Charging and discharging power control device and method for energy storage element of aircraft and product

Abstract

The invention relates to a charging and discharging power control device, method and product of an aircraft energy storage element, and is applied to the technical field of aircraft energy management. The charging and discharging power control device for the energy storage element of the aircraft comprises the energy storage element, a switch element, a high-voltage direct-current bus, an energy storage charging and discharging controller and a bus voltage regulation module, and one end of the switch element is connected with the energy storage element and the other end is connected with the high-voltage DC bus. The energy storage charging and discharging controller is used for determining the working state of the switching element based on the power generation power of the aircraft generator and the power utilization power of the aircraft load, and determining the target bus voltage of the high-voltage direct-current bus under the condition that the switching element is working in the working state; the charge-discharge state of the energy storage element is changed based on the operating state. And the bus voltage regulation module is used for regulating and controlling the voltage value of the high-voltage direct-current bus to the target bus voltage so as to change the charging and discharging power of the energy storage element through the target bus voltage and realize accurate regulation and control of the charging and discharging power of the energy storage element.

Description

Technical Field

[0001] The present application belongs to the field of aircraft energy management technology, and specifically relates to a charge and discharge power control device, method and product for aircraft energy storage elements. Background Art

[0002] In aircraft onboard power supply architectures, energy storage systems or components can provide peak energy for high-power loads and effectively absorb feedback energy from constant-power loads such as electric actuators, achieving peak load shaving and valley filling, thereby improving the robustness, reliability, and efficiency of the onboard power supply system. To ensure the normal operation of energy storage components, precise control of the charge and discharge power of the energy storage or components is particularly important.

[0003] Typically, airborne power supply architectures utilize bidirectional DC-DC converters (DC-DC converters) to control the bidirectional flow of energy and the charging and discharging of stored energy by varying the voltage differential between the energy storage element and the high-voltage DC bus. However, the volume and weight of DC-DC converters are proportional to their power, making them unable to meet the volume and weight requirements of airborne platforms, potentially leading to excessive volume and weight. Eliminating the DC-DC converter also reduces the accuracy of charge and discharge power control. Summary of the Invention

[0004] In view of the above problems, the present disclosure is proposed. The present disclosure provides a charge and discharge power control device, method and product for an aircraft energy storage element, which can accurately control the charge and discharge power of the energy storage element.

[0005] According to one aspect of the present disclosure, there is provided a charge and discharge power control device for an aircraft energy storage element, the device comprising an energy storage element, a switching element, a high-voltage DC bus, an energy storage charge and discharge controller, and a bus voltage regulation module;

[0006] One end of the switch element is connected to the energy storage element, and the other end is connected to the high-voltage DC bus;

[0007] The energy storage charge and discharge controller is configured to determine an operating state of the switching element based on the power generated by the aircraft generator and the power consumed by the aircraft load, and to determine a target bus voltage of the high-voltage DC bus when the operating state is working; and to change the charge and discharge state of the energy storage element based on the operating state;

[0008] The bus voltage regulation module is used to regulate the voltage value of the high-voltage DC bus to the target bus voltage, so as to change the charging and discharging power of the energy storage element according to the target bus voltage.

[0009] Optionally, the energy storage charge and discharge controller is used to:

[0010] The working state of the switching element is determined by comparing the absolute value of the power difference between the generated power and the consumed power with a preset power fluctuation threshold.

[0011] Optionally, the energy storage charge and discharge controller is used to:

[0012] When the power difference is less than zero and the absolute value of the power difference is greater than the preset power fluctuation threshold, the operating state of the switching element is determined to be working, and the switching element is controlled to be closed, wherein the charge and discharge state of the energy storage element is a discharge state, and the current direction is from the energy storage element to the high-voltage DC bus; the target bus voltage is determined by the terminal voltage of the energy storage element, the power difference, the equivalent resistance between the energy storage element and the high-voltage DC bus, and the load equivalent resistance.

[0013] Optionally, the energy storage charge and discharge controller is used to:

[0014] When the power difference is greater than zero and the absolute value of the power difference is greater than the preset power fluctuation threshold, the operating state of the switching element is determined to be working, and the switching element is controlled to be closed, wherein the charge and discharge state of the energy storage element is a charging state, and the current direction is from the high-voltage DC bus to the energy storage element; and the target bus voltage is determined by the terminal voltage of the energy storage element, the power difference, and the equivalent resistance between the energy storage element and the high-voltage DC bus.

[0015] Optionally, the energy storage charge and discharge controller is used to:

[0016] When the absolute value of the power difference is less than or equal to the preset power fluctuation threshold, the working state of the switching element is determined to be non-working, and the switching element is controlled to be disconnected, wherein the charging and discharging state of the energy storage element is a non-working state.

