Multi-condition thermal control structure and temperature regulation method for flat-panel satellites

Abstract

This invention discloses a multi-condition thermal control structure for flat-panel satellites, including a partitioned orthogonal heat pipe network, a precision temperature control universal adaptable thermal control structure, a dedicated thermal control module for external equipment (star sensors), multi-layer thermal insulation components, a graded heating circuit, a phase change energy storage device, a thermal control white paint radiant heat dissipation surface, and an intelligent temperature control and regulation unit. The partitioned orthogonal heat pipe network separately achieves heat dissipation in high heat flux areas and isolated temperature control for individual equipment heat dissipation channels. The pre-embedded phase change energy storage device is coupled to the orthogonal heat pipe network, enabling long-distance heat transfer and storage when the high-power antenna is powered on. Simultaneously, the phase change energy storage device, relying on the orthogonal heat pipe network, achieves timely heat dissipation. This invention is rationally designed, combining structural optimization with intelligent control strategies to achieve efficient heat dissipation for high-power payloads, precise temperature control under multiple conditions, compatibility with various types of equipment, and anti-interference temperature control for external equipment, meeting the temperature stability and uniformity requirements of various key equipment.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control technology, and in particular to a multi-condition thermal control structure and temperature regulation method for flat-panel satellites. Background Technology

[0002] Flat-panel satellites face a complex space thermal environment during on-orbit operation, requiring them to adapt to various operating modes, including launch, orbit control, and fault response. Furthermore, critical equipment such as the navigation enhancement system, laser system, Ka-band antenna, and S / S antenna have stringent requirements for temperature stability and uniformity. For example, the rubidium atomic clock must maintain a temperature change rate of no more than ±1℃ / 24h, the S / S antenna mounting surface temperature consistency requirement is ≤8℃, and the lithium-ion battery pack must maintain an operating temperature range of 10℃~30℃.

[0003] Existing thermal control technologies have the following shortcomings: First, traditional heat pipe layouts are difficult to adapt to the compact single-unit layout of flat-panel satellites, and cannot efficiently solve the concentrated heat dissipation problem of high-power payloads (such as the S / S antenna active subarray with a single unit heat dissipation of 249.2W); second, a single thermal control strategy cannot cover the temperature regulation requirements under multiple operating conditions, including working conditions, storage conditions, orbit control conditions, and fault conditions, and the compensation heating efficiency is insufficient under storage conditions; third, there is a lack of universal thermal control design for different beam antennas, resulting in poor equipment compatibility; fourth, key equipment (such as star sensors and flywheels) is exposed outside the cabin, resulting in significant external heat flow interference and making it difficult to guarantee temperature control accuracy. Therefore, we propose a multi-condition thermal control structure and temperature regulation method for flat-panel satellites to address these problems. Summary of the Invention

[0004] The purpose of this invention is to solve the problems existing in the prior art. It proposes a multi-condition thermal control structure and temperature regulation method for flat-panel satellites. Through the combination of structural optimization design and intelligent control strategy, it achieves efficient heat dissipation of high-power payloads, precise temperature control under multiple conditions, compatibility and adaptation of multiple types of equipment, and anti-interference temperature control of external equipment, thus meeting the temperature stability and uniformity requirements of various key equipment.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: The multi-condition thermal control structure of the flat-panel satellite includes a partitioned orthogonal heat pipe network, coupling of the orthogonal heat pipe network with a pre-embedded phase change energy storage device, a precision temperature control universal adaptable thermal control structure, a dedicated thermal control module for extravehicular equipment, multi-layer thermal insulation components, a graded heating circuit, a thermal control white paint radiant heat dissipation surface, and an intelligent temperature control unit. The partitioned orthogonal heat pipe network includes a +Z compartment orthogonal aluminum-ammonia channel heat pipe network and a -Z compartment aluminum-ammonia channel heat pipe network, which respectively realize heat dissipation in high heat flux areas and isolated temperature control of equipment heat dissipation channels; The orthogonal heat pipe network is coupled with the pre-embedded phase change energy storage device to enable long-distance heat transfer and storage when the high-power antenna is turned on. At the same time, the phase change energy storage device relies on the orthogonal heat pipe network to achieve timely heat dissipation. The precision temperature control universal adaptable thermal control structure consists of an externally attached aluminum-ammonia channel heat pipe and a phase change device, and is compatible with two types of high heat dissipation antennas. The dedicated thermal control module for extravehicular equipment is configured with a combined structure of "multi-layer heat insulation components covered by a sunshade + heat dissipation plate + precision heating components" and is used for the extravehicular equipment of the star sensor. The thermal control white paint is sprayed on the outer surface of the +Z compartment plate, the radiation heat dissipation surface of the S / S antenna active subarray, the radiation heat dissipation surface of the Ka antenna, and the extended radiation area of ​​the cold end of the orthogonal heat pipe of the +Z compartment plate. The intelligent temperature control unit includes a temperature acquisition module, an operating condition identification module, and a thermal control strategy execution module. The temperature acquisition module collects temperature data from various satellite devices and cabins. The operating condition identification module switches according to different operating conditions of the satellite in orbit. The thermal control strategy execution module matches the corresponding thermal control strategy according to the identified operating conditions, controls the working state of the graded heating circuit, and executes the corresponding thermal control temperature threshold based on the operating condition identification results.

