Aircraft starter generator, control method, computer equipment and storage medium

Abstract

The present invention discloses an aircraft starter generator, control method, computer equipment, and storage medium, relating to the field of avionics technology. The invention enables the motor to have a higher number of series turns during the starting phase and a lower number of parallel turns during the power generation phase, thereby reducing the starting current and increasing the power generation limit. The main technical solution of the present invention is as follows: a stator winding circuit, a controller, an inverter, a contactor, and a DC busbar; the stator winding circuit is connected to the DC busbar via the inverter and the contactor; one end of the controller is used to receive a control signal indicating the motor's operating status, and the other end is connected to the stator winding circuit. The controller controls multiple switching devices in the stator winding circuit based on the motor's operating status to achieve series or parallel connection of multiple windings in the stator winding circuit. The motor operating status includes a motor starting state and a motor power generation state.

Description

Technical Field

[0001] The present invention relates to the field of avionics technology, and in particular to an aircraft starter generator, a control method, a computer device, and a storage medium. Background Art

[0002] The starter generator is used to start aircraft engines. Once the engines are ignited, they enter a power generation phase, powered by the engines and supplying power to all aircraft loads. A crucial component of modern aircraft power systems, the starter generator typically utilizes a three-stage synchronous motor, though research is also underway on models with permanent magnet synchronous motors.

[0003] During the starting phase, in order to limit the starting current, the motor stator winding is usually required to have a higher number of series turns. During the generating phase, in order to reduce the armature reaction reactance, increase the power limit, and reduce the surge voltage and its duration, the motor is usually required to have a lower number of series turns. Summary of the Invention

[0004] The present invention provides an aircraft starter generator, a control method, a computer device and a storage medium, which enable a motor to have a higher number of series turns during the starting phase and a lower number of parallel turns during the power generation phase, thereby facilitating a reduction in starting current and an increase in the power generation limit.

[0005] An embodiment of the present invention provides an aircraft starting generator, the generator comprising:

[0006] Stator winding circuit, controller, inverter, contactor, DC busbar;

[0007] The stator winding circuit is connected to the DC busbar via the inverter and the contactor;

[0008] One end of the controller is used to receive a control signal of the motor operating status, and the other end is connected to the stator winding circuit, and controls multiple switching devices in the stator winding circuit according to the motor operating status to realize the series or parallel connection of multiple windings in the stator winding circuit. The motor operating status includes the motor starting state and the motor generating state.

[0009] An embodiment of the present invention provides a method for controlling an aircraft starter generator, the method comprising:

[0010] The controller receives a control signal of the motor operation state, wherein the motor operation state includes a motor starting state and a motor power generation state;

[0011] Converting the control signal of the motor operation state into a first secondary drive signal and a second secondary drive signal;

[0012] Controlling the on / off states of the first switching device, the second switching device, and the third switching device in the stator winding circuit by the first secondary drive signal;

[0013] controlling the on / off states of the fourth switching device, the fifth switching device, the sixth switching device, and the seventh switching device in the stator winding circuit by the second secondary drive signal;

[0014] The series connection or parallel connection of multiple windings in the stator winding circuit is achieved according to the opening and closing states of multiple switching devices in the stator winding circuit.

[0015] A computer device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the method for controlling an aircraft starter generator is implemented.

[0016] A computer-readable storage medium stores a computer program, which, when executed by a processor, implements the above-mentioned method for controlling an aircraft starter generator.

[0017] The present invention provides an aircraft starter generator, control method, computer device, and storage medium, comprising: a stator winding circuit, a controller, an inverter, a contactor, and a DC busbar. The stator winding circuit is connected to the DC busbar via the inverter and the contactor. One end of the controller is used to receive a control signal indicating the motor's operating status, and the other end is connected to the stator winding circuit. The controller controls multiple switching devices in the stator winding circuit based on the motor's operating status to achieve series or parallel connection of multiple windings in the stator winding circuit. The motor's operating status includes a motor starting state and a motor generating state. Specifically, the present invention uses switching devices to switch the motor's stator windings between the starting and generating stages, resulting in a higher number of series turns in the starting stage and a lower number of series turns in the generating stage. This helps reduce starting current, increase the generating power limit, and reduce surge voltage and its duration. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0019] Figure 1 is a structural diagram of an aircraft starter generator according to one embodiment of the present invention;

