CN116257098A - Method for autonomously adjusting satellite solar cell array temperature and satellite communication system - Google Patents
Method for autonomously adjusting satellite solar cell array temperature and satellite communication system Download PDFInfo
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Abstract
The application discloses a method for autonomously adjusting the temperature of a satellite solar cell array and a satellite communication system, wherein the method comprises the following steps: acquiring a value of a solar point telemetry abnormal zone bit, and judging whether the satellite is normal in each orbit period according to the value of the solar point telemetry abnormal zone bit; if so, judging whether an auxiliary heating loop starting instruction is sent in the track period; if not, acquiring the state information of the current whole star; judging whether a preset condition for starting an auxiliary heating loop is met or not based on the state information of the current whole satellite; if the temperature of the auxiliary heating circuit is met, sending an auxiliary heating circuit opening instruction, and opening the heating circuit on the auxiliary heating plate through the auxiliary heating circuit opening instruction so as to realize the on-orbit closed-loop temperature control function. The technical problem that the temperature of the system cannot be reduced by adjusting the incident angle of the sun in the prior art is solved.
Description
Technical Field
The application relates to the technical field of satellites, in particular to a method for autonomously adjusting the temperature of a satellite solar cell array and a satellite communication system.
Background
For satellites employing body mounted solar wings, the energy source of the satellite for the solar wings. When the satellite is more sufficient in energy under the sun-facing state, the power supply system is stable in illumination after entering the sun-lighting area, the temperature of the solar wing is higher than that of a conventional unfolded solar wing, the service temperature of the solar wing adhesive layer can be exceeded, and the risk of on-orbit failure is likely to occur. After the charging is completed, most of the solar wing array works in the whole array open state, so that the whole array open state caused by excessive energy supply cannot be avoided, and a mode of reducing the incident angle of the sun can be adopted for reducing the temperature of the solar cell array corresponding to the solar wing in the sun-to-sun orientation mode of the satellite. However, when the satellite enters the normal earth-working mode, the solar incidence conditions and relations are determined by the constraint conditions such as the orbit state and the rolling traction angle, so that the temperature cannot be reduced by reducing the solar incidence angle. The problem brought by the method is that when the incident angle of the sun is large, the energy supply quantity of the whole satellite is higher than the energy consumption quantity, and the solar cell array is designed to be in a partial array whole array open circuit working state at the moment, so that the temperature of the solar cell array is increased and exceeds a safe temperature range, and the satellite needs to reach the whole satellite energy balance by increasing the energy consumption quantity at the moment, so that the whole solar cell array open circuit is controlled, and the damage to the solar cell array caused by the temperature increase is avoided.
Disclosure of Invention
Due to different rails and different postures and different illumination conditions, the solar cell arrays have different power generation capacities, and the embodiment of the application hopes that the load power can be adjusted. According to the embodiment of the application, the radiating plate is arranged at the cone section of the satellite, the heating loop is additionally arranged on the back of the radiating plate, the size of the increased load is regulated by controlling the switch of the heating loop, and the energy consumption capacity on the satellite is actively controlled, so that the aim of controlling the working state of the solar cell array is fulfilled.
In a first aspect, embodiments of the present application provide a method for autonomously adjusting a temperature of a satellite solar array, the method comprising: acquiring a value of a solar point telemetry abnormal zone bit, and judging whether the satellite is normal in each orbit period according to the value of the solar point telemetry abnormal zone bit; if so, judging whether an auxiliary heating loop starting instruction is sent in the track period; if not, acquiring the state information of the current whole star; judging whether a preset condition for starting an auxiliary heating loop is met or not based on the state information of the current whole satellite; if the temperature of the auxiliary heating circuit is met, sending an auxiliary heating circuit opening instruction, and opening the heating circuit on the auxiliary heating plate through the auxiliary heating circuit opening instruction so as to realize the on-orbit closed-loop temperature control function.
Optionally, before obtaining the value of the abnormal bit of the remote measurement of the meeting point, the method further includes: calculating an included angle between a projection vector of an XOZ plane and a Z axis in a coordinate system corresponding to a satellite; and setting the value of the remote measuring abnormal zone bit of the meeting day point according to the included angle.
