Distributed autonomous large signal stability control method suitable for more-electric aircraft power supply system

Abstract

The invention relates to a distributed autonomous large signal stability control method suitable for a more-electric aircraft power supply system, and belongs to the field of power electronic DC-DC converter control. Using the sampled current and voltage values to design a required state-space equation of the Boost converter; designing a nonlinear expansion disturbance observer based on the state-space equation, and designing an improved droop controller considering the nonlinearity of the constant-power load by using an output value of the nonlinear expansion disturbance observer; designing a sliding mode surface of integral sliding mode control based on a sliding mode control theory, and designing a control law based on the sliding mode surface; the control law is inversely transformed to obtain the value of the duty ratio of the actual control quantity converter, the value is used as input, a switching signal is adjusted through a PWM modulator to serve as a driving signal of a converter switching tube, and the output voltage of the converter is adjusted through real-time control over the duty ratio. The method is used for achieving direct-current bus voltage stabilization and accurate power distribution when a power supply system is provided with a constant-power load and encounters large signal disturbance.

Description

Technical Field

[0001] The present invention belongs to the field of power electronic DC-DC converter control, and relates to a decentralized autonomous large-signal control method for a power supply system of a multi-electric aircraft to maintain output DC bus voltage stability and precise power distribution under various large-signal disturbances. Background Art

[0002] With the development trend of aviation electrification, the power electronics characteristics of more-electric aircraft power supply systems are becoming more and more obvious. The power electronics-based more-electric aircraft power supply systems are characterized by strong nonlinearity, high complexity, multiple uncertainties and strong energy coupling, which not only makes system modeling difficult, but also puts forward new requirements and challenges for the design of high-performance control strategies and the realization of control objectives.

[0003] At present, there have been many studies on the control strategy of the power supply system of more-electric aircraft, but the load is assumed to be a pure resistive load by default. However, in the application scenario of more-electric aircraft, a large number of constant power loads (such as electric actuators, motor drivers, etc.) will be connected to the DC bus of the power supply system. These strictly regulated constant power loads have negative impedance and nonlinear characteristics. Among them, negative impedance will reduce the output damping of the aircraft power supply system, causing instability of the control system; and nonlinearity will cause a nonlinear relationship between the input and output of the converter, causing the most common linear PI controller in actual engineering to fail. At the same time, the coordination of multiple power sources in the existing more-electric aircraft power supply system generally adopts traditional voltage-current droop control or voltage-power droop control, and does not consider the impact of constant power load nonlinearity on the power distribution accuracy between multiple power sources under traditional droop control.

[0004] Through the above analysis, the problems and defects of the existing technology are as follows: the existing control strategies rarely consider the situation where the load of the power supply system of the more-electric aircraft is a constant power load, and there is little research on the stability under large signal disturbances such as load switching, converter input voltage jump, converter plug-and-play, converter parameter perturbation, etc. Summary of the invention

[0005] The technical problems to be solved by the present invention are:

[0006] In order to avoid the shortcomings of the prior art, the present invention provides a distributed autonomous nonlinear control method for a power supply system of a more-electric aircraft, which is used to solve the problem of achieving DC bus voltage stability and precise power distribution when the power supply system encounters large signal disturbances such as load switching, converter input voltage jump, converter plug-and-play, converter parameter perturbation, etc. when carrying a constant power load.

[0007] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0008] A decentralized autonomous large signal stabilization control method applicable to a power supply system of a multi-electric aircraft, characterized by comprising:

[0009] S1: Obtain the current and voltage values ​​of the Boost converter, and establish the original state space equation of the Boost converter with the known circuit element parameters, and convert the original state space equation into the state variable form required for the nonlinear extended-order disturbance observer and sliding mode control design;

[0010] S2: Design a nonlinear extended-order disturbance observer based on the transformed state-space equations;

[0011] S3: Based on the estimated value of the output of the nonlinear extended-order disturbance observer, an improved droop controller is designed that takes into account the nonlinearity of the constant power load;

[0012] S4: Calculate the estimated reference value of the state variable based on the estimated value of the output of the nonlinear extended-order disturbance observer and the reference voltage output by the improved droop controller;

[0013] S5: According to the sliding mode control theory, the sliding surface of the integral sliding mode control is designed based on the state space equation after form transformation, and the control law is designed based on the sliding surface and the estimated reference value of the state variable;

[0014] S6: Perform inverse transformation on the control law to obtain the actual control quantity of the Boost converter, and use the actual control quantity as the input of the PWM modulator. The switching signal regulated by the PWM modulator is used as the driving signal of the converter switch tube, and the output voltage of the converter is adjusted by real-time control of the duty cycle.

