Method and device for modeling energy system of near space solar-powered aircraft

Abstract

The application relates to the technical field of energy management and scheduling of an aircraft energy system, and provides a near-space solar aircraft energy system modeling method and device. The method comprises the following steps: determining a maximum power point voltage based on the voltage-current response characteristics of a solar cell model under target environmental parameters; determining a target working mode and working parameters of a power supply controller model according to the state information of a high-voltage bus and the maximum power point voltage; determining the power characteristics of the solar cell model according to the target working mode and working parameters, and updating the solar cell model based on the power characteristics; and determining an energy system simulation model of a near-space solar aircraft based on the power supply controller model, a solar radiation model, an energy storage battery model, a load model and the updated solar cell model. The application can truly reflect the voltage-current characteristics of the aircraft energy system while ensuring high simulation efficiency.

Description

Technical Field

[0001] This application relates to the field of energy management and scheduling technology for aircraft energy systems, and in particular to a modeling method and apparatus for a near-space solar-powered aircraft energy system. Background Technology

[0002] Near-space solar-powered vehicles (SWPVs) exhibit significant advantages over traditional aerospace vehicles due to their long endurance, wide coverage area, and high payload capacity. To achieve the mission objective of long-endurance, day-and-night flight for SWPVs, efficient energy management and scheduling strategies are essential to ensure stable system operation. Constructing a precise virtual simulation environment for the SWPV energy system is the foundation and prerequisite for studying such management and scheduling strategies.

[0003] Currently, existing modeling methods for near-space vehicle energy systems face numerous limitations and challenges in practical applications. On the one hand, vehicle energy systems involve complex dynamic processes, control logic, and multiple interconnected subsystems. Near space also faces extreme environments such as low air pressure, strong radiation, frequent atmospheric discharges, and drastic diurnal temperature variations. Traditional modeling methods struggle to accurately depict these complex relationships and simulate the adverse effects of these extreme environments on the performance of various system modules. On the other hand, introducing the current-voltage (IV) characteristic of solar cells into the traditional framework necessitates the development of a complex maximum power point tracking (MPPT) algorithm for output regulation, significantly increasing the computational load and reducing simulation efficiency. Therefore, most existing modeling methods fail to consider the IV characteristics of solar cells, typically describing their role in the energy system solely through photoelectric conversion efficiency, focusing only on power generation. This severely neglects the actual impact of the dynamic current and voltage output of solar cells on the entire vehicle energy system.

[0004] Therefore, it is of great significance to solve the technical problem that existing near-space vehicle energy system modeling methods cannot balance simulation accuracy and computational efficiency, and to achieve both realistic reflection of the voltage and current characteristics of the vehicle's energy system and high simulation efficiency. Summary of the Invention

[0005] This application provides a modeling method and apparatus for a near-space solar-powered aircraft energy system, which solves the technical problem that existing near-space aircraft energy system modeling methods cannot balance simulation accuracy and computational efficiency, and achieves both realistic reflection of the voltage and current characteristics of the solar-powered aircraft energy system and high simulation efficiency.

[0006] In a first aspect, this application provides a modeling method for an energy system of a near-space solar-powered aircraft, the method comprising: Construct power controller models, solar cell models, solar irradiance models, energy storage battery models, and load models; Based on the voltage and current response characteristics of the solar cell model under target environmental parameters, the maximum power point voltage is determined. Based on the status information of the high-voltage bus and the voltage at the maximum power point, determine the target operating mode and operating parameters of the power controller model; Based on the target operating mode and operating parameters, the power characteristics of the solar cell model are determined, and the solar cell model is updated based on the power characteristics. Based on the power controller model, solar irradiance model, energy storage battery model, load model, and updated solar cell model, the energy system simulation model of the near-space solar-powered spacecraft is determined.

[0007] Optionally, according to the near-space solar-powered vehicle energy system modeling method of this application, the state information of the high-voltage bus includes the bus voltage and the bus current; the operating parameters include the voltage value at the output terminal of the power controller model, the current value at the output terminal of the power controller model, and the voltage value at the input terminal of the power controller model. The step of determining the target operating mode and operating parameters of the power controller model based on the status information of the high-voltage bus and the maximum power point voltage includes: When the bus voltage is greater than or equal to the preset voltage value, the target operating mode is determined to be constant voltage mode, and the voltage value at the output terminal of the power controller model is maintained at the preset voltage value. If the bus current is greater than or equal to the preset current value, the target operating mode is determined to be constant current mode, and the current value at the output terminal of the power controller model is maintained at the preset current value. When the bus voltage is less than the preset voltage value and the bus current is less than the preset current value, the target operating mode is determined to be the maximum power point tracking (MPPT) mode, and the voltage value at the input terminal of the power controller model is maintained at the maximum power point voltage.