Optionally, setting the value of the meeting day point telemetry anomaly flag according to the included angle includes: judging whether the included angle is not smaller than a first preset threshold value or not; if not, starting a timer to start timing; and if the value of the timer is larger than a second preset threshold value in the track period, setting the solar point telemetry anomaly flag bit as a first value, wherein the first value indicates the current anomaly.
Optionally, before calculating the included angle between the projection vector of the XOZ plane and the Z axis in the coordinate system corresponding to the satellite, the method further includes: and receiving a remote control instruction sent by the ground station, controlling to start or close the on-orbit closed-loop temperature control function of the solar cell array according to the remote control instruction, and setting an enabling zone bit based on the on-orbit closed-loop temperature control function.
Optionally, the state information of the current whole star includes a value of a single instruction sending flag bit, a value of an energy state flag bit and a value of the timer;
judging whether a preset condition for starting an auxiliary heating loop is met or not based on the state information of the current whole star comprises the following steps: acquiring a value of a single instruction sending flag bit, wherein the value of the single instruction sending flag bit is set to a second value to indicate that an auxiliary heating loop starting instruction is not sent; if the value of the single instruction sending flag bit is the second value, acquiring the value of the energy state flag bit; judging whether the value of the energy state flag bit is a designated value or not and whether the value of the timer is not larger than a third preset threshold value or not; if the value of the energy state flag bit is a specified value and the value of the timer is not greater than a third preset threshold, sending an auxiliary heating loop opening instruction, and opening a heating loop on an auxiliary heat dissipation plate through the auxiliary heating loop opening instruction so as to control the working state of each sub-array in the solar cell array
Optionally, the determining whether the condition of opening the auxiliary heating loop is met based on the state information of the current whole satellite further includes: if the value of the single instruction sending flag bit is the third value, judging whether the value of the energy status flag bit is a designated value or not and whether the value of the timer is larger than a fourth preset threshold value or not, wherein the third value indicates that an auxiliary heating loop opening instruction is sent; and if the value of the energy state flag bit is a specified value and the value of the timer is larger than a fourth preset threshold, sending an instruction for closing the auxiliary heating loop, closing the heating loop on the auxiliary cooling plate through the instruction for closing the auxiliary heating loop, and exiting the on-orbit closed-loop temperature control function of the solar cell array.
Optionally, power supply output states of all sub-arrays in the solar cell array are obtained, the whole-star energy balance state is determined based on the power supply output states, and the value of the energy state zone bit is set based on the whole-star energy balance state.
In a second aspect, embodiments of the present application provide a satellite communication system, the system comprising: ground stations and satellites; the ground station sends a remote control instruction to the satellite, wherein the remote control instruction instructs the satellite to start or close the on-orbit closed-loop temperature control function of the solar cell array;
the satellite receives the remote control instruction and performs the method of the first aspect based on the remote control instruction.
Compared with the prior art, the scheme provided by the embodiment of the application has at least the following beneficial effects:
in the scheme provided by the embodiment of the application, an autonomous on-board energy balance steady-state closed-loop control mode is designed on the satellite, so that the satellite solar cell array can be cooled, and the on-orbit failure caused by the fact that the temperature of the solar cell array exceeds a safe temperature range is avoided; and secondly, the power load autonomous adjustment method is utilized to ensure that the on-board energy reaches steady state balance, thereby changing the working state of the solar cell array, avoiding the solar cell array from entering an open-circuit working mode when a certain sub-array is in a peak value of a meeting day, reducing the temperature exceeding a safe temperature range caused by the sudden rise of heat consumption due to overlong open-circuit time, ensuring the on-track reliability of the solar cell array, simultaneously ensuring flexible and variable adjustment of the power load, meeting the different energy adjustment requirements of various satellites and improving the control efficiency of satellite energy balance.
Drawings
Fig. 1 is a schematic structural diagram of a satellite communication system according to an embodiment of the present application;
FIG. 2 is a schematic flow chart of a method for autonomously adjusting the temperature of a satellite solar cell array according to an embodiment of the present disclosure;
FIG. 3 is a relationship between an included angle alpha FS and a satellite latitude value according to an embodiment of the present application;
fig. 4 is a schematic diagram of a relationship between an incident angle of sunlight and heat consumption of a battery array according to an embodiment of the present disclosure;
FIG. 5 is a logic flow diagram of steady-state closed-loop temperature control provided by an embodiment of the present application;
FIG. 6 is a schematic flow chart of another method for autonomously adjusting the temperature of a satellite solar array according to an embodiment of the present application;
fig. 7 is a graph of heat consumption versus temperature for a solar cell array according to an embodiment of the present disclosure.