[0017] Optionally, the switching element is a solid-state power controller.

[0018] According to another aspect of the present disclosure, a method for controlling the charge and discharge power of an aircraft energy storage element is provided, comprising:

[0019] Determining an operating state of a switching element based on the power generated by the aircraft generator and the power consumed by the aircraft load, and determining a target bus voltage of a high-voltage direct current bus when the operating state is working; wherein one end of the switching element is connected to the energy storage element, and the other end is connected to the high-voltage direct current bus;

[0020] The voltage value of the high-voltage DC bus is regulated to the target bus voltage, so as to change the charge and discharge power of the energy storage element according to the target bus voltage.

[0021] According to another aspect of the present disclosure, an electronic device is provided, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the above-mentioned method for controlling the charging and discharging power of an aircraft energy storage element.

[0022] According to another aspect of the present disclosure, a computer-readable storage medium is provided, on which a computer program is stored. The program is executed by a processor to implement the above-mentioned method for controlling the charge and discharge power of an aircraft energy storage element.

[0023] According to another aspect of the present disclosure, a computer program product is provided, comprising a computer-readable code, or a non-volatile computer-readable storage medium carrying the computer-readable code. When the computer-readable code runs in a processor of an electronic device, the processor in the electronic device executes the above-mentioned method for controlling the charging and discharging power of an aircraft energy storage element.

[0024] In the present disclosure, the charge and discharge power control device of the aircraft energy storage element includes an energy storage element, a switching element, a high-voltage DC bus, an energy storage charge and discharge controller and a bus voltage regulation module; one end of the switching element is connected to the energy storage element, and the other end is connected to the high-voltage DC bus. The energy storage charge and discharge controller is used to determine the working state of the switching element based on the power generation power of the aircraft generator and the power consumption of the aircraft load, and when the working state is working, determine the target bus voltage of the high-voltage DC bus; and change the charge and discharge state of the energy storage element based on the working state. The bus voltage regulation module is used to regulate the voltage value of the high-voltage DC bus to the target bus voltage, so as to change the charge and discharge power of the energy storage element through the target bus voltage. The requirements of the airborne platform for the volume and weight of the equipment are met, the problem of exceeding the volume and weight limit is avoided, and the power-to-weight ratio is improved. The target bus voltage is used to dynamically adjust the bilateral pressure difference, so that the charge and discharge power of the energy storage element can be accurately adjusted.

[0025] It is to be understood that both the foregoing general description and the following detailed description are exemplary, and are intended to provide further explanation of the technology as claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above and other purposes, features, and advantages of the present disclosure will become more apparent through a more detailed description of the embodiments of the present disclosure in conjunction with the accompanying drawings. The accompanying drawings are intended to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and are not intended to limit the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0027] Figure 1 A schematic structural diagram of a charge and discharge power control device for an aircraft energy storage element provided by the present disclosure.

[0028] Figure 2 Another structural schematic diagram of a charge and discharge power control device for an aircraft energy storage element provided by the present disclosure.

[0029] Figure 3 This is another structural schematic diagram of a charge and discharge power control device for an aircraft energy storage element provided by the present disclosure.

[0030] Figure 4 Another structural schematic diagram of a charge and discharge power control device for an aircraft energy storage element provided by the present disclosure.

[0031] Figure 5 A flow chart of a method for controlling the charge and discharge power of an aircraft energy storage element provided by the present disclosure.

[0032] Figure 6 Another flow chart of a method for controlling the charge and discharge power of an aircraft energy storage element provided by the present disclosure.

[0033] Figure 7 A hardware block diagram of an electronic device provided in the present disclosure.

[0034] Figure 8 A schematic diagram of a computer program product provided by the present disclosure. DETAILED DESCRIPTION

[0035] In order to enable those skilled in the art to more clearly understand the technical solution of the present application, the application scenario of the solution of the present application is first described below.

[0036] As aircraft evolve toward highly information-based, intelligent, and multi-tasking capabilities, high-power radars, directed energy weapons, and other equipment are placing higher instantaneous power demands on onboard power supply systems. Furthermore, constant-power loads such as multiple electric actuators operate in four-quadrants, and the feedback energy they generate impacts the onboard power supply system. Adding energy storage to the existing onboard power supply architecture is a key technical approach to maintaining grid stability. The introduction of energy storage systems or components not only provides peak energy for high-power loads but also effectively absorbs the feedback energy from constant-power loads such as electric actuators, achieving peak-shaving and valley-filling, thereby improving the robustness, reliability, and efficiency of the onboard power supply system. To ensure efficient operation of energy storage or components, precise control of their charge and discharge power is crucial, crucial for ensuring aircraft flight safety and enhancing their sustained combat capability.

