Control method and device of space power station energy management system, terminal equipment and storage medium
By adopting a combined converter topology of IPOS boost module and ISOP buck module in space power stations, the problem of low output power in space power stations is solved, and more efficient energy transmission and power output are achieved.
Patent Information
- Application Number
- CN202411753358.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-02
- Publication Date
- 2025-03-04
AI Technical Summary
When collecting solar energy, the space power stations consume a large loss of direct transmission of electricity, resulting in a low output power.
A control method of a space power station energy management system is adopted to obtain the input voltage generated by the photovoltaic array, and voltage regulation is used to control the power supply of the microwave transmitting array by using the IPOS boost module and the ISOP buck module.
Through the combined converter topology of the IPOS boost module and the ISOP buck module, the voltage or current that electronic devices bear, the loss of high-voltage transmission is reduced, and the output power of the space power station is increased.
Smart Images
Figure CN119561001A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the field of vehicle body control technology, and in particular to a control method, device, terminal equipment and storage medium for a space power station energy management system. Background Art
[0002] As the shortage of fossil energy and the pollution to the environment become increasingly serious, people have begun to look for renewable alternative clean energy, such as solar energy, wind energy, tidal energy, etc. Solar energy has been widely studied due to its abundant and clean characteristics. When collecting solar energy, existing space power stations directly transmit the electrical energy converted from solar energy, but the direct transmission method has a large loss, resulting in the problem of low output power of space power stations.
[0003] Therefore, there is an urgent need for a control strategy for a space power station energy management system to solve the problem of low output power of space power stations. Summary of the invention
[0004] The embodiments of the present invention provide a control method, an apparatus, a terminal device and a storage medium for a space power station energy management system to solve the problem of low output power in a space power station.
[0005] In order to solve the above problem, an embodiment of the present invention provides a control method for a space power station energy management system, including:
[0006] Obtaining the input voltage of the space power station energy management system; wherein the space power station energy management system includes: a plurality of photovoltaic arrays, a DC bus, a plurality of IPOS boost modules, a plurality of ISOP buck modules, and a plurality of microwave transmitting arrays; each photovoltaic array is respectively connected to each of the IPOS boost modules, each of the IPOS boost modules is respectively connected to each of the ISOP buck modules through the DC bus, and each of the ISOP buck modules is respectively connected to each of the microwave transmitting arrays; the input voltage is generated by each of the photovoltaic arrays;
[0007] Based on the input voltage and the preset three-loop control strategy, each IPOS boost module is boosted to obtain a boost output;
[0008] Each boost output is transmitted to the corresponding ISOP buck module through the DC bus for buck control to obtain a buck output;
[0009] Based on the stepped-down output, the power supply of the corresponding microwave transmitting array is controlled.
[0010] As an improvement of the above solution, the IPOS boost module includes: a voltage outer loop controller, a plurality of voltage balancing ring controllers, a plurality of current inner loop controllers, and a plurality of boost units;
[0011] Among them, the input of the boost unit is respectively connected to the output of the voltage equalizing ring controller and the output of the current inner loop controller, each boost unit corresponds to each voltage equalizing ring controller, and each boost unit corresponds to each current inner loop controller; the voltage outer loop controller is respectively connected to each voltage equalizing ring controller.
[0012] As an improvement of the above solution, the boost control is performed on each IPOS boost module based on the input voltage and the preset three-loop control strategy to obtain the boost output, including:
[0013] In each IPOS boost module, an outer loop input of a voltage outer loop controller is calculated based on a corresponding input voltage and a reference voltage; wherein the voltage outer loop controller generates an outer loop output based on the outer loop input;
[0014] In each IPOS boost module, based on the input partial voltage of each boost unit and the unit mean of the input voltage, the voltage grading ring input of each voltage grading ring controller is calculated; wherein the sum of the input partial voltages of each IPOS boost module is the same as the input voltage; wherein each of the voltage grading ring controllers generates a voltage grading ring output based on the voltage grading ring input;
[0015] In each IPOS boost module, based on the outer loop output of the voltage outer loop controller and the voltage balancing loop output of each voltage balancing loop controller, the inner loop input of each current inner loop controller is confirmed; wherein each current inner loop controller generates an inner loop output based on the inner loop input;
[0016] In each IPOS boost module, each boost unit is respectively boosted based on the inner loop output of each current inner loop controller to complete the boost control of each IPOS boost module and obtain the boost output.