Detailed Description
In the solutions provided by the embodiments of the present application, the described embodiments are only some embodiments of the present application, and not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
In order to better understand the technical solutions described above, the following detailed description of the technical solutions of the present application is provided through the accompanying drawings and specific embodiments, and it should be understood that the specific features of the embodiments and embodiments of the present application are detailed descriptions of the technical solutions of the present application, and not limit the technical solutions of the present application, and the technical features of the embodiments and embodiments of the present application may be combined with each other without conflict.
Fig. 1 illustrates a schematic structural diagram of a satellite communication system according to an embodiment of the present application.
By way of example, in fig. 1, the satellite communication system includes a ground station and a satellite; wherein communication between the ground station and the satellite is possible. In order to realize the automatic regulation of the temperature of the solar cell array corresponding to the solar wing on the satellite, a radiating plate is arranged on the satellite, a heating loop is arranged on the radiating plate, the temperature of the solar cell array is regulated by controlling the opening work or the closing work of the heating loop, and the energy consumption capacity on the satellite is actively controlled, so that the aim of controlling the working state of the solar cell array is fulfilled.
In order to enable the satellite solar wing to meet the control of temperature in various working states, an on-orbit closed-loop temperature control function of an autonomous on-satellite energy balance steady state is designed on the satellite, the control period of the on-orbit closed-loop temperature control function is one orbit period, the on-satellite energy state in each orbit period needs to be evaluated, and then the whole satellite energy is autonomously adjusted according to the evaluation result. When the on-orbit closed-loop temperature control function of the solar cell array is started, the heating loop can be controlled to be started or closed to adjust the temperature of the solar cell array. For example, turning on or off the solar array on-orbit closed-loop temperature control function may be by the ground station sending a remote control command to the satellite, which turns on or off the solar array on-orbit closed-loop temperature control function based on the remote control command. As shown in fig. 1, the satellite includes a satellite computer, a control computer, a power down computer, and a payload management unit. The satellite realizes the function of adjusting the temperature of the solar cell array by controlling the opening work or the closing work of the heating loop through the interaction among the satellite computer, the control computer, the power supply lower computer and the effective load management unit. The operation of the particular star computer, control computer, power down computer, and payload management unit is described below.
The method for autonomously adjusting the temperature of the satellite solar cell array according to the embodiment of the application is described in further detail below with reference to the accompanying drawings, and the specific implementation manner of the method may include the following steps (the method flow is shown in fig. 2):
step 201, obtaining the value of the abnormal bit of the remote measurement of the meeting point, and judging whether the satellite is normal in each orbit period according to the value of the abnormal bit of the remote measurement of the meeting point.
As an example, in the running process of the satellite, a satellite service center computer on each orbit period satellite is provided with a solar point telemetry abnormal zone bit; the indication of the solar point telemetry abnormal flag bit is used for judging whether the operation is normal or not in the track period. For example, a value of 1 for a meeting point telemetry exception flag bit indicates an exception; a value of 0 for the solar point telemetry anomaly flag bit indicates normal.
As another example, before obtaining the value of the abnormal bit of the remote measurement of the meeting point, the method further includes: calculating an included angle between a projection vector of an XOZ plane and a Z axis in a coordinate system corresponding to a satellite; and setting the value of the remote measuring abnormal zone bit of the meeting day point according to the included angle.
Optionally, setting a value of a solar point telemetry anomaly flag according to the included angle includes: judging whether the included angle is not smaller than a first preset threshold value or not; if not, starting a timer to start timing; and if the value of the timer is larger than a second preset threshold value in the track period, setting the solar point telemetry anomaly flag bit as a first value, wherein the first value indicates the current anomaly.
