A method for autonomously adjusting the temperature of a satellite solar array and a satellite communication system

Abstract

This application discloses a method for autonomously adjusting the temperature of a satellite solar array and a satellite communication system. The method includes: acquiring the value of a telemetry anomaly flag at the synchrotron point; determining whether the satellite is normal in each orbital cycle based on the value of the telemetry anomaly flag; if normal, determining whether an auxiliary heating circuit activation command has been sent within the orbital cycle; if not, acquiring the current overall satellite status information; determining whether preset conditions for activating the auxiliary heating circuit are met based on the current overall satellite status information; if met, sending an auxiliary heating circuit activation command to activate the heating circuit on the auxiliary heat sink, thereby achieving on-orbit closed-loop temperature control. This application solves the technical problem in the prior art that the system temperature cannot be reduced by adjusting the solar incidence angle.

Description

Technical Field

[0001] This application relates to the field of satellite technology, and in particular to a method for autonomously adjusting the temperature of a satellite solar array and a satellite communication system. Background Technology

[0002] For satellites using integrally mounted solar arrays, the energy source for these solar arrays is crucial. When the satellite is in a solar-facing state with sufficient energy, and the power system operates under stable sunlight after entering the sunlit area, the solar array temperature is higher than that of conventionally deployable solar arrays. This temperature may exceed the operating temperature of the solar array's adhesive layer, potentially leading to on-orbit failure.

[0003] After charging is complete, most of the solar arrays operate in an open-circuit state, making it unavoidable for them to remain in this state due to excess energy supply. Therefore, to reduce the temperature of the solar arrays corresponding to the solar arrays in the satellite's sun-oriented mode, the solar incidence angle can be reduced. However, once the satellite enters normal Earth-oriented mode, constraints such as orbital state and roll traction angle determine the solar incidence conditions and relationships, making it impossible to lower the temperature by reducing the solar incidence angle. This leads to a problem: when the solar incidence angle is large, the overall satellite energy supply exceeds energy consumption. In this case, the solar array is designed with some subarrays operating in an open-circuit state, causing the solar array temperature to rise and exceed the safe temperature range. The satellite needs to increase its energy consumption at this time to achieve overall satellite energy balance, thereby controlling the open-circuit operation of the solar arrays and preventing damage from the increased temperature. Summary of the Invention

[0004] Due to differences in orbit and attitude, as well as varying lighting conditions, the power generation capacity of solar arrays differs. This application aims to achieve adjustable load power. In this embodiment, a heat sink is configured on the conical section of the satellite, and a heating circuit is added to the back of the heat sink. By controlling its switching, the load can be adjusted, actively controlling the satellite's energy consumption capacity, thereby achieving the goal of controlling the operational status of the solar array subarrays.

[0005] In a first aspect, embodiments of this application provide a method for autonomously adjusting the temperature of a satellite solar array. The method includes: acquiring the value of a telemetry anomaly flag at the synchrotron point; determining whether the satellite is normal within each orbital cycle based on the value of the telemetry anomaly flag; if normal, determining whether an auxiliary heating circuit activation command has been sent within the orbital cycle; if not, acquiring the current overall satellite status information; determining whether preset conditions for activating the auxiliary heating circuit are met based on the current overall satellite status information; if met, sending an auxiliary heating circuit activation command to activate the heating circuit on the auxiliary heat sink, thereby achieving on-orbit closed-loop temperature control.

[0006] Optionally, before obtaining the value of the telemetry anomaly flag at the symposium point, the method further includes: calculating the angle between the projection vector of the sun onto the XOZ plane in the coordinate system corresponding to the satellite and the Z-axis; and setting the value of the telemetry anomaly flag at the symposium point based on the angle.

[0007] Optionally, setting the value of the telemetry anomaly flag bit at the meeting point based on the included angle includes: determining whether the included angle is not less than a first preset threshold; if it is not less than, starting a timer to begin timing; if the value of the timer is greater than a second preset threshold within the orbital period, setting the telemetry anomaly flag bit at the meeting point to a first value, wherein the first value indicates the current anomaly.