[0020] Figure 21 is a schematic diagram of the winding circuit structure in one embodiment of the present invention;

[0021] Figure 3 1 is a schematic diagram of windings connected in series in a starting state in one embodiment of the present invention;

[0022] Figure 4 This is a schematic diagram of parallel connection of windings in a power generation state in one embodiment of the present invention;

[0023] Figure 5 is a flow chart for determining the operating status of a generator in one embodiment of the present invention;

[0024] Figure 6 is a schematic diagram of an interlocking drive circuit in one embodiment of the present invention;

[0025] Figure 7 1 is a schematic diagram of an embodiment of the present invention taking an AC starter generator as an example;

[0026] Figure 8 is a flow chart of controlling an aircraft starter generator in one embodiment of the present invention;

[0027] Figure 9 FIG. 1 is a schematic diagram of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0028] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0029] like Figure 1 As shown, an embodiment of the present invention provides an aircraft starting generator, the generator comprising:

[0030] Stator winding circuit, controller, inverter, contactor, DC busbar;

[0031] The stator winding circuit is connected to the DC busbar via the inverter and the contactor QF1;

[0032] One end of the controller is used to receive a control signal of the motor operating status, and the other end is connected to the stator winding circuit, and controls multiple switching devices in the stator winding circuit according to the control signal of the motor operating status to realize the series or parallel connection of multiple windings in the stator winding circuit. The motor operating status includes the motor starting state and the motor generating state.

[0033] Specific examples Figure 2As shown, the stator winding circuit consists of six windings, seven switching devices, and one uncontrolled rectifier bridge. The six windings are 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. The seven switching devices are 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.

[0034] like Figure 3 As shown, if the controller receives a control signal indicating the motor is in the starting state, it controls the first switch device S1, the second switch device S2, and the third switch device S3 in the stator winding circuit to be turned on, and the fourth switch device S4, the fifth switch device S5, the sixth switch device S6, and the seventh switch device S7 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;

[0035] like Figure 4 As shown, if the controller receives a control signal of the motor power generation state, it controls the first switch device S1, the second switch device S2, and the third switch device S3 in the stator winding circuit to be disconnected, and the fourth switch device S4, the fifth switch device S5, the sixth switch device S6, and the seventh switch device S7 to be turned on, so 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.

[0036] like Figure 5 As shown, the control signal of the motor operating state is composed of a first primary drive signal and a second primary drive signal; the controller includes an interlocking drive circuit, one end of the interlocking drive circuit is used to receive the first primary drive signal and the second primary drive signal, and the other end outputs a first secondary drive signal and a second secondary drive signal.

[0037] Specifically, the interlock drive circuit determines a first secondary drive signal and a second secondary drive signal according to the received first primary drive signal and the second primary drive signal;

[0038] 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;

[0039] 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. 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.

[0040] Specific examples Figure 6 As shown, if the controller receives a control signal of the motor starting state, it controls the first primary drive signal to be a high level 3V and the second primary drive signal to be a low level 0: the first transistor T1 in the interlock drive circuit is turned on, the second transistor T2 is turned off, the first diode D1 is turned on, the second diode D2 is turned off, the third diode D3 is turned on, the fourth diode D4 is turned on, the first secondary drive signal outputs a high level, and the second secondary drive signal outputs a low level;

[0041] If the controller receives a control signal of the motor power generation state, it controls the first primary drive signal to be a low level 0 and the second primary drive signal to be a high level 3V; the first transistor T1 in the interlock drive circuit 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, and the fourth diode D4 is turned on, the first secondary drive signal outputs a low level, and the second secondary drive signal outputs a high level.

[0042] Furthermore, when the first primary drive signal and the second primary drive signal are both at a low level, the first transistor T1 in the interlock drive 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, and the fourth diode D4 is turned on, the first secondary drive signal outputs a low level, and the second secondary drive signal outputs a low level;

[0043] Furthermore, when both the first and second primary drive signals are high, the first transistor T1 and second transistor T2 in the interlocked drive circuit are turned on, the first diode D1 and second diode D2 are turned on, the third diode D3 and fourth diode D4 are turned off, and the first and second secondary drive signals both output a low level. This interlocking of the two drive signals prevents the first to third switch devices S1 to S3 and the fourth to seventh switch devices S4 to S7 from being turned on simultaneously, thus avoiding the risk of a three-phase short circuit.