Calculating an included angle alpha FS between a projection vector in an XOZ plane and a Z axis in a coordinate system corresponding to the satellite by a control computer; the control computer sends a telemetry packet to the star service center computer, wherein the telemetry packet comprises an alpha FS parameter. After receiving the telemetry packet, the star service center computer extracts the alpha FS parameter from the telemetry packet, and when judging that the alpha FS is less than or equal to 0.5, the star service center computer is a satellite sun-meeting peak illumination point, and a timer is set in the star service center computer for zero clearing and is used as a starting point of a steady-state closed-loop control period; when the alpha FS is larger than 0.5, starting a timer for timing, calculating according to the time of one track period, setting 5700 seconds as the upper limit of one control period, and setting a solar point telemetry abnormal flag bit by a star service center computer. For example, when the timer counts 5700 seconds, the value of the solar point telemetry abnormality flag bit is set to a value corresponding to an abnormality, and the abnormal exit of the solar cell array on-orbit closed-loop temperature control function is indicated in response to the value of the solar point telemetry abnormality flag bit. Fig. 3 shows a relationship between an included angle AlphaFS and a satellite latitude value according to an embodiment of the present application.
As already explained above, in order to enable the satellite solar wing to meet the control of temperature under various working conditions, an autonomous on-orbit closed-loop temperature control function of on-board energy balance and steady state is designed on the satellite. Therefore, before calculating the included angle between the projection vector of the XOZ plane and the Z axis in the coordinate system corresponding to the satellite, the method further includes: and receiving a remote control instruction sent by the ground station, controlling to start or close the on-orbit closed-loop temperature control function of the solar cell array according to the remote control instruction, and setting an enabling zone bit based on the on-orbit closed-loop temperature control function.
Step 202, if it is normal, determining whether an auxiliary heating loop opening command has been sent within the track period.
In order to increase the effectiveness of the heating circuit operation, for example, the heating circuit is controlled to be turned on once in each track period, i.e. the auxiliary heating circuit opening command has been sent once in said track period. Therefore, if the value of the solar point telemetry abnormal flag bit is normal in a track period, judging whether an auxiliary heating loop starting command is sent in the track period. According to the embodiment of the application, the star service center computer indicates the condition of sending the auxiliary heating loop starting instruction by setting the single-path instruction sending flag bit.
And 203, if not, acquiring the state information of the current whole satellite.
As an example, the state information of the current whole star includes a value of a single instruction transmission flag bit, a value of an energy state flag bit, and a value of the timer.
And 204, judging whether a preset condition for starting an auxiliary heating loop is met or not based on the state information of the current whole star.
As an example, determining whether a preset condition for starting the auxiliary heating circuit is satisfied based on the state information of the current whole star includes: acquiring a value of a single instruction sending flag bit, wherein the value of the single instruction sending flag bit is set to a second value to indicate that an auxiliary heating loop starting instruction is not sent; if the value of the single instruction sending flag bit is the second value, acquiring the value of the energy state flag bit; judging whether the value of the energy state flag bit is a designated value or not and whether the value of the timer is not larger than a third preset threshold value or not; if the value of the energy state flag bit is a specified value and the value of the timer is not greater than a third preset threshold, sending an auxiliary heating loop opening instruction, and opening a heating loop on an auxiliary heat dissipation plate through the auxiliary heating loop opening instruction so as to control the working state of each sub-array in the solar cell array
As another example, determining whether the preset condition for starting the auxiliary heating loop is satisfied based on the state information of the current whole satellite further includes: if the value of the single instruction sending flag bit is the third value, judging whether the value of the energy status flag bit is a designated value or not and whether the value of the timer is larger than a fourth preset threshold value or not, wherein the third value indicates that an auxiliary heating loop opening instruction is sent; and if the value of the energy state flag bit is a specified value and the value of the timer is larger than a fourth preset threshold, sending an instruction for closing the auxiliary heating loop, closing the heating loop on the auxiliary cooling plate through the instruction for closing the auxiliary heating loop, and exiting the on-orbit closed-loop temperature control function of the solar cell array.
According to the embodiment of the application, the temperature of the satellite solar cell array is regulated autonomously, and autonomous closed loop stability on the satellite is controlled specifically through adjustment of a time threshold. Two threshold times T1 (the third preset threshold above) and T2 (the fourth preset threshold above) are designed in the control, when the whole array shunt of a certain sub-array of the solar cell array occurs before T1, the long-term power consumption of the whole star is increased, and when the whole array open circuit of a certain sub-array of the solar cell array occurs after T2, the working threshold of the whole star is reduced. T1 and T2 are related to the solar wing solar incidence angle; the time point T1 is required to be based on simulation results of solar wing temperatures under different working conditions by a thermal control system, and is limited by the fact that when a certain subarray of the solar cell array is in an open state, the temperature of the subarray is still lower than an allowable value (such as 110 ℃), the temperature rise effect caused by self-hot melting of the solar wing is considered, the time point T1 is determined by combining the above considerations, and meanwhile, the time point T1 is required to be as close to a solar point as possible within a temperature allowable range. In addition, in order to be convenient for on-track management, the T1 point can be determined to cover different working conditions, namely different track illumination conditions. The T2 time point is determined according to the energy balance analysis result, and can be determined by comprehensively considering a certain open circuit time of the power supply system under the allowable maximum load power consumption condition under different track illumination conditions according to simulation results of the maximum load power consumption supported by the power supply system under different track illumination conditions. For convenience in on-track management, the determination of the T2 time point can cover different working conditions, namely different track illumination conditions.