[0015] A further technical solution of the present invention is: the original state space equation is converted into the form required for the disturbance observer design and the sliding mode controller design, specifically:

[0016]

[0017] in, x i2 =E i i Li is the state variable, the disturbance variable

[0018] is the control rate, L i0 , C i0 are the rated inductance and capacitance of the i-th Boost converter, L i and C i are the actual inductance and capacitance of the i-th Boost converter, ΔL i and ΔC iare the perturbations of the inductance and capacitance of the i-th Boost converter, d i is the duty cycle, v i0 is the output voltage of the i-th Boost converter, i Li is the inductor current, E i is the input voltage.

[0019] A further technical solution of the present invention: the nonlinear extended-order disturbance observer is specifically:

[0020]

[0021] in, and is the disturbance d i1 and d i2 The estimated value of and It is a disturbance and The estimated value of K i11 ,K i12 ,K i21 ,K i22 is the observer gain, β i11 ,β i12 ,β i21 ,β i22 is the internal state of the observer.

[0022] A further technical solution of the present invention: the improved droop controller is specifically:

[0023]

[0024] The power distribution relationship of each converter in the power supply system of a multi-electric aircraft is:

[0025]

[0026] A further technical solution of the present invention is as follows: the sliding surface is specifically:

[0027]

[0028] in, is the state variable error, is the state variable x i1 Estimated reference value The derivative with respect to time, a i is an adjustable control parameter.

[0029] A further technical solution of the present invention: the control law is specifically:

[0030]

[0031] in, is the disturbance variable d i1 The observed output value, s i is the sliding mode function, K is1 , K is2 It is an adjustable parameter.

[0032] A further technical solution of the present invention is as follows: the control law is inversely transformed, specifically:

[0033] The control rate k i Substitute the Boost converter duty cycle d i To control rate k i In the relationship, calculate the duty cycle d i , the duty cycle is passed through the PWM modulator to generate a driving signal as the control signal of the switch tube;

[0034] The Boost converter duty cycle d i To control rate k i The relationship is:

[0035]

[0036] A decentralized autonomous large signal stability control system suitable for a power supply system of a multi-electric aircraft, characterized in that it comprises: a current sensor, a voltage sensor, a state variable calculation module, a reference value calculation module, an improved droop control module, a nonlinear extended-order disturbance observer module, a sliding mode controller, a control law inverse transformation module and a PWM modulator module;

[0037] The current sensor is used to obtain the inductor current of the Boost converter;

[0038] The voltage sensor is used to obtain the output capacitor voltage of the Boost converter;

[0039] The state variable calculation module is used to calculate the real-time value of the state variable;

[0040] The nonlinear extended-order disturbance observer module is used to calculate the change in output power of the Boost converter;

[0041] The reference value calculation module is used to calculate the estimated reference value of the state variable in real time according to the output of the nonlinear extended-order disturbance observer module;

[0042] The sliding mode controller is used to design a sliding mode surface of the sliding mode control according to an estimated reference value of the state variable, and to design a control law based on the sliding mode surface;

[0043] The control rate inverse transformation module is used to perform inverse transformation on the control law in the sliding mode controller to calculate the actual control quantity, that is, the value of the duty cycle of the converter;

[0044] The improved droop control module is used to calculate the output reference voltage of the Boost converter;

[0045] The PWM modulation module is used to obtain a driving signal of the Boost converter based on the value of the duty cycle obtained by the control rate inverse conversion module, and adjust the output voltage of the Boost converter by real-time control of the duty cycle.

[0046] An electronic device, comprising:

[0047] processor;

[0048] a memory for storing processor-executable instructions;

[0049] The processor is configured to execute the decentralized autonomous large signal stabilization control method applicable to a multi-electric aircraft power supply system as claimed in the claims above.

[0050] A computer-readable storage medium having instructions stored thereon, characterized in that when the instructions are executed by a processor, the above-mentioned decentralized autonomous large-signal stabilization control method applicable to a power supply system of a multi-electric aircraft is implemented.