[0044] The aircraft starter generator provided by the present invention reduces starting current during the aircraft engine starting phase by controlling the power switching devices to ensure a larger number of series turns in the motor windings, thereby reducing aircraft cable weight. During the power generation phase, controlling the power switching devices to ensure a lower number of series turns in the motor windings reduces armature reaction reactance, improves power limit, reduces surge voltage and its duration, and minimizes heat loss in a single winding. Furthermore, the dual windings provide redundancy, resulting in high reliability. During the switching process, an interlocked drive control method eliminates the risk of short circuits, eliminating the need for a current-limiting winding and reducing the total number of controllable power switching devices to seven, resulting in high reliability.

[0045] Based on the above invention, a DC starting and generating system implementation method based on a permanent magnet synchronous motor is further proposed. Figure 1 As shown, the stator winding circuit is connected to the DC busbar via an inverter and a contactor QF1, and the controller controls the first to seventh switching devices according to the above control method.

[0046] During the engine startup phase, the controller sends a high-level drive signal to turn on switches S1, S2, and S3, and a low-level drive signal to turn off switches S4, S5, S6, and S7. Windings W1 and W2 are connected in series, W3 and W4 in series, and W5 and W6 in series. The controller closes QF1, and the inverter draws power from the DC busbar and converts it into three-phase AC power to power the motor's three-phase stator windings.

[0047] During the power generation phase, the controller issues a low-level drive signal to turn off switches S1, S2, and S3, and a high-level drive signal to turn on switches S4, S5, S6, and S7. Windings W1 and W2 are connected in parallel, W3 and W4 in parallel, and W5 and W6 in parallel. The controller controls the inverter to operate in rectification mode, converting the three-phase AC power generated by the motor into DC power and feeding it to the DC busbar through the closed QF1.

[0048] Based on the above invention, an AC starting and generating system implementation method based on a three-stage synchronous motor is further proposed. Figure 7 As shown, the stator winding of the main motor is connected to an inverter and also to the AC busbar via contactor QF2. The inverter is connected to the DC busbar via contactor QF1. The controller controls the first to seventh switching devices according to the aforementioned control method.

[0049] During the engine startup phase, the controller sends a high-level drive signal to turn on switches S1, S2, and S3, and a low-level drive signal to turn off switches S4, S5, S6, and S7. Windings W1 and W2 are connected in series, W3 and W4 in series, and W5 and W6 in series. The controller closes QF1 and opens QF2 and QF3. It then controls the inverter to draw power from the DC bus, converting it into three-phase AC power to drive the motor.

[0050] During the power generation phase, the controller sends a low-level drive signal to turn off switches S1, S2, and S3, and a high-level drive signal to turn on switches S4, S5, S6, and S7. Windings W1 and W2 are connected in parallel, W3 and W4 in parallel, and W5 and W6 in parallel. The controller opens QF1 and closes QF2 and QF3. The motor generates three-phase AC power and feeds it to the AC busbar.

[0051] like Figure 8 As shown, an embodiment of the present invention provides a method for controlling an aircraft starter generator, the method comprising:

[0052] S10. The controller receives a control signal of the motor operating state, where the motor operating state includes a motor starting state and a motor generating state.

[0053] like Figure 5 As shown, the control signal of the motor operating state is composed of a first primary drive signal and a second primary drive signal; the controller includes an interlocking drive circuit, one end of which is used to receive the first primary drive signal and the second primary drive signal.

[0054] S20 , converting the control signal of the motor operation state into a first secondary drive signal and a second secondary drive signal.

[0055] 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.

[0056] Specific examples Figure 6 As shown, if the controller receives a control signal of the motor starting state, it controls the first primary drive signal to be a high level 3V and the second primary drive signal to be a low level 0: the first transistor T1 in the interlock drive circuit is turned on, the second transistor T2 is turned off, the first diode D1 is turned on, the second diode D2 is turned off, the third diode D3 is turned on, the fourth diode D4 is turned on, the first secondary drive signal outputs a high level, and the second secondary drive signal outputs a low level;

[0057] If the controller receives a control signal of the motor power generation state, it controls the first primary drive signal to be a low level 0 and the second primary drive signal to be a high level 3V; the first transistor T1 in the interlock drive circuit 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, and the fourth diode D4 is turned on, the first secondary drive signal outputs a low level, and the second secondary drive signal outputs a high level.