[0037] Currently, bidirectional DC-DC converters (DC-DC converters) can be used in airborne power supply architectures to control the bidirectional flow of energy and the charging and discharging of stored energy by varying the voltage differential between the energy storage element and the high-voltage DC bus. However, the volume and weight of a DC-DC converter are proportional to its power. Compared to ground-based platforms such as new energy vehicles, renewable energy, and microgrids, DC-DC converters cannot meet the volume and weight requirements of aircraft-based platforms. Matching a bidirectional DC-DC converter to the maximum discharge power of the energy storage element may result in excessive volume and weight, making it unsuitable for installation on an aircraft platform. Furthermore, eliminating the DC-DC converter reduces the accuracy of charge and discharge power control.

[0038] In order to solve the above-mentioned technical problems, the present disclosure provides a charge and discharge power control device, method and product for an aircraft energy storage element. In the present disclosure, the charge and discharge power control device for an aircraft energy storage element includes an energy storage element, a switching element, a high-voltage DC bus, an energy storage charge and discharge controller and a bus voltage regulation module; one end of the switching element is connected to the energy storage element, and the other end is connected to the high-voltage DC bus. The energy storage charge and discharge controller is used to determine the target bus voltage of the high-voltage DC bus based on the power generation power of the aircraft generator and the power consumption of the aircraft load, and to determine the working state of the switching element; and to change the charge and discharge state of the energy storage element based on the working state. The bus voltage regulation module is used to regulate the voltage value of the high-voltage DC bus to the target bus voltage, so as to change the charge and discharge power of the energy storage element through the target bus voltage. The use of switching elements can meet the requirements of the airborne platform for the volume and weight of the equipment, avoid the problem of exceeding the volume and weight limit, and improve the power-to-weight ratio. The target bus voltage is used to dynamically adjust the bilateral pressure difference, so that the charge and discharge power of the energy storage element can be accurately adjusted.

[0039] In order to make the purpose, technical solutions and advantages of the present disclosure more apparent, the following will describe in detail exemplary embodiments of the present disclosure with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited to the exemplary embodiments described herein.

[0040] Figure 1 This is a schematic diagram of the structure of a charge and discharge power control device for an aircraft energy storage element provided by the present disclosure. Figure 1 As shown, the device includes: energy storage elements, switching elements, high-voltage DC bus, energy storage charge and discharge controller and bus voltage regulation module.

[0041] One end of the switching element is connected to the energy storage element, and the other end is connected to the high-voltage DC bus, thereby establishing an energy flow path between the energy storage element and the high-voltage DC bus. In this embodiment, the switching element can be a device that has the function of controlling the on / off function of the circuit. Compared with bidirectional DC-DC converters in related technologies, the use of switching elements can simplify the structure of the charge and discharge power control device, reduce weight compensation, and improve the power-to-weight ratio of the device.

[0042] The energy storage charge and discharge controller is used to determine the operating state of the switching element based on the power generation power of the aircraft generator and the power consumption of the aircraft load, and to determine the target bus voltage of the high-voltage DC bus when the operating state is working; and to change the charge and discharge state of the energy storage element based on the operating state.

[0043] Specifically, based on the aircraft's current power generation and power consumption, it can be determined whether the onboard power supply system requires the introduction of energy storage elements under the current flight conditions to determine the operating state of the switching elements. The energy storage charge and discharge controller has a signal data transmission relationship with the energy storage elements, switching elements, high-voltage DC bus, and bus voltage regulation module. It is understood that this signal data transmission relationship can use either an electrical connection or a wireless signal transmission method, and this disclosure does not specifically limit this.

[0044] If the generator's power generation differs significantly from the load's power demand, creating an imbalance in the grid's energy supply and demand and requiring the introduction of an energy storage element, the energy storage charge and discharge controller will issue a switch-closing command, closing the switch element and reconnecting the energy flow path. The switch element is now in an active state, which in turn changes the charge and discharge state of the energy storage element, allowing it to be either charged or discharged. The target bus voltage of the high-voltage DC bus can be determined based on the aircraft's generator power generation and the aircraft's load power.

[0045] If the generator's power generation is close to the load's power demand, the energy supply and demand in the power grid is balanced, and there is no need to introduce energy storage elements. In this case, the energy storage charge and discharge controller needs to send a switch disconnect instruction to disconnect the switch element and cut off the energy flow path. At this time, the switch element is in an inoperative state, thereby changing the charge and discharge state of the energy storage element. At this time, the energy storage element can be in an inoperative state.