[0051] The beneficial effects of the present invention are:

[0052] The present invention provides a decentralized autonomous large-signal stable control method for a power supply system of a multi-electric aircraft. For the case where the load is a constant power load, the decentralized autonomous large-signal stable control framework based on the "improved droop controller + nonlinear extended-order disturbance observer + sliding mode controller" can significantly improve the anti-interference ability and dynamic response performance of the system, and can effectively suppress the adverse effects of large-signal disturbances such as load switching, converter input voltage jump, converter plug-and-play, and converter parameter perturbation on the system. The details are as follows:

[0053] 1. Design a nonlinear extended-order disturbance observer, which calculates the change in the output power of the Boost converter; design a sliding mode controller, which designs a sliding surface of the sliding mode control according to an estimated reference value of the state variable, and designs a control law based on the sliding surface; use the nonlinear extended-order disturbance observer and the sliding mode control in combination to optimize the control effect.

[0054] 2. Design an improved droop controller, wherein the improved droop controller calculates the reference voltage of the Boost converter according to the estimated value of the nonlinear extended-order disturbance observer; and use the improved droop controller to realize decentralized power distribution that does not rely on the output current sensor. BRIEF DESCRIPTION OF THE DRAWINGS

[0055] The drawings are only for the purpose of illustrating specific embodiments and are not to be considered limiting of the present invention. Like reference symbols denote like components throughout the drawings.

[0056] Figure 1 It is a control principle diagram of a decentralized autonomous large-signal stability control method based on an "improved droop controller + nonlinear extended-order disturbance observer + sliding mode controller" for a multi-electric aircraft power supply system with a constant power load provided by an embodiment of the present invention.

[0057] Figure 2 This is a diagram showing the effects of DC bus voltage control and power distribution when the input voltage changes according to the control strategy of the present invention.

[0058] Figure 3 This is a diagram showing the effects of DC bus voltage control and power distribution when the converter is plug-and-play using the control strategy of the present invention.

[0059] Figure 4 It is a comparison chart of the mainstream bus voltage control and power distribution effects of the control strategy of the present invention and the traditional control method under the same load transformation. DETAILED DESCRIPTION

[0060] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0061] For the power supply system of a more-electric aircraft with a constant power load, taking into account the output stability under large signal disturbances, the present invention proposes a decentralized autonomous large signal stability control method and system based on "improved droop controller + nonlinear extended-order disturbance observer + sliding mode controller".

[0062] Example 1

[0063] The decentralized autonomous large signal stabilization control method based on "improved droop controller + nonlinear extended-order disturbance observer + sliding mode controller" for the power supply system of a more-electric aircraft proposed in the present invention takes the most commonly used boost DC-DC converter (Boost converter) in the power supply system of a more-electric aircraft as an example, and the steps are as follows:

[0064] S01, using the current and voltage values ​​obtained by sampling and the known circuit element parameters, establish the state space equation of the Boost converter required for the disturbance observer design and the sliding mode controller design;

[0065] S02, using the state space equation obtained in S01, based on the design method of nonlinear disturbance observer, design a nonlinear extended-order disturbance observer;

[0066] S03, using the output value of the nonlinear expanded disturbance observer, an improved droop controller considering the nonlinearity of the constant power load is designed to achieve decentralized power distribution that does not rely on the output current sensor;

[0067] S04, using the state space equation obtained in S01, based on the sliding mode control theory, design the sliding surface of the integral sliding mode control, design the control law based on the sliding surface, and optimize the control effect by combining the nonlinear extended disturbance observer with the sliding mode control;

[0068] S06, inversely transform the control law to obtain the actual control quantity, that is, the value of the converter duty cycle, which is used as input, and then the switching signal is adjusted by the PWM modulator as the driving signal of the converter switch tube, and the output voltage of the converter is adjusted by real-time control of the duty cycle.

[0069] In a specific embodiment, considering that the circuit parameters of the inductor and capacitor in the Boost converter are affected by the aging of the power electronic components in actual work, which leads to an error between the actual inductance value / capacitance value and the nominal value, the inductance value and the capacitance value of the i-th Boost converter of the multi-electric aircraft power supply system are expressed as:

[0070]

[0071] Among them, L i and C i is the actual inductance and capacitance, L0 and C0 are the rated inductance and capacitance, ΔL i and ΔC i Represents the perturbation of inductance and capacitance values.