Because the satellite runs in a three-axis stable earth posture, the solar wing is in a body wing, the incident angle of the solar wing is related to the position of the satellite on the orbit, and the orbit height and the orbit period of the satellite are given values, the position of the satellite on the orbit can be given by the time from the solar point. For illustrating the closed-loop temperature control scheme of the embodiment of the present application, a schematic diagram of the relationship between the incident angle of sunlight and the heat consumption of the cell array is shown in fig. 4.
The star service center calculates and calculates a star-based real-time judgment solar cell array open circuit state mark of a certain array, judges the value of a current counter when the mark bit is 1, and sends an instruction C1 when the value of the counter is smaller than T1; when the counter value is greater than T2, instruction C2 is issued.
C1: the effective load management unit controls the whole star power consumption to increase by one gear;
c2: the payload management unit controls the overall star power consumption to be reduced by one gear.
As shown in fig. 5, in order to achieve long-term steady-state closed-loop temperature control, the star-service center computer transmits only one command to increase power consumption (e.g., a command to turn on the auxiliary heating circuit) or one command to decrease power consumption (e.g., a command to turn off the auxiliary heating circuit) per control cycle.
The specific software flow is as follows: the star service center computer sets a single-way instruction sending zone bit, judges the energy balance zone bit when judging that the single-way instruction sending zone bit is not sent, and sends an instruction of opening an auxiliary heating loop when the energy balance zone bit=BBH and T < = T1 and the instruction sending zone bit is not sent, wherein the single-way instruction sending zone bit is sent and exits; when energy balance zone bit=bbh and T > T2, sending an instruction of "closing auxiliary heating loop", marking the single-path sending instruction as sent and exiting; and when the single instruction sending flag bit is sent, exiting. The flow chart of the star service center computer software is shown in fig. 6.
Step 205, if yes, sending an auxiliary heating loop opening instruction, and opening the heating loop on the auxiliary heat dissipation plate by the auxiliary heating loop opening instruction so as to realize an on-orbit closed-loop temperature control function.
The satellite adjustable long-term power consumption load is realized by an additionally added heating loop, so as to meet the requirement of power consumption adjustment. For example, 14 heating loops are arranged on the radiating plate, the total power consumption of each heating loop is 15W, the total power consumption of each heating loop is 210W, the total power consumption of each heating loop and each heating loop are 535W, and the total power consumption of each heating loop and each heating loop are 325W, so that the long-term power consumption of each heating loop can meet the requirement of the satellite. Thus the power consumption adjustment is divided into 14 steps, a first step open loop 1, a second step open loop 1, 2, and so on.