[0058] Furthermore, when the first primary drive signal and the second primary drive signal are both at a low level, the first transistor T1 in the interlock drive 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, and the fourth diode D4 is turned on, the first secondary drive signal outputs a low level, and the second secondary drive signal outputs a low level;

[0059] Furthermore, when both the first and second primary drive signals are high, the first transistor T1 and second transistor T2 in the interlocked drive circuit are turned on, the first diode D1 and second diode D2 are turned on, the third diode D3 and fourth diode D4 are turned off, and the first and second secondary drive signals both output a low level. This interlocking of the two drive signals prevents the first to third switch devices S1 to S3 and the fourth to seventh switch devices S4 to S7 from being turned on simultaneously, thus avoiding the risk of a three-phase short circuit.

[0060] S30. Control the on / off states of the first switching device, the second switching device, and the third switching device in the stator winding circuit by using the first secondary drive signal.

[0061] If the first secondary drive signal is high, the first switch device S1, the second switch device S2, and the third switch device S3 are turned on; if the first secondary drive signal is low, the first switch device S1, the second switch device S2, and the third switch device S3 are turned off.

[0062] S40 . Controlling the on / off states of the fourth switching device, the fifth switching device, the sixth switching device, and the seventh switching device in the stator winding circuit by using the second secondary drive signal.

[0063] If the second secondary drive signal is at a high level, the fourth switch device S4, the fifth switch device S5, the sixth switch device S6, and the seventh switch device S7 are turned on; if the second secondary drive signal is at a low level, the fourth switch device S4, the fifth switch device S5, the sixth switch device S6, and the seventh switch device S7 are turned off.

[0064] S50: Implement series connection or parallel connection of multiple windings in the stator winding circuit according to the opening and closing states of multiple switching devices in the stator winding circuit.

[0065] like Figure 3 As shown, if the controller receives a control signal indicating a motor start state, the first secondary drive signal outputs a high level and the second secondary drive signal outputs a low level; the first switching device, the second switching device, and the third switching device in the stator winding circuit are controlled to be turned on, and the fourth switching device, the fifth switching device, the sixth switching device, and the seventh switching device are controlled to be turned off, so that the first winding is connected in series with the second winding, the third winding is connected in series with the fourth winding, and the fifth winding is connected in series with the sixth winding;

[0066] like Figure 4 As shown, if the controller receives a control signal of the motor power generation state, the first primary drive signal is controlled to be low level and the second primary drive signal is controlled to be high level; the first switch device, the second switch device, and the third switch device in the stator winding circuit are controlled to be disconnected, and the fourth switch device, the fifth switch device, the sixth switch device, and the seventh switch device are controlled to be turned on, so that the first winding is connected in parallel with the second winding, the third winding is connected in parallel with the fourth winding, and the fifth winding is connected in parallel with the sixth winding.

[0067] The method for controlling an aircraft starter generator provided by an embodiment of the present invention uses power switching devices to switch the motor's stator windings between the starting and generating phases. This results in a higher number of series turns during the starting phase and a lower number of series turns during the generating phase, which helps reduce starting current, improve the generating power limit, and reduce surge voltage and its duration. Compared to existing solutions, the present invention directly connects the windings in parallel at the motor end, eliminating the need for a spatial phase difference between the windings. This expands the scope of application and is applicable to both DC starting and generating systems and variable-frequency AC starting and generating systems. The interlocked drive control method eliminates the current-limiting winding required in existing solutions, significantly reducing motor weight. Only seven power switching devices need to be controlled, improving reliability compared to the eight power switching devices required in existing solutions.

[0068] It should be understood that the size of the serial numbers of the steps in the above embodiments does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present invention.

[0069] In one embodiment, a computer device is provided. The computer device may be a server, and its internal structure diagram may be as follows: Figure 9As shown. The computer device includes a processor, memory, a network interface, and a database connected via a device bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating device, a computer program, and a database. The internal memory provides an environment for the operation of the operating device and computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal via a network connection. When executed by the processor, the computer program implements a method for controlling an aircraft starter generator.