[0072] Usually, the reduced-order model of the i-th Boost converter in the power supply system is derived from the full-order model, that is, the original state space equation is expressed as:

[0073]

[0074] Among them, v i0 is the output voltage of the converter, i Li is the inductor current, P i is the output power, E i is the input voltage, d i is the duty cycle.

[0075] In order to facilitate the design of disturbance observer and sliding mode controller, the original state space equation is transformed into the form required for sliding mode control and disturbance observer design by changing the coordinates:

[0076]

[0077] in x i2 =E i i Li is the state variable, the disturbance

[0078] is the control rate. The disturbance is mainly composed of output power, input voltage, output voltage and parameter perturbation.

[0079] In a specific embodiment, in order to eliminate the influence of load power change on the output voltage and realize autonomous decentralized control, disturbance information needs to be obtained. Designing a suitable disturbance observer not only helps to provide a fast dynamic response to external disturbances, but also reduces the number of sensors. Therefore, the design of the nonlinear extended-order disturbance observer of the i-th Boost converter is as follows:

[0080]

[0081] in, and is the disturbance d i1 and d i2 The estimated value of and It is a disturbance and The estimated value of K i11 ,K i12 ,K i21 ,K i22 is the observer gain, β i11 ,β i12 ,β i21 ,β i22 is the internal state of the observer.

[0082] In a specific embodiment, according to the sliding mode control theory, the sliding mode surface is set to:

[0083]

[0084] Among them, a i is an adjustable control parameter, is the state error, is the state quantity x i1 Estimated reference value The derivative with respect to time. Since the state quantity x i1 Stores energy for the converter, so its estimated reference value That is the expected storage energy. State quantity x i2is the converter input power. Considering that the converter input and output power are balanced in steady state, the state variable x i2 Estimated reference value Can be compared with the observed output value Therefore, the estimated reference value of the state variable in the control design is:

[0085]

[0086] For i The derivative is:

[0087]

[0088] According to the sliding mode control theory, in order to make s i Converges to zero, the designed control law k i for:

[0089]

[0090] Among them, K is1 , K is2 It is an adjustable parameter.

[0091] At this time i The derivative of can be expressed as:

[0092]

[0093] When K is1 , K is2 When taking appropriate values, the sliding mode function s i Converges to 0. When s i When it converges to zero, we can get

[0094]

[0095] When satisfied When xi1 The static error of can converge to 0. is the reference value of the output voltage, is the disturbance d i1 The observed output value of is obtained by the disturbance observer designed above. xi1 When it converges to 0, the output voltage of the i-th Boost converter is equal to the reference voltage value, and the output power is equal to the observed value.

[0096] In a specific embodiment, the control law k i Get the actual control quantity duty cycle d i , Boost converter duty cycle d i To control rate k i The relationship is:

[0097]

[0098] The k obtained by the control system i Substituting this into the equation, we can calculate the duty cycle d i , and generates a PWM signal through a modulator as the control signal of the switching tube.

[0099] In a specific embodiment, considering the nonlinearity of the constant power load, the droop controller of the i-th Boost converter can be designed as:

[0100]

[0101] Among them, m i is the droop coefficient, and The maximum and minimum voltage allowed by the DC bus, P i max is the power capacity of the power supply.

[0102] The output voltage and power distribution relationship of each converter in the power supply system is:

[0103]

[0104] Using the nonlinear extended-order disturbance observer, the output power P of the i-th Boost converter is i is equal to the output value of the nonlinear extended-order disturbance observer, that is,

[0105] Therefore, eliminating the output current sensor, the improved droop controller can be designed as:

[0106]

[0107] The power distribution relationship of each converter in the power supply system of the multi-electric aircraft under the improved droop control is:

[0108]

[0109] Example 2

[0110] Corresponding to the decentralized autonomous large-signal stability control method based on "improved droop controller + nonlinear extended-order disturbance observer + sliding mode controller" for a multi-electric aircraft power supply system with a constant power load provided in the above embodiment, a specific embodiment of the present invention also provides a decentralized autonomous large-signal stability control system based on "improved droop controller + nonlinear extended-order disturbance observer + sliding mode controller" for a multi-electric aircraft power supply system. The control system includes: a current sensor, a voltage sensor, a state variable calculation module, a reference value calculation module, a droop control module, a disturbance observer module, a sliding mode controller, a control law inverse transformation module and a PWM modulator module. Combined with Figure 1 Provide detailed explanation.