The effective load management unit receives the instruction of increasing power consumption or the instruction of reducing power consumption of the star service center computer, executes satellite energy adjustment, and is designed to complete the function by using 5 instructions, as shown in the following table:
| sequence number | Instruction | Instruction name | |
| 1 | 116CAAAAH | The 14-path heating loop is totally closed | |
| 2 | 116DAAAAH | All 14-path heating loops are opened | |
| 3 | 116EAAAAH | One of the 14 heating loops is opened | |
| 4 | 116FAAAAH | 14 heating loops close one of them | |
| 5 | 1170XXYYH | Control N-way heating loop to be opened simultaneously |
The following operations are completed according to the instructions sent by the star service center computer:
(1) When a command of opening one path of auxiliary heating loop sent by a star host is received, opening one path of heating loops of 14 paths in sequence, wherein the star host command does not specify which path to open, and the command is judged by a payload management unit, so that the heating loops which are already opened are prevented from being repeatedly opened;
(2) When a command of closing one path of auxiliary heating loop sent by a star host is received, opening and closing one path of 14 paths of heating loops according to sequence, wherein the command of the star host does not specify which path to close, and the command is judged by a payload management unit, so that the closed heating loops are prevented from being repeatedly closed;
(3) The effective load management unit sets the heating loop on/off state bit, so that the ground can observe whether the instruction is executed correctly;
(4) When 14 heating loops are all opened and a command of opening one heating loop is received, the effective load management unit sets a flag bit to indicate that the load power is insufficient, and when the load power is smaller than 14 heating loops, the opened flag bit can be cleared to 0;
(5) The payload management unit is required to set a flag bit to indicate that the load power is too high when 14 heating loops are all closed and a command of closing one heating loop is received, and the flag bit can be cleared to 0 when the load power is larger than the load power and the heating loop is opened;
(6) The device has the function of controlling the heating loops of N paths (N paths are absolute open paths) to be simultaneously opened/closed by the ground sending indirect instructions, wherein N=1-14, parameters can be modified on the track, and the ground control flexibility is improved.
In the scheme provided by the embodiment of the application, an autonomous on-board energy balance steady-state closed-loop control mode is designed on the satellite, so that the satellite solar cell array can be cooled, and the on-orbit failure caused by the fact that the temperature of the solar cell array exceeds a safe temperature range is avoided; and secondly, the power load autonomous adjustment method is utilized to ensure that the on-board energy reaches steady state balance, thereby changing the working state of the solar cell array, avoiding the solar cell array from entering an open-circuit working mode when a certain sub-array is in a peak value of a meeting day, reducing the temperature exceeding a safe temperature range caused by the sudden rise of heat consumption due to overlong open-circuit time, ensuring the on-track reliability of the solar cell array, simultaneously ensuring flexible and variable adjustment of the power load, meeting the different energy adjustment requirements of various satellites and improving the control efficiency of satellite energy balance.
In order to facilitate understanding of the effects of the embodiments of the present application, the following description is given by way of example.
For example, when the self-main on-satellite energy balance steady-state closed-loop temperature control is not used, under the worst satellite working condition (the maximum incident angle of the sun can reach 90 degrees when the satellite is at Beta angle=15 degrees and the whole satellite is rolled and pulled at-15 degrees), the long-term on-satellite power consumption is 325W, the power supply system finishes charging, the whole-satellite energy supply quantity is higher than the energy consumption quantity, the solar cell array part-array is in an open-circuit working state, the temperature continues to rise after the heat consumption of the whole array is instantaneously increased, and the maximum solar wing temperature reaches the level exceeding 120-degree safety temperature just because the heat consumption duration of the whole array is too long at the near 700W.
After the self-main on-satellite energy balance steady-state closed-loop control is used, under the worst working condition of the satellite (the maximum incident angle of the satellite can reach 90 degrees when the satellite is in Beta angle=15 degrees and the whole satellite is in rolling traction-15 degrees), the long-term power consumption of the satellite is adjusted to 390W in a small step mode through a closed loop system, the using power consumption of the satellite is increased when the illumination condition of a power supply system is best, and the energy supply quantity and the energy consumption quantity of the whole satellite are balanced in a steady state, so that the heat consumption of the whole solar cell array in an open circuit state is reduced, and the duration of the power supply system is effectively controlled although the whole solar cell array is still in a partial open circuit working state, so that the maximum solar wing temperature is always and stably kept in a safe temperature range below 120 degrees.
Based on a detailed simulation model, the relationship between the heat consumption and the temperature of the solar cell array under the condition that the long-term power consumption of the satellite is 325W and the power consumption of the satellite is regulated to 390W is as shown in FIG. 7:
as can be seen from the simulation result of fig. 7, when the whole star has 390W long-term power consumption, although the solar cell array still has the whole array open circuit condition in this state, the whole array open circuit avoids the peak area of illumination and occurs in the temperature falling area due to the fact that the constant current charging time of the whole star is compressed and then extends, so that the adverse effect on the temperature of the array is avoided.
It will be appreciated by those skilled in the art that embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, magnetic disk storage, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may 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, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
It will be apparent to those skilled in the art that various modifications and variations can be made in the present application without departing from the spirit or scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims and the equivalents thereof, the present application is intended to cover such modifications and variations.