[0017] As an improvement of the above solution, the design method of the IPOS boost module includes:
[0018] Obtaining initial device parameters of the IPOS boost system; wherein the IPOS boost system comprises: a plurality of IPOS boost modules; the types of initial device parameters include: input capacitance, filter capacitance, inductance, transformer ratio, duty cycle, and load resistance equivalent to the resistance of each IPOS boost module;
[0019] Based on the initial parameters of the device, a small signal model of the IPOS boost system is constructed;
[0020] The small signal model is simulated and run, and the initial parameters of each device are adjusted according to the open-loop transfer function of the voltage outer loop controller, the closed-loop transfer function of the current inner loop controller, and the open-loop transfer function of the voltage balancing loop controller to obtain the final parameters of the device corresponding to the initial parameters of each device;
[0021] The IPOS boost module is designed according to the final parameters of each device.
[0022] As an improvement of the above solution, the open-loop transfer function of the voltage outer loop controller satisfies the following conditions:
[0023]
[0024] In the formula, R is the output resistance, C is the filter capacitor, N is the number of modules, G is v_ol1 is the voltage outer loop open-loop transfer function value.
[0025] As an improvement of the above solution, the closed-loop transfer function of the current inner-loop controller satisfies the following conditions:
[0026]
[0027] In the formula, G i_cl1 is the closed-loop transfer function value, is the small disturbance of the inductor current of the nth module, N is the number of modules, V in is the input voltage, R is the output resistance, G i is the current inner loop compensation function, G v is the voltage outer loop compensation function, R d =4n 2 Lf s , L is the filter inductance, f s is the switching frequency.
[0028] As an improvement of the above solution, the open-loop transfer function of the voltage-equalizing ring controller satisfies the following conditions:
[0029]
[0030] Where C is the capacitance, G is avg_ol1 is the open-loop transfer function value.
[0031] Accordingly, an embodiment of the present invention further provides a control device for a space power station energy management system, comprising: a data acquisition module, a boost control module, a buck control module and a power supply module;
[0032] The data acquisition module is used to acquire the input voltage of the space power station energy management system; wherein the space power station energy management system includes: a plurality of photovoltaic arrays, a DC bus, a plurality of IPOS boost modules, a plurality of ISOP buck modules, and a plurality of microwave transmitting arrays; each photovoltaic array is respectively connected to each of the IPOS boost modules, each of the IPOS boost modules is respectively connected to each of the ISOP buck modules through the DC bus, and each of the ISOP buck modules is respectively connected to each of the microwave transmitting arrays; the input voltage is generated by each of the photovoltaic arrays;
[0033] The boost control module is used to perform boost control on each IPOS boost module based on the input voltage and the preset three-loop control strategy to obtain a boost output;
[0034] The step-down control module is used to transmit each boost output to the corresponding ISOP step-down module through the DC bus for step-down control to obtain a step-down output;
[0035] The power supply module is used to control the power supply of the corresponding microwave transmitting array based on the stepped-down output.
[0036] Correspondingly, an embodiment of the present invention also provides a computer terminal device, including a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, and when the processor executes the computer program, it implements a control method of a space power station energy management system as described in the present invention.
[0037] Correspondingly, an embodiment of the present invention further provides a computer-readable storage medium, which includes a stored computer program, wherein when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute a control method for a space power station energy management system as described in the present invention.