[0111] The current sensor is used to obtain the inductor current of the Boost converter;

[0112] The voltage sensor is used to obtain the output capacitor voltage of the Boost converter;

[0113] The state variable calculation module calculates the real-time value of the state variable based on the established state space model of the Boost converter;

[0114] The reference value calculation module calculates the reference value of the state variable in real time according to the output of other modules;

[0115] The droop control module is used to calculate the output reference voltage of the Boost converter based on the design method of the improved droop controller;

[0116] The disturbance observer module is based on a state space model and a design method of a nonlinear extended-order disturbance observer, and is used to calculate the output power variation of the Boost converter and the constant power load variation of the power supply system;

[0117] The sliding mode controller designs a sliding mode surface of the sliding mode control based on the linear system model obtained by the state variable calculation module and the sliding mode control theory, and designs a control law based on the sliding mode surface;

[0118] The control rate inverse transformation module is used to transform the control law in the sliding mode control module and calculate the actual control quantity, that is, the value of the converter duty cycle.

[0119] The PWM modulation module obtains the drive signal of the converter through the modulation module based on the duty cycle value obtained by the inverse conversion module, and adjusts the output voltage of the converter through real-time control of the duty cycle.

[0120] The effect of the present invention can be illustrated by the following simulation experiment.

[0121] Simulation conditions

[0122] The present invention is a simulation performed by using MATLAB / Simulink software on a CPU of I10th Gen Intel(R) Core(TM) i7-10710U 1.61GHz, a RAM of 16G, and a WINDOWS10 operating system.

[0123] In MATLAB / Simulink, the decentralized autonomous large signal stabilization control method based on "improved droop controller + nonlinear extended-order disturbance observer + sliding mode controller" proposed in the present invention for a multi-electric aircraft power supply system with a constant power load was simulated and verified to confirm its effectiveness. All simulations were performed under the condition of three Boost converters (converter 1#, converter 2#, converter 3#) running in parallel with a constant power load.

[0124] First, verify that there is a sudden change in the converter input voltage. Figure 2 As shown, a step change is added to the input voltage at t=0.3s (converter 2# from 100V to 80V) and t=0.5s (converter 3# from 50V to 60V), respectively. The proposed controller still stabilizes the DC bus voltage at its reference value, and the output power of each converter remains consistent with the disturbance observer output.

[0125] Then the plug-and-play of the converter was verified. Figure 3 As shown in the figure, at the beginning of the simulation, the three converters jointly supplied power to the 5kW constant power load at a ratio of 3:2:1. At 0.3s, converter 3# was disconnected, and at 0.5s, converter 3# was reconnected. After a small fluctuation, the output voltage quickly tracked the reference voltage, and the output power of each converter in normal working state remained consistent with the output of the disturbance observer.

[0126] Finally, the proposed control method is compared with the traditional voltage-power droop controller + PI controller. Figure 4 The output response of the multi-electric aircraft power supply system controlled by this method and the traditional controller under the same constant power load power change is shown. It can be seen that at 0.3s, when the power of the constant power load increases from 2500W to 5000W, the multi-electric aircraft power supply system controlled by the traditional control loses the DC bus voltage stability and precise power distribution capability, and the controller designed by this method maintains the stable DC bus voltage and precise power distribution of the multi-electric aircraft power supply system. And compared with the traditional control, when using the controller of the present invention, the system output has a faster dynamic response speed.

[0127] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be included in the protection scope of the present invention.

Claims

1. A decentralized autonomous large signal stabilization control method for a power supply system of a multi-electric aircraft, characterized in that: include: S1: Obtain the current and voltage values ​​of the Boost converter, and establish the original state space equation of the Boost converter with the known circuit element parameters, and convert the original state space equation into the state variable form required for the nonlinear extended-order disturbance observer and sliding mode control design; S2: Design a nonlinear extended-order disturbance observer based on the transformed state-space equations; S3: Based on the estimated value of the output of the nonlinear extended-order disturbance observer, an improved droop controller is designed that takes into account the nonlinearity of the constant power load; S4: Calculate the estimated reference value of the state variable based on the estimated value of the output of the nonlinear extended-order disturbance observer and the reference voltage output by the improved droop controller; S5: According to the sliding mode control theory, the sliding surface of the integral sliding mode control is designed based on the state space equation after form transformation, and the control law is designed based on the sliding surface and the estimated reference value of the state variable; S6: Perform inverse transformation on the control law to obtain the actual control quantity of the Boost converter, and use the actual control quantity as the input of the PWM modulator. The switching signal regulated by the PWM modulator is used as the driving signal of the converter switch tube, and the output voltage of the converter is adjusted by real-time control of the duty cycle.