Claims (8)
1. A method for autonomously regulating the temperature of a satellite solar array, comprising:
acquiring a value of a solar point telemetry abnormal zone bit, and judging whether the satellite is normal in each orbit period according to the value of the solar point telemetry abnormal zone bit;
if so, judging whether an auxiliary heating loop starting instruction is sent in the track period;
if not, acquiring the state information of the current whole star;
judging whether a preset condition for starting an auxiliary heating loop is met or not based on the state information of the current whole satellite;
if the temperature of the auxiliary heating circuit is met, sending an auxiliary heating circuit opening instruction, and opening the heating circuit on the auxiliary heating plate through the auxiliary heating circuit opening instruction so as to realize the on-orbit closed-loop temperature control function.
2. The method of claim 1, further comprising, prior to obtaining the value of the meeting point telemetry anomaly flag bit:
calculating an included angle between a projection vector of an XOZ plane and a Z axis in a coordinate system corresponding to a satellite;
and setting the value of the remote measuring abnormal zone bit of the meeting day point according to the included angle.
3. The method of claim 2, wherein setting the value of the meeting day point telemetry anomaly flag according to the angle comprises:
judging whether the included angle is not smaller than a first preset threshold value or not;
if not, starting a timer to start timing;
and if the value of the timer is larger than a second preset threshold value in the track period, setting the solar point telemetry anomaly flag bit as a first value, wherein the first value indicates the current anomaly.
4. The method of claim 3, further comprising, prior to calculating an angle between the projected vector of the XOZ plane and the Z axis in a coordinate system corresponding to the satellite,:
and receiving a remote control instruction sent by the ground station, controlling to start or close the on-orbit closed-loop temperature control function of the solar cell array according to the remote control instruction, and setting an enabling zone bit based on the on-orbit closed-loop temperature control function.
5. The method of claim 4, wherein the status information of the current whole star comprises a value of a single instruction send flag, a value of an energy status flag, and a value of the timer;
judging whether a preset condition for starting an auxiliary heating loop is met or not based on the state information of the current whole star comprises the following steps:
acquiring a value of a single instruction sending flag bit, wherein the value of the single instruction sending flag bit is set to a second value to indicate that an auxiliary heating loop starting instruction is not sent;
if the value of the single instruction sending flag bit is the second value, acquiring the value of the energy state flag bit;
judging whether the value of the energy state flag bit is a designated value or not and whether the value of the timer is not larger than a third preset threshold value or not;
and if the value of the energy state flag bit is a specified value and the value of the timer is not greater than a third preset threshold, sending an auxiliary heating loop opening instruction, and opening a heating loop on the auxiliary heat dissipation plate through the auxiliary heating loop opening instruction so as to control the working state of each sub-array in the solar cell array.
6. The method of claim 5, wherein determining whether a preset condition for opening an auxiliary heating circuit is satisfied based on the state information of the current whole star further comprises:
if the value of the single instruction sending flag bit is the third value, judging whether the value of the energy status flag bit is a designated value or not and whether the value of the timer is larger than a fourth preset threshold value or not, wherein the third value indicates that an auxiliary heating loop opening instruction is sent;
and if the value of the energy state flag bit is a specified value and the value of the timer is larger than a fourth preset threshold, sending an instruction for closing the auxiliary heating loop, closing the heating loop on the auxiliary cooling plate through the instruction for closing the auxiliary heating loop, and exiting the on-orbit closed-loop temperature control function of the solar cell array.
7. The method of claim 6, wherein,
and acquiring power supply output states of all sub-arrays in the solar cell array, determining the energy balance state of the whole star based on the power supply output states, and setting the value of the energy state zone bit based on the energy balance state of the whole star.
8. A satellite communications system, comprising: ground stations and satellites; wherein,,
the ground station sends a remote control instruction to the satellite, wherein the remote control instruction instructs the satellite to start or close the on-orbit closed-loop temperature control function of the solar cell array;
the satellite receives the remote control instructions, and performs the method according to any one of claims 1 to 7 based on the remote control instructions.
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| CN202211666212.4A CN116257098A (en) | 2022-12-23 | 2022-12-23 | Method for autonomously adjusting satellite solar cell array temperature and satellite communication system |
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| CN202211666212.4A CN116257098A (en) | 2022-12-23 | 2022-12-23 | Method for autonomously adjusting satellite solar cell array temperature and satellite communication system |
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