Light storage type airplane static variable power supply control method

Abstract

The invention relates to the technical field of aircraft ground services, and discloses a light storage type aircraft static variable power supply control method, which comprises the following steps: acquiring first operation data associated with a light storage type aircraft static variable power supply, the first operation data comprises voltage and current of an alternating-current power grid, bus-side current of a photovoltaic module, bus-side current of an energy storage system, voltage of a direct-current bus and voltage and current of a power supply output end; calculating second operation data based on the first operation data, wherein the second operation data comprises alternating current power grid power, photovoltaic module power, energy storage system power and load power of a power supply output end; and based on the second operation data and the battery capacity SOC of the energy storage system, controlling the voltage of the direct current bus, the power of the power grid, the power of the photovoltaic module and the power of the energy storage system, so that the light storage type airplane static variable power supply stably supplies power at the airplane end. According to the invention, the aircraft ground static variable power supply can efficiently and stably utilize photovoltaic energy storage to supply power to the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft ground services, and particularly to a control method for a photovoltaic energy storage type aircraft static inverter power supply. Background Art

[0002] Traditional aircraft ground power supplies usually rely on fuel generators or external power grids for power supply, which have problems such as high energy consumption, large environmental pollution, and high operating costs. With the development of new energy technologies, photovoltaic energy storage systems have gradually been applied to the aviation field. However, in the existing technologies, there is a lack of an efficient control scheme for aircraft static inverter power supplies, and it is impossible to make full use of the advantages of photovoltaic energy storage systems, making it difficult to achieve efficient energy utilization and stable operation of the system.

[0003] Patent CN113078733B discloses an aircraft static inverter power supply with integrated energy management, including a power distribution device, a rectification device, an energy storage device, an inversion device, and a controller. The controller communicates with the power distribution device, the rectification device, the energy storage device, and the inversion device respectively to control the operation of each device and perform energy management; the power distribution device is externally connected to the power grid, power generation equipment, and electrical equipment, and is internally connected to the rectification device, and is provided with corresponding switches to control the energy path of the external connection; the rectification device is connected to the energy storage device and the inversion device, and is used to rectify industrial frequency alternating current into direct current and transmit it to the energy storage device and the inversion device; the energy storage device is composed of lithium batteries and is used to store electrical energy; the inversion device is used to invert direct current into alternating current that meets the aircraft auxiliary power supply standard and output it externally to the aircraft. However, this invention mainly relates to the energy scheduling method of energy storage and cannot solve the problems of output voltage stability and efficiency.

[0004] Patent CN110855157B discloses a control method for the DC bus of an aircraft ground static inverter power supply based on active rectification, belonging to the technical field of aircraft ground services. The control method includes: using an ACDC active rectifier as the grid side and inputting the grid voltage, using a 400Hz inverter as the output side and outputting the supply voltage, and transmitting through the DC bus between the ACDC active rectifier and the 400Hz inverter; calculating the first minimum threshold of the DC bus voltage according to the current grid voltage and recording it as Udc_min1; calculating the second minimum threshold of the DC bus voltage according to the current load power and recording it as Udc_min2; calculating the reference value of the DC bus voltage and recording it as Udc_ref; converting the reference value of the DC bus voltage into a driving signal to control the 400Hz inverter, so as to dynamically adjust the DC bus voltage through the grid voltage and the load power, thereby improving the utilization rate of the main circuit of the entire 400Hz inverter. This invention mainly effectively solves the efficiency problem of the grid static inverter power supply through DC bus voltage control, but the output voltage is affected by the grid and it is also impossible to make full use of photovoltaic energy storage.

[0005] The invention patent application CN119496105A discloses an aircraft ground static inverter power supply supporting zero crossing and low crossing, and its control method and working method. The aircraft ground static inverter power supply includes a main circuit, an energy storage system, and an auxiliary power supply part. The main circuit consists of an input main switch, an ACDC rectifier, a DCAC inverter, and an output contactor connected in sequence. The energy storage system consists of an auxiliary switch, an ACDC charging device, and a supercapacitor energy storage device connected in sequence. The grid alternating current supplies power to the supercapacitor energy storage device through the auxiliary switch and the ACDC charging device in sequence, and the supercapacitor energy storage device supports the DC bus through a discharge diode. The auxiliary power supply part includes an isolation transformer and an AC-DC power supply. The grid alternating current is independently input into the AC-DC power supply after passing through the isolation transformer, and the high-voltage DC power of the DC bus is independently input into the AC-DC power supply to output low-voltage DC power. This invention increases the zero crossing time and low crossing time, reduces the volume and weight of the aircraft ground static inverter power supply, but mainly solves the problem that the grid voltage dip affects the output stability of the grid static inverter power supply and cannot make full use of photovoltaic energy storage.