2. According to claim 1, a decentralized autonomous large signal stabilization control method applicable to a power supply system of a multi-electric aircraft is characterized in that: The original state space equation is converted into the form required for disturbance observer design and sliding mode controller design, specifically: in, x i2 =E i i Li is the state variable, the disturbance variable is the control rate, L i0 , C i0 are the rated inductance and capacitance of the i-th Boost converter, L i and C i are the actual inductance and capacitance of the i-th Boost converter, ΔL i and ΔC i are the perturbations of the inductance and capacitance of the i-th Boost converter, d i is the duty cycle, v i0 is the output voltage of the i-th Boost converter, i Li is the inductor current, E i is the input voltage.

3. According to claim 2, a decentralized autonomous large signal stabilization control method applicable to a power supply system of a multi-electric aircraft is characterized in that: The nonlinear extended-order disturbance observer is specifically: in, and is the disturbance d i1 and d i2 The estimated value of and It is a disturbance and The estimated value of K i11 ,K i12 ,K i21 ,K i22 is the observer gain, β i11 ,β i12 ,β i21 ,β i22 is the internal state of the observer.

4. According to claim 3, a decentralized autonomous large signal stabilization control method applicable to a power supply system of a multi-electric aircraft is characterized in that: The improved droop controller is specifically: The power distribution relationship of each converter in the power supply system of a multi-electric aircraft is:

5. According to claim 4, a decentralized autonomous large signal stabilization control method applicable to a power supply system of a multi-electric aircraft is characterized in that: The sliding surface is specifically: in, is the state variable error, is the state variable x i1 Estimated reference value The derivative with respect to time, a i is an adjustable control parameter.

6. A decentralized autonomous large signal stabilization control method for a power supply system of a multi-electric aircraft according to claim 5, characterized in that: The control law is specifically: in, is the disturbance variable d i1 The observed output value, s i is the sliding mode function, K is1 , K is2 It is an adjustable parameter.

7. A decentralized autonomous large signal stabilization control method for a power supply system of a multi-electric aircraft according to claim 6, characterized in that: The control law is inversely transformed as follows: The control rate k i Substitute the Boost converter duty cycle d i To control rate k i In the relationship, calculate the duty cycle d i , the duty cycle is passed through the PWM modulator to generate a driving signal as the control signal of the switch tube; The Boost converter duty cycle d i To control rate k i The relationship is:

8. A decentralized autonomous large signal stability control system for a power supply system of a multi-electric aircraft, characterized in that: include: Current sensor, voltage sensor, state variable calculation module, reference value calculation module, improved droop control module, nonlinear extended-order disturbance observer module, sliding mode controller, control law inverse transformation module and PWM modulator module; The current sensor is used to obtain the inductor current of the Boost converter; The voltage sensor is used to obtain the output capacitor voltage of the Boost converter; The state variable calculation module is used to calculate the real-time value of the state variable; The nonlinear extended-order disturbance observer module is used to calculate the change in output power of the Boost converter; The reference value calculation module is used to calculate the estimated reference value of the state variable in real time according to the output of the nonlinear extended-order disturbance observer module; The sliding mode controller is used to design a sliding mode surface of the sliding mode control according to an estimated reference value of the state variable, and to design a control law based on the sliding mode surface; The control rate inverse transformation module is used to perform inverse transformation on the control law in the sliding mode controller to calculate the actual control quantity, that is, the value of the duty cycle of the converter; The improved droop control module is used to calculate the output reference voltage of the Boost converter; The PWM modulation module is used to obtain a driving signal of the Boost converter based on the value of the duty cycle obtained by the control rate inverse conversion module, and adjust the output voltage of the Boost converter by real-time control of the duty cycle.

9. An electronic device, characterized in that: include: processor; a memory for storing processor-executable instructions; Wherein, the processor is configured to execute the decentralized autonomous large signal stabilization control method applicable to the power supply system of a multi-electric aircraft as described in any one of claims 1 to 7.

10. A computer-readable storage medium having instructions stored thereon, characterized in that: When the instructions are executed by the processor, the decentralized autonomous large signal stabilization control method applicable to the power supply system of a multi-electric aircraft as described in any one of claims 1 to 7 is implemented.

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