[0006] Preferably, in the precision temperature control universal adaptable thermal control structure, the phase change device is filled with n-octadecane working fluid.

[0007] Preferably, in the dedicated thermal control module for extravehicular equipment, the outer surface of the sunshade is covered with multiple layers of heat insulation components, the heat expansion plate is an aluminum alloy structure, and the precision heating component adopts a thin-film heating element and a temperature sensor.

[0008] Preferably, in the intelligent temperature control unit, the heating circuit has 106 circuits, including a main heating circuit and a backup heating circuit. It uses polyimide copper foil heating elements and combines PID and PWM to achieve precise temperature control. The main heating circuit corresponds to each device, and the backup heating circuit is shared by multiple devices. The multi-layer heat insulation component has 10 units, which are composed of alternating aluminum-plated film and polyester mesh, and have excellent heat insulation performance under vacuum.

[0009] This invention also discloses a multi-condition thermal control temperature regulation method for flat-panel satellites, which, based on the aforementioned thermal control structure, includes the following steps: S1. Operating Condition Identification: Based on the satellite orbit, attitude, and equipment operating status, determine the operating condition, storage condition, orbit control condition, or fault condition. S2. Match thermal control temperature threshold strategy according to working condition identification results: The working condition relies on the thermal control white paint of the +Z compartment plate and antenna area to enhance radiation heat dissipation; the storage condition starts the storage mode temperature control threshold and combines multi-layer heat insulation components to keep the heat; the fault condition switches to emergency thermal control mode to prioritize the temperature stability of core equipment. S3, Closed-loop control: The rubidium atomic clock is subjected to temperature change rate constraint control, the mounting surface of the S / S antenna is subjected to uniform temperature control, the lithium-ion battery pack is subjected to temperature range maintenance, the Ka antenna is subjected to temperature fluctuation smoothing through a phase change device, and the external equipment is subjected to high-precision temperature control through shading, heat expansion and precise heating. S4. Adaptive Adjustment: Real-time feedback of temperature data, dynamic adjustment of heating power and heat dissipation path, ensuring stable and compliant temperature performance under various operating conditions.

[0010] Preferably, in step S1, the designed temperature control threshold is adapted to different working modes and takes into account the high and low temperature conditions under different working modes. It is controlled by the satellite service software, and when the satellite service software switches between different working modes, the temperature control threshold also switches simultaneously with the working mode.

[0011] Preferably, in S1, the high and low temperature operating conditions under each operating mode have been considered in the detailed design, and the temperature control threshold only changes with the switching of the operating mode of the spacecraft's operational software. The high and low temperature operating conditions are determined by the magnitude of the average external heat flux experienced by the spacecraft during its on-orbit service life and the heat consumption under each operating mode.