[0046] The bus voltage regulation module is used to regulate the voltage value of the high-voltage DC bus to the target bus voltage, so as to change the charging and discharging power of the energy storage element through the target bus voltage.

[0047] Specifically, the bus voltage regulation module has a signal data transmission relationship with the high-voltage DC bus. As an actuator, the bus voltage regulation module can adjust the voltage of the high-voltage DC bus after collecting the voltage value of the high-voltage DC bus. When the bus voltage regulation module receives the target bus voltage from the energy storage charge and discharge controller, the bus voltage regulation module increases or decreases the voltage of the high-voltage DC bus according to the target bus voltage, thereby changing the voltage difference between the energy storage element and the high-voltage DC bus in real time to change the charge and discharge power of the energy storage element.

[0048] In the present disclosure, the charge and discharge power control device for an aircraft energy storage element includes an energy storage element, a switching element, a high-voltage DC bus, an energy storage charge and discharge controller, and a bus voltage regulation module; one end of the switching element is connected to the energy storage element, and the other end is connected to the high-voltage DC bus. The energy storage charge and discharge controller is used to determine the working state of the switching element based on the power generation power of the aircraft generator and the power consumption of the aircraft load, and when the working state is working, determine the target bus voltage of the high-voltage DC bus; and change the charge and discharge state of the energy storage element based on the working state. The bus voltage regulation module is used to regulate the voltage value of the high-voltage DC bus to the target bus voltage, so as to change the charge and discharge power of the energy storage element through the target bus voltage. The use of switching elements can meet the requirements of the airborne platform for the volume and weight of the equipment and avoid the problem of exceeding the volume and weight limit. By changing the connection state of the switching element between the energy storage element and the high-voltage DC bus through the target bus voltage, the bilateral pressure difference can be dynamically adjusted, thereby accurately adjusting the charge and discharge power of the energy storage element.

[0049] In one possible implementation, the switching element is a solid-state power controller.

[0050] Specifically, in this embodiment, the switching element can be a solid-state power controller. A solid-state power controller is a contactless switch capable of controlling power on and off. It features fast switching speeds, no arcing, minimal electromagnetic interference, high reliability, and ease of control. Furthermore, the solid-state power controller's small size and weight can reduce weight compensation, improve the device's power-to-weight ratio, meet aircraft equipment size and weight requirements, and avoid exceeding size and weight limits.

[0051] In one possible implementation, the energy storage charge and discharge controller is used to:

[0052] The working state of the switching element is determined by comparing the absolute value of the power difference between the generated power and the consumed power with a preset power fluctuation threshold.

[0053] Specifically, the energy storage charge and discharge controller can obtain the generator's generated power and the load's power consumption under current flight conditions, compare the absolute value of the power difference between the generated power and the power consumption with a fluctuation threshold, and determine the operating state of the switching element based on the comparison result, thereby changing the switching element's closing or opening state, thereby controlling the charge and discharge state of the energy storage element. The preset power fluctuation threshold can be set based on different aircraft models and flight requirements, and this disclosure does not specifically limit this.

[0054] In one possible implementation, the energy storage charge and discharge controller is used to:

[0055] When the power difference is less than zero and the absolute value of the power difference is greater than the preset power fluctuation threshold, the working state of the switching element is determined to be working, and the switching element is controlled to be closed; the target bus voltage is determined by the terminal voltage of the energy storage element, the power difference, the equivalent resistance between the energy storage element and the high-voltage DC bus, and the load equivalent resistance.

[0056] Specifically, when the power difference is less than zero and the absolute value of the power difference is greater than the preset power fluctuation threshold, it means that the current generator output power cannot meet the load's power demand, and the energy storage element needs to discharge to fill the energy gap. That is, the charge and discharge state of the energy storage element needs to be regulated to the discharge state. Therefore, the operating state of the switching element is determined to be working, and the energy storage charge and discharge controller needs to send a turn-on command to the switching element to control the switching element to close. By adjusting the target bus voltage, the direction of energy flow is regulated to flow from the energy storage element to the high-voltage DC bus. Among them, the discharge power of the energy storage element is the power difference.

[0057] The power difference can be calculated using the following formula:

[0058] ΔP=P gen -P load

[0059] Where ΔP is the power difference, P gen is the power generation power, P load For electrical power.

