Spacecraft multi-path parallel autonomous temperature control method and system

Abstract

This invention provides a method and system for multi-channel parallel autonomous temperature control of a spacecraft, comprising: updating the telemetry information of the heater switch status at time t, and determining whether autonomous temperature control is permitted for the current spacecraft. If so, the system reads the telemetry information of the heater switch status and determines whether the current heater telemetry packet is correct. If correct, the system controls the corresponding heater switch command position for each channel by determining the temperature acquisition strategy for each channel, thereby performing multi-channel parallel autonomous temperature control of the heaters. If not, the system proceeds to the next cycle of temperature control. This invention determines the corresponding temperature acquisition temperature for each channel based on different temperature acquisition strategies, and then determines the heater switch command position information based on the temperature acquisition temperature and high-temperature and low-temperature thresholds, thereby enabling multi-channel parallel autonomous temperature control of the spacecraft. This effectively improves the spacecraft's temperature control response time and frequency, thereby enhancing temperature control accuracy and efficiency. Furthermore, the judgment involved in this invention is simple and easy to implement.

Description

Technical Field

[0001] This invention relates to the field of autonomous thermal control management technology for spacecraft, specifically to a method and system for multi-channel parallel autonomous temperature control of spacecraft. Background Technology

[0002] Currently, two common temperature control methods are used on spacecraft: active temperature control and passive temperature control. The spacecraft autonomous temperature control system measures and controls the temperature of each section of the spacecraft, ensuring that structural components and instruments are within a suitable temperature range in the space environment so that they can function normally. This is one of the most frequently used active temperature control technologies. Its operation involves sending the collected temperature signals to a processor for calculation and decision-making to determine whether to activate or deactivate the heaters, thereby controlling the temperature within a specific range.

[0003] With the development of technology, the temperature control accuracy of instruments and equipment is getting higher and higher, and the demand for the number of heaters and temperature measurement points is increasing. Traditional serial temperature control methods cannot achieve parallel control of multiple heaters in a spacecraft within a control cycle. As the number of heaters increases, the temperature control response time will slow down and the temperature control accuracy will be lower.

[0004] Patent document CN110018679A discloses a closed-loop test system and test method for a spacecraft autonomous temperature control system in the field of spaceborne electronic equipment technology; the test system includes a spacecraft autonomous temperature control system and a closed-loop test system; the spacecraft autonomous temperature control system includes a telemetry acquisition module, a heater drive module, and a processor module; the closed-loop test system includes a thermistor simulation board, a heater drive detection board, a host computer, and a test terminal.

[0005] Patent document CN112181023B discloses a highly reliable autonomous temperature control method for temperature consistency in different regions, which includes the following steps: end-temperature differential control enable state judgment step, end temperature acquisition step, end temperature comparison step with set maximum threshold, end temperature comparison step with set minimum threshold, end-temperature differential threshold judgment step, heating circuit driving step, and fixed delay step.

[0006] Patent document CN104102245A discloses a thermal control device and method for improving the temperature control accuracy of satellites. The thermal control device includes a heating element, a heat insulation pad, a cuboid, and heat insulation material. The bottom surface of the cuboid serves as the equipment mounting base plate, and the other five surfaces of the cuboid together serve as the temperature control box.

[0007] Patent document CN104750137A discloses a satellite temperature control data processing method based on a lookup table. It establishes a lookup table based on the mapping relationship between thermistor temperature and the voltage of the temperature measurement circuit containing the thermistor, and the correspondence between thermistor serial number and temperature control circuit serial number. This table is stored on-board with triple-modulus redundancy. Ground users only need to compile and upload instructions according to the instruction template; after receiving and parsing the instructions, the satellite autonomously completes tasks such as temperature control settings, adding, modifying, or deleting lookup table information.

[0008] However, in summary, existing satellite temperature control technologies cannot meet the demand for parallel and rapid temperature control as temperature control accuracy increases and the number of heaters and temperature measurement points increases. Summary of the Invention

[0009] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method and system for multi-channel parallel autonomous temperature control of spacecraft.

[0010] A spacecraft multi-channel parallel autonomous temperature control method according to the present invention includes:

[0011] Step S1: Update the telemetry information of the heater switch status at time t, and determine whether the spacecraft is allowed to perform autonomous temperature control. If yes, proceed to step S2; otherwise, perform temperature control for the next cycle.

[0012] Step S2: Read the heater switch status telemetry information and determine whether the current heater telemetry package is correct. If yes, proceed to step S3; otherwise, proceed to the next cycle of temperature control.