[0006] Therefore, there is an urgent need for a control scheme that can combine a photovoltaic energy storage system and an aircraft static inverter power supply to achieve efficient, stable, and environmentally friendly power supply. Summary of the Invention

[0007] To solve the above problems, the present invention proposes a control method for a photovoltaic energy storage type aircraft static inverter power supply, which is used to efficiently and stably utilize photovoltaic energy storage to supply power to an aircraft for the aircraft ground static inverter power supply. The present invention aims to stabilize the 400Hz voltage output, control the energy supply of photovoltaic, energy storage, and the grid, and can achieve the efficient and stable operation of the aircraft static inverter power supply, reducing energy consumption and environmental pollution.

[0008] The technical solution adopted by the present invention is as follows:

[0009] A control method for a photovoltaic energy storage type aircraft static inverter power supply, comprising:

[0010] Collecting first operation data related to the photovoltaic energy storage type aircraft static inverter power supply, the first operation data including the voltage and current of the AC grid, the bus-side current I of the photovoltaic module v , the bus-side current I of the energy storage system b , the DC bus voltage U dc , and the voltage and current at the power output end;

[0011] Calculating second operation data based on the first operation data, the second operation data including the AC grid power P g , the photovoltaic module power P v , the energy storage system power P b , and the load power P at the power output end L ;

[0012] Control the DC bus voltage U based on the second operating data and the state of charge (SOC) of the energy storage system dc and control the grid power P g as well as the power P of the photovoltaic modules v and the power P of the energy storage system b to ensure stable power supply at the aircraft end for the photovoltaic-storage aircraft static inverter

[0013] Furthermore, the control of the DC bus voltage U dc and the control of the grid power P g as well as the power P of the photovoltaic modules v and the power P of the energy storage system b , based on the second operating data and the state of charge (SOC) of the energy storage system, include

[0014] When the state of charge (SOC) of the energy storage system is less than α, execute the first control strategy; where α is the first threshold

[0015] When executing the first control strategy, charge the battery of the energy storage system; if the power P of the photovoltaic modules v is greater than the load power P L , then control the power to satisfy P g = P b = P n -(P v - P L ); if the power P of the photovoltaic modules v is less than the load power P L , then control the power to satisfy P g = P b +(P L - P v ) ≤ P n ; where P n is the rated power of the photovoltaic-storage aircraft static inverter

[0016] Furthermore, the control of the DC bus voltage U dc and the control of the grid power P g as well as the power P of the photovoltaic modules v and the power P of the energy storage system b , based on the second operating data and the state of charge (SOC) of the energy storage system, include

[0017] When α ≤ SOC ≤ β, execute the second control strategy; where α is the first threshold and β is the second threshold

[0018] When executing the second control strategy, reduce the use of power from the AC grid for power supply; if the power P of the photovoltaic modules v is greater than the load power P L , then control the power to satisfy P g = P v-P L ≤P n , discharge to the AC grid; if the power of the photovoltaic module P v <the load power P L , then control the power to satisfy P b =P L -P v ≤P n , and P g =0, so that the energy storage system discharges; where P n is the rated power of the photovoltaic energy storage aircraft static inverter power supply.

[0019] Further, based on the second operating data and the battery state of charge SOC of the energy storage system, control the DC bus voltage U dc , control the grid power P g , the photovoltaic module power P v and the energy storage system power P b , including:

[0020] When the battery state of charge SOC of the energy storage system > β, execute the third control strategy; where β is the second threshold;

[0021] When executing the third control strategy, stop charging the battery of the energy storage system; if the photovoltaic module power P v > the load power P L , then control the power to satisfy P g =P v -P L ≤P n , discharge to the AC grid; if the photovoltaic module power P v <the load power P L , then control the power to satisfy P b =P L -P v ≤P n , and P g =0, so that the energy storage system discharges; where P n is the rated power of the photovoltaic energy storage aircraft static inverter power supply.

