阅读说明：本技术 飞机起动发电机、控制方法、计算机设备及存储介质 (Aircraft starter generator, control method, computer device, and storage medium ) 是由 陈畅 王跃 回彦年 康元丽 于 2021-01-08 设计创作，主要内容包括：本发明公开了一种飞机起动发电机、控制方法、计算机设备及存储介质,涉及航空电子技术领域,使电机在起动阶段具有较高的串联匝数,在发电阶段具有较低的并联匝数,有利于降低起动电流,提高发电功率极限。本发明的主要技术方案为：定子绕组电路、控制器、逆变器、接触器、直流汇流条；所述定子绕组电路通过所述逆变器经所述接触器与所述直流汇流条连接；所述控制器的一端用于接收电机运行状态的控制信号,另一端连接所述定子绕组电路,并根据所述电机运行状态控制所述定子绕组电路中多个开关器件,以实现所述定子绕组电路中多个绕组的串联或并联,所述电机运行状态包括电机起动状态、电机发电状态。(The invention discloses an aircraft starting generator, a control method, computer equipment and a storage medium, and relates to the technical field of avionics. The main technical scheme of the invention is as follows: the device comprises a stator winding circuit, a controller, an inverter, a contactor and a direct current bus bar; the stator winding circuit is connected with the direct current bus bar through the inverter through the contactor; one end of the controller is used for receiving a control signal of the running state of the motor, the other end of the controller is connected with the stator winding circuit, and the plurality of switching devices in the stator winding circuit are controlled according to the running state of the motor so as to realize series connection or parallel connection of the plurality of windings in the stator winding circuit, and the running state of the motor comprises a starting state of the motor and a generating state of the motor.)

1. An aircraft starter generator, the generator comprising:

the device comprises a stator winding circuit, a controller, an inverter, a contactor and a direct current bus bar;

the stator winding circuit is connected with the direct current bus bar through the inverter through the contactor;

one end of the controller is used for receiving a control signal of the running state of the motor, the other end of the controller is connected with the stator winding circuit, and the plurality of switching devices in the stator winding circuit are controlled according to the running state of the motor so as to realize series connection or parallel connection of the plurality of windings in the stator winding circuit, and the running state of the motor comprises a starting state of the motor and a generating state of the motor.

2. An aircraft starter generator according to claim 1 wherein the stator winding circuit consists of 6 said windings, 7 switching devices and 1 uncontrolled rectifier bridge;

if the controller receives a control signal of a motor starting state, the controller controls a first switching device, a second switching device and a third switching device in the stator winding circuit to be switched on, and controls a fourth switching device, a fifth switching device, a sixth switching device and a seventh switching device in the stator winding circuit to be switched off, so that the first winding is connected with the second winding in series, the third winding is connected with the fourth winding in series, and the fifth winding is connected with the sixth winding in series;

if the controller receives a control signal of the power generation state of the motor, the controller controls the first switching device, the second switching device and the third switching device in the stator winding circuit to be switched off, and controls the fourth switching device, the fifth switching device, the sixth switching device and the seventh switching device to be switched on, so that the first winding is connected with the second winding in parallel, the third winding is connected with the fourth winding in parallel, and the fifth winding is connected with the sixth winding in parallel.

3. An aircraft starter generator according to claim 2 wherein the control signal for the operating state of the electrical machine is comprised of a first primary drive signal and a second primary drive signal; the controller comprises an interlock driving circuit, one end of which is used for receiving the first primary driving signal and the second primary driving signal;

the interlock driving circuit determines a first secondary driving signal and a second secondary driving signal according to the received first primary driving signal and the second primary driving signal;

the first switching device, the second switching device and the third switching device are controlled by the first secondary driving signal;

the fourth switching device, the fifth switching device, the sixth switching device and the seventh switching device are controlled by a second secondary driving signal.