[0070] In one embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the following steps are performed:

[0071] The controller receives a control signal of the motor operation state, wherein the motor operation state includes a motor starting state and a motor power generation state;

[0072] Converting the control signal of the motor operation state into a first secondary drive signal and a second secondary drive signal;

[0073] Controlling the on / off states of the first switching device, the second switching device, and the third switching device in the stator winding circuit by the first secondary drive signal;

[0074] controlling the on / off states of the fourth switching device, the fifth switching device, the sixth switching device, and the seventh switching device in the stator winding circuit by the second secondary drive signal;

[0075] The series connection or parallel connection of multiple windings in the stator winding circuit is achieved according to the opening and closing states of multiple switching devices in the stator winding circuit.

[0076] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the following steps are implemented:

[0077] The controller receives a control signal of the motor operation state, wherein the motor operation state includes a motor starting state and a motor power generation state;

[0078] Converting the control signal of the motor operation state into a first secondary drive signal and a second secondary drive signal;

[0079] Controlling the on / off states of the first switching device, the second switching device, and the third switching device in the stator winding circuit by the first secondary drive signal;

[0080] controlling the on / off states of the fourth switching device, the fifth switching device, the sixth switching device, and the seventh switching device in the stator winding circuit by the second secondary drive signal;

[0081] The series connection or parallel connection of multiple windings in the stator winding circuit is achieved according to the opening and closing states of multiple switching devices in the stator winding circuit.

[0082] Those skilled in the art will appreciate that all or part of the processes in the above-mentioned embodiments can be implemented by instructing the relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. 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 various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0083] Those skilled in the art will clearly understand that for the sake of convenience and brevity of description, only the division of the above-mentioned functional units and modules is used as an example. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above.

[0084] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention, and should all be included in the scope of protection of the present invention.

Claims

1. An aircraft starter generator, characterized in that: The generator comprises: Stator winding circuit, controller, inverter, contactor, DC busbar; The stator winding circuit is connected to the DC busbar via the inverter and the contactor; One end of the controller is used to receive a control signal of the motor operating state, and the other end is connected to the stator winding circuit, and controls multiple switching devices in the stator winding circuit according to the motor operating state to achieve series or parallel connection of multiple windings in the stator winding circuit. The motor operating state includes the motor starting state and the motor generating state; The control signal of the motor running state is composed of a first primary drive signal and a second primary drive signal; the controller includes an interlock drive circuit, one end of which is used to receive the first primary drive signal and the second primary drive signal; The interlock drive circuit determines a first secondary drive signal and a second secondary drive signal according to the received first primary drive signal and the second primary drive signal; and controls a plurality of switching devices in the stator winding circuit by using the first secondary drive signal and the second secondary drive signal; The interlock drive circuit includes a first transistor, a second transistor, a first diode, a second diode, a third diode, and a fourth diode; the base of the first transistor receives a first primary drive signal, the collector of the first transistor is connected to a three-volt power supply and the cathode of the first diode, the anode of the first diode is connected to a twelve-volt power supply and the anode of the third diode and outputs a second secondary drive signal, the cathode of the third diode is connected to the base of the second transistor, the base of the second transistor receives the second primary drive signal, the collector of the second transistor is connected to the three-volt power supply and the cathode of the second diode; the anode of the second diode is connected to the twelve-volt power supply and the anode of the fourth diode and outputs the first secondary drive signal, and the cathode of the fourth diode is connected to the base of the first transistor.

2. The aircraft starter generator according to claim 1, characterized in that: The stator winding circuit is composed of 6 windings, 7 switching devices and 1 uncontrolled rectifier bridge; One end of the first winding, the third winding, and the fifth winding are respectively connected to the three-phase output end of the inverter, and the other ends of the first winding, the third winding, and the fifth winding are respectively connected to one end of the first switching device, the second switching device, and the third switching device; the other ends of the first switching device, the second switching device, and the third switching device are respectively connected to one end of the second winding, the fourth winding, and the sixth winding; the other ends of the second winding, the fourth winding, and the sixth winding are connected together; the three-phase input end of the uncontrolled rectifier bridge is respectively connected to the other ends of the first winding, the third winding, and the fifth winding; the output end of the uncontrolled rectifier bridge is connected in parallel with the fourth switching device, one end of the fifth switching device, the sixth switching device, and the seventh switching device are respectively connected to one end of the first winding, the third winding, and the fifth winding, and the other ends of the fifth switching device, the sixth switching device, and the seventh switching device are respectively connected to the other ends of the first switching device, the second switching device, and the third switching device; If the controller receives a control signal indicating a motor starting state, the controller controls the first switch device, the second switch device, and the third switch device in the stator winding circuit to be turned on, and the fourth switch device, the fifth switch device, the sixth switch device, and the seventh switch device to be turned off, so that the first winding is connected in series with the second winding, the third winding is connected in series with the fourth winding, and the fifth winding is connected in series with the sixth winding; If the controller receives a control signal of the motor power generation status, it controls the first switching device, the second switching device, and the third switching device in the stator winding circuit to be disconnected, and the fourth switching device, the fifth switching device, the sixth switching device, and the seventh switching device to be turned on, so that the first winding is connected in parallel with the second winding, the third winding is connected in parallel with the fourth winding, and the fifth winding is connected in parallel with the sixth winding.

3. The aircraft starter generator according to claim 2, characterized in that: 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. The aircraft starter generator according to claim 3, characterized in that: If the controller receives a control signal indicating the motor is in the starting state, the first primary drive signal is controlled to be high level and the second primary drive signal is controlled to be low level: The first transistor in the interlock drive circuit is turned on, the second transistor is turned off, the first diode is turned on, the second diode is turned off, the third diode is turned on, the fourth diode is turned on, the first secondary drive signal outputs a high level, and the second secondary drive signal outputs a low level; If the controller receives a control signal indicating the motor power generation state, the controller controls the first primary drive signal to be low level and the second primary drive signal to be high level; The first transistor in the interlock drive circuit is turned off, the second transistor is turned on, the first diode is turned off, the second diode is turned on, the third diode is turned on, the fourth diode is turned on, the first secondary drive signal outputs a low level, and the second secondary drive signal outputs a high level.

5. The aircraft starter generator according to claim 3, characterized in that: When the first primary drive signal and the second primary drive signal are both at a low level, the first transistor in the interlock drive circuit is turned off, the second transistor is turned off, the first diode is turned off, the second diode is turned off, the third diode is turned on, and the fourth diode is turned on, and the first secondary drive signal outputs a low level, and the second secondary drive signal outputs a low level; When the first primary drive signal and the second primary drive signal are both at a high level, the first transistor in the interlock drive circuit is turned on, the second transistor is turned on, the first diode is turned on, the second diode is turned on, the third diode is turned off, and the fourth diode is turned off, the first secondary drive signal outputs a low level, and the second secondary drive signal outputs a low level.

6. The aircraft starter generator according to any one of claims 1 to 5, characterized in that: The generator further includes an AC bus bar, and the stator winding circuit is connected to the AC bus bar through the contactor.

7. A method for controlling an aircraft starter generator, characterized in that: The method is applied to the aircraft starter generator according to any one of claims 2 to 5, and the method comprises: The controller receives a control signal of the motor operation state, wherein the motor operation state includes a motor starting state and a motor power generation state; Converting the control signal of the motor operation state into a first secondary drive signal and a second secondary drive signal; Controlling the on / off states of the first switching device, the second switching device, and the third switching device in the stator winding circuit by the first secondary drive signal; controlling the on / off states of the fourth switching device, the fifth switching device, the sixth switching device, and the seventh switching device in the stator winding circuit by the second secondary drive signal; The series connection or parallel connection of multiple windings in the stator winding circuit is achieved according to the opening and closing states of multiple switching devices in the stator winding circuit.

8. The method for controlling an aircraft starter generator according to claim 7, characterized in that: If the controller receives a control signal indicating a motor start state, the first secondary drive signal outputs a high level and the second secondary drive signal outputs a low level; Controlling the first, second, and third switching devices in the stator winding circuit to be turned on and the fourth, fifth, sixth, and seventh switching devices to be turned off, so that the first winding is connected in series with the second winding, the third winding is connected in series with the fourth winding, and the fifth winding is connected in series with the sixth winding; If the controller receives a control signal indicating the motor power generation state, the controller controls the first primary drive signal to be low level and the second primary drive signal to be high level; The first, second, and third switching devices in the stator winding circuit are controlled to be disconnected, and the fourth, fifth, sixth, and seventh switching devices are controlled to be turned on, so that the first winding is connected in parallel with the second winding, the third winding is connected in parallel with the fourth winding, and the fifth winding is connected in parallel with the sixth winding.

9. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the method for controlling an aircraft starter generator according to any one of claims 7 to 8 is implemented.

10. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the method for controlling an aircraft starter generator according to any one of claims 7 to 8 is implemented.

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