[0060] After determining the power difference, the terminal voltage of the energy storage element, the equivalent resistance between the energy storage element and the high-voltage DC bus, and the equivalent resistance of the load are obtained. The target bus voltage can be calculated and determined according to the following formula to change the discharge power of the energy storage element according to the target bus voltage:

[0061]

[0062] Among them, U bus-r is the target bus voltage, U bat is the terminal voltage of the energy storage element, R′ is the equivalent resistance between the energy storage element and the high-voltage DC bus, ΔP is the power difference, and R is the load equivalent resistance.

[0063] Figure 2 This is another structural diagram of a charge and discharge power control device for an aircraft energy storage element provided by the present disclosure, such as Figure 2 As shown, the switch element is in a closed state, and the current flows from the energy storage element to the high-voltage DC bus.

[0064] In one possible implementation, the energy storage charge and discharge controller is used to:

[0065] When the power difference is greater than zero and the absolute value of the power difference is greater than the preset power fluctuation threshold, the working state of the switching element is determined to be working, and the switching element is controlled to be closed; the target bus voltage is determined by the terminal voltage of the energy storage element, the power difference and the equivalent resistance between the energy storage element and the high-voltage DC bus.

[0066] Specifically, when the power difference is greater than zero, and the absolute value of the power difference is greater than the preset power fluctuation threshold, it means that the output power of the current generator exceeds the power demand of the load, and the energy storage element needs to be charged to absorb the excess electric energy, that is, the charge and discharge state of the energy storage element needs to be adjusted to the charging state. Therefore, it is determined that the working state of the switching element is working, and the energy storage charge and discharge controller needs to send a connection instruction to the switching element to control the switching element to close, and adjust the target bus voltage to adjust the direction of energy flow from the high-voltage DC bus to the energy storage element. Among them, the charging power of the energy storage element is the power difference, and the method for calculating the power difference has been described in detail above and will not be repeated here.

[0067] After determining the power difference, the terminal voltage of the energy storage element and the equivalent resistance between the energy storage element and the high-voltage DC bus are obtained. The target bus voltage can be calculated and determined according to the following formula, so that the charging power of the energy storage element can be changed according to the target bus voltage:

[0068]

[0069] Among them, U bus-r is the target bus voltage, U bat is the terminal voltage of the energy storage element, R′ is the equivalent resistance between the energy storage element and the high-voltage DC bus, and ΔP is the power difference.

[0070] Figure 3 This is another structural diagram of a charge and discharge power control device for an aircraft energy storage element provided by the present disclosure, such as Figure 3 As shown, the switch element is in a closed state, and the current flows from the high-voltage DC bus to the energy storage element.

[0071] In one possible implementation, the energy storage charge and discharge controller is used to:

[0072] When the absolute value of the power difference is less than or equal to the preset power fluctuation threshold, the working state of the switching element is determined to be non-working, and the switching element is controlled to be disconnected.

[0073] Specifically, Figure 4 This is another structural diagram of a charge and discharge power control device for an aircraft energy storage element provided by the present disclosure, such as Figure 4 As shown, the switching element is in the disconnected state. When the absolute value of the power difference is less than or equal to the preset power fluctuation threshold, it indicates that the aircraft's generated power is close to the power demand, the energy supply and demand in the power grid are balanced, and the energy storage element is not required to operate. Therefore, to determine that the operating state of the switching element is non-operating, the energy storage charge and discharge controller needs to send a disconnect instruction to the switching element, controlling the switching element to disconnect, cutting off the energy flow path between the energy storage element and the high-voltage DC bus, so that the charge and discharge state of the energy storage element is regulated to the non-operating state.

[0074] Figure 5 This is a flow chart of a method for controlling the charge and discharge power of an aircraft energy storage element provided by the present disclosure. Figure 5 As shown, the method includes:

[0075] S501: Determine the operating state of the switching element based on the power generation power of the aircraft generator and the power consumption of the aircraft load, and determine the target bus voltage of the high-voltage DC bus when the operating state is working; wherein one end of the switching element is connected to the energy storage element, and the other end is connected to the high-voltage DC bus.

[0076] S502: Regulating the voltage value of the high-voltage DC bus to a target bus voltage, so as to change the charge and discharge power of the energy storage element according to the target bus voltage.

[0077] Optionally, the control method includes:

[0078] The working state of the switching element is determined by comparing the absolute value of the power difference between the generated power and the consumed power with a preset power fluctuation threshold.

[0079] Optionally, the control method includes:

[0080] When the power difference is less than zero and the absolute value of the power difference is greater than the preset power fluctuation threshold, the operating state of the switching element is determined to be working, and the switching element is controlled to be closed, wherein the charge and discharge state of the energy storage element is a discharge state, and the current direction is from the energy storage element to the high-voltage DC bus; the target bus voltage is determined by the terminal voltage of the energy storage element, the power difference, the equivalent resistance between the energy storage element and the high-voltage DC bus, and the load equivalent resistance.

[0081] Optionally, the control method includes:

[0082] When the power difference is greater than zero and the absolute value of the power difference is greater than the preset power fluctuation threshold, the operating state of the switching element is determined to be working, and the switching element is controlled to be closed, wherein the charge and discharge state of the energy storage element is a charging state, and the current direction is from the high-voltage DC bus to the energy storage element; and the target bus voltage is determined by the terminal voltage of the energy storage element, the power difference, and the equivalent resistance between the energy storage element and the high-voltage DC bus.

[0083] Optionally, the control method includes:

[0084] When the absolute value of the power difference is less than or equal to the preset power fluctuation threshold, the working state of the switching element is determined to be non-working, and the switching element is controlled to be disconnected, wherein the charging and discharging state of the energy storage element is a non-working state.

[0085] Optionally, the switching element is a solid-state power controller.

[0086] Figure 6 Another flow chart of a method for controlling the charge and discharge power of an aircraft energy storage element provided by the present disclosure. Figure 6 As shown, the method includes:

[0087] S601: Obtain the power generated by the aircraft generator and the power consumed by the aircraft load.

[0088] Specifically, in this embodiment, the aircraft may have multiple loads, and the generator may be a turbine generator. Therefore, it is necessary to obtain the turbine power and the total power consumption of the multiple loads. It is understood that the generator may also be other types of generators, and this disclosure does not specifically limit this.

[0089] S602: Determine the working state of the solid-state power controller based on the comparison of the absolute value of the power difference between the generated power and the consumed power with a preset power fluctuation threshold.

[0090] Specifically, the relationship between the absolute value of the power difference and a preset power fluctuation threshold is determined, and the operating state of the solid-state power controller is determined based on the comparison result. If the absolute value is greater than the preset power fluctuation threshold, it indicates that the solid-state power controller is currently operating, and step S604 is executed. If the absolute value is less than or equal to the preset power fluctuation threshold, it indicates that the solid-state power controller is currently not operating, and step S603 is executed.

[0091] S603: Disconnect the solid-state power controller.

[0092] Specifically, when the absolute value is less than or equal to the preset power fluctuation threshold, that is, the supply and demand between the turbine's generated power and the load's power consumption is balanced, and no energy storage element is required, then the solid-state power controller needs to be controlled in an inoperative state, that is, the solid-state power controller needs to be disconnected, and then step S601 is executed to continue monitoring the current aircraft's generated power and power consumption.

[0093] S604: Closing the solid-state power controller according to a comparison result between the absolute value and a preset power fluctuation threshold.

[0094] Specifically, when the absolute value is greater than the preset power fluctuation threshold, that is, the turbine's power generation power is unbalanced with the load's power consumption, the solid-state power controller needs to be controlled to be in working state, that is, to control the solid-state power controller to be closed.

[0095] S605: Determine a target bus voltage based on the power difference.

[0096] Specifically, when it is determined that the solid-state power controller is in a working state, the target bus voltage of the high-voltage DC bus when the energy storage element needs to remain in a discharge state when the power difference is less than zero can be determined based on the power difference, the terminal voltage of the energy storage element, the equivalent resistance between the energy storage element and the high-voltage DC bus, and the load equivalent resistance. The target bus voltage can be used to determine whether the current direction changes to flow from the energy storage element to the high-voltage DC bus; the target bus voltage of the high-voltage DC bus when the energy storage element needs to remain in a charging state when the power difference is greater than zero can be determined based on the power difference, the terminal voltage of the energy storage element, and the equivalent resistance between the energy storage element and the high-voltage DC bus. The target bus voltage can be used to determine whether the current direction changes to flow from the high-voltage DC bus to the energy storage element.

[0097] S606: Adjust the voltage value of the high-voltage DC bus according to the target bus voltage.

[0098] Specifically, when the energy storage element needs to remain in a discharged state, the energy storage charge and discharge controller sends a voltage regulation instruction to the bus voltage regulation module to reduce the voltage of the high-voltage DC bus. When the energy storage element needs to remain in a charged state, the energy storage charge and discharge controller sends a voltage regulation instruction to the bus voltage regulation module to increase the voltage of the high-voltage DC bus. It is understood that the bus voltage regulation range of the present disclosure is within the voltage regulation range required by the national military standard.

[0099] S607: Changing the charge and discharge power of the energy storage element.

[0100] Specifically, the target bus voltage can be used to dynamically adjust the bilateral voltage difference, thereby accurately adjusting the charging and discharging power of the energy storage element.