[0038] As can be seen from the above, the present invention has the following beneficial effects:
[0039] The present invention provides a control method for a space power station energy management system, which obtains the input voltage of the space power station energy management system; wherein the space power station energy management system includes: a plurality of photovoltaic arrays, a DC bus, a plurality of IPOS boost modules, a plurality of ISOP buck modules, and a plurality of microwave transmitting arrays; based on the input voltage and a preset three-loop control strategy, each IPOS boost module is boosted to obtain a boost output; each boost output is transmitted to the corresponding ISOP buck module through a DC bus for buck control to obtain a buck output; based on the buck output, the power supply of the corresponding microwave transmitting array is controlled. The present invention uses the IPOS boost module to boost and the ISOP to buck, and the energy transmission mode formed can not only reduce the withstand voltage or current of the electronic device, but also reduce the loss during high-voltage transmission, which is conducive to improving the output power of the space power station. BRIEF DESCRIPTION OF THE DRAWINGS
[0040] Figure 1 It is a flow chart of a control method of a space power station energy management system provided by an embodiment of the present invention;
[0041] Figure 2 It is a structural schematic diagram of a control device of a space power station energy management system provided by an embodiment of the present invention;
[0042] Figure 3 This is a schematic diagram of the structure of a terminal device provided by an embodiment of the present invention;
[0043] Figure 4 is a schematic structural diagram of an IPOS boost module provided by an embodiment of the present invention;
[0044] Figure 5 1 is a schematic diagram of the structure of an ISOP step-down module provided by an embodiment of the present invention;
[0045] Figure 6 It is a structural diagram of a space power station energy management system provided by an embodiment of the present invention;
[0046] Figure 7 is a topological schematic diagram of an IPOS boost module provided in one embodiment of the present invention;
[0047] Figure 8 is a schematic diagram of a three-loop control strategy of an IPOS boost module provided by an embodiment of the present invention;
[0048] Fig. 9 is an output voltage current loop control block diagram provided by an embodiment of the present invention;
[0049] Fig.10 is a small signal block diagram of an IPOS boost module provided by an embodiment of the present invention;
[0050] Fig.11 This is a control block diagram of an output voltage balancing loop of an IPOS step-down module provided in one embodiment of the present invention;
[0051] Fig.12 is a Bode diagram of a voltage loop transfer function provided by an embodiment of the present invention;
[0052] Fig.13 is an output voltage waveform diagram provided by an embodiment of the present invention;
[0053] Fig.14 is a Bode diagram when transformer parameters are mismatched according to an embodiment of the present invention;
[0054] Fig.15 is the module output voltage of the transformer parameter mismatch provided by an embodiment of the present invention. DETAILED DESCRIPTION
[0055] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.
[0056] Embodiment 1
[0057] See also Figure 1 , Figure 1 FIG. 1 is a flow chart of a control method of a space power station energy management system provided by an embodiment of the present invention. Figure 1 As shown, this embodiment includes steps 101 to 104, and each step is specifically as follows:
[0058] Step 101: Obtain the input voltage of the space power station energy management system; wherein the space power station energy management system includes: a plurality of photovoltaic arrays, a DC bus, a plurality of IPOS boost modules, a plurality of ISOP buck modules, and a plurality of microwave transmitting arrays; each photovoltaic array is respectively connected to each of the IPOS boost modules, each of the IPOS boost modules is respectively connected to each of the ISOP buck modules through the DC bus, and each of the ISOP buck modules is respectively connected to each of the microwave transmitting arrays; the input voltage is generated by each of the photovoltaic arrays.
[0059] In a specific embodiment, the space power station energy management system is a two-stage system, the front stage is to boost the voltage by connecting multiple modules with input terminals in parallel and output terminals in series (Input Parallel Output Series, IPOS) (i.e., the IPOS boost module described in the present invention), and the rear stage is to buck the voltage by connecting multiple modules with input terminals in series and output terminals in parallel (Input Series Output Parallel, ISOP) (i.e., the ISOP buck module described in the present invention). Taking N modules as an example, the IPOS boost module is as follows: Figure 4 , ISOP buck module such as Figure 5 As shown in Figure 2, the architecture of the space power station energy management system is as follows: Figure 6 shown.
[0060] It is understandable that the modular series-parallel combination converter topology has the following advantages:
[0061] 1) The input or output of a single module is connected in series or in parallel to share the total voltage stress or current stress. Taking N modules as an example, the voltage or current borne by the power electronic devices of a single converter is 1 / N of the original, so low-voltage power electronic devices can be selected;
[0062] 2) The topology is highly modular and easy to expand. The topology and control strategy of each module are consistent, which facilitates the redundant design of the system and improves the system reliability;
[0063] 3) The topology can realize centralized energy transmission, and the high transmission voltage level can effectively reduce energy loss and thus reduce the overall cost.
[0064] In this embodiment, the IPOS boost module includes: a voltage outer loop controller, a plurality of voltage balancing ring controllers, a plurality of current inner loop controllers, and a plurality of boost units;
[0065] Among them, the input of the boost unit is respectively connected to the output of the voltage equalizing ring controller and the output of the current inner loop controller, each boost unit corresponds to each voltage equalizing ring controller, and each boost unit corresponds to each current inner loop controller; the voltage outer loop controller is respectively connected to each voltage equalizing ring controller.
[0066] Step 102: Based on the input voltage and the preset three-loop control strategy, each IPOS boost module is boosted to obtain a boosted output.
[0067] In this embodiment, the IPOS boost module may be: an IPOS combined converter.
[0068] In this embodiment, the step of performing boost control on each IPOS boost module based on the input voltage and the preset three-loop control strategy to obtain a boost output includes:
[0069] In each IPOS boost module, an outer loop input of a voltage outer loop controller is calculated based on a corresponding input voltage and a reference voltage; wherein the voltage outer loop controller generates an outer loop output based on the outer loop input;
[0070] In each IPOS boost module, based on the input partial voltage of each boost unit and the unit mean of the input voltage, the voltage grading ring input of each voltage grading ring controller is calculated; wherein the sum of the input partial voltages of each IPOS boost module is the same as the input voltage; wherein each of the voltage grading ring controllers generates a voltage grading ring output based on the voltage grading ring input;
[0071] In each IPOS boost module, based on the outer loop output of the voltage outer loop controller and the voltage balancing loop output of each voltage balancing loop controller, the inner loop input of each current inner loop controller is confirmed; wherein each current inner loop controller generates an inner loop output based on the inner loop input;
[0072] In each IPOS boost module, each boost unit is respectively boosted based on the inner loop output of each current inner loop controller to complete the boost control of each IPOS boost module and obtain the boost output.
[0073] It should be noted that the photovoltaic array is boosted by the DC / DC converter of the IPOS boost module to the DC bus, and then the DC bus is transmitted and then stepped down by the DC / DC converter of the ISOP buck module to power the energy transmitting unit. The common control strategy is voltage and current dual-loop control, where the voltage outer loop achieves the control target and the current inner loop adjusts the control performance and responds quickly. However, since there are multiple modules in the multi-module series-parallel combination, if only the voltage and current dual-loop control is used, the power distribution between modules cannot be balanced. When the imbalance of a single sub-module is large, the system may not work properly. Therefore, the realization of equal voltage and current of each sub-module can ensure the advantages of the series-parallel combination system. Taking the IPOS combined converter as an example, its topology diagram is shown in Figure 7.
[0074] Therefore, in order to improve the reliability of the IPOS system, the present invention adds a pressure equalization loop control on the basis of the conventional dual-loop control strategy, and its control structure is as follows: Figure 8 As shown in the figure, Gi is the current inner loop controller, Gv is the voltage outer loop controller, and Gavg is the voltage equalizing loop controller.
[0075] In this embodiment, the design method of the IPOS boost module includes:
[0076] Obtaining initial device parameters of the IPOS boost system; wherein the IPOS boost system comprises: a plurality of IPOS boost modules; the types of initial device parameters include: input capacitance, filter capacitance, inductance, transformer ratio, duty cycle, and load resistance equivalent to the resistance of each IPOS boost module;
[0077] Based on the initial parameters of the device, a small signal model of the IPOS boost system is constructed;
[0078] The small signal model is simulated and run, and the initial parameters of each device are adjusted according to the open-loop transfer function of the voltage outer loop controller, the closed-loop transfer function of the current inner loop controller, and the open-loop transfer function of the voltage balancing loop controller to obtain the final parameters of the device corresponding to the initial parameters of each device;
[0079] The IPOS boost module is designed according to the final parameters of each device.
[0080] In this embodiment, the open-loop transfer function of the voltage outer loop controller satisfies the following conditions:
[0081]
[0082] In the formula, R is the output resistance, C is the filter capacitor, N is the number of modules, G is v_ol1 is the voltage outer loop open-loop transfer function value.
[0083] In this embodiment, the closed-loop transfer function of the current inner-loop controller satisfies the following conditions:
[0084]
[0085] In the formula, G i_cl1 is the closed-loop transfer function value, is the small disturbance of the inductor current of the nth module, N is the number of modules, V in is the input voltage, R is the output resistance, G i is the current inner loop compensation function, G v is the voltage outer loop compensation function, R d =4n 2 Lf s , L is the filter inductance, f s is the switching frequency.
[0086] In this embodiment, the open-loop transfer function of the voltage-equalizing ring controller satisfies the following conditions:
[0087]
[0088] Where C is the capacitance, G is avg_ol1 is the open-loop transfer function value.
[0089] In order to analyze the effect of the three-loop control strategy and design the control parameters, it is necessary to derive the transfer function of the system. Existing studies have only established a control model for a single module, ignoring the coupling relationship between modules, resulting in inaccurate parameter design and affecting the control effect.
[0090] The output double-loop structure diagram after decoupling of the IPOS system composed of N modules is as follows: Fig. 9 As shown. x1 , G y1 It is the relationship between the small disturbance of inductor current and the small disturbance of duty cycle of each module, and its expression is related to the circuit topology.
[0091] The phase-shifted full-bridge converter has the advantages of high conversion efficiency and isolation and is often used in high-power DC / DC conversion applications. Fig.10 The small signal model diagram is composed of N phase-shifted full-bridge modules connected by IPOS. Assume that each module uses the same parameter device, that is, the input capacitor is C in , the filter capacitor and inductor are C and L respectively, the transformer ratio is n, and the duty cycle is D eff , the load resistance is equivalent to the resistance of each submodule is R / N. The KVL and KCL equations are listed as follows:
[0092]
[0093] Then the relationship between the small disturbance of the filter inductor current and the small disturbance of the duty cycle is obtained and extended to N modules:
[0094]
[0095] in,
[0096]
[0097] The relationship between the small disturbance of the filter inductor current and the small disturbance of the duty cycle is extended to the formula corresponding to N modules. Substituting the relationship between the small disturbance of the filter inductor current and the small disturbance of the duty cycle into the closed-loop transfer function of N modules and the current inner-loop controller, the transfer function of the voltage and current dual loops can be obtained.
[0098] The system has a current relationship:
[0099]
[0100] Subtracting the KCL equation of module 1 from the KCL equation of the jth module yields:
[0101]
[0102] Add N-1 equations like equation (7) to get:
[0103]
[0104] Since the sum of the duty cycle components generated by the output voltage balancing loop is zero, that is, the sum of the small disturbance components of the inductor current is zero, Draw the control block diagram of the output voltage equalization loop of module 1 as shown in 11. sh (s) is the compensation function of the output voltage equalizing ring.
[0105] The open-loop control transfer function of the pressure equalization loop is expressed as:
[0106]
[0107] Step 103: Transmit each boost output to the corresponding ISOP buck module through the DC bus for buck control to obtain a buck output.
[0108] Step 104: Based on the step-down output, control the power supply of the corresponding microwave transmitting array.
[0109] In a specific embodiment, in order to verify the established three-loop control strategy model, an IPOS system consisting of 6 modules is designed and the voltage loop transfer function Bode diagram is drawn in the simulation software. Fig.12 shown.
[0110] The PI controller is used to compensate the system. The cutoff frequency of the open-loop system considering coupling differs by about 3kHz from that without coupling, and the phase margin differs by 28°. Therefore, the system has a smaller bandwidth and phase margin after coupling. The same PI compensator is used to compensate the voltage outer loop. Compared with the Bode diagram without coupling, the cutoff frequency differs by 0.3kHz and the phase margin differs by 14° after coupling.
[0111] It can be seen that there are obvious differences in the crossover frequency and phase margin before and after considering coupling. Establishing a small signal model after considering coupling can help design more accurate device parameters and compensation parameters, thereby obtaining better dynamic effects.
[0112] According to the Bode diagram, a larger proportional control coefficient can lead to a higher system bandwidth and less adjustment time, but the system overshoot will also increase. Fig.13 (a) Output voltage waveforms with different voltage outer loop proportional control coefficients confirm the Bode plot analysis; Fig.13 (b) is load jump, Fig.13 (c) is the output voltage waveform when the input jumps. The system can respond quickly and the voltage ripple and overshoot meet the requirements. Therefore, the control strategy designed according to the control model has good dynamic characteristics and steady-state characteristics.
[0113] Draw the loop gain Bode diagram for the three transformer parameters as shown below: Fig.14 As shown, the loop amplitude and phase angle are very different, which verifies that the system dynamic characteristics are not greatly affected by the transformer parameter mismatch.
[0114] Depend on Fig.15 (a) and (b) are the module output voltages before and after adding the voltage balancing ring. The difference in the waveform dynamic characteristics can be ignored, but there are steady-state differences. After adding the output voltage balancing ring, the voltage imbalance problem between modules can be well balanced.
[0115] It is understandable that the topology of the space power station energy management system is suitable for high-power space power station occasions, and has the characteristics of high stability, low loss, high modularity and high redundancy. At the same time, the control strategy adopts three-loop control, adding a voltage-equalizing control outer loop on the basis of the traditional output dual-loop control. Even if individual components in the space environment are aged or damaged and difficult to repair, it can still ensure power balance between each sub-module and stable operation of the system.
[0116] In addition, the small signal model of the series-parallel combination converter established in the prior art does not consider the coupling between modules, and only models a single module, so the designed compensation effect deviates greatly from the actual effect. The present invention establishes a small signal model after considering the coupling between modules. The duty cycle of each module is affected by the inductor current of other modules. By deriving the relationship between the small disturbance of the inductor current of each module and the small disturbance of the duty cycle, the transfer functions of the three control loops are derived, which helps to design the compensation parameters of the controller, improves the dynamic characteristics and steady-state characteristics of the system, and verifies the correctness of the model in the simulation model.
[0117] See also Figure 2 , Figure 2 It is a structural schematic diagram of a control device of a space power station energy management system provided by an embodiment of the present invention, comprising: a data acquisition module 201, a boost control module 202, a buck control module 203 and a power supply module 204;
[0118] The data acquisition module is used to acquire the input voltage of the space power station energy management system; wherein the space power station energy management system includes: a plurality of photovoltaic arrays, a DC bus, a plurality of IPOS boost modules, a plurality of ISOP buck modules, and a plurality of microwave transmitting arrays; each photovoltaic array is respectively connected to each of the IPOS boost modules, each of the IPOS boost modules is respectively connected to each of the ISOP buck modules through the DC bus, and each of the ISOP buck modules is respectively connected to each of the microwave transmitting arrays; the input voltage is generated by each of the photovoltaic arrays;
[0119] The boost control module is used to perform boost control on each IPOS boost module based on the input voltage and the preset three-loop control strategy to obtain a boost output;
[0120] The step-down control module is used to transmit each boost output to the corresponding ISOP step-down module through the DC bus for step-down control to obtain a step-down output;
[0121] The power supply module is used to control the power supply of the corresponding microwave transmitting array based on the stepped-down output.
[0122] It can be understood that the above-mentioned system item embodiments correspond to the method item embodiments of the present invention, which can implement the control method of the space power station energy management system provided by any one of the above-mentioned method item embodiments of the present invention.
[0123] This embodiment obtains the input voltage of the space power station energy management system; wherein the space power station energy management system includes: a number of photovoltaic arrays, a DC bus, a number of IPOS boost modules, a number of ISOP buck modules, and a number of microwave transmitting arrays; based on the input voltage and the preset three-loop control strategy, each IPOS boost module is boosted to obtain a boost output; each boost output is transmitted to the corresponding ISOP buck module through the DC bus for buck control to obtain a buck output; based on the buck output, the power supply of the corresponding microwave transmitting array is controlled. The present invention uses the IPOS boost module to boost and the ISOP to buck, and the energy transmission mode formed can not only reduce the voltage or current that the electronic device can withstand, but also reduce the loss during high-voltage transmission, which is conducive to improving the output power of the space power station.
[0124] Embodiment 2
[0125] See also Figure 3 , Figure 3 It is a schematic diagram of the structure of a terminal device provided in one embodiment of the present invention.
[0126] A terminal device of this embodiment includes: a processor 301, a memory 302, and a computer program stored in the memory 302 and executable on the processor 301. When the processor 301 executes the computer program, the steps of the control method of each space power station energy management system in the embodiment are implemented, for example Figure 1 Alternatively, when the processor executes the computer program, the functions of each module in the above-mentioned device embodiments are realized, for example: Figure 2 All modules of the control device of the space power station energy management system are shown.
[0127] In addition, an embodiment of the present invention also provides a computer-readable storage medium, which includes a stored computer program, wherein when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute the control method of the space power station energy management system as described in any of the above embodiments.
[0128] Those skilled in the art will understand that the schematic diagram is merely an example of a terminal device and does not constitute a limitation on the terminal device. The terminal device may include more or fewer components than shown in the diagram, or a combination of certain components, or different components. For example, the terminal device may also include input and output devices, network access devices, buses, etc.
[0129] The processor 301 may be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor may be a microprocessor or any conventional processor, etc. The processor 301 is the control center of the terminal device, and uses various interfaces and lines to connect various parts of the entire terminal device.
[0130] The memory 302 can be used to store the computer program and / or module. The processor 301 implements various functions of the terminal device by running or executing the computer program and / or module stored in the memory and calling the data stored in the memory 302. The memory 302 can mainly include a program storage area and a data storage area, wherein the program storage area can store an operating system, an application required for at least one function (such as a sound playback function, an image playback function, etc.), etc.; the data storage area can store data created according to the use of the mobile phone (such as audio data, a phone book, etc.), etc. In addition, the memory can include a high-speed random access memory, and can also include a non-volatile memory, such as a hard disk, a memory, a plug-in hard disk, a smart memory card (Smart Media Card, SMC), a secure digital (Secure Digital, SD) card, a flash card (Flash Card), at least one disk storage device, a flash memory device, or other volatile solid-state storage devices.
[0131] Wherein, if the module / unit integrated in the terminal device is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on such an understanding, the present invention implements all or part of the processes in the above-mentioned embodiment method, and can also be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium, and the computer program can implement the steps of the above-mentioned various method embodiments when executed by the processor. Wherein, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form, etc. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording medium, U disk, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), electric carrier signal, telecommunication signal and software distribution medium, etc.
[0132] It should be noted that the device embodiments described above are merely schematic, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. In addition, in the accompanying drawings of the device embodiments provided by the present invention, the connection relationship between the modules indicates that there is a communication connection between them, which may be specifically implemented as one or more communication buses or signal lines. A person of ordinary skill in the art may understand and implement it without paying any creative effort.
[0133] The above is a preferred embodiment of the present invention. It should be pointed out that a person skilled in the art can make several improvements and modifications without departing from the principle of the present invention. These improvements and modifications are also considered to be within the scope of protection of the present invention.
Claims
1. A control method for a space power station energy management system, characterized in that: include: Obtaining the input voltage of the space power station energy management system; wherein the space power station energy management system includes: a plurality of photovoltaic arrays, a DC bus, a plurality of IPOS boost modules, a plurality of ISOP buck modules, and a plurality of microwave transmitting arrays; each photovoltaic array is respectively connected to each of the IPOS boost modules, each of the IPOS boost modules is respectively connected to each of the ISOP buck modules through the DC bus, and each of the ISOP buck modules is respectively connected to each of the microwave transmitting arrays; the input voltage is generated by each of the photovoltaic arrays; Based on the input voltage and the preset three-loop control strategy, each IPOS boost module is boosted to obtain a boost output; Each boost output is transmitted to the corresponding ISOP buck module through the DC bus for buck control to obtain a buck output; Based on the stepped-down output, the power supply of the corresponding microwave transmitting array is controlled.
2. The control method of the space power station energy management system according to claim 1, characterized in that: The IPOS boost module includes: a voltage outer loop controller, a plurality of voltage balancing ring controllers, a plurality of current inner loop controllers, and a plurality of boost units; Among them, the input of the boost unit is respectively connected to the output of the voltage equalizing ring controller and the output of the current inner loop controller, each boost unit corresponds to each voltage equalizing ring controller, and each boost unit corresponds to each current inner loop controller; the voltage outer loop controller is respectively connected to each voltage equalizing ring controller.