[0013] Step S3: By determining the temperature acquisition strategy for each channel, control the corresponding heater switch command position for each channel to perform parallel autonomous temperature control of multiple heaters.

[0014] Preferably, step S3 includes:

[0015] Step S3.1: Set the valid temperature flag of the j-th channel to 1, and determine whether the j-th channel heater of the spacecraft is allowed to perform autonomous temperature control. If yes, proceed to step S3.2; otherwise, proceed to the next cycle of temperature control.

[0016] Step S3.2: Obtain the temperature sampling strategy for the j-th channel, and perform temperature sampling according to the temperature sampling strategy to obtain the temperature value of the j-th channel.

[0017] Step S3.3: Based on the temperature value of the j-th channel, determine whether the valid flag of the j-th channel temperature of the spacecraft is valid. If yes, proceed to step S3.4; otherwise, the switch command bit of the j-th channel heater remains unchanged in the current cycle.

[0018] Step S3.4: Compare the temperature value of the j-th channel with the preset high temperature threshold and the preset low temperature threshold respectively to determine the switch command position of the j-th channel heater and obtain the corresponding command bit information;

[0019] Step S3.5: Traverse all num-channel heater switch command bit information, generate heater parallel temperature control command packets, and send heater switch commands. If the command bit information is 0, execute the corresponding heater off operation; if the command bit information is 1, execute the corresponding heater on operation.

[0020] Preferably, the temperature sampling strategy includes:

[0021] If the current temperature sampling strategy is used, the temperature sampled is selected from the temperature of the j-th temperature point; if the highest temperature sampling strategy is used, the highest temperature value among the multiple temperature points of the j-th channel is selected; if the lowest temperature sampling strategy is used, the lowest temperature value among the multiple temperature points of the j-th channel is selected; if the average temperature sampling strategy is used, the average temperature value among the multiple temperature points of the j-th channel is selected.

[0022] The temperature sampling strategy is modified according to the ground injection command. The temperature sampling strategy for different routes can be set as needed, and different routes can be set to different temperature sampling strategies.

[0023] Preferably, step S3.4 includes:

[0024] Step S3.4.1: Determine whether the temperature of the j-th channel is greater than the high temperature threshold. If yes, set the switch command position of the j-th channel heater to off; if no, proceed to step S3.4.2.

[0025] Step S3.4.2: Determine whether the temperature of the j-th channel is lower than the low temperature threshold. If yes, set the switch command position of the j-th channel heater to "on". If no, keep the switch command position of the j-th channel heater unchanged from the previous cycle.

[0026] Preferably, the high temperature threshold and the low temperature threshold are set according to the ground injection number;

[0027] In the parallel temperature control command packet format, the packet data field is an even number of bytes, and the length is determined according to the actual number of heaters on the spacecraft. Each byte can represent the command bit information of 8 heaters. When the actual number of heaters does not meet the even number of bytes requirement, byte padding is performed.

[0028] A spacecraft multi-channel parallel autonomous temperature control system according to the present invention includes:

[0029] Module M1: Updates the telemetry information of the heater switch status at time t, and determines whether the spacecraft is allowed to perform autonomous temperature control. If so, it triggers module M2; otherwise, it performs temperature control for the next cycle.

[0030] Module M2: Reads the heater switch status telemetry information and determines whether the current heater telemetry package is correct. If it is, it triggers module M3; otherwise, it performs the temperature control for the next cycle.

[0031] Module M3: By determining the temperature acquisition strategy for each channel, it controls the corresponding heater switching command position for each channel, enabling parallel autonomous temperature control of multiple heaters.

[0032] Preferably, the module M3 includes:

[0033] Module M3.1: Set the valid temperature flag of the j-th channel to 1, and determine whether the j-th channel heater of the spacecraft is allowed to perform autonomous temperature control. If yes, trigger module M3.2; otherwise, proceed with the temperature control of the next cycle.

[0034] Module M3.2: Obtain the temperature sampling strategy for the j-th channel, and perform temperature sampling according to the temperature sampling strategy to obtain the temperature value of the j-th channel.

[0035] Module M3.3: Based on the temperature value of the j-th channel, determine whether the valid flag of the j-th channel temperature of the spacecraft is valid. If it is, then trigger module M3.4; if not, then the switch command bit of the j-th channel heater remains unchanged in the current cycle.