[0101] The present application also provides an electronic device to implement the above-mentioned method for controlling the charge and discharge power of the aircraft energy storage element. Figure 7 It shows a schematic diagram of an electronic device provided by some embodiments of the present application. Figure 7 As shown, the electronic device 70 includes: a processor 700, a memory 701, a bus 702 and a communication interface 703, and the processor 700, the communication interface 703 and the memory 701 are connected via the bus 702; the memory 701 stores a computer program that can be run on the processor 700, and when the processor 700 runs the computer program, it executes the charging and discharging power control method of the aircraft energy storage element provided in any of the aforementioned embodiments of the present application.

[0102] The memory 701 may include high-speed random access memory (RAM) and may also include non-volatile memory, such as at least one disk storage. The communication connection between the device network element and at least one other network element is achieved through at least one communication interface 703 (which may be wired or wireless), and may use the Internet, a wide area network, a local area network, a metropolitan area network, etc.

[0103] Bus 702 may be an ISA bus, a PCI bus, or an EISA bus. The bus may be divided into an address bus, a data bus, a control bus, and the like. Memory 701 is used to store programs, and processor 700 executes the programs upon receiving execution instructions. The method for controlling the charge and discharge power of an aircraft energy storage element disclosed in any of the aforementioned embodiments of the present application may be applied to or implemented by processor 700.

[0104] The processor 700 may be an integrated circuit chip with signal processing capabilities. During implementation, each step of the above method can be completed by hardware integrated logic circuits in the processor 700 or by software instructions. The processor 700 may be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it may also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), an off-the-shelf field programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. It can implement or execute the various methods, steps, and logic block diagrams disclosed in the embodiments of this application. The general-purpose processor may be a microprocessor or any conventional processor. The steps of the method disclosed in conjunction with the embodiments of this application can be directly implemented and executed by a hardware decoding processor, or by a combination of hardware and software modules in the decoding processor. The software module can be located in a storage medium mature in the art, such as random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, etc. The storage medium is located in the memory 701 , and the processor 700 reads the information in the memory 701 and completes the steps of the above method in combination with its hardware.

[0105] The electronic device provided in the embodiment of the present application and the method for controlling the charging and discharging power of the aircraft energy storage element provided in the embodiment of the present application are based on the same inventive concept and have the same beneficial effects as the methods adopted, operated or implemented therein.

[0106] An embodiment of the present application also provides a computer-readable storage medium corresponding to the charge and discharge power control method of the aircraft energy storage element provided in the aforementioned embodiment. The computer-readable storage medium shown therein may be a CD having a computer program stored thereon. When the computer program is run by a processor, it will execute the charge and discharge power control method of the aircraft energy storage element provided in any of the aforementioned embodiments.

[0107] It should be noted that examples of the computer-readable storage medium may also include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other optical or magnetic storage media, which are not listed here one by one.

[0108] The computer-readable storage medium provided in the above-mentioned embodiments of the present application and the method for controlling the charging and discharging power of an aircraft energy storage element provided in the embodiments of the present application are based on the same inventive concept and have the same beneficial effects as the methods adopted, run or implemented by the application programs stored therein.

[0109] The present application also provides a computer program product 800. Figure 8 The computer program product carries a computer program 801, and the program code includes instructions that can be used to execute the steps of the method for controlling the charge and discharge power of an aircraft energy storage element described in the above method embodiment. For details, please refer to the above method embodiment and will not be repeated here.

[0110] The computer program product may be implemented in hardware, software, or a combination thereof. In one embodiment, the computer program product is implemented as a computer storage medium. In another embodiment, the computer program product is implemented as a software product, such as a software development kit (SDK).

[0111] The basic principles of the present disclosure have been described above in conjunction with specific embodiments. However, it should be noted that the advantages, strengths, and effects mentioned in this disclosure are merely illustrative and not restrictive, and should not be construed as necessarily possessed by each embodiment of the present disclosure. Furthermore, the specific details disclosed above are provided for illustrative purposes and to facilitate understanding, rather than as limitations. These details do not limit the present disclosure to necessarily being implemented using these specific details.

[0112] The block diagrams of the devices, devices, equipment, and systems involved in this disclosure are merely illustrative examples and are not intended to require or imply that they must be connected, arranged, or configured in the manner shown in the block diagrams. As will be appreciated by those skilled in the art, these devices, devices, equipment, and systems can be connected, arranged, or configured in any manner. Words such as "include," "comprise," "have," and the like are open-ended words, meaning "including but not limited to," and can be used interchangeably therewith. The words "or" and "and" used herein refer to the words "and / or" and can be used interchangeably therewith, unless the context clearly indicates otherwise. The word "such as" used herein refers to the phrase "such as but not limited to," and can be used interchangeably therewith.