[0008] Optionally, before calculating the angle between the projection vector of the sun on the XOZ plane in the coordinate system corresponding to the satellite and the Z-axis, the method further includes: receiving a remote control command sent by the ground station, controlling the on-orbit closed-loop temperature control function of the solar cell array to be turned on or off according to the remote control command, and setting an enable flag based on turning the on-orbit closed-loop temperature control function on or off.

[0009] Optionally, the current satellite status information includes the value of the single command transmission flag, the value of the power status flag, and the value of the timer;

[0010] Determining whether the preset conditions for activating the auxiliary heating circuit are met based on the current overall satellite status information includes: obtaining the value of a single command transmission flag, wherein the value of the single command transmission flag is set to a second value indicating that no command to activate the auxiliary heating circuit has been sent; if the value of the single command transmission flag is the second value, obtaining the value of an energy status flag; determining whether the value of the energy status flag is a specified value and whether the value of the timer is not greater than a third preset threshold; if the value of the energy status flag is the specified value and the value of the timer is not greater than the third preset threshold, sending a command to activate the auxiliary heating circuit, thereby activating the heating circuit on the auxiliary heat sink to control the working status of each subarray in the solar cell array;

[0011] Optionally, determining whether the preset conditions for activating the auxiliary heating circuit are met based on the current overall satellite status information further includes: if the value of the single command sending flag is a third value, determining whether the value of the energy status flag is a specified value and whether the value of the timer is greater than a fourth preset threshold, wherein the third value indicates that an activation command for the auxiliary heating circuit has been sent; if the value of the energy status flag is a specified value and the value of the timer is greater than the fourth preset threshold, sending an activation command for the auxiliary heating circuit, thereby shutting down the heating circuit on the auxiliary heat sink and exiting the on-orbit closed-loop temperature control function of the solar cell array.

[0012] Optionally, the power supply output status of each subarray in the solar cell array is obtained, the overall satellite energy balance status is determined based on the power supply output status, and the value of the energy status flag is set based on the overall satellite energy balance status.

[0013] Secondly, this application provides a satellite communication system, which includes a ground station and a satellite; wherein the ground station sends remote control commands to the satellite, wherein the remote control commands instruct the satellite to turn on or off the on-orbit closed-loop temperature control function of the solar cell array;

[0014] The satellite receives the remote control command and executes the method described in the first aspect based on the remote control command.

[0015] Compared with the prior art, the solution provided in this application has at least the following beneficial effects:

[0016] The solution provided in this application embodiment features an autonomous on-board energy balance steady-state closed-loop control system. This system can cool the satellite solar array, preventing it from exceeding the safe temperature range and causing on-orbit failure. Secondly, by utilizing an autonomous power load adjustment method, the on-board energy reaches a steady-state balance, thereby changing the operating state of the solar array. This prevents any subarray from entering open-circuit operation mode during peak solar activity, reducing the risk of its temperature exceeding the safe range due to a sudden increase in heat dissipation caused by prolonged open-circuit time. This ensures the on-orbit reliability of the solar array. Furthermore, the power load adjustment is flexible and variable, meeting the different energy regulation needs of various satellites and improving the control efficiency of satellite energy balance. Attached Figure Description

[0017] Figure 1 The provided diagram illustrates the structure of a satellite communication system according to an embodiment of this application.

[0018] Figure 2 This is a schematic flowchart of a method for autonomously adjusting the temperature of a satellite solar array, provided in an embodiment of this application.

[0019] Figure 3 The relationship between the included angle AlphaFS and the satellite latitude value provided in the embodiments of this application;

[0020] Figure 4 A schematic diagram illustrating the relationship between the angle of sunlight incidence and the heat dissipation of the battery array, provided in an embodiment of this application.

[0021] Figure 5 The following is a logic flowchart of the steady-state closed-loop temperature control provided in the embodiments of this application;

[0022] Figure 6A schematic flowchart illustrating another method for autonomously adjusting the temperature of a satellite solar cell array provided in this application embodiment;

[0023] Figure 7 The graph shows the relationship between heat dissipation and temperature for a solar cell array provided in an embodiment of this application. Detailed Implementation

[0024] The embodiments described in this application are only a part of the embodiments, not all of them. 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] To better understand the above technical solutions, the technical solutions of this application will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments of this application and the specific features in the embodiments are detailed descriptions of the technical solutions of this application, rather than limitations on the technical solutions of this application. In the absence of conflict, the embodiments of this application and the technical features in the embodiments can be combined with each other.

[0026] Figure 1 A schematic diagram of the structure of a satellite communication system provided in an embodiment of this application is shown.

[0027] As an example, in Figure 1 The satellite communication system comprises a ground station and a satellite, which can communicate with each other. To achieve autonomous temperature regulation of the solar arrays corresponding to the solar panels on the satellite, a heat sink is installed on the satellite, with a heating circuit on the heat sink. By controlling the activation or deactivation of the heating circuit, the temperature of the solar arrays is adjusted, actively controlling the satellite's energy consumption and thus achieving the goal of controlling the operational status of the solar array subarrays.

[0028] To ensure consistent temperature control for the satellite's solar arrays under various operating conditions, an autonomous on-orbit closed-loop temperature control function for energy balance and steady-state operation is designed. This function operates on a one-orbit cycle, requiring the satellite to assess its energy status during each cycle and then autonomously adjust the overall satellite energy levels based on the assessment results. When the on-orbit closed-loop temperature control function is activated, the heating circuit can be turned on or off to adjust the solar array's temperature. For example, the activation or deactivation of the on-orbit closed-loop temperature control function can be controlled by a ground station sending remote commands to the satellite, which then activates or deactivates the function accordingly. Figure 1As shown, the satellite includes a satellite computer, a control computer, a power supply slave device, and a payload management unit. The satellite adjusts the temperature of the solar array by controlling the heating circuit to turn on or off through the cooperation of these components. The specific working process of the satellite computer, control computer, power supply slave device, and payload management unit is described below.

[0029] The following description, in conjunction with the accompanying drawings, provides a more detailed explanation of a method for autonomously adjusting the temperature of a satellite solar array provided in this application. The specific implementation of this method may include the following steps (method flow as follows): Figure 2 (as shown)

[0030] Step 201: Obtain the value of the telemetry anomaly flag at the meeting point, and determine whether the satellite is normal in each orbital period based on the value of the telemetry anomaly flag at the meeting point.

[0031] For example, during satellite operation, the satellite's onboard computer at the satellite's operational center sets a rendezvous point telemetry anomaly flag for each orbital cycle. This flag indicates whether the satellite is operating normally within the orbital cycle. For instance, a value of 1 for the rendezvous point telemetry anomaly flag indicates an anomaly, while a value of 0 indicates normal operation.

[0032] As another example, before obtaining the value of the telemetry anomaly flag at the synoptic point, the method further includes: calculating the angle between the projection vector of the sun on the XOZ plane in the coordinate system corresponding to the satellite and the Z-axis; and setting the value of the telemetry anomaly flag at the synoptic point based on the angle.

[0033] Optionally, setting the value of the telemetry anomaly flag bit at the meeting point based on the included angle includes: determining whether the included angle is not less than a first preset threshold; if it is not less than, starting a timer to begin timing; if the value of the timer is greater than a second preset threshold within the orbital period, setting the telemetry anomaly flag bit at the meeting point to a first value, wherein the first value indicates the current anomaly.

[0034] The control computer calculates the angle AlphaFS between the sun's projection vector in the XOZ plane of the satellite's coordinate system and the Z-axis. The control computer then sends telemetry packets, including the AlphaFS parameter, to the satellite's central control computer. Upon receiving the telemetry packets, the central control computer extracts the AlphaFS parameter. If AlphaFS is less than or equal to 0.5, it indicates the peak solar illumination point. The central control computer then resets its internal timer to zero, marking the start of a steady-state closed-loop control cycle. If AlphaFS is greater than 0.5, the timer starts, calculating based on one orbital cycle. For example, 5700 seconds is set as the upper limit of one control cycle. The central control computer sets a solar illumination point telemetry anomaly flag. For instance, when the timer reaches 5700 seconds, the solar illumination point telemetry anomaly flag is set to the value corresponding to an anomaly, indicating an abnormality and exiting the on-orbit closed-loop temperature control function for the solar array. Figure 3 The relationship between the included angle AlphaFS and the satellite latitude value provided in the embodiments of this application is shown.

[0035] As described above, to ensure temperature control of the satellite's solar arrays under various operating conditions, an autonomous on-orbit closed-loop temperature control function for on-board energy balance and steady-state operation is designed. Therefore, before calculating the angle between the projection vector of the sun onto the XOZ plane in the satellite's coordinate system and the Z-axis, the process includes: receiving remote control commands from the ground station, controlling the activation or deactivation of the on-orbit closed-loop temperature control function of the solar array according to the remote control commands, and setting an enable flag based on activating or deactivating the on-orbit closed-loop temperature control function.

[0036] Step 202: If normal, determine whether an auxiliary heating circuit activation command has been sent within the orbital cycle.

[0037] To improve the effectiveness of the heating circuit operation, for example, the heating circuit is controlled to be activated once within each orbital period, meaning that an auxiliary heating circuit activation command has been sent once within the orbital period. Therefore, if the value of the solar telemetry anomaly flag indicates that the satellite is normal within one orbital period, it is determined whether an auxiliary heating circuit activation command has been sent within that orbital period. In this embodiment, the satellite service center computer indicates the status of sending an auxiliary heating circuit activation command by setting a single-path command transmission flag.

[0038] Step 203: If no data is sent, obtain the current status information of the entire satellite.

[0039] For example, the current satellite status information includes the value of the single command transmission flag, the value of the power status flag, and the value of the timer.

[0040] Step 204: Determine whether the preset conditions for activating the auxiliary heating circuit are met based on the current status information of the entire satellite.

[0041] As an example, determining whether the preset conditions for activating the auxiliary heating circuit are met based on the current overall satellite status information includes: obtaining the value of a single command transmission flag, wherein the value of the single command transmission flag is set to a second value indicating that no command to activate the auxiliary heating circuit has been sent; if the value of the single command transmission flag is the second value, obtaining the value of an energy status flag; determining whether the value of the energy status flag is a specified value and whether the value of the timer is not greater than a third preset threshold; if the value of the energy status flag is the specified value and the value of the timer is not greater than the third preset threshold, sending a command to activate the auxiliary heating circuit, thereby activating the heating circuit on the auxiliary heat sink to control the working state of each subarray in the solar cell array;

[0042] As another example, determining whether the preset conditions for activating the auxiliary heating circuit are met based on the current overall satellite status information further includes: if the value of the single command sending flag is a third value, determining whether the value of the energy status flag is a specified value and whether the value of the timer is greater than a fourth preset threshold, wherein the third value indicates that an activation command for the auxiliary heating circuit has been sent; if the value of the energy status flag is a specified value and the value of the timer is greater than the fourth preset threshold, sending an activation command for the auxiliary heating circuit, thereby shutting down the heating circuit on the auxiliary heat sink and exiting the on-orbit closed-loop temperature control function of the solar cell array.