[0036] Module M3.4: Compare the temperature value of the j-th channel with the preset high temperature threshold and the preset low temperature threshold respectively to determine the switch command position of the j-th channel heater and obtain the corresponding command bit information;

[0037] Module M3.5: Traverses all num-channel heater switch command bit information, generates heater parallel temperature control command packets, and sends heater switch commands. If the command bit information is 0, the corresponding heater is turned off; if the command bit information is 1, the corresponding heater is turned on.

[0038] Preferably, the temperature sampling strategy includes:

[0039] If the current temperature sampling strategy is used, the temperature sampled is selected from the temperature of the j-th temperature point; if the highest temperature sampling strategy is used, the highest temperature value among the multiple temperature points of the j-th channel is selected; if the lowest temperature sampling strategy is used, the lowest temperature value among the multiple temperature points of the j-th channel is selected; if the average temperature sampling strategy is used, the average temperature value among the multiple temperature points of the j-th channel is selected.

[0040] The temperature sampling strategy is modified according to the ground injection command. The temperature sampling strategy for different routes can be set as needed, and different routes can be set to different temperature sampling strategies.

[0041] Preferably, module M3.4 includes:

[0042] Module M3.4.1: Determine whether the temperature of the j-th channel is greater than the high temperature threshold. If yes, set the switch command position of the j-th channel heater to off; otherwise, trigger module M3.4.2.

[0043] Module M3.4.2: Determine whether the temperature of the j-th channel is lower than the low temperature threshold. If yes, set the switch command position of the j-th channel heater to "on". If no, keep the switch command position of the j-th channel heater unchanged from the previous cycle.

[0044] Preferably, the high temperature threshold and the low temperature threshold are set according to the ground injection number;

[0045] In the parallel temperature control command packet format, the packet data field is an even number of bytes, and the length is determined according to the actual number of heaters on the spacecraft. Each byte can represent the command bit information of 8 heaters. When the actual number of heaters does not meet the even number of bytes requirement, byte padding is performed.

[0046] Compared with the prior art, the present invention has the following beneficial effects:

[0047] This invention determines the corresponding temperature for each channel based on different temperature acquisition strategies, and then determines the heater switching command information based on the acquired temperature and high-temperature and low-temperature thresholds. This enables multi-channel parallel autonomous temperature control of the spacecraft, effectively improving the spacecraft's temperature control response time and frequency, thereby enhancing temperature control accuracy and efficiency. Furthermore, the judgments involved in this invention are simple and easy to implement. Attached Figure Description

[0048] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0049] Figure 1 This is a schematic diagram of the workflow of the present invention. Detailed Implementation

[0050] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0051] According to the present invention, a multi-channel parallel autonomous temperature control method for spacecraft is provided, such as... Figure 1 As shown, it includes:

[0052] Step S1: Update the telemetry information of the heater switch status at time t, and determine whether the spacecraft is currently allowed to perform autonomous temperature control. If yes, proceed to step S2; otherwise, proceed to the next cycle of temperature control. Whether autonomous temperature control is allowed is determined based on the ground-based marker indicating that it can be modified.

[0053] Step S2: Read the heater switch status telemetry information and determine whether the current heater telemetry package is correct. If yes, proceed to step S3; otherwise, proceed to the next cycle of temperature control. Specifically, the correctness of the telemetry package can be determined through package verification.

[0054] Step S3: By determining the temperature acquisition strategy for each channel, control the corresponding heater switching command position for each channel to perform parallel autonomous temperature control of multiple heaters. Step S3 includes:

[0055] Step S3.1: Set the valid temperature flag FT(j) of the j-th channel to 1, and determine whether the j-th channel heater of the spacecraft is allowed to perform autonomous temperature control. If yes, proceed to step S3.2; otherwise, perform temperature control for the next cycle. The j-th channel heater iterates through all num heaters of the spacecraft.

[0056] Step S3.2: Obtain the temperature acquisition strategy for the j-th channel, and acquire the temperature value for the j-th channel according to the acquisition strategy. The acquisition strategy includes: if it is the current acquisition strategy, the acquisition temperature TH(j) is selected from the temperature of the j-th channel temperature point; if it is the highest acquisition strategy, the acquisition temperature TH(j) is selected from the highest temperature value of multiple temperature measurement points in the j-th channel; if it is the lowest acquisition strategy, the acquisition temperature TH(j) is selected from the lowest temperature value of multiple temperature measurement points in the j-th channel; if it is the average acquisition strategy, the acquisition temperature TH(j) is selected from the average temperature value of multiple temperature measurement points in the j-th channel; otherwise, the valid flag of the j-th channel temperature is set to invalid, that is, FT(j) is set to 0.