[0022] Further, based on the second operating data and the battery state of charge SOC of the energy storage system, control the DC bus voltage U dc , control the grid power P g , the photovoltaic module power P v and the energy storage system power P b , including:

[0023] Based on the aircraft's need for a stable 400Hz / 115V power supply, adjust the output voltage V of the photovoltaic energy storage aircraft static inverter power supply according to the load power or current when the load changes 0 :

[0024]

[0025] Among them, I L is the load current, R L is the DC internal resistance of the cable, X L is the inductive reactance of the cable, and is the load power factor;

[0026] Calculate the inverter voltage V 1 of the 400Hz converter in the photovoltaic and energy storage aircraft static inverter power supply:

[0027] V 1 = V 0 ×N (2)

[0028] Among them, N is the transformer turns ratio;

[0029] Calculate the inverter current I 1 of the 400Hz converter:

[0030] I 1 = I L ÷N (3)

[0031] Calculate the loss ΔP of the 400Hz converter:

[0032]

[0033] Among them, V CE(sat) , k on , k off are constants related to the characteristics of semiconductor switching devices, U dc is the DC bus voltage, f sw is the switching frequency;

[0034] Calculate the minimum voltage U dc-min of the DC bus:

[0035]

[0036] Among them, K 1 is the line voltage drop coefficient;

[0037] According to formula (4) and formula (5), use the substitution method to calculate the bus voltage U dc when the loss value of the 400Hz converter is the lowest;

[0038] Calculate the relationship between power and DC bus voltage:

[0039]

[0040] Among them, C is the capacitance value of the DC bus, dUdc is the voltage fluctuation value of the DC bus;

[0041] Determine the power supply quality target:

[0042]

[0043] where ε is the voltage fluctuation threshold of the DC bus;

[0044] According to the constraint relationship between formula (6) and formula (7), control the DC bus voltage U dc , control the grid power P g , the photovoltaic module power P v and the energy storage system power P b .

[0045] Furthermore, the photovoltaic and energy storage type aircraft static inverter power supply includes a grid-side converter, a DC bus, a maximum power point tracking system, an energy storage system, a 400Hz converter, a transformer, an output contactor and a control system; one end of the grid-side converter is connected to the AC grid, and the other end is connected to the DC bus and the control system; one end of the maximum power point tracking system is connected to the photovoltaic module, and the other end is connected to the DC bus; the energy storage system is respectively connected to the DC bus and the control system; one end of the 400Hz converter is connected to the DC bus, and the other end is connected to the transformer and the control system; one end of the output contactor is connected to the transformer and the control system, and the other end is connected to the load.

[0046] Furthermore, the grid-side converter is configured to convert the alternating current of the AC grid into direct current, or convert direct current into alternating current.

[0047] Furthermore, the maximum power point tracking system is configured to track the maximum power point of the photovoltaic module battery in real time and transfer the photovoltaic power generation to the DC bus.

[0048] Furthermore, the energy storage system is configured to control the storage and release of electric energy and manage the energy storage medium.

[0049] Furthermore, the 400Hz converter is configured to convert direct current into 400Hz alternating current; the control system is configured to control the stable output of 400Hz alternating current, adjust the power supply and the DC bus voltage.

[0050] The beneficial effects of the present invention are as follows:

[0051] (1) Voltage stability: Keep the 400Hz / 115V power supply stable and avoid the influence of photovoltaic and grid fluctuations on the power supply.

[0052] (2) Energy balance: Dynamically adjust the energy flow according to the photovoltaic power generation, the state of the energy storage battery and the load demand to ensure the power balance of the system.

[0053] (3) Quick response: When the load suddenly changes or there are fluctuations in photovoltaic power generation or the power grid, it can quickly adjust the DC bus voltage to ensure system stability.

[0054] In summary, according to the 400Hz output power and converter losses, the present invention can control the static inverter power supply to output voltage at 400Hz to ensure stable power supply at the aircraft port. The present invention coordinates and controls the power of photovoltaic, energy storage, power grid, and load, and according to the system efficiency and DC bus voltage fluctuation constraints, can achieve multi-level energy management with priority for photovoltaic power generation, energy storage supplementation, and backup power supply guarantee. Description of the Drawings

[0055] Figure 1 It is a flowchart of the control method for the photovoltaic and energy storage type aircraft static inverter power supply in Embodiment 1 of the present invention.