4. An aircraft starter generator according to claim 3,

if the controller receives a control signal of the motor starting state, the first primary driving signal is controlled to be at a high level, and the second primary driving signal is controlled to be at a low level:

a first transistor in the interlocking driving circuit is turned on, a second transistor is turned off, a first diode is turned on, a second diode is turned off, a third diode is turned on, a fourth diode is turned on, a first secondary driving signal outputs a high level, and a second secondary driving signal outputs a low level;

if the controller receives a control signal of the power generation state of the motor, the first primary driving signal is controlled to be at a low level, and the second primary driving signal is controlled to be at a high level;

a first transistor in the interlocking driving circuit is cut off, a second transistor is conducted, a first diode is cut off, a second diode is conducted, a third diode is conducted, a fourth diode is conducted, a first secondary driving signal outputs a low level, and a second secondary driving signal outputs a high level.

5. An aircraft starter generator according to claim 3,

when the first primary driving signal and the second primary driving signal are both at a low level, a first transistor in the interlock driving circuit is turned off, a second transistor is turned off, a first diode is turned off, a second diode is turned off, a third diode is turned on, a fourth diode is turned on, the first secondary driving signal outputs a low level, and the second secondary driving signal outputs a low level;

when the first primary driving signal and the second primary driving signal are both at a high level, a first transistor in the interlock driving circuit is turned on, a second transistor is turned on, a first diode is turned on, a second diode is turned on, a third diode is turned off, a fourth diode is turned off, the first secondary driving signal outputs a low level, and the second secondary driving signal outputs a low level.

6. An aircraft starter generator as claimed in any one of claims 1 to 5 wherein the generator further comprises an AC bus bar to which the stator winding circuit is connected via the contactor.

7. A method of controlling an aircraft starter generator, the method comprising:

the controller receives a control signal of a motor running state, wherein the motor running state comprises a motor starting state and a motor generating state;

converting the control signal of the motor running state into a first secondary driving signal and a second secondary driving signal;

controlling the opening and closing states of a first switching device, a second switching device and a third switching device in the stator winding circuit through the first secondary driving signal;

controlling the opening and closing states of a fourth switching device, a fifth switching device, a sixth switching device and a seventh switching device in the stator winding circuit through the second secondary driving signal;

and realizing the series connection or the parallel connection of a plurality of windings in the stator winding circuit according to the opening and closing states of a plurality of switching devices in the stator winding circuit.

8. The method of controlling an aircraft starter generator of claim 7,

if the controller receives a control signal of the starting state of the motor, the first secondary driving signal outputs a high level, and the second secondary driving signal outputs a low level;

controlling a first switching device, a second switching device and a third switching device in the stator winding circuit to be conducted, and controlling a fourth switching device, a fifth switching device, a sixth switching device and a seventh switching device to be disconnected, so that the first winding is connected with the second winding in series, the third winding is connected with the fourth winding in series, and the fifth winding is connected with the sixth winding in series;

if the controller receives a control signal of the power generation state of the motor, the first primary driving signal is controlled to be at a low level, and the second primary driving signal is controlled to be at a high level;

and controlling the first switching device, the second switching device and the third switching device in the stator winding circuit to be switched off, and controlling the fourth switching device, the fifth switching device, the sixth switching device and the seventh switching device to be switched on, so that the first winding is connected with the second winding in parallel, the third winding is connected with the fourth winding in parallel, and the fifth winding is connected with the sixth winding in parallel.

9. Computer arrangement comprising a memory, a processor and a computer program stored in the memory and executable on the processor, characterized in that the processor implements the method of controlling an aircraft starter generator according to any one of claims 7 to 8 when executing the computer program.

10. A computer-readable storage medium, in which a computer program is stored which, when being executed by a processor, carries out a method of controlling an aircraft starter generator according to any one of claims 7 to 8.

Technical Field

The invention relates to the technical field of avionics, in particular to an aircraft starter generator, a control method, computer equipment and a storage medium.

Background

The starting generator is used for starting the aircraft engine, enters a power generation state after the aircraft engine is ignited to work, is dragged by the engine to generate power and supplies power to a full-motor electric load. The starter generator is an important component in a modern airplane power supply system, generally adopts a three-level synchronous motor, and also has research on models such as a permanent magnet synchronous motor and the like.

In the starting phase, the stator winding of the motor is generally required to have a high number of series turns in order to limit the starting current, while in the power generation phase, the motor is generally required to have a low number of series turns in order to reduce the armature reactive reactance, increase the power limit, reduce the surge voltage and its duration.