[0057] The temperature sampling strategy is modified according to the ground injection instructions. The temperature sampling strategy for different routes can be set as needed, and different routes can be set to different temperature sampling strategies.

[0058] Step S3.3: Based on the temperature value of the j-th temperature sensor, determine whether the valid temperature flag FT(j) of the j-th temperature sensor is valid. If yes, proceed to step S3.4; otherwise, the switch command bit of the j-th heater remains unchanged in the current cycle. FT(j) = 1 indicates validity, and FT(j) = 0 indicates invalidity.

[0059] Step S3.4: Compare the temperature value of the j-th temperature sensor with the preset high-temperature threshold and the preset low-temperature threshold respectively to determine the switch command position of the j-th heater and obtain the corresponding command bit information. The high-temperature threshold and the low-temperature threshold are set according to the number of ground gauges. Step S3.4 includes: determining whether the temperature TH(j) of the j-th temperature sensor is greater than the high-temperature threshold TH.m (j), if TH(j)>TH m If (j), then set the switch command position of the j-th heater to off, and the command bit information to 0; otherwise, determine whether the temperature TH(j) of the j-th temperature sampling channel is less than the low temperature threshold TH. n (j), if it is TH(j) <TH n (j) Set the switch command position of the j-th heater to ON, and set the command bit information to 1; otherwise, TH n (j)≤TH(j)≤TH m If (j), then the position of the heater switch command for the j-th channel remains unchanged from the position of the heater switch command in the previous cycle.

[0060] Step S3.5: Traverse all num-channel heater switch command bit information, generate a heater parallel temperature control command packet, and send the heater switch command. Command bits of 0 indicate the corresponding heater off operation, and command bits of 1 indicate the corresponding heater on operation. The heater parallel temperature control command packet can be generated according to the CCSDS encapsulation protocol. The format of the parallel temperature control command packet is shown in Table 1 below:

[0061] Table 1. Parallel Temperature Control Command Packet Format

[0062]

[0063] In the parallel temperature control command packet format, the packet data field is generally an even number of bytes, with the length determined by the actual number of heaters on the spacecraft. Each byte can represent 8 heater command bits. When the actual number of heaters does not meet the even number of bytes requirement, byte padding is performed. The heater command bits in the packet data field of the parallel temperature control command packet format are defined as follows: each bit represents whether the corresponding heater needs to be switched on or off, with 1 representing on and 0 representing off. Specific command bit identifiers are shown in Table 2.

[0064] Table 2. Definition of Heater Switching Command Bit Identifier

[0065]

[0066] The present invention also provides a spacecraft multi-channel parallel autonomous temperature control system. Those skilled in the art can implement the spacecraft multi-channel parallel autonomous temperature control system by executing the steps of the spacecraft multi-channel parallel autonomous temperature control method. That is, the spacecraft multi-channel parallel autonomous temperature control method can be understood as a preferred implementation of the spacecraft multi-channel parallel autonomous temperature control system.

[0067] A spacecraft multi-channel parallel autonomous temperature control system according to the present invention includes:

[0068] Module M1: Updates the telemetry information of the heater switch status at time t, and determines whether the spacecraft is allowed to perform autonomous temperature control. If so, it triggers module M2; otherwise, it performs temperature control for the next cycle.

[0069] Module M2: Reads the heater switch status telemetry information and determines whether the current heater telemetry package is correct. If it is, it triggers module M3; otherwise, it performs the temperature control for the next cycle.

[0070] Module M3: Controls the on / off command position of the corresponding heater for each channel by determining the temperature acquisition strategy for each channel, enabling parallel autonomous temperature control of multiple heaters. Module M3 includes:

[0071] Module M3.1: Set the valid temperature flag of the j-th channel to 1, and determine whether the j-th channel heater of the spacecraft is allowed to perform autonomous temperature control. If yes, then trigger module M3.2; otherwise, proceed with the temperature control of the next cycle.

[0072] Module M3.2: Obtains the temperature acquisition strategy for the j-th channel, acquires temperature data according to the strategy, and obtains the temperature value for the j-th channel. The temperature acquisition strategy includes: if it is the current strategy, the temperature is selected from the j-th channel temperature point; if it is the highest strategy, the highest temperature value among multiple temperature points on the j-th channel is selected; if it is the lowest strategy, the lowest temperature value among multiple temperature points on the j-th channel is selected; if it is the average strategy, the average temperature value among multiple temperature points on the j-th channel is selected. The temperature acquisition strategy is modified according to ground-based instructions. Different channels can have different temperature acquisition strategies as needed, and different numbers of channels can be configured with different strategies.

[0073] Module M3.3: Based on the temperature value of the j-th channel, determine whether the valid flag of the j-th channel temperature of the spacecraft is valid. If it is, then trigger module M3.4; if not, then the switch command bit of the j-th channel heater remains unchanged in the current cycle.

[0074] Module M3.4: Compares the temperature value of the j-th temperature sensor with the preset high-temperature threshold and the preset low-temperature threshold respectively to determine the switch command position of the j-th heater and obtain the corresponding command bit information. Module M3.4 includes: Module M3.4.1: Determines whether the temperature of the j-th temperature sensor is greater than the high-temperature threshold. If yes, it sets the switch command position of the j-th heater to "off"; if no, it triggers module M3.4.2. Module M3.4.2: Determines whether the temperature of the j-th temperature sensor is less than the low-temperature threshold. If yes, it sets the switch command position of the j-th heater to "on"; if no, it keeps the switch command position of the j-th heater unchanged from the previous cycle. The high-temperature threshold and the low-temperature threshold are set according to the ground gauge number.

[0075] Module M3.5: Iterates through all num-channel heater switch command bit information, generates a parallel heater temperature control command packet, and sends heater switch commands. A command bit of 0 triggers the corresponding heater off operation, and a command bit of 1 triggers the corresponding heater on operation. The parallel temperature control command packet format has an even number of bytes in the data field, with the length determined by the actual number of heater channels on the spacecraft. Each byte represents 8 heater command bit information channels. If the actual number of heater channels does not meet the even number of bytes requirement, byte padding is performed.

[0076] Those skilled in the art will understand that, in addition to implementing the system, apparatus, and their modules provided by this invention in purely computer-readable program code, the same program can be implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system, apparatus, and their modules provided by this invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; alternatively, modules for implementing various functions can be considered both software programs implementing the method and structures within the hardware component.

[0077] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for multi-channel parallel autonomous temperature control in spacecraft, characterized in that, include: Step S1: Update the telemetry information of the heater switch status at time t, and determine whether the spacecraft is allowed to perform autonomous temperature control. If yes, proceed to step S2; otherwise, perform temperature control for the next cycle. Step S2: Read the heater switch status telemetry information and determine whether the current heater telemetry package is correct. If yes, proceed to step S3; otherwise, proceed to the next cycle of temperature control. Step S3: By determining the temperature acquisition strategy for each channel, control the corresponding heater switch command position for each channel to perform parallel autonomous temperature control of multiple heaters; Step S3 includes: Step S3.1: Set the valid temperature flag of the j-th channel to 1, and determine whether the j-th channel heater of the spacecraft is allowed to perform autonomous temperature control. If yes, proceed to step S3.2; otherwise, proceed to the next cycle of temperature control. Step S3.2: Obtain the temperature sampling strategy for the j-th channel, and perform temperature sampling according to the temperature sampling strategy to obtain the temperature value of the j-th channel. Step S3.3: Based on the temperature value of the j-th channel, determine whether the valid flag of the j-th channel temperature of the spacecraft is valid. If yes, proceed to step S3.4; otherwise, the switch command bit of the j-th channel heater remains unchanged in the current cycle. Step S3.4: Compare the temperature value of the j-th channel with the preset high temperature threshold and the preset low temperature threshold respectively to determine the switch command position of the j-th channel heater and obtain the corresponding command bit information; Step S3.5: Traverse all num-path heater switch command bit information, generate heater parallel temperature control command packets, and send heater switch commands. If the command bit information is 0, execute the corresponding heater off operation; if the command bit information is 1, execute the corresponding heater on operation. The temperature acquisition strategy includes: If the current temperature sampling strategy is used, the temperature sampled is selected from the temperature of the j-th temperature point; if the highest temperature sampling strategy is used, the highest temperature value among the multiple temperature points of the j-th channel is selected; if the lowest temperature sampling strategy is used, the lowest temperature value among the multiple temperature points of the j-th channel is selected; if the average temperature sampling strategy is used, the average temperature value among the multiple temperature points of the j-th channel is selected. Otherwise, set the temperature validity flag of the j-th channel to invalid and set the temperature validity flag to 0; The temperature sampling strategy is modified according to the ground injection command. The temperature sampling strategy for different routes can be set as needed, and different routes can be set to different temperature sampling strategies.