[0056] Figure 2 It is one of the schematic diagrams of the photovoltaic and energy storage type aircraft static inverter power supply in Embodiment 1 of the present invention.

[0057] Figure 3 It is the second schematic diagram of the photovoltaic and energy storage type aircraft static inverter power supply in Embodiment 1 of the present invention Description of the Drawings:

[0059] 1 - grid - side converter, 2 - DC bus, 3 - maximum power point tracking system, 4 - energy storage system, 5 - 400Hz converter, 6 - transformer, 7 - output contactor, 8 - control system, 9 - filter capacitor; 801 - grid - side sampling terminal, 802 - DC - side sampling terminal, 803 - 400Hz - side sampling terminal; A - AC power grid, B - photovoltaic module, C - load (power output terminal). Detailed Embodiments

[0060] In order to have a clearer understanding of the technical features, objectives, and effects of the present invention, the detailed embodiments of the present invention are now described. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention, that is, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts fall within the protection scope of the present invention.

[0061] Embodiment 1

[0062] As Figure 1 shown, this embodiment provides a control method for a photovoltaic and energy storage type aircraft static inverter power supply, including:

[0063] Collect the first operating data associated with the photovoltaic and energy storage type aircraft static inverter power supply, where the first operating data includes the voltage and current of the AC power grid, and the bus - side current I of the photovoltaic module v, the bus - side current I of the energy storage system b , the DC bus voltage U dc and the voltage and current at the power supply output terminal;

[0064] Calculate the second - run data based on the first - run data. The second - run data includes the AC grid power P g , the photovoltaic module power P v , the energy storage system power P b and the load power P at the power supply output terminal L ;

[0065] Control the DC bus voltage U dc , control the grid power P g , the photovoltaic module power P v and the energy storage system power P b based on the second - run data and the state of charge (SOC) of the battery of the energy storage system, so as to make the static inverter power supply for photovoltaic - energy - storage aircraft stable in power supply at the aircraft end.

[0066] As Figure 2 and Figure 3 shown, the static inverter power supply for photovoltaic - energy - storage aircraft in this embodiment includes a grid - side converter, a DC bus, a maximum power point tracking system, an energy storage system, a 400 - Hz converter, a transformer, an output contactor, and a control system. Among them, one end of the grid - side converter is connected to the AC grid, and the other end is connected to the DC bus and the control system; one end of the maximum power point tracking system is connected to the photovoltaic module, and the other end is connected to the DC bus; the energy storage system is connected to the DC bus and the control system respectively; one end of the 400 - Hz converter is connected to the DC bus, and the other end is connected to the transformer and the control system; one end of the output contactor is connected to the transformer and the control system, and the other end is connected to the load.

[0067] Specifically, the corresponding descriptions of the components of the static inverter power supply for photovoltaic - energy - storage aircraft in this embodiment are as follows:

[0068] Grid - side converter: mainly used to convert the alternating current of the AC grid into direct current, or convert direct current into alternating current. Preferably, the grid - side converter can be implemented by a three - phase half - bridge circuit.

[0069] DC bus: mainly used to collect various DC interfaces and has a DC filtering function.

[0070] Maximum power point tracking system (MPPT): mainly used to track the maximum power point of the photovoltaic module battery in real - time and transfer the photovoltaic power generation to the DC bus.

[0071] Energy storage system: mainly used to control the storage and release of electric energy and manage the energy storage medium.

[0072] 400Hz Inverter: mainly used to convert direct current into 400Hz alternating current. Preferably, the 400Hz inverter can be implemented by a three-phase full-bridge circuit.

[0073] Transformer: having functions of filtering, voltage conversion and electrical isolation.

[0074] Output Contactor: the output switch powered by 400Hz electricity.

[0075] Control System: mainly used to control the stable output of 400Hz alternating current, and regulate the power supply and the DC bus voltage.

