-reverse circuit, and is connected to the positive excitation terminal of the generator through the power generation switch; the magnetization control module is connected to the power generation switch, and controls the electronic switch to be turned on when receiving the magnetization control signal; The magnetization control signal is generated by the controller after the generator switch is closed.

2. The voltage building circuit of the aircraft engine low voltage DC starting power generation system according to claim 1, characterized in that: The magnetization control signal lasts for 100 to 500 ms.

3. The voltage building circuit of the aircraft engine low voltage DC starting power generation system according to claim 2, characterized in that: The negative terminal of the generator excitation and the negative terminal of the controller power supply are connected to the electrical ground.

4. The voltage building circuit of the aircraft engine low voltage DC starting power generation system according to claim 3, characterized in that: The residual magnetic voltage building anti-reverse circuit adopts anti-reverse diode V1; The magnetizing anti-reverse circuit uses an anti-reverse diode V2; The electronic switch uses a photo MOS tube field effect tube or a triode.

5. The voltage building circuit of the aircraft engine low voltage DC starting power generation system according to claim 4, characterized in that: The magnetization control module includes a resistor R1 and a resistor R2, wherein one end of the resistor R1 can be connected to the magnetization control signal, and the other end is connected to the positive control terminal of the electronic switch; one end of the resistor R2 is connected to the negative control terminal of the electronic switch, and the other end is connected to the line between the resistor R1 and the positive control terminal of the electronic switch.

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