[0043] This application embodiment autonomously adjusts the temperature of the satellite's solar array, specifically by adjusting time thresholds to control the satellite's autonomous closed-loop stability. Two threshold times, T1 (the third preset threshold mentioned above) and T2 (the fourth preset threshold mentioned above), are designed for control. When the shunt of a solar array subarray occurs before T1, the long-term power consumption of the entire satellite is increased; when the open circuit of a solar array subarray occurs after T2, the operating threshold of the entire satellite is decreased. T1 and T2 are related to the solar incidence angle of the solar array. The T1 time point is determined by the thermal control system based on simulation results of the solar array temperature under different operating conditions. The limit is that when a solar array subarray is in an open circuit state, its temperature is still below the allowable value (e.g., 110 degrees Celsius), taking into account the temperature rise caused by the thermal melting of the solar array itself. Considering all these factors, the T1 time point should be determined as close as possible to the synoptic point within the allowable temperature range. Furthermore, for convenient on-orbit management, the determination of the T1 point should cover different operating conditions, i.e., different orbital illumination conditions. The T2 time point is determined based on the energy balance analysis results. It can be determined by comprehensively considering the open-circuit time of a certain array under the maximum allowable load power consumption under different orbital illumination conditions, based on the simulation results of the maximum load power consumption supported by the power system under different orbital illumination conditions. For ease of on-orbit management, the determination of the T2 time point should cover different operating conditions, i.e., different orbital illumination conditions.

[0044] Since the satellite operates in a three-axis stable Earth-oriented attitude and the solar array is a body-mounted wing, the solar array's incident angle is related to the satellite's position in orbit. Since the satellite's orbital altitude and period are given values, the satellite's position in orbit can be determined by the time elapsed since the synodic point. To illustrate the closed-loop temperature control scheme of this application embodiment, a schematic diagram showing the relationship between the solar incident angle and the battery array's heat dissipation is shown below. Figure 4 As shown.

[0045] The satellite mission center's computer determines the open-circuit status flag of a certain subarray of the solar cell array in real time on the satellite. When the flag is 1, it checks the current counter value. If the counter value is less than T1, it sends instruction C1; if the counter value is greater than T2, it sends instruction C2.

[0046] C1: The payload management unit controls the overall satellite power consumption to increase by one level;

[0047] C2: The payload management unit controls the overall satellite power consumption to decrease by one level.

[0048] like Figure 5 As shown, in order to achieve long-term steady-state closed-loop temperature control, the Star Service Center computer sends only one instruction to increase power consumption (as shown below, the instruction to turn on the auxiliary heating circuit) or decrease power consumption (as shown below, the instruction to turn off the auxiliary heating circuit) in each control cycle.

[0049] The specific software flow is as follows: The Star Service Center computer sets a single-channel command transmission flag. If the single-channel command transmission flag is not transmitted, it checks the energy balance flag. If the energy balance flag = BBH and T <= T1, and the command transmission flag is not transmitted, it sends the command "Start Auxiliary Heating Circuit," sets the single-channel command transmission flag to transmitted, and exits. If the energy balance flag = BBH and T > T2, it sends the command "Close Auxiliary Heating Circuit," sets the single-channel command transmission flag to transmitted, and exits. If the single-channel command transmission flag is transmitted, it exits. The Star Service Center computer software flowchart is as follows: Figure 6 As shown.

[0050] Step 205: If the conditions are met, send an auxiliary heating circuit activation command to activate the heating circuit on the auxiliary heat sink, thereby achieving on-orbit closed-loop temperature control.

[0051] The satellite's adjustable long-term power consumption load is achieved through additional heating circuits to meet the power consumption regulation requirements. For example, 14 heating circuits are configured on the heat sink, each consuming 15W, totaling 210W. This, combined with the satellite's conventional long-term power consumption of 325W, amounts to 535W, meeting the aforementioned long-term power consumption requirement of 390W. Therefore, the power consumption regulation is divided into 14 levels. The first level activates heating circuit 1 in an open loop, the second level activates heating circuits 1 and 2 in an open loop, and so on.

[0052] The payload management unit receives instructions from the satellite operations center computer to increase or decrease power consumption and performs satellite power adjustments. The payload management unit is designed to use five instructions to accomplish this function, as shown in the table below:

[0053]

[0054] Complete the following operations according to the instructions sent by the Star Service Center computer:

[0055] (1) When the satellite host receives the instruction to “open one auxiliary heating circuit”, one of the 14 heating circuits will be opened in sequence. The instruction from the satellite host does not specify which circuit to open. The payload management unit needs to make the decision to avoid repeatedly opening the heating circuit that has already been opened.

[0056] (2) When the satellite host receives the instruction to "close one auxiliary heating circuit", the 14 heating circuits will be closed in sequence. The instruction from the satellite host does not specify which circuit to close. The payload management unit will determine this to avoid repeatedly closing heating circuits that have already been closed.

[0057] (3) The payload management unit is equipped with a heating circuit on / off status position to facilitate ground observation of whether the command is executed correctly;

[0058] (4) The effective load management unit needs to set a flag bit to indicate that the load power is insufficient when all 14 heating circuits have been turned on and a command to "turn on one heating circuit" is received. When the load power is less than 14 heating circuits turned on, the flag bit can be cleared to 0.

[0059] (5) The effective load management unit needs to set a flag bit to indicate that the load power is too high when all 14 heating circuits have been turned off and a command to "turn off one heating circuit" is received. When the load power is greater than that of one heating circuit, the flag bit can be cleared to 0.

[0060] (6) It has the function of controlling the simultaneous opening of N heating circuits (N being the absolute number of open circuits) by sending indirect commands from the ground. N=1~14, and the parameters can be modified on the track, increasing the flexibility of ground control.

[0061] The solution provided in this application embodiment features an autonomous on-board energy balance steady-state closed-loop control system. This system can cool the satellite solar array, preventing it from exceeding the safe temperature range and causing on-orbit failure. Secondly, by utilizing an autonomous power load adjustment method, the on-board energy reaches a steady-state balance, thereby changing the operating state of the solar array. This prevents any subarray from entering open-circuit operation mode during peak solar activity, reducing the risk of its temperature exceeding the safe range due to a sudden increase in heat dissipation caused by prolonged open-circuit time. This ensures the on-orbit reliability of the solar array. Furthermore, the power load adjustment is flexible and variable, meeting the different energy regulation needs of various satellites and improving the control efficiency of satellite energy balance.

[0062] To facilitate understanding of the effects of the embodiments of this application, the following description is provided in the form of examples.

[0063] As an example, when the satellite's autonomous on-board energy balance steady-state closed-loop temperature control of this invention is not used, under the worst operating conditions (when the satellite is at a Beta angle of 15 degrees and the maximum angle of solar incidence can reach 90 degrees when the entire satellite is rolling and pulling at -15 degrees), the long-term power consumption of the satellite is 325W. The power system has completed charging, and the energy supply of the entire satellite is higher than the energy consumption. This causes some of the solar cell arrays to enter an open-circuit working state. After the heat dissipation of the entire array increases instantaneously, the temperature continues to rise. It is precisely because the heat dissipation of nearly 700W in the open circuit of the entire array lasts for too long that the temperature of the solar array reaches a level exceeding the safe temperature of 120 degrees.

[0064] After using the autonomous on-board energy balance steady-state closed-loop control of this invention, even under the worst operating conditions (when the satellite is at Beta angle = 15 degrees and the total satellite roll traction is -15 degrees, the maximum solar incidence angle can reach 90 degrees), the long-term power consumption of the satellite is adjusted to 390W in small steps through the closed-loop system. This increases the power consumption of the satellite when the power system has the best lighting conditions, so that the total energy supply and energy consumption of the satellite are in steady-state balance. This reduces the heat loss when the solar array is open. Although the power system still has some open-circuit operation states, its duration is effectively controlled. Therefore, the maximum temperature of the solar array is always kept within a safe temperature range below 120 degrees.

[0065] Based on a detailed simulation model, the relationship between heat dissipation and temperature of the solar cell array is compared between a long-term satellite power consumption of 325W and a satellite power consumption adjustment of 390W. Figure 7 As shown:

[0066] from Figure 7 The simulation results show that when the entire satellite has a long-term power consumption of 390W, although the solar cell array still has an open circuit under this state, the constant current charging time of the entire satellite is compressed and delayed, so that the open circuit avoids the peak area of ​​illumination and occurs in the temperature drop area, thus having no adverse effect on the temperature of the individual arrays.