[0008] Optionally, according to the near-space solar-powered aircraft energy system modeling method of this application, the solar cell model is a five-parameter solar cell model; The determination of the maximum power point voltage based on the voltage and current response characteristics of the solar cell model under target environmental parameters includes: Based on the equivalent circuit parameters and target environmental parameters of the five-parameter solar cell model, determine the equivalent resistance at the maximum power point; Based on the voltage and current response characteristics of the five-parameter solar cell model under the target environmental parameters and the equivalent resistance at the maximum power point, the maximum power point voltage is determined. The equivalent circuit parameters include at least one of the following: photocurrent parameters, reverse saturation current parameters, diode influence factor parameters, series resistance parameters, and parallel resistance parameters.

[0009] Optionally, according to the near-space solar-powered vehicle energy system modeling method of this application, the method further includes: The output terminal of the power controller model is connected to a preset resistor; The preset resistor is used to characterize the wire resistance at the output terminal of the power controller model.

[0010] Optionally, according to the near-space solar-powered aircraft energy system modeling method of this application, the construction of the power controller model includes: The power loss of the power controller model is determined based on the voltage value at the input terminal of the power controller model, the current value at the input terminal of the power controller model, and the conversion efficiency of the power controller model. A power controller model is constructed based on the voltage value at the input terminal of the power controller model, the current value at the input terminal of the power controller model, the voltage value at the output terminal of the power controller model, the current value at the output terminal of the power controller model, and the power loss of the power controller model.

[0011] Optionally, according to the near-space solar-powered aircraft energy system modeling method of this application, the target environmental parameters include at least one of solar irradiance, flight attitude, and solar cell temperature.

[0012] Secondly, this application also provides a near-space solar-powered aircraft energy system modeling device, the device comprising: The building module is used to build power controller models, solar cell models, solar irradiance models, energy storage battery models, and load models; The first determining module is used to determine the maximum power point voltage based on the voltage and current response characteristics of the solar cell model under target environmental parameters. The second determining module is used to determine the target operating mode and operating parameters of the power controller model based on the status information of the high-voltage bus and the maximum power point voltage. An update module is used to determine the power characteristics of the solar cell model based on the target operating mode and operating parameters, and update the solar cell model based on the power characteristics; The third determination module is used to determine the energy system simulation model of the near-space solar-powered aircraft based on the power controller model, solar irradiance model, energy storage battery model, load model, and the updated solar cell model.

[0013] Thirdly, this application provides an electronic device, including 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 near-space solar-powered vehicle energy system modeling method as described in the first aspect above.

[0014] Fourthly, this application provides a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the near-space solar-powered vehicle energy system modeling method as described in the first aspect above.

[0015] Fifthly, this application also provides a computer program product, including a computer program that, when executed by a processor, implements the near-space solar-powered vehicle energy system modeling method as described in the first aspect above.

[0016] This application provides a modeling method and apparatus for the energy system of a near-space solar-powered aircraft. By analyzing the voltage and current response characteristics of a solar cell model under target environmental parameters, the maximum power point voltage (MPPT) is determined. Based on the state information of the high-voltage bus and the MPPT, the target operating mode and operating parameters of the power controller model are determined. This method and apparatus achieve joint modeling of the solar cell model and the power controller model, eliminating the need to run complex MPPT algorithms during simulation, significantly simplifying the computational load and improving simulation efficiency. Furthermore, the power characteristics of the solar cell model are updated using the target operating mode and operating parameters. Based on the power controller model, solar irradiance model, energy storage battery model, load model, and the updated solar cell model, the simulation model of the near-space solar-powered aircraft's energy system is determined. This method and apparatus solve the technical problem of existing near-space aircraft energy system modeling methods struggling to balance simulation accuracy and computational efficiency, realistically reflecting the voltage and current characteristics of the aircraft's energy system while ensuring high simulation efficiency. Attached Figure Description

[0017] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0018] Figure 1 This is a flowchart illustrating the near-space solar-powered aircraft energy system modeling method provided in this application.

[0019] Figure 2 This is an example diagram illustrating the interaction between the power controller model and the solar cell model provided in this application.

[0020] Figure 3 This is an example diagram of the five-parameter solar cell model provided in this application.

[0021] Figure 4 This is an example diagram of the power controller model provided in this application.

[0022] Figure 5 This is a schematic diagram of the near-space solar-powered aircraft energy system modeling device provided in this application.

[0023] Figure 6 This is a schematic diagram of the structure of the electronic device provided in this application. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0025] Figure 1 This is a flowchart illustrating the near-space solar-powered aircraft energy system modeling method provided in this application, as shown below. Figure 1 As shown, the method may include: Step 110: Construct the power controller model, solar cell model, solar irradiance model, energy storage battery model, and load model; Step 120: Determine the maximum power point voltage based on the voltage and current response characteristics of the solar cell model under the target environmental parameters; Step 130: Based on the status information of the high-voltage bus and the voltage at the maximum power point, determine the target operating mode and operating parameters of the power controller model; Step 140: Determine the power characteristics of the solar cell model based on the target operating mode and operating parameters, and update the solar cell model based on the power characteristics; Step 150: Based on the power controller model, solar irradiance model, energy storage battery model, load model, and updated solar cell model, construct a simulation model of the energy system of the near-space solar-powered aircraft.