2. The spacecraft multi-channel parallel autonomous temperature control method according to claim 1, characterized in that, Step S3.4 includes: Step S3.4.1: Determine whether the temperature of the j-th channel is greater than the high temperature threshold. If yes, set the switch command position of the j-th channel heater to off; if no, proceed to step S3.4.

2. Step S3.4.2: Determine whether the temperature of the j-th channel is lower than the low temperature threshold. If yes, set the switch command position of the j-th channel heater to "on". If no, keep the switch command position of the j-th channel heater unchanged from the previous cycle.

3. The spacecraft multi-channel parallel autonomous temperature control method according to claim 1, characterized in that, The high temperature threshold and low temperature threshold are set according to the ground injection number; In the parallel temperature control command packet format, the packet data field is an even number of bytes, and the length is determined according to the actual number of heaters on the spacecraft. Each byte can represent the command bit information of 8 heaters. When the actual number of heaters does not meet the even number of bytes requirement, byte padding is performed.

4. A spacecraft multi-channel parallel autonomous temperature control system, characterized in that, include: Module M1: Updates the telemetry information of the heater switch status at time t, and determines whether the spacecraft is allowed to perform autonomous temperature control. If so, it triggers module M2; otherwise, it performs temperature control for the next cycle. Module M2: Reads the heater switch status telemetry information and determines whether the current heater telemetry package is correct. If it is, it triggers module M3; otherwise, it performs the temperature control for the next cycle. Module M3: By determining the temperature acquisition strategy for each channel, it controls the corresponding heater switching command position for each channel, enabling parallel autonomous temperature control of multiple heaters. The module M3 includes: Module M3.1: Set the valid temperature flag of the j-th channel to 1, and determine whether the j-th channel heater of the spacecraft is allowed to perform autonomous temperature control. If yes, trigger module M3.2; otherwise, proceed with the temperature control of the next cycle. Module M3.2: Obtain the temperature sampling strategy for the j-th channel, and perform temperature sampling according to the temperature sampling strategy to obtain the temperature value of the j-th channel. Module M3.3: Based on the temperature value of the j-th channel, determine whether the valid flag of the j-th channel temperature of the spacecraft is valid. If it is, then trigger module M3.4; if not, then the switch command bit of the j-th channel heater remains unchanged in the current cycle. Module M3.4: Compare the temperature value of the j-th channel with the preset high temperature threshold and the preset low temperature threshold respectively to determine the switch command position of the j-th channel heater and obtain the corresponding command bit information; Module M3.5: Traverses all num-channel heater switch command bit information, generates heater parallel temperature control command packets, and sends heater switch commands. If the command bit information is 0, the corresponding heater is turned off; if the command bit information is 1, the corresponding heater is turned on. The temperature acquisition strategy includes: If the current temperature sampling strategy is used, the temperature sampled is selected from the temperature of the j-th temperature point; if the highest temperature sampling strategy is used, the highest temperature value among the multiple temperature points of the j-th channel is selected; if the lowest temperature sampling strategy is used, the lowest temperature value among the multiple temperature points of the j-th channel is selected; if the average temperature sampling strategy is used, the average temperature value among the multiple temperature points of the j-th channel is selected. Otherwise, set the temperature validity flag of the j-th channel to invalid and set the temperature validity flag to 0; The temperature sampling strategy is modified according to the ground injection command. The temperature sampling strategy for different routes can be set as needed, and different routes can be set to different temperature sampling strategies.

5. The spacecraft multi-channel parallel autonomous temperature control system according to claim 4, characterized in that, Module M3.4 includes: Module M3.4.1: Determine whether the temperature of the j-th channel is greater than the high temperature threshold. If yes, set the switch command position of the j-th channel heater to off; otherwise, trigger module M3.4.

2. Module M3.4.2: Determine whether the temperature of the j-th channel is lower than the low temperature threshold. If yes, set the switch command position of the j-th channel heater to "on". If no, keep the switch command position of the j-th channel heater unchanged from the previous cycle.

6. The spacecraft multi-channel parallel autonomous temperature control system according to claim 4, characterized in that, The high temperature threshold and low temperature threshold are set according to the ground injection number; In the parallel temperature control command packet format, the packet data field is an even number of bytes, and the length is determined according to the actual number of heaters on the spacecraft. Each byte can represent the command bit information of 8 heaters. When the actual number of heaters does not meet the even number of bytes requirement, byte padding is performed.

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