Disclosure of Invention

The invention provides an aircraft starting generator, a control method, computer equipment and a storage medium, which enable the motor to have higher series turn number in the starting stage and lower parallel turn number in the generating stage, are beneficial to reducing starting current and improving the limit of generating power.

An embodiment of the present invention provides an aircraft starter generator, including:

the device comprises a stator winding circuit, a controller, an inverter, a contactor and a direct current bus bar;

the stator winding circuit is connected with the direct current bus bar through the inverter through the contactor;

one end of the controller is used for receiving a control signal of the running state of the motor, the other end of the controller is connected with the stator winding circuit, and the plurality of switching devices in the stator winding circuit are controlled according to the running state of the motor so as to realize series connection or parallel connection of the plurality of windings in the stator winding circuit, and the running state of the motor comprises a starting state of the motor and a generating state of the motor.

The embodiment of the invention provides a method for controlling an aircraft starter generator, which comprises the following steps:

the controller receives a control signal of a motor running state, wherein the motor running state comprises a motor starting state and a motor generating state;

converting the control signal of the motor running state into a first secondary driving signal and a second secondary driving signal;

controlling the opening and closing states of a first switching device, a second switching device and a third switching device in the stator winding circuit through the first secondary driving signal;

controlling the opening and closing states of a fourth switching device, a fifth switching device, a sixth switching device and a seventh switching device in the stator winding circuit through the second secondary driving signal;

and realizing the series connection or the parallel connection of a plurality of windings in the stator winding circuit according to the opening and closing states of a plurality of switching devices in the stator winding circuit.

A computer arrangement comprising a memory, a processor and a computer program stored in the memory and executable on the processor, the processor implementing the above-mentioned method of controlling an aircraft starter generator when executing the computer program.

A computer-readable storage medium, in which a computer program is stored which, when being executed by a processor, carries out the above-mentioned method of controlling an aircraft starter generator.

The invention provides an aircraft starting generator, a control method, computer equipment and a storage medium, wherein the aircraft starting generator comprises the following components: the device comprises a stator winding circuit, a controller, an inverter, a contactor and a direct current bus bar; the stator winding circuit is connected with the direct current bus bar through the inverter through the contactor; one end of the controller is used for receiving a control signal of the running state of the motor, the other end of the controller is connected with the stator winding circuit, and the plurality of switching devices in the stator winding circuit are controlled according to the running state of the motor so as to realize series connection or parallel connection of the plurality of windings in the stator winding circuit, and the running state of the motor comprises a starting state of the motor and a generating state of the motor. The invention realizes the switching of the motor stator winding in the starting stage and the generating stage through the switching device, so that the motor has higher series turns in the starting stage and lower series turns in the generating stage, thereby being beneficial to reducing the starting current, improving the generating power limit and reducing the surge voltage and the duration time thereof.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments of the present invention will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without inventive labor.

FIG. 1 is a block diagram of an aircraft starter generator in accordance with an embodiment of the present invention;

FIG. 2 is a schematic diagram of a winding circuit according to an embodiment of the present invention;

FIG. 3 is a schematic diagram of the series connection of windings in a start-up state according to an embodiment of the present invention;

FIG. 4 is a schematic diagram of the parallel connection of the windings in the power generating state according to an embodiment of the present invention;

FIG. 5 is a flow chart of generator operating condition determination according to an embodiment of the present invention;

FIG. 6 is a schematic diagram of an interlock driving circuit according to an embodiment of the present invention;

FIG. 7 is a schematic diagram of an embodiment of an alternator as an example in accordance with an embodiment of the present invention;

FIG. 8 is a flow chart of controlling an aircraft starter generator in accordance with an embodiment of the present invention;

FIG. 9 is a schematic diagram of a computer device according to an embodiment of the invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

As shown in fig. 1, an embodiment of the present invention provides an aircraft starter generator, the generator comprising:

the device comprises a stator winding circuit, a controller, an inverter, a contactor and a direct current bus bar;

the stator winding circuit is connected with the direct current bus bar through the inverter through the contactor QF 1;

one end of the controller is used for receiving a control signal of the motor running state, the other end of the controller is connected with the stator winding circuit, and the plurality of switching devices in the stator winding circuit are controlled according to the control signal of the motor running state so as to realize series connection or parallel connection of the plurality of windings in the stator winding circuit, and the motor running state comprises a motor starting state and a motor generating state.

Specifically, as shown in fig. 2, the stator winding circuit is composed of 6 windings, 7 switching devices and 1 uncontrolled rectifier bridge. The 6 windings are respectively a first winding W1, a second winding W2, a third winding W3, a fourth winding W4, a fifth winding W5 and a sixth winding W6, and the 7 switching devices are respectively a first switching device S1, a second switching device S2, a third switching device S3, a fourth switching device S4, a fifth switching device S5, a sixth switching device S6 and a seventh switching device S7.

As shown in fig. 3, if the controller receives a control signal of a motor start state, the controller controls the first switching device S1, the second switching device S2 and the third switching device S3 in the stator winding circuit to be turned on, and controls the fourth switching device S4, the fifth switching device S5, the sixth switching device S6 and the seventh switching device S7 in the stator winding circuit to be turned off, so that the first winding W1 is connected in series with the second winding W2, the third winding W3 is connected in series with the fourth winding W4, and the fifth winding W5 is connected in series with the sixth winding W6;

as shown in fig. 4, if the controller receives a control signal indicating a power generation state of the motor, the controller controls the first switching device S1, the second switching device S2, and the third switching device S3 in the stator winding circuit to be turned off, and controls the fourth switching device S4, the fifth switching device S5, the sixth switching device S6, and the seventh switching device S7 in the stator winding circuit to be turned on, such that the first winding W1 is connected in parallel with the second winding W2, the third winding W3 is connected in parallel with the fourth winding W4, and the fifth winding W5 is connected in parallel with the sixth winding W6.

As shown in fig. 5, the control signal of the motor operation state is composed of a first primary driving signal and a second primary driving signal; the controller comprises an interlock driving circuit, one end of the interlock driving circuit is used for receiving the first primary driving signal and the second primary driving signal, and the other end of the interlock driving circuit outputs a first secondary driving signal and a second secondary driving signal.

Specifically, the interlock driving circuit determines a first secondary driving signal and a second secondary driving signal according to the received first primary driving signal and the second primary driving signal;

the first switching device S1, the second switching device S2 and the third switching device S3 are controlled by the first secondary driving signal; if the first secondary driving signal is at a high level, the first switching device S1, the second switching device S2, and the third switching device S3 are turned on; if the first secondary driving signal is at a low level, the first switching device S1, the second switching device S2, and the third switching device S3 are turned off;

the fourth switching device S4, the fifth switching device S5, the sixth switching device S6 and the seventh switching device S7 are controlled by a second secondary driving signal. If the second secondary driving signal is at a high level, the fourth switching device S4, the fifth switching device S5, the sixth switching device S6, and the seventh switching device S7 are turned on, and if the second secondary driving signal is at a low level, the fourth switching device S4, the fifth switching device S5, the sixth switching device S6, and the seventh switching device S7 are turned off.

Specifically, as shown in fig. 6, if the controller receives a control signal of a motor start state, the controller controls the first primary driving signal to be at a high level 3V, and the second primary driving signal to be at a low level 0: a first transistor T1 in the interlock driving circuit is turned on, a second transistor T2 is turned off, a first diode D1 is turned on, a second diode D2 is turned off, a third diode D3 is turned on, a fourth diode D4 is turned on, a first secondary driving signal outputs a high level, and a second secondary driving signal outputs a low level;

if the controller receives a control signal of the power generation state of the motor, the first primary driving signal is controlled to be at a low level of 0, and the second primary driving signal is controlled to be at a high level of 3V; in the interlock driving circuit, the first transistor T1 is turned off, the second transistor T2 is turned on, the first diode D1 is turned off, the second diode D2 is turned on, the third diode D3 is turned on, the fourth diode D4 is turned on, the first secondary driving signal outputs a low level, and the second secondary driving signal outputs a high level.

Further, when both the first primary driving signal and the second primary driving signal are at a low level, the first transistor T1 in the interlock driving circuit is turned off, the second transistor T2 is turned off, the first diode D1 is turned off, the second diode D2 is turned off, the third diode D3 is turned on, the fourth diode D4 is turned on, the first secondary driving signal outputs a low level, and the second secondary driving signal outputs a low level;

further, when the first primary driving signal and the second primary driving signal are both at a high level, the first transistor T1 in the interlock driving circuit is turned on, the second transistor T2 is turned on, the first diode D1 is turned on, the second diode D2 is turned on, the third diode D3 is turned off, the fourth diode D4 is turned off, the first secondary driving signal outputs a low level, and the second secondary driving signal outputs a low level. This realizes the interlocking of two driving signals, and can prevent the first switching device S1 to the third switching device S3 and the fourth switching device S4 to the seventh switching device S7 from being turned on simultaneously, thereby avoiding the risk of three-phase short circuit.

The aircraft starting generator provided by the invention has the advantages that in the stage of starting the aircraft engine, the motor winding has larger number of turns in series by controlling the power switch device, the starting current can be reduced, and the weight of an aircraft cable is favorably reduced. In the power generation stage, the motor winding has lower series turns by controlling the power switch device, so that the armature reaction reactance can be reduced, the power limit is improved, the surge voltage and the duration time thereof are reduced, the heat loss of a single set of winding is reduced, and the double windings are mutually redundant and have high reliability. In the switching process, the short circuit risk is avoided through an interlocking drive control method, the current-limiting winding is omitted, the total number of the controllable power switch devices is reduced to 7, and the reliability is high.

Based on the foregoing disclosure, an embodiment of a dc start power generation system based on a permanent magnet synchronous motor is further provided, as shown in fig. 1, a stator winding circuit is connected to a dc bus bar through a contactor QF1 via an inverter, and a controller controls the first to seventh switching devices according to the foregoing control method.

In the stage of starting the aircraft engine, the controller sends out a high-level driving signal to enable the switching devices S1, S2 and S3 to be conducted, and sends out a low-level driving signal to enable the switching devices S4, S5, S6 and S7 to be turned off, and the windings W1 and W2 are connected in series, W3 and W4 are connected in series, and W5 and W6 are connected in series. The controller closes QF1 and the inverter takes power from the dc bus and inverts into three phase ac power to power the stator three phase windings of the motor.

In the power generation phase, the controller sends out a low-level driving signal to enable the switching devices S1, S2 and S3 to be turned off, sends out a high-level driving signal to enable the switching devices S4, S5, S6 and S7 to be turned on, and connects the windings W1 in parallel with the windings W2, the windings W3 in parallel with the windings W4 and the windings W5 in parallel with the windings W6. The controller controls the inverter to work in a rectification mode, converts three-phase alternating current generated by the motor into direct current and feeds the direct current to the direct current bus bar through the closed QF 1.

Based on the above disclosure, an embodiment of an ac starting power generation system based on a three-stage synchronous motor is further provided, as shown in fig. 7, the stator winding of the main motor is connected to both an inverter and an ac bus bar through a contactor QF 2. The inverter is connected to a dc bus bar via a contactor QF 1. The controller controls the first to seventh switching devices according to the aforementioned control method.

In the stage of starting the aircraft engine, the controller sends out a high-level driving signal to enable the switching devices S1, S2 and S3 to be conducted, and sends out a low-level driving signal to enable the switching devices S4, S5, S6 and S7 to be turned off, and the windings W1 and W2 are connected in series, W3 and W4 are connected in series, and W5 and W6 are connected in series. The controller closes QF1 and opens QF2 and QF3, and then controls the inverter to take power from the dc bus bar, convert to three-phase ac power, and drive the motor.

In the power generation phase, the controller sends out a low-level driving signal to enable the switching devices S1, S2 and S3 to be turned off, sends out a high-level driving signal to enable the switching devices S4, S5, S6 and S7 to be turned on, and connects the windings W1 in parallel with the windings W2, the windings W3 in parallel with the windings W4 and the windings W5 in parallel with the windings W6. The controller opens QF1 and closes QF2 and QF3, the motor emits three-phase alternating current and feeds the alternating current bus bar.

As shown in fig. 8, an embodiment of the present invention provides a method of controlling an aircraft starter generator, the method comprising:

and S10, the controller receives a control signal of the motor running state, wherein the motor running state comprises a motor starting state and a motor generating state.

As shown in fig. 5, the control signal of the motor operation state is composed of a first primary driving signal and a second primary driving signal; the controller includes an interlock drive circuit having one end for receiving the first primary drive signal and the second primary drive signal.

And S20, converting the control signal of the motor running state into a first secondary driving signal and a second secondary driving signal.

The interlock driving circuit determines a first secondary driving signal and a second secondary driving signal according to the received first primary driving signal and the second primary driving signal.

Specifically, as shown in fig. 6, if the controller receives a control signal of a motor start state, the controller controls the first primary driving signal to be at a high level 3V, and the second primary driving signal to be at a low level 0: a first transistor T1 in the interlock driving circuit is turned on, a second transistor T2 is turned off, a first diode D1 is turned on, a second diode D2 is turned off, a third diode D3 is turned on, a fourth diode D4 is turned on, a first secondary driving signal outputs a high level, and a second secondary driving signal outputs a low level;

if the controller receives a control signal of the power generation state of the motor, the first primary driving signal is controlled to be at a low level of 0, and the second primary driving signal is controlled to be at a high level of 3V; in the interlock driving circuit, the first transistor T1 is turned off, the second transistor T2 is turned on, the first diode D1 is turned off, the second diode D2 is turned on, the third diode D3 is turned on, the fourth diode D4 is turned on, the first secondary driving signal outputs a low level, and the second secondary driving signal outputs a high level.

Further, when both the first primary driving signal and the second primary driving signal are at a low level, the first transistor T1 in the interlock driving circuit is turned off, the second transistor T2 is turned off, the first diode D1 is turned off, the second diode D2 is turned off, the third diode D3 is turned on, the fourth diode D4 is turned on, the first secondary driving signal outputs a low level, and the second secondary driving signal outputs a low level;

further, when the first primary driving signal and the second primary driving signal are both at a high level, the first transistor T1 in the interlock driving circuit is turned on, the second transistor T2 is turned on, the first diode D1 is turned on, the second diode D2 is turned on, the third diode D3 is turned off, the fourth diode D4 is turned off, the first secondary driving signal outputs a low level, and the second secondary driving signal outputs a low level. This realizes the interlocking of two driving signals, and can prevent the first switching device S1 to the third switching device S3 and the fourth switching device S4 to the seventh switching device S7 from being turned on simultaneously, thereby avoiding the risk of three-phase short circuit.

And S30, controlling the opening and closing states of the first switching device, the second switching device and the third switching device in the stator winding circuit through the first secondary driving signal.

If the first secondary driving signal is at a high level, the first switching device S1, the second switching device S2, and the third switching device S3 are turned on; if the first secondary driving signal is at a low level, the first switching device S1, the second switching device S2, and the third switching device S3 are turned off.

And S40, controlling the opening and closing states of a fourth switching element, a fifth switching element, a sixth switching element and a seventh switching element in the stator winding circuit through the second secondary driving signal.

If the second secondary driving signal is at a high level, the fourth switching device S4, the fifth switching device S5, the sixth switching device S6, and the seventh switching device S7 are turned on, and if the second secondary driving signal is at a low level, the fourth switching device S4, the fifth switching device S5, the sixth switching device S6, and the seventh switching device S7 are turned off.

And S50, realizing series connection or parallel connection of a plurality of windings in the stator winding circuit according to the opening and closing states of a plurality of switching devices in the stator winding circuit.

As shown in fig. 3, if the controller receives a control signal of a motor start state, the first secondary driving signal outputs a high level, and the second secondary driving signal outputs a low level; controlling a first switching device, a second switching device and a third switching device in the stator winding circuit to be conducted, and controlling a fourth switching device, a fifth switching device, a sixth switching device and a seventh switching device to be disconnected, so that the first winding is connected with the second winding in series, the third winding is connected with the fourth winding in series, and the fifth winding is connected with the sixth winding in series;

as shown in fig. 4, if the controller receives a control signal of a motor power generation state, the controller controls the first primary driving signal to be at a low level, and the second primary driving signal to be at a high level; and controlling the first switching device, the second switching device and the third switching device in the stator winding circuit to be switched off, and controlling the fourth switching device, the fifth switching device, the sixth switching device and the seventh switching device to be switched on, so that the first winding is connected with the second winding in parallel, the third winding is connected with the fourth winding in parallel, and the fifth winding is connected with the sixth winding in parallel.

According to the method for controlling the aircraft starting generator, the switching of the stator winding of the motor in the starting stage and the generating stage is realized through the power switch device, so that the motor has higher series turns in the starting stage and lower series turns in the generating stage, the starting current is favorably reduced, the generating power limit is improved, and the surge voltage and the duration time thereof are reduced. Compared with the prior art, the winding is directly connected in parallel at the motor end, the winding space phase difference is not required to be set, the application range is expanded, and the winding is generally used for a direct-current starting power generation system and a variable-frequency alternating-current starting power generation system; the interlocking drive control method is adopted, the current-limiting winding of the existing scheme is cancelled, and the weight of the motor can be greatly reduced; only 7 power switch devices need to be controlled, and compared with 8 power switch devices in the existing scheme, the reliability is higher.

It should be understood that, the sequence numbers of the steps in the foregoing embodiments do not imply an execution sequence, and the execution sequence of each process should be determined by its function and inherent logic, and should not constitute any limitation to the implementation process of the embodiments of the present invention.

In one embodiment, a computer device is provided, which may be a server, and its internal structure diagram may be as shown in fig. 9. The computer apparatus includes a processor, a memory, a network interface, and a database connected by a device bus. Wherein the processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device comprises a nonvolatile storage medium and an internal memory. The nonvolatile storage medium stores an operating device, a computer program, and a database. The internal memory provides an environment for the operation device in the nonvolatile storage medium and the execution of the computer program. The network interface of the computer device is used for communicating with an external terminal through a network connection. The computer program is executed by a processor to implement a method of controlling an aircraft starter generator.

In one embodiment, a computer device is provided, comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, the processor implementing the following steps when executing the computer program:

the controller receives a control signal of a motor running state, wherein the motor running state comprises a motor starting state and a motor generating state;

converting the control signal of the motor running state into a first secondary driving signal and a second secondary driving signal;

controlling the opening and closing states of a first switching device, a second switching device and a third switching device in the stator winding circuit through the first secondary driving signal;

controlling the opening and closing states of a fourth switching device, a fifth switching device, a sixth switching device and a seventh switching device in the stator winding circuit through the second secondary driving signal;

and realizing the series connection or the parallel connection of a plurality of windings in the stator winding circuit according to the opening and closing states of a plurality of switching devices in the stator winding circuit.

In one embodiment, a computer-readable storage medium is provided, having a computer program stored thereon, which when executed by a processor, performs the steps of:

the controller receives a control signal of a motor running state, wherein the motor running state comprises a motor starting state and a motor generating state;

converting the control signal of the motor running state into a first secondary driving signal and a second secondary driving signal;

controlling the opening and closing states of a first switching device, a second switching device and a third switching device in the stator winding circuit through the first secondary driving signal;

controlling the opening and closing states of a fourth switching device, a fifth switching device, a sixth switching device and a seventh switching device in the stator winding circuit through the second secondary driving signal;

and realizing the series connection or the parallel connection of a plurality of windings in the stator winding circuit according to the opening and closing states of a plurality of switching devices in the stator winding circuit.

It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by hardware instructions of a computer program, which can be stored in a non-volatile computer-readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in the embodiments provided herein may include non-volatile and/or volatile memory, among others. Non-volatile memory can include read-only memory (ROM), Programmable ROM (PROM), Electrically Programmable ROM (EPROM), Electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms such as Static RAM (SRAM), Dynamic RAM (DRAM), Synchronous DRAM (SDRAM), Double Data Rate SDRAM (DDRSDRAM), Enhanced SDRAM (ESDRAM), Synchronous Link DRAM (SLDRAM), Rambus Direct RAM (RDRAM), direct bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

It will be apparent to those skilled in the art that, for convenience and brevity of description, only the above-mentioned division of the functional units and modules is illustrated, and in practical applications, the above-mentioned function distribution may be performed by different functional units and modules according to needs, that is, the internal structure of the apparatus is divided into different functional units or modules to perform all or part of the above-mentioned functions.

The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present invention, and are intended to be included within the scope of the present invention.