[0026] It should be noted that the execution entity of the aforementioned near-space solar-powered vehicle energy system modeling method can be a computer device. Specifically, this computer device can be a server, simulation workstation, desktop computer, laptop computer, or dedicated equipment loaded with energy system simulation modeling software, etc. This application does not impose specific limitations in this regard.

[0027] Unless otherwise specified, the following embodiments use a computer device as the execution subject to illustrate the near-space solar-powered aircraft energy system modeling method of this application.

[0028] A power controller model refers to a model used to control and schedule energy flow, voltage conversion, and operating point in a simulated aircraft energy system. For example, a power controller model can be a DC / DC (Direct Current / Direct Current) converter model; it can also be other power electronic regulator models with power control and mode switching functions. This application does not specifically limit its scope.

[0029] A solar cell model refers to a model used to characterize the electrical output behavior and power characteristics of a solar cell array under specific environmental conditions. For example, a solar cell model can be a mechanistic model based on IV characteristics; it can also be a black-box model based on fitting measured data. This application does not specifically limit this.

[0030] It is understandable that the output characteristics of solar cell models are affected by target environmental parameters, and different target environmental parameters correspond to different model parameters.

[0031] A solar irradiance model refers to a model used to simulate the intensity of external solar radiation received by a near-space solar-powered spacecraft in complex environments. For example, a solar irradiance model can be a theoretical irradiance model calculated based on parameters such as flight time, latitude and longitude, flight attitude, and altitude; it can also be an empirical model corrected using meteorological data. This application does not impose specific limitations on this.

[0032] An energy storage battery model refers to a mathematical or physical model used to characterize the electrical response and state changes of energy storage devices inside near-space solar-powered aircraft during charging and discharging. For example, an energy storage battery model can be an equivalent circuit model of a lithium-ion battery; it can also be a state-of-charge estimation model based on the ampere-hour integration method. This application does not impose specific limitations on this.

[0033] A load model refers to a model used to simulate the power consumption characteristics of various electrical devices and payloads of a near-space solar-powered aircraft. For example, a load model can be a constant power load model; it can also be a variable power load model that dynamically changes with flight phases and mission scheduling. This application does not impose specific limitations on this.

[0034] Target environmental parameters refer to environmental parameters that affect the photoelectric conversion and operating status of solar cells. For example, target environmental parameters can be solar irradiance; they can also be flight attitude or solar cell temperature. This application does not specifically limit these parameters.

[0035] The status information of the high-voltage bus is used to characterize the electrical status and load requirements of the main power supply network for near-space solar-powered aircraft. This application does not specifically limit this.

[0036] The target operating mode refers to the specific control strategy adopted by the power controller model under the current electrical state.

[0037] Specifically, in step 110, based on the topology of the near-space solar-powered vehicle energy system, a power controller model, a solar cell model, a solar irradiance model, an energy storage battery model, and a load model are constructed respectively. These models constitute the foundation of the near-space solar-powered vehicle energy system.

[0038] In step 120, there are electrical interfaces and information interaction interfaces between the solar cell model and the power controller model. The electrical interface is used to transmit voltage and current; the information interaction interface is used to transmit the solar cell's maximum power point voltage and the power controller's target operating mode.

[0039] The target environmental parameters at the current moment are obtained and input into the solar cell model. Based on its own voltage and current response characteristics, the solar cell model determines the maximum power point voltage under the corresponding target environmental parameters.

[0040] In step 130, the solar cell model inputs the determined maximum power point voltage into the power controller model via an information interaction interface. Based on the high-voltage bus status information and the maximum power point voltage, the power controller model determines its target operating mode and operating parameters.

[0041] In step 140, the power controller model outputs the determined target operating mode to the solar cell model through the information interaction interface. The solar cell model then determines its current power characteristics based on this target operating mode and updates accordingly.

[0042] In step 150, the updated solar cell model, combined with the power controller model, solar irradiance model, energy storage battery model, and load model, is used to determine the energy system simulation model of the near-space solar-powered aircraft.

[0043] This application provides a modeling method for the energy system of a near-space solar-powered aircraft. By analyzing the voltage and current response characteristics of a solar cell model under target environmental parameters, the maximum power point voltage (MPPT) is determined. Based on the state information of the high-voltage bus and the MPPT, the target operating mode and operating parameters of the power controller model are determined. This method enables joint modeling of the solar cell model and the power controller model, eliminating the need for additional complex MPPT algorithms during simulation. This significantly simplifies the computational load and improves simulation efficiency. Furthermore, the power characteristics of the solar cell model are updated using the target operating mode and operating parameters. Based on the power controller model, solar irradiance model, energy storage battery model, load model, and the updated solar cell model, the simulation model of the near-space solar-powered aircraft's energy system is determined. This method solves the technical problem of existing near-space aircraft energy system modeling methods struggling to balance simulation accuracy and computational efficiency. It accurately reflects the voltage and current characteristics of the aircraft's energy system while ensuring high simulation efficiency.