[0067] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product implemented on one or more computer-usable storage media (including, but not limited to, disk storage and optical storage) containing computer-usable program code.

[0068] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0069] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0070] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0071] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A method of autonomously regulating the temperature of a satellite solar array, characterized by, The method comprises the following steps: acquiring a value of a perigee telemetry anomaly flag, and judging whether the satellite is normal in each orbit period according to the value of the perigee telemetry anomaly flag; if the satellite is normal, judging whether an auxiliary heating loop opening instruction has been sent in the orbit period; if the auxiliary heating loop opening instruction has not been sent, acquiring current satellite state information; judging whether a preset auxiliary heating loop opening condition is met based on the current satellite state information; if the preset auxiliary heating loop opening condition is met, sending an auxiliary heating loop opening instruction to open the auxiliary heating loop on the auxiliary heat dissipation plate to realize in-orbit closed-loop temperature control function; wherein the current satellite state information comprises a single-instruction sending flag value, an energy source state flag value and a timer value; judging whether the preset auxiliary heating loop opening condition is met based on the current satellite state information comprises: acquiring the single-instruction sending flag value, wherein the single-instruction sending flag value is set to a second value to indicate that the auxiliary heating loop opening instruction has not been sent; if the single-instruction sending flag value is the second value, acquiring the energy source state flag value; judging whether the energy source state flag value is a specified value and whether the timer value is not greater than a third preset threshold value; if the energy source state flag value is the specified value and the timer value is not greater than the third preset threshold value, sending the auxiliary heating loop opening instruction to open the auxiliary heating loop on the auxiliary heat dissipation plate to realize control of the working state of each sub-array in the solar cell array; if the single-instruction sending flag value is a third value, judging whether the energy source state flag value is the specified value and whether the timer value is greater than a fourth preset threshold value, wherein the third value indicates that the auxiliary heating loop opening instruction has been sent; if the energy source state flag value is the specified value and the timer value is greater than the fourth preset threshold value, sending a auxiliary heating loop closing instruction to close the auxiliary heating loop on the auxiliary heat dissipation plate to exit the in-orbit closed-loop temperature control function of the solar cell array.

2. The method of claim 1, wherein, Before acquiring the value of the perigee telemetry anomaly flag, the method further comprises: calculating the angle between the projection vector of the sun on the XOZ plane of the coordinate system corresponding to the satellite and the Z axis; setting the value of the perigee telemetry anomaly flag according to the angle.

3. The method of claim 2, wherein, Setting the value of the perigee telemetry anomaly flag according to the angle comprises: judging whether the angle is not less than a first preset threshold value; if the angle is not less than the first preset threshold value, starting the timer to start timing; if the timer value is greater than a second preset threshold value in the orbit period, setting the perigee telemetry anomaly flag to a first value, wherein the first value indicates that the current state is abnormal.

4. The method of claim 3, wherein, Before calculating the angle between the projection vector of the sun on the XOZ plane of the coordinate system corresponding to the satellite and the Z axis, the method further comprises: receiving a remote control instruction sent by a ground station, controlling the opening or closing of the in-orbit closed-loop temperature control function of the solar cell array according to the remote control instruction, and setting an enable flag based on the opening or closing of the in-orbit closed-loop temperature control function.

5. The method of claim 1, wherein, wherein Obtaining power supply output states of each sub-array in a solar cell array, determining an overall satellite energy balance state based on the power supply output states, and setting a value of an energy state flag bit based on the overall satellite energy balance state.

6. A satellite communication system, characterized by Comprise: A ground station and a satellite; wherein, The ground station sends a remote control instruction to the satellite, wherein the remote control instruction instructs the satellite to turn on or turn off an on-orbit closed-loop temperature control function of a solar cell array; The satellite receives the remote control instruction and executes the method according to any one of claims 1-5 based on the remote control instruction.

Images