3. The control method of the space power station energy management system according to claim 2, characterized in that: The step of performing boost control on each IPOS boost module based on the input voltage and the preset three-loop control strategy to obtain a boost output includes: In each IPOS boost module, an outer loop input of a voltage outer loop controller is calculated based on a corresponding input voltage and a reference voltage; wherein the voltage outer loop controller generates an outer loop output based on the outer loop input; In each IPOS boost module, based on the input partial voltage of each boost unit and the unit mean of the input voltage, the voltage grading ring input of each voltage grading ring controller is calculated; wherein the sum of the input partial voltages of each IPOS boost module is the same as the input voltage; wherein each of the voltage grading ring controllers generates a voltage grading ring output based on the voltage grading ring input; In each IPOS boost module, based on the outer loop output of the voltage outer loop controller and the voltage balancing loop output of each voltage balancing loop controller, the inner loop input of each current inner loop controller is confirmed; wherein each current inner loop controller generates an inner loop output based on the inner loop input; In each IPOS boost module, each boost unit is respectively boosted based on the inner loop output of each current inner loop controller to complete the boost control of each IPOS boost module and obtain the boost output.
4. The control method of the space power station energy management system according to claim 3, characterized in that: The design method of the IPOS boost module comprises: Obtaining initial device parameters of the IPOS boost system; wherein the IPOS boost system comprises: a plurality of IPOS boost modules; the types of initial device parameters include: input capacitance, filter capacitance, inductance, transformer ratio, duty cycle, and load resistance equivalent to the resistance of each IPOS boost module; Based on the initial parameters of the device, a small signal model of the IPOS boost system is constructed; The small signal model is simulated and run, and the initial parameters of each device are adjusted according to the open-loop transfer function of the voltage outer loop controller, the closed-loop transfer function of the current inner loop controller, and the open-loop transfer function of the voltage balancing loop controller to obtain the final parameters of the device corresponding to the initial parameters of each device; The IPOS boost module is designed according to the final parameters of each device.
5. The control method of the space power station energy management system according to claim 4, characterized in that: The open-loop transfer function of the voltage outer loop controller satisfies the following conditions: In the formula, R is the output resistance, C is the filter capacitor, N is the number of modules, G is v_ol1 is the voltage outer loop open-loop transfer function value.
6. The control method of the space power station energy management system according to claim 4, characterized in that: The closed-loop transfer function of the current inner-loop controller satisfies the following conditions: In the formula, G i_cl1 is the closed-loop transfer function value, is the small disturbance of the inductor current of the nth module, N is the number of modules, V in is the input voltage, R is the output resistance, G i is the current inner loop compensation function, G v is the voltage outer loop compensation function, R d =4n 2 Lf s , L is the filter inductance, f s is the switching frequency.
7. The control method of the space power station energy management system according to claim 4, characterized in that: The open-loop transfer function of the voltage-equalizing ring controller satisfies the following conditions: Where C is the capacitance, G is avg_ol1 is the open-loop transfer function value.
8. A control device for a space power station energy management system, characterized in that: include: Data acquisition module, boost control module, buck control module and power supply module; The data acquisition module is used to acquire the input voltage of the space power station energy management system; wherein the space power station energy management system includes: a plurality of photovoltaic arrays, a DC bus, a plurality of IPOS boost modules, a plurality of ISOP buck modules, and a plurality of microwave transmitting arrays; each photovoltaic array is respectively connected to each of the IPOS boost modules, each of the IPOS boost modules is respectively connected to each of the ISOP buck modules through the DC bus, and each of the ISOP buck modules is respectively connected to each of the microwave transmitting arrays; the input voltage is generated by each of the photovoltaic arrays; The boost control module is used to perform boost control on each IPOS boost module based on the input voltage and the preset three-loop control strategy to obtain a boost output; The step-down control module is used to transmit each boost output to the corresponding ISOP step-down module through the DC bus for step-down control to obtain a step-down output; The power supply module is used to control the power supply of the corresponding microwave transmitting array based on the stepped-down output.
9. A computer terminal device, characterized in that: It includes a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, and when the processor executes the computer program, it implements a control method for a space power station energy management system as described in any one of claims 1 to 7.
10. A computer-readable storage medium, characterized in that: The computer-readable storage medium includes a stored computer program, wherein when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute a control method for a space power station energy management system as described in any one of claims 1 to 7.