[0044] In one embodiment, the target environmental parameters include at least one of solar irradiance, flight attitude, and solar cell temperature.

[0045] Specifically, solar irradiance refers to the energy power of solar radiation projected onto a specific area. For example, solar irradiance can be the intensity of direct solar radiation in a near-space environment; it can also be the intensity of scattered radiation after reflection from clouds or the atmosphere. This application does not specifically limit this.

[0046] Flight attitude refers to the three-dimensional orientation of an aircraft in space. For example, flight attitude can be the pitch angle, yaw angle, or roll angle of an aircraft. This application does not specifically limit this.

[0047] The solar cell temperature refers to the actual physical temperature of the solar cell model during operation. For example, the solar cell temperature can be a high temperature state after being heated by strong radiation; it can also be a low temperature state under frequent atmospheric discharge and at night when the side is in shadow. This application does not make a specific limitation in this regard.

[0048] Figure 2 This is an example diagram illustrating the interaction between the power controller model and the solar cell model provided in this application, such as... Figure 2 As shown, the three solid triangles represent "solar irradiance," "flight attitude," and "solar cell temperature," respectively. These three parameters change dynamically depending on the actual environment of the solar-powered spacecraft in near space. Furthermore, the solar cell model receives operating mode commands from the power controller to determine the current power characteristics.

[0049] In terms of interface connection, the output end of the solar cell model and the input end of the power controller model are deeply integrated. The right side of the solar cell model and the left side of the power controller model are physically and electrically connected through interfaces with "+" (positive) and "-" (negative) terminals. Simultaneously, a bidirectional information closed-loop feedback loop is formed. That is, after the solar cell model calculates the maximum power point voltage based on the current target environmental parameters, it feeds this maximum power point voltage back to the power controller model as information input. The core function of the power controller model is to control the operating point of the solar cell model at the input end and maintain consistency with the high-voltage bus voltage at the output end. In other words, the power controller model determines the target operating mode by judging the state of the output end (i.e., the bus side) and feeds this target operating mode back to the solar cell model, thereby achieving overall energy scheduling and closed-loop control.

[0050] In one embodiment, the status information of the high-voltage bus includes the bus voltage and the bus current; the operating parameters include the voltage value at the output terminal of the power controller model, the current value at the output terminal of the power controller model, and the voltage value at the input terminal of the power controller model. Based on the status information of the high-voltage bus and the voltage at the maximum power point, the target operating mode and operating parameters of the power controller model are determined, including: When the bus voltage is greater than or equal to the preset voltage value, the target operating mode is determined to be constant voltage mode, and the voltage value at the output of the power controller model is maintained at the preset voltage value. When the bus current is greater than or equal to the preset current value, the target operating mode is determined to be constant current mode, and the current value at the output of the power controller model is kept at the preset current value. When the bus voltage is less than the preset voltage value and the bus current is less than the preset current value, the target operating mode is determined to be MPPT mode, and the voltage value at the input terminal of the power controller model is kept at the maximum power point voltage.

[0051] Specifically, the preset voltage value refers to the maximum voltage value that the bus can withstand. The preset voltage value can be determined by the maximum bus voltage; it can also be determined by the battery charging cut-off voltage. This application does not specifically limit it in this regard.

[0052] The preset current value refers to the maximum current value that the system is allowed to output. The preset current value can be determined by the rated output power of the power controller; it can also be determined by the maximum charging power. This application does not specifically limit it in this regard.

[0053] Specifically, to balance the power generation efficiency of the solar cell model with the safety of the bus power supply, different target operating modes need to be set and switched. For example, when the solar-powered aircraft is in extreme environments, sudden changes in sunlight or load unloading can cause the bus to face overvoltage or overcurrent risks. If maximum power output is continued, it will lead to overcharging of the energy storage battery or damage to the bus. Therefore, this application sets three operating modes: constant voltage, constant current, and MPPT. Through logical determination of the bus state, the solution stability and simulation efficiency are significantly improved while ensuring power supply safety and avoiding overcharging.

[0054] Optionally, if the bus voltage is greater than or equal to a preset voltage value, the target operating mode is determined to be constant voltage mode. In this case, the core control logic of the power controller limits the voltage, maintaining the voltage value at the output of the power controller model at the preset voltage value. The preset voltage value can be the maximum voltage that the bus can withstand; alternatively, it can be determined by the battery charging cut-off voltage.

[0055] Optionally, if the bus current is greater than or equal to a preset current value, the target operating mode is determined to be constant current mode. In this case, the core control logic of the power controller limits the current, maintaining the current value at the output of the power controller model at the preset current value. The preset current value can be determined by the rated output power of the power controller or by the maximum charging power.

[0056] Optionally, if the bus voltage is less than a preset voltage value and the bus current is less than a preset current value, the target operating mode is determined to be Maximum Power Point Tracking (MPPT) mode. In this case, the voltage value at the input terminal of the power controller model is maintained at the maximum power point voltage.

[0057] The near-space solar-powered aircraft energy system modeling method provided in this application enters constant voltage mode when the bus voltage is greater than or equal to a preset voltage value; enters constant current mode when the bus current is greater than or equal to a preset current value; and determines the target operating mode as MPPT mode when the bus voltage is less than the preset voltage value and the bus current is less than the preset current value. This method can accurately simulate the dynamic response and self-protection mechanism under different operating conditions, and achieves rapid switching between multiple operating modes without complex algorithms. While maintaining simulation accuracy, it greatly simplifies the computation and improves simulation efficiency.

[0058] In one embodiment, the solar cell model is a five-parameter solar cell model; Based on the voltage and current response characteristics of a solar cell model under target environmental parameters, the maximum power point voltage is determined, including: Based on the equivalent circuit parameters and target environmental parameters of the five-parameter solar cell model, determine the equivalent resistance at the maximum power point; Based on the voltage and current response characteristics of a five-parameter solar cell model under target environmental parameters and the equivalent resistance at the maximum power point, the maximum power point voltage is determined.

[0059] The equivalent circuit parameters include at least one of the following: photocurrent parameters, reverse saturation current parameters, diode influence factor parameters, series resistance parameters, and parallel resistance parameters.

[0060] Specifically, the five-parameter solar cell model refers to an equivalent circuit virtual simulation model built based on five key circuit parameters to simulate the power generation characteristics of real physical components. For example, the five-parameter solar cell model can be a photoelectric response model used to simulate the solar cell array on the wing of a near-space solar-powered aircraft under extreme environments; it can also be a standard photovoltaic module simulation model applied to energy systems of other complex aerospace vehicles. This application does not specifically limit it in this regard.

[0061] Equivalent circuit parameters are the core variables that determine the output characteristics of a five-parameter solar cell model.

[0062] Figure 3 This is an example diagram of the five-parameter solar cell model provided in this application, such as... Figure 3 As shown, Represents the parameters of photogenerated current. Indicates the reverse saturation current parameter. This represents the diode's influence factor parameter. Indicates the series resistance parameter. The parallel resistance parameter is represented. The output characteristics of the five-parameter solar cell model are determined by at least one of the following: photocurrent parameter, reverse saturation current parameter, diode influence factor parameter, series resistance parameter, and parallel resistance parameter. Furthermore, the output characteristics of the five-parameter solar cell model are directly affected by the target environmental parameters; different target environmental parameters will correspond to different equivalent circuit parameters.

[0063] Based on the actual target environmental parameters, the corresponding equivalent circuit parameters are obtained, and then the equivalent resistance at the maximum power point is calculated and determined. The calculation process of the equivalent resistance at the maximum power point is shown in formula (1): Formula (1) in, Represents the equivalent resistance at the maximum power point; Indicates the parameters of photogenerated current; Indicates the reverse saturation current parameter; This represents the diode's influence factor parameter; Indicates the series resistance parameter; Indicates the parameters of the parallel resistors; This refers to an intermediate parameter calculated based on temperature, which can be called thermal voltage. Indicates the temperature of the solar cell; Expressed as the electron charge constant, usually as ; This represents the Boltzmann constant, usually expressed as . .

[0064] After accurately determining the equivalent resistance at the maximum power point, the voltage at the maximum power point is calculated based on the voltage and current response characteristics of the five-parameter solar cell model under the target environmental parameters, according to formula (2): Formula (2) in, This represents the voltage at the maximum power point.

[0065] The near-space solar-powered vehicle energy system modeling method provided in this application determines the equivalent resistance at the maximum power point through the equivalent circuit parameters of the five-parameter solar cell model. This method can accurately quantify the dynamic changes inside the solar cell under target environmental parameters. Furthermore, based on the voltage and current response characteristics of the five-parameter solar cell model under target environmental parameters and the equivalent resistance at the maximum power point, the maximum power point voltage is determined. This method can realistically reflect the voltage and current characteristics of the vehicle energy system while ensuring high simulation efficiency.

[0066] In one embodiment, the method further includes: A preset resistor is connected to the output terminal of the power controller model. The preset resistor is used to characterize the wire resistance at the output terminal of the power controller model.

[0067] Specifically, the preset resistor is implemented using an equivalent electronic component with an extremely small fixed resistance value. For example, the preset resistor could be a virtual resistor module with a resistance value of 0.00008 ohms; it could also be a tiny resistance component precisely calculated based on the material and length of the actual aircraft's physical wires. This application does not impose any specific limitations on this.

[0068] The resistance of a conductor refers to the inherent parasitic resistance of the physical wiring connecting electrical components in a solar-powered aircraft energy system. For example, conductor resistance can be the resistance of a metal cable that generates a small voltage drop when transmitting a large current; it can also be the distributed resistance of interconnecting conductors between different modules. This application does not specifically limit this.

[0069] Specifically, to accurately depict the complex control logic and multiple interconnected subsystems within the aircraft's energy system, the main architecture of the power controller model consists of a DC-DC (Direct Current / Direct Current) control algorithm, electrical interfaces, and information interaction interfaces. A preset resistor with an extremely small resistance is connected in series at the output of the power controller model. The core function of this preset resistor is to realistically simulate the resistance of the output wires in the physical world.

[0070] Understandably, in the complex operating conditions of near-space solar-powered aircraft flying for extended periods day and night, neglecting the impedance of physical circuits in the simulation model would lead to singular or infinitely iterative numerical results in the circuit voltage calculations. Therefore, this preset resistor is an essential part of the entire power controller model; without it, a stable solution for the solar-powered aircraft's energy system cannot be achieved.

[0071] The near-space solar-powered vehicle energy system modeling method provided in this application connects a preset resistor to the output terminal of the power controller model, enabling the method to achieve an accurate equivalent expression of the wire resistance. This effectively avoids the distortion of the simulation model caused by ignoring physical line losses, and significantly improves the robustness and computational efficiency of the near-space solar-powered vehicle energy system simulation model.

[0072] In one embodiment, constructing a power controller model includes: The power loss of the power controller model is determined based on the voltage value at the input terminal of the power controller model, the current value at the input terminal of the power controller model, and the conversion efficiency of the power controller model. A power controller model is constructed based on the voltage and current values ​​at the input terminals, the voltage and current values ​​at the output terminals, and the power loss of the power controller model.

[0073] Specifically, the conversion efficiency of a power controller model refers to the proportion of power that the power controller effectively converts into power at the output during operation.

[0074] Power loss refers to the power dissipation that a power controller cannot transmit to the output due to internal losses during energy transmission and operating mode switching.

[0075] Specifically, firstly, the power loss of the power controller model is determined based on the voltage and current values ​​at the input terminals of the power controller model and the conversion efficiency of the power controller model. This power loss is related to the voltage and current values ​​at the input terminals of the power controller model and can be expressed by formula (3): Formula (3) in, This represents the power loss of the power controller model; This indicates the conversion efficiency of the power controller model; This represents the voltage value at the input terminal of the power controller model; This represents the current value at the input terminal of the power controller model.

[0076] Next, based on the power balance relationship between the input and output ports of the power controller model, and combining the voltage and current values ​​at the input, output, and power losses of the power controller model, a power controller model is constructed. The power controller model can be implemented using a two-port model. The power balance relationship satisfied by the power controller model is shown in equation (4): Formula (4) in, This represents the current value at the output of the power controller model; This represents the voltage value at the output terminal of the power controller model.

[0077] Figure 4 This is an example diagram of the power controller model provided in this application, such as... Figure 4 As shown, if the implementation process of different MPPT algorithms is not considered, the power controller can be simplified to a DC / DC converter and control strategy, and implemented using a two-port model. Specifically, the DCDC module in the figure represents the core DC-DC conversion logic and control algorithm, which is used to realize voltage conversion and power balance between the input and output terminals of the power controller model; Figure 4 The left side represents the input terminal of the power controller model. i1 represents the input current, which is the DC current flowing from the solar cell model into the power controller model. p1 represents the positive terminal electrical interface, which is used to connect to the positive terminal of the five-parameter solar cell model. n1 represents the negative terminal electrical interface, which is used to connect to the negative terminal of the five-parameter solar cell model. Figure 4The right side represents the output terminal of the power controller model. i2 represents the output current, which is the DC current flowing from the power controller model to the high-voltage bus side. p2 represents the positive terminal electrical interface of the output terminal, which is used to connect to the positive terminal of the high-voltage bus side. n2 represents the negative terminal electrical interface of the output terminal, which is used to connect to the negative terminal of the high-voltage bus side. resistor represents the preset resistor located at the positive terminal of the power controller model output terminal, with a resistance value of 0.00008 ohms.

[0078] The method for constructing a power controller model provided in this application determines the power loss of the power controller model by using the voltage and current values ​​at the input terminals of the power controller model and the preset conversion efficiency of the power controller model. This method enables accurate quantification of the dynamic losses within the power controller model, avoiding errors caused by idealized models. Furthermore, the power controller model is constructed using the voltage and current values ​​at the input terminals of the power controller model, the voltage and current values ​​at the output terminals of the power controller model, and the power loss of the power controller model. This method enables the simulation of the power controller based on the power balance equivalence relationship without the need to build a complex MPPT algorithm, greatly simplifying the computational workload of energy system simulation models.

[0079] The following describes the near-space solar-powered vehicle energy system modeling device provided in this application. The near-space solar-powered vehicle energy system modeling device described below can be referred to in correspondence with the near-space solar-powered vehicle energy system modeling method described above, and can achieve the same technical effect. It will not be repeated here.

[0080] Figure 5 This is a schematic diagram of the structure of the near-space solar-powered aircraft energy system modeling device provided in this application, such as... Figure 5 As shown, the device may include: Module 510 is used to build power controller models, solar cell models, solar irradiance models, energy storage battery models, and load models. The first determining module 520 is used to determine the maximum power point voltage based on the voltage and current response characteristics of the solar cell model under target environmental parameters. The second determining module 530 is used to determine the target operating mode and operating parameters of the power controller model based on the status information of the high-voltage bus and the maximum power point voltage. The update module 540 is used to determine the power characteristics of the solar cell model according to the target working mode and working parameters, and update the solar cell model based on the power characteristics; The third determining module 550 is used to determine the energy system simulation model of the near-space solar-powered vehicle based on the power controller model, solar irradiance model, energy storage battery model, load model, and the updated solar cell model.

[0081] In one embodiment, the status information of the high-voltage bus includes bus voltage and bus current; the operating parameters include the voltage value at the output terminal of the power controller model, the current value at the output terminal of the power controller model, and the voltage value at the input terminal of the power controller model. The second determining module 530 is specifically used for: When the bus voltage is greater than or equal to the preset voltage value, the target operating mode is determined to be constant voltage mode, and the voltage value at the output terminal of the power controller model is maintained at the preset voltage value. If the bus current is greater than or equal to the preset current value, the target operating mode is determined to be constant current mode, and the current value at the output terminal of the power controller model is maintained at the preset current value. When the bus voltage is less than the preset voltage value and the bus current is less than the preset current value, the target operating mode is determined to be the maximum power point tracking (MPPT) mode, and the voltage value at the input terminal of the power controller model is maintained at the maximum power point voltage.

[0082] In one embodiment, the solar cell model is a five-parameter solar cell model; The first determining module 520 is specifically used for: Based on the equivalent circuit parameters and target environmental parameters of the five-parameter solar cell model, determine the equivalent resistance at the maximum power point; Based on the voltage and current response characteristics of the five-parameter solar cell model under the target environmental parameters and the equivalent resistance at the maximum power point, the maximum power point voltage is determined. The equivalent circuit parameters include at least one of the following: photocurrent parameters, reverse saturation current parameters, diode influence factor parameters, series resistance parameters, and parallel resistance parameters.

[0083] In one embodiment, the method further includes: The output terminal of the power controller model is connected to a preset resistor; The preset resistor is used to characterize the wire resistance at the output terminal of the power controller model.

[0084] In one embodiment, the construction module 510 is specifically used for: The power loss of the power controller model is determined based on the voltage value at the input terminal of the power controller model, the current value at the input terminal of the power controller model, and the conversion efficiency of the power controller model. A power controller model is constructed based on the voltage value at the input terminal of the power controller model, the current value at the input terminal of the power controller model, the voltage value at the output terminal of the power controller model, the current value at the output terminal of the power controller model, and the power loss of the power controller model.

[0085] In one embodiment, the target environmental parameters include at least one of solar irradiance, flight attitude, and solar cell temperature.

[0086] Figure 6 This is a schematic diagram of the structure of the electronic device provided in this application, such as... Figure 6 As shown, the electronic device may include: a processor 610, a communications interface 620, a memory 630, and a communication bus 640, wherein the processor 610, the communications interface 620, and the memory 630 communicate with each other via the communication bus 640. The processor 610 can call logical instructions in the memory 630 to execute the near-space solar-powered vehicle energy system modeling method described in any of the above embodiments, for example including: Construct power controller models, solar cell models, solar irradiance models, energy storage battery models, and load models; Based on the voltage and current response characteristics of the solar cell model under target environmental parameters, the maximum power point voltage is determined. Based on the status information of the high-voltage bus and the voltage at the maximum power point, determine the target operating mode and operating parameters of the power controller model; Based on the target operating mode and operating parameters, the power characteristics of the solar cell model are determined, and the solar cell model is updated based on the power characteristics. Based on the power controller model, solar irradiance model, energy storage battery model, load model, and updated solar cell model, the energy system simulation model of the near-space solar-powered spacecraft is determined.

[0087] Furthermore, the logical instructions in the aforementioned memory 630 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0088] On the other hand, this application also provides a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, is implemented to perform the near-space solar-powered vehicle energy system modeling method provided by the above methods, the method comprising: Construct power controller models, solar cell models, solar irradiance models, energy storage battery models, and load models; Based on the voltage and current response characteristics of the solar cell model under target environmental parameters, the maximum power point voltage is determined. Based on the status information of the high-voltage bus and the voltage at the maximum power point, determine the target operating mode and operating parameters of the power controller model; Based on the target operating mode and operating parameters, the power characteristics of the solar cell model are determined, and the solar cell model is updated based on the power characteristics. Based on the power controller model, solar irradiance model, energy storage battery model, load model, and updated solar cell model, the energy system simulation model of the near-space solar-powered spacecraft is determined.

[0089] Furthermore, this application also provides a computer program product, which includes a computer program that can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer is able to execute the near-space solar-powered vehicle energy system modeling method provided by the above methods, the method comprising: Construct power controller models, solar cell models, solar irradiance models, energy storage battery models, and load models; Based on the voltage and current response characteristics of the solar cell model under target environmental parameters, the maximum power point voltage is determined. Based on the status information of the high-voltage bus and the voltage at the maximum power point, determine the target operating mode and operating parameters of the power controller model; Based on the target operating mode and operating parameters, the power characteristics of the solar cell model are determined, and the solar cell model is updated based on the power characteristics. Based on the power controller model, solar irradiance model, energy storage battery model, load model, and updated solar cell model, the energy system simulation model of the near-space solar-powered spacecraft is determined.

[0090] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0091] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0092] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. A modeling method for the energy system of a near-space solar-powered aircraft, characterized in that, The method includes: Construct power controller models, solar cell models, solar irradiance models, energy storage battery models, and load models; Based on the voltage and current response characteristics of the solar cell model under target environmental parameters, the maximum power point voltage is determined. Based on the status information of the high-voltage bus and the voltage at the maximum power point, determine the target operating mode and operating parameters of the power controller model; Based on the target operating mode and operating parameters, the power characteristics of the solar cell model are determined, and the solar cell model is updated based on the power characteristics. Based on the power controller model, solar irradiance model, energy storage battery model, load model, and updated solar cell model, the energy system simulation model of the near-space solar-powered spacecraft is determined.

2. The near-space solar-powered aircraft energy system modeling method according to claim 1, characterized in that, The status information of the high-voltage bus includes the bus voltage and the bus current; the operating parameters include the voltage value at the output terminal of the power controller model, the current value at the output terminal of the power controller model, and the voltage value at the input terminal of the power controller model. The step of determining the target operating mode and operating parameters of the power controller model based on the status information of the high-voltage bus and the maximum power point voltage includes: When the bus voltage is greater than or equal to the preset voltage value, the target operating mode is determined to be constant voltage mode, and the voltage value at the output terminal of the power controller model is maintained at the preset voltage value. If the bus current is greater than or equal to the preset current value, the target operating mode is determined to be constant current mode, and the current value at the output terminal of the power controller model is maintained at the preset current value. When the bus voltage is less than the preset voltage value and the bus current is less than the preset current value, the target operating mode is determined to be the maximum power point tracking (MPPT) mode, and the voltage value at the input terminal of the power controller model is maintained at the maximum power point voltage.

3. The near-space solar-powered aircraft energy system modeling method according to claim 1, characterized in that, The solar cell model is a five-parameter solar cell model; The determination of the maximum power point voltage based on the voltage and current response characteristics of the solar cell model under target environmental parameters includes: Based on the equivalent circuit parameters and target environmental parameters of the five-parameter solar cell model, determine the equivalent resistance at the maximum power point; Based on the voltage and current response characteristics of the five-parameter solar cell model under the target environmental parameters and the equivalent resistance at the maximum power point, the maximum power point voltage is determined. The equivalent circuit parameters include at least one of the following: photocurrent parameters, reverse saturation current parameters, diode influence factor parameters, series resistance parameters, and parallel resistance parameters.

4. The near-space solar-powered aircraft energy system modeling method according to claim 1, characterized in that, Also includes: The output terminal of the power controller model is connected to a preset resistor; The preset resistor is used to characterize the wire resistance at the output terminal of the power controller model.

5. The near-space solar-powered aircraft energy system modeling method according to claim 1, characterized in that, The construction of the power controller model includes: The power loss of the power controller model is determined based on the voltage value at the input terminal of the power controller model, the current value at the input terminal of the power controller model, and the conversion efficiency of the power controller model. A power controller model is constructed based on the voltage value at the input terminal of the power controller model, the current value at the input terminal of the power controller model, the voltage value at the output terminal of the power controller model, the current value at the output terminal of the power controller model, and the power loss of the power controller model.

6. The near-space solar-powered aircraft energy system modeling method according to claim 1, characterized in that, The target environmental parameters include at least one of solar irradiance, flight attitude, and solar cell temperature.

7. A modeling device for the energy system of a near-space solar-powered aircraft, characterized in that, The device includes: The building module is used to build power controller models, solar cell models, solar irradiance models, energy storage battery models, and load models; The first determining module is used to determine the maximum power point voltage based on the voltage and current response characteristics of the solar cell model under target environmental parameters. The second determining module is used to determine the target operating mode and operating parameters of the power controller model based on the status information of the high-voltage bus and the maximum power point voltage. An update module is used to determine the power characteristics of the solar cell model based on the target operating mode and operating parameters, and update the solar cell model based on the power characteristics; The third determination module is used to determine the energy system simulation model of the near-space solar-powered aircraft based on the power controller model, solar irradiance model, energy storage battery model, load model, and the updated solar cell model.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and running on the processor, characterized in that, When the processor executes the computer program, it implements the near-space solar-powered vehicle energy system modeling method as described in any one of claims 1 to 6.

9. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the near-space solar-powered vehicle energy system modeling method as described in any one of claims 1 to 6.

10. A computer program product, comprising a computer program, characterized in that, When the computer program is executed by the processor, it implements the near-space solar-powered vehicle energy system modeling method as described in any one of claims 1 to 6.

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