[0113] Additionally, as used herein, "or" used in a list of items beginning with "at least one" indicates a separate list, so that, for example, a list of "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word "exemplary" does not mean that the example described is preferred or better than other examples.

[0114] It should also be noted that in the system and method of the present disclosure, each component or each step can be decomposed and / or recombined. Such decomposition and / or recombination should be regarded as equivalent solutions of the present disclosure.

[0115] Various changes, substitutions, and modifications may be made to the technology described herein without departing from the teachings defined by the appended claims. Moreover, the scope of the claims of this disclosure is not limited to the specific aspects of the processes, machines, manufactures, compositions of things, means, methods, and actions described above. Currently existing or later developed processes, machines, manufactures, compositions of things, means, methods, or actions that perform substantially the same function or achieve substantially the same results as the corresponding aspects described herein may be utilized. Accordingly, the appended claims include within their scope such processes, machines, manufactures, compositions of things, means, methods, or actions.

[0116] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but rather to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0117] The above description has been provided for the purpose of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although a number of example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.

Claims

1. A charge and discharge power control device for an aircraft energy storage element, characterized in that: The device includes an energy storage element, a switching element, a high-voltage DC bus, an energy storage charge and discharge controller, and a bus voltage regulation module; One end of the switch element is connected to the energy storage element, and the other end is connected to the high-voltage DC bus; The energy storage charge and discharge controller is configured to determine an operating state of the switching element based on the power generated by the aircraft generator and the power consumed by the aircraft load, and to determine a target bus voltage of the high-voltage DC bus when the operating state is working; and to change the charge and discharge state of the energy storage element based on the operating state; The bus voltage regulation module is used to regulate the voltage value of the high-voltage DC bus to the target bus voltage, so as to change the charge and discharge power of the energy storage element according to the target bus voltage.

2. The device according to claim 1, characterized in that The energy storage charge and discharge controller is used to: The working state of the switching element is determined by comparing the absolute value of the power difference between the generated power and the consumed power with a preset power fluctuation threshold.

3. The device according to claim 2, characterized in that The energy storage charge and discharge controller is used to: When the power difference is less than zero and the absolute value of the power difference is greater than the preset power fluctuation threshold, the operating state of the switching element is determined to be working, and the switching element is controlled to be closed, wherein the charge and discharge state of the energy storage element is a discharge state, and the current direction is from the energy storage element to the high-voltage DC bus; the target bus voltage is determined by the terminal voltage of the energy storage element, the power difference, the equivalent resistance between the energy storage element and the high-voltage DC bus, and the load equivalent resistance.

4. The device according to claim 2, characterized in that The energy storage charge and discharge controller is used to: When the power difference is greater than zero and the absolute value of the power difference is greater than the preset power fluctuation threshold, the operating state of the switching element is determined to be working, and the switching element is controlled to be closed, wherein the charge and discharge state of the energy storage element is a charging state, and the current direction is from the high-voltage DC bus to the energy storage element; and the target bus voltage is determined by the terminal voltage of the energy storage element, the power difference, and the equivalent resistance between the energy storage element and the high-voltage DC bus.

5. The device according to claim 2, characterized in that The energy storage charge and discharge controller is used to: When the absolute value of the power difference is less than or equal to the preset power fluctuation threshold, the working state of the switching element is determined to be non-working, and the switching element is controlled to be disconnected, wherein the charging and discharging state of the energy storage element is a non-working state.

6. The device according to any one of claims 1 to 5, characterized in that The switching element is a solid-state power controller.

7. A method for controlling the charge and discharge power of an aircraft energy storage element, characterized in that: include: Determining an operating state of a switching element based on the power generated by the aircraft generator and the power consumed by the aircraft load, and determining a target bus voltage of a high-voltage direct current bus when the operating state is working; wherein one end of the switching element is connected to the energy storage element, and the other end is connected to the high-voltage direct current bus; The voltage value of the high-voltage DC bus is regulated to the target bus voltage, so as to change the charge and discharge power of the energy storage element according to the target bus voltage.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: The processor runs the computer program to implement the method as claimed in claim 7.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: The program is executed by a processor to implement the method as claimed in claim 7.

10. A computer program product, characterized in that The invention comprises a computer-readable code or a non-volatile computer-readable storage medium carrying a computer-readable code. When the computer-readable code runs in a processor of an electronic device, the processor in the electronic device executes the method as claimed in claim 7.

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