[0076] Preferably, the control system is connected with a grid-side sampling terminal, a DC-side sampling terminal and a 400Hz-side sampling terminal. Among them, the grid-side sampling terminal is used to collect the voltage and current signals on the AC grid side and transmit them to the control system for control; the DC-side sampling terminal is used to collect the voltage and current signals on the DC bus side and transmit them to the control system for control; the 400Hz-side sampling terminal is used to collect the voltage and current signals on the output side of the 400Hz inverter and the power supply output side and transmit them to the control system for control.

[0077] Preferably, the photovoltaic and energy storage type aircraft static inverter power supply of this embodiment further includes a filter capacitor, and the filter capacitor is arranged between the transformer and the output contactor.

[0078] Preferably, based on the second operating data and the state of charge SOC of the energy storage system, control the DC bus voltage U dc , control the grid power P g , the photovoltaic module power P v and the energy storage system power P b , including:

[0079] When the state of charge SOC of the energy storage system < α, execute the first control strategy to charge the battery of the energy storage system; if the photovoltaic module power P v > the load power P L , then control the power to satisfy P g = P b = P n - (P v - P L ); if the photovoltaic module power P v < the load power P L , then control the power to satisfy P g = P b + (P L - P v ) ≤ P n ; where α is the first threshold, which can be specifically set to 20%; P n is the rated power of the photovoltaic and energy storage type aircraft static inverter power supply.

[0080] When α ≤ SOC ≤ β, the second control strategy is executed to reduce the power supplied from the AC grid. If the power of the photovoltaic module P v > the power of the load P L , then the controlled power satisfies P g = P v - P L ≤ P n , and discharges to the AC grid. If the power of the photovoltaic module P v < the power of the load P L , then the controlled power satisfies P b = P L - P v ≤ P n , and P g = 0, enabling the energy storage system to discharge. Among them, β is the second threshold, which can be specifically set to 90%.

[0081] When the battery power SOC of the energy storage system > β, the third control strategy is executed to stop charging the battery of the energy storage system. If the power of the photovoltaic module P v > the power of the load P L , then the controlled power satisfies P g = P v - P L ≤ P n , and discharges to the AC grid. If the power of the photovoltaic module P v < the power of the load P L , then the controlled power satisfies P b = P L - P v ≤ P n , and P g = 0, enabling the energy storage system to discharge.

[0082] Preferably, based on the second operating data and the battery power SOC of the energy storage system, controlling the DC bus voltage U dc , controlling the grid power P g , the power of the photovoltaic module P v and the power of the energy storage system P b , further includes:

[0083] Since the aircraft requires a stable 400Hz / 115V power supply, but the voltage at the aircraft power supply port will fluctuate when the load changes, the photovoltaic energy storage type aircraft static inverter power supply needs to adjust the output voltage in a timely manner according to the load power (current) to ensure the stability of the power supply voltage at the aircraft port. Therefore, when the load changes, the output voltage V of the photovoltaic energy storage type aircraft static inverter power supply is adjusted according to the load power or current 0 :

[0084]

[0085] Among them, I L is the load current, R L is the DC internal resistance of the cable, X L is the inductive reactance of the cable, and is the load power factor;

[0086] Calculate the inversion voltage V of the 400Hz converter in the static inverter power supply for photo - storage aircraft 1 :

[0087] V 1 = V 0 ×N (2)

[0088] Among them, N is the transformer turns ratio;

[0089] Calculate the inversion current I of the 400Hz converter 1 :

[0090] I 1 = I L ÷N (3)

[0091] Calculate the loss ΔP of the 400Hz converter:

[0092]

[0093] Among them, V CE(sat) , k on , k off are constants related to the characteristics of semiconductor switching devices, U dc is the DC bus voltage, f sw is the switching frequency;

[0094] Calculate the minimum voltage U of the DC bus dc-min :

[0095]

[0096] Among them, K 1 is the line voltage drop coefficient, and the specific value can be taken as 1.05;

[0097] According to formula (4) and formula (5), use the substitution method to calculate the bus voltage U when the loss value of the 400Hz converter is the lowest dc ;

[0098] Calculate the relationship between power and DC bus voltage:

[0099]

[0100] Among them, C is the capacitance value of the DC bus capacitor, dU dc is the voltage fluctuation value of the DC bus;

[0101] Determine the power supply quality target:

[0102]

[0103] Among them, ε is the voltage fluctuation threshold of the DC bus, which can be specifically set to 5%;

[0104] According to the constraint relationship between formula (6) and formula (7), control the DC bus voltage U dc 、control the grid power P g 、the power of the photovoltaic module P v and the power of the energy storage system P b so as to realize the efficient and stable operation of the static inverter power supply for photovoltaic energy storage aircraft.

[0105] To sum up, according to the 400Hz output power and converter loss of the present invention, the static inverter power supply can be controlled to output voltage at 400Hz to ensure stable power supply at the aircraft port. The present invention coordinates the control of the power of photovoltaic, energy storage, grid and load, and according to the system efficiency and DC bus fluctuation constraints, can realize multi-level energy management with priority of photovoltaic power generation, energy storage supplement and backup power supply guarantee.

[0106] Embodiment 2

[0107] On the basis of Embodiment 1, this embodiment:

[0108] This embodiment provides a computer device, including a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, it realizes the control method of the static inverter power supply for photovoltaic energy storage aircraft in Embodiment 1. Among them, the computer program can be in the form of source code, object code, executable file or some intermediate form, etc.

[0109] Embodiment 3

[0110] On the basis of Embodiment 1, this embodiment:

[0111] This embodiment provides a computer-readable storage medium, storing a computer program, and when the computer program is executed by a processor, it realizes the control method of the static inverter power supply for photovoltaic energy storage aircraft in Embodiment 1. Among them, the computer program can be in the form of source code, object code, executable file or some intermediate form, etc. The storage medium includes: any entity or device capable of carrying computer program code, recording medium, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium, etc. It should be noted that the content included in the storage medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, the storage medium does not include electrical carrier signals and telecommunication signals.

[0112] It should be noted that, for the foregoing method embodiments, for the sake of simplicity of description, they are expressed as a series of action combinations. However, those skilled in the art should know that this application is not limited by the described action sequence, because according to this application, certain steps can be performed in other sequences or simultaneously. Secondly, those skilled in the art should also know that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily essential to this application. In addition, terms such as "first", "second", "third", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

Claims

1. A method for controlling a photovoltaic storage aircraft static variable power supply, characterized in that: include: Collect the first operation data associated with the photovoltaic storage aircraft static variable power supply, the first operation data including the voltage and current of the AC power grid, the bus side current I of the photovoltaic module v 、Bus side current I of energy storage system b , DC bus voltage U dc and the voltage and current at the power supply output; The second operating data is calculated based on the first operating data, wherein the second operating data includes the AC grid power P g , Photovoltaic module power P v 、Energy storage system power P b And the load power P at the power output L ; Based on the second operating data and the battery capacity SOC of the energy storage system, the DC bus voltage U is controlled dc , control grid power P g , Photovoltaic module power P v and energy storage system power P b , so that the photovoltaic storage type aircraft static variable power supply can provide stable power supply at the aircraft end.

2. The method for controlling a photovoltaic storage aircraft static variable power supply according to claim 1, characterized in that: The DC bus voltage U is controlled based on the second operating data and the battery power SOC of the energy storage system. dc , control grid power P g , Photovoltaic module power P v and energy storage system power P b ,include: When the battery power SOC of the energy storage system is less than α, the first control strategy is executed; wherein α is the first threshold value; When the first control strategy is executed, the battery of the energy storage system is charged; if the photovoltaic module power P v >Load power P L , then the control power satisfies P g =P b =P n -(P v -P L );If the photovoltaic module power P v <Load power P L , then the control power satisfies P g =P b +(P L -P v )≤P n ; Among them, P n It is the rated power of the photovoltaic storage type aircraft static variable power supply.

3. The control method of the photovoltaic storage aircraft static variable power supply according to claim 1, characterized in that: The DC bus voltage U is controlled based on the second operating data and the battery power SOC of the energy storage system. dc , control grid power P g , Photovoltaic module power P v and energy storage system power P b ,include: When α≤SOC≤β, the second control strategy is executed; wherein α is the first threshold and β is the second threshold; When the second control strategy is executed, the power used in the AC grid is reduced; if the PV panel power P v >Load power P L , then the control power satisfies P g =P v -P L ≤P n , discharge to the AC grid; if the photovoltaic module power P v <Load power P L , then the control power satisfies P b =P L -P v ≤P n , and P g =0, the energy storage system is discharged; where P n It is the rated power of the photovoltaic storage type aircraft static variable power supply.

4. The method for controlling a photovoltaic storage aircraft static variable power supply according to claim 1, characterized in that: The DC bus voltage U is controlled based on the second operating data and the battery power SOC of the energy storage system. dc , control grid power P g , Photovoltaic module power P v and energy storage system power P b ,include: When the battery power SOC of the energy storage system is greater than β, the third control strategy is executed; wherein β is the second threshold value; When the third control strategy is executed, the battery of the energy storage system is stopped from charging; if the photovoltaic module power P v >Load power P L , then the control power satisfies P g =P v -P L ≤P n , discharge to the AC grid; if the photovoltaic module power P v <Load power P L , then the control power satisfies P b =P L -P v ≤P n , and P g =0, the energy storage system is discharged; where P n It is the rated power of the photovoltaic storage type aircraft static variable power supply.

5. The photovoltaic storage aircraft static variable power supply control method according to claim 1, characterized in that: The DC bus voltage U is controlled based on the second operating data and the battery power SOC of the energy storage system. dc , control grid power P g , Photovoltaic module power P v and energy storage system power P b ,include: Based on the aircraft's need for a stable 400Hz / 115V power supply, the output voltage V0 of the photovoltaic aircraft static variable power supply is adjusted according to the load power or current when the load changes: Among them, I L is the load current, R L is the DC internal resistance of the cable, X L is the cable inductive reactance, and is the load power factor; Calculate the inverter voltage V1 of the 400Hz converter in the photovoltaic storage aircraft static power supply: V1=V0×N (2) Where N is the transformer ratio; Calculate the inverter current I1 of the 400Hz converter: I1=I L ÷N (3) Calculate the loss ΔP of the 400Hz converter: Among them, V CE(sat) ,k on ,k off is a constant related to the characteristics of semiconductor switching devices, U dc is the DC bus voltage, f sw is the switching frequency; Calculate the minimum voltage U of the DC bus dc-min : Among them, K1 is the line voltage drop coefficient; According to formula (4) and formula (5), the bus voltage U when the 400Hz converter loss value is the lowest is calculated by substitution method: dc ; Calculate the relationship between power and DC bus voltage: Where C is the capacitance of the DC bus, dU dc is the voltage fluctuation value of the DC bus; Determine power supply quality goals: Among them, ε is the voltage fluctuation threshold of the DC bus; According to the constraints of formula (6) and formula (7), the DC bus voltage U is controlled dc , control grid power P g , Photovoltaic module power P v and energy storage system power P b .

6. The photovoltaic storage aircraft static variable power supply control method according to claim 1, characterized in that: The photovoltaic storage type aircraft static variable power supply includes a grid-side converter, a DC bus, a maximum power point tracking system, an energy storage system, a 400Hz converter, a transformer, an output contactor and a control system; one end of the grid-side converter is connected to the AC power grid, and the other end is connected to the DC bus and the control system; one end of the maximum power point tracking system is connected to the photovoltaic module, and the other end is connected to the DC bus; the energy storage system is respectively connected to the DC bus and the control system; one end of the 400Hz converter is connected to the DC bus, and the other end is connected to the transformer and the control system; one end of the output contactor is connected to the transformer and the control system, and the other end is connected to the load.

7. The method for controlling a photovoltaic storage aircraft static variable power supply according to claim 6, characterized in that: The grid-side converter is configured to convert AC power of the AC power grid into DC power, or convert DC power into AC power.

8. The method for controlling a photovoltaic storage aircraft static variable power supply according to claim 6, characterized in that: The maximum power point tracking system is configured to track the maximum power point of the photovoltaic module battery in real time and transfer the photovoltaic power generation to the DC bus.

9. The method for controlling a photovoltaic storage aircraft static variable power supply according to claim 6, characterized in that: The energy storage system is configured to control the storage and release of electrical energy, and manage energy storage media.

10. The method for controlling a photovoltaic storage aircraft static variable power supply according to claim 6, characterized in that: The 400Hz converter is configured to convert direct current into 400Hz alternating current; the control system is configured to control the stable output of the 400Hz alternating current and adjust the power supply and the direct current bus voltage.

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