[0012] Preferably, in step S2, the specific thermal control strategy is as follows: Operating conditions: The satellite software switches the temperature control threshold to the working mode, relying on the inorganic white paint on the outer surface of the +Z panel to enhance radiation heat dissipation. Through the partitioned orthogonal heat pipe network, the concentrated heat dissipation of the high heat flux load of the Ka antenna and S / S antenna is quickly conducted to the satellite heat dissipation surface. The phase change device with a universal and adaptable thermal control structure is used to buffer temperature fluctuations and ensure that the temperature of each device does not exceed its upper limit of operating temperature. Storage Mode: The satellite maintenance software switches the temperature control threshold to storage mode. This reduces heat loss through the satellite's surface, lithium-ion battery pack, and the 10-unit multi-layer thermal insulation components in the propulsion subsystem. The lithium-ion battery pack is a crucial component with a narrow temperature control range. Through tiered temperature control on the panels and the battery pack itself, the temperature is maintained between 10°C and 30°C. When the battery pack is not in operation, its storage temperature requirements are lower, and the lower temperature control threshold reduces the platform heater duty cycle, conserving onboard energy. This ensures that the maximum compensated heating power meets the satellite's power resource requirements under extreme low-temperature storage conditions. Orbit control mode: The satellite software switches the temperature control threshold to orbit control mode. The Ka antenna, laser system payload and other equipment do not work. Their temperature control threshold requirements are lower to save satellite energy and ensure the working temperature requirements of the Hall propulsion unit. Other platform equipment maintains the conventional temperature control strategy. Fault Condition: When a satellite malfunctions, the satellite administration software switches the temperature control threshold to fault mode. To minimize platform energy loss, only some critical operational units are kept running, while the remaining units are shut down and their temperatures are controlled according to the stored temperature control thresholds. This ensures that the temperature of the satellite's core equipment meets requirements even under fault conditions.

[0013] Preferably, in S3, the closed-loop control is specifically as follows: For rubidium atomic clocks, the power of the heating element is dynamically adjusted using a PID algorithm to ensure that its temperature change rate does not exceed ±1℃ / 24h; For S / S antennas, the temperature of each measuring point on the mounting surface is monitored in real time through the temperature equalization effect of the partitioned orthogonal heat pipe network to ensure that the temperature consistency is ≤8℃. For lithium-ion battery packs, heat dissipation is enhanced through a heat pipe network, and the temperature is monitored in real time. When the temperature is below 10°C, the heating power is increased, and when the temperature is above 30°C, the heating circuit is shut off, thereby achieving effective temperature control. For the star sensor and flywheel outside the cabin, the duty cycle of the heating circuit will be adjusted according to the change of external heat flow to ensure that its temperature is maintained within the operating temperature range. If the temperature does not meet the preset threshold requirement, the ground can send a command, and the thermal control strategy execution module will immediately adjust the execution parameters of the thermal control strategy until the temperature of each device and panel stabilizes within the preset range, thus achieving closed-loop temperature control.

[0014] Compared with the prior art, the beneficial effects of this invention are as follows: 1. In this invention, the partitioned orthogonal heat pipe network is designed for the load distribution characteristics of the ±Z compartment. The +Z compartment orthogonal heat pipe network accurately covers the high heat flux area, and the -Z compartment heat pipe network partitions to isolate the heat dissipation channels of the equipment. This solves the problems of poor adaptability of traditional heat pipe layout and insufficient heat dissipation of high-power loads, and improves the heat dissipation efficiency of the S / S antenna active subarray.

[0015] 2. In this invention, through the working condition identification and strategy matching mechanism, combined with the graded heating circuit and multi-layer heat insulation components, precise temperature control under various working conditions is achieved, the working condition compensation heating is stored to meet the satellite energy constraints, and the temperature indicators of each device are guaranteed.

[0016] 3. In this invention, the universal structure of "external heat pipe + phase change device" can be compatible with two types of high-power antennas without the need for separate adaptation structure design, thus reducing design and manufacturing costs.

[0017] 4. In this invention, the external equipment adopts a combination design of "multi-layer heat insulation component covering + heat expansion plate + precision heating", which effectively isolates external heat flow interference, and the temperature control accuracy of equipment such as star sensor and flywheel reaches a certain level. The temperature change rate of rubidium atomic clock is ≤±1℃ / 24h, and the temperature consistency of S / S antenna mounting surface is ≤6℃, meeting the stringent requirements of key equipment. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the multi-condition thermal control structure for flat-panel satellites proposed in this invention; Figure 2 This is a schematic flowchart of the multi-condition thermal control junction temperature regulation method for flat-panel satellites proposed in this invention. Detailed Implementation

[0019] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0020] Reference Figures 1-2 The multi-condition thermal control structure of the flat-panel satellite includes a partitioned orthogonal heat pipe network, coupling of the orthogonal heat pipe network with a pre-embedded phase change energy storage device, a precision temperature control universal adaptable thermal control structure, a dedicated thermal control module for extravehicular equipment, multi-layer thermal insulation components, a graded heating circuit, a thermal control white paint radiant heat dissipation surface, and an intelligent temperature control and regulation unit. To address the differences in load distribution across the ±Z compartments of the flat-panel satellite, a partitioned orthogonal heat pipe layout is adopted. This partitioned orthogonal heat pipe network includes an orthogonal aluminum-ammonia channel heat pipe network for the +Z compartment and an aluminum-ammonia channel heat pipe network for the -Z compartment, respectively achieving heat dissipation in high heat flux areas and isolated temperature control of equipment heat dissipation channels. Specifically, the aluminum-ammonia channel heat pipes are arranged in an orthogonal grid to form a high-density heat pipe network, covering the high heat flux areas of the Ka antenna and S / S antenna active subarrays. This network is used to quickly dissipate concentrated heat and flatten the temperature field in the +Z compartment. The aluminum-ammonia channel heat pipes are pre-embedded in the -Z compartment, isolating the heat dissipation channels of the lithium-ion battery pack, rubidium atomic clock, and laser processor from each other, enabling individual temperature control of each device and avoiding thermal interference.

[0021] A precision temperature-controlled, universally compatible thermal control structure is located in the Ka antenna mounting area, compatible with two types of high heat dissipation antennas. It consists of an externally attached aluminum-ammonia channel heat pipe and a phase change device. The externally attached aluminum-ammonia channel heat pipe is attached to the bottom of the Ka antenna to efficiently conduct the high heat flux generated by the antenna operation. The phase change device is located between the externally attached aluminum-ammonia channel heat pipe and the Ka antenna mounting surface. A phase change device is also located on the rubidium atomic clock mounting surface. The phase change device is filled with n-octadecane working fluid to buffer temperature fluctuations during antenna start-up and shutdown, ensuring temperature stability.

[0022] The dedicated thermal control module for external equipment features a combined structure of "multi-layered heat insulation components covered by a light shield + heat dissipation plate + precision heating components" for the star sensor's external equipment. The star sensor's light shield is covered with multiple layers of heat insulation components. The heat dissipation plate, made of aluminum alloy, is connected to the equipment housing to increase the heat dissipation area and quickly dissipate the equipment's own heat. The precision heating component uses heating elements and temperature sensors, fitted to key parts of the equipment, for precise temperature compensation under storage conditions, achieving millisecond-level temperature response. The heating elements employ a zoned design (3 zones for the star sensor and 4 zones for the flywheel), with each zone independently temperature-controlled. Temperature sensors are located at the center of the heating elements and on the surface of core equipment components (spacing ≤30mm).

[0023] Thermal control white paint is sprayed on the outer surface of the +Z compartment panel, the radiating surface of the active subarray of the S / S antenna, the radiating and heat dissipation surface of the Ka antenna, and the extended radiating area of ​​the cold end of the orthogonal heat pipe of the +Z compartment panel to form a high emissivity radiating and heat dissipation surface. This is used to directly radiate the heat of the high-power load to deep space under working conditions. The area covered by the multi-layer heat insulation component, the lithium-ion battery pack and the rubidium atomic clock installation area are not sprayed with thermal control white paint to avoid excessive heat dissipation and interference from external heat flow.

[0024] The intelligent temperature control unit includes a temperature acquisition module, an operating condition identification module, and a thermal control strategy execution module. The temperature acquisition module collects temperature data from various satellite devices and cabins. The operating condition identification module identifies the satellite's on-orbit operating conditions. The thermal control strategy execution module matches the corresponding thermal control temperature threshold according to the identified operating conditions, controls the working state of the graded heating circuit, and executes the corresponding thermal control temperature threshold based on the operating condition identification results.

[0025] The graded heating circuit has 106 circuits, including main heating circuits and backup heating circuits. It uses polyimide copper foil heating elements and combines PID and PWM to achieve precise temperature control. There are 53 main heating circuits with a total power of 300W and 53 backup heating circuits with a total power of 200W. The main heating circuits correspond one-to-one with each piece of equipment, while the backup heating circuits are shared by multiple pieces of equipment. The multi-layer thermal insulation component consists of 10 units, composed of alternating layers of aluminized film and polyester mesh, for effective thermal insulation. The 10 units of the multi-layer thermal insulation component are arranged according to the principle of "partial coverage of the cabin plate + protection of external equipment", and are fixed by Velcro and buckles, with reserved clearance holes. The external equipment is covered with star sensor light shields, which takes into account both thermal insulation and equipment functional compatibility.

[0026] This invention also discloses a multi-condition thermal control temperature regulation method for flat-panel satellites, which, based on the aforementioned thermal control structure, includes the following steps: S1. Operating Condition Identification: Based on the satellite orbit, attitude, and equipment operating status, determine the operating condition, storage condition, orbit control condition, or fault condition.

[0027] S2. Matching thermal control strategies based on operating condition identification results: High-temperature operating condition is determined when the platform payload is powered on and operating in a high-temperature environment mode with external heat flow from sunlight. Under this condition, the satellite is in operating mode, with steady-state orbital cruise, high-precision mission attitude orientation, and all payloads such as the Ka antenna and laser system operating normally. Low-temperature storage condition is determined when the platform payload is not working and operating in a low-temperature environment mode with external heat flow from the Earth's shadow. Under this condition, the satellite enters hibernation mode, retaining only the essential onboard survival systems. Orbit control condition is determined when performing orbital adjustment tasks such as orbit maintenance, orbit change, and space debris avoidance. Under this condition, the satellite switches to high-priority orbit control mode, switches to dedicated thrust attitude, shuts down service payloads, and the propulsion system operates at full capacity. Fault condition is when the satellite deviates from the above-mentioned normal operating modes and enters the whole-satellite emergency temperature control state. In normal operating conditions, the thermal control system utilizes the white paint on the +Z compartment panel and antenna area to enhance radiative heat dissipation, requiring no additional energy consumption. In storage mode, the thermal control mode switches to storage mode and incorporates multi-layer insulation components to reduce heat loss. In fault mode, the system switches to emergency thermal control mode, prioritizing the temperature stability of core equipment, such as the battery pack, and cutting off heating circuits for non-essential equipment. Specific strategies are as follows: Operating conditions: The thermal control mode is switched to the working mode. Relying on the inorganic white paint on the outer surface of the +Z panel to enhance radiation heat dissipation, the concentrated heat dissipation of high heat flux loads such as Ka antenna and S / S antenna is quickly conducted to the satellite heat dissipation surface through a partitioned orthogonal heat pipe network. The phase change device of the universally adapted thermal control structure and the phase change device of the rubidium atomic clock mounting surface are used to buffer the temperature fluctuations of Ka antenna and rubidium atomic clock, ensuring that the temperature of each device does not exceed its upper limit of operating temperature.

[0028] Storage conditions: 10-unit multi-layer thermal insulation components for satellite surfaces, lithium-ion battery packs, propulsion subsystems, etc., effectively reduce heat loss from the satellite; tiered heating circuits are activated based on equipment temperature priority. First priority is given to lithium-ion battery packs, whose heating circuits are activated first to ensure temperatures are maintained between 10℃ and 30℃; second priority is given to equipment with high temperature stability requirements, such as rubidium atomic clocks and laser processors, whose main heating circuits are activated; third priority is given to external equipment such as star sensors and flywheels, whose dedicated heating circuits are activated; under extreme storage conditions (where individual satellite units are in long-term hibernation), a thermal control hibernation mode is switched to ensure that the maximum compensated heating power does not exceed 600W under extreme storage conditions, and the average power consumption meets the satellite's power resource requirements.

[0029] Track control mode: Switch to track control mode thermal control, shut down the heating circuit of load equipment such as Ka antenna, start the heating circuit of propulsion subsystem (Hall thruster, power processing and control unit, gas cylinder, etc.) to ensure the working temperature requirements of Hall thruster unit, and maintain the conventional temperature control strategy for other platform equipment.

[0030] Fault conditions: When an open circuit is detected in the heater, the corresponding backup heating circuit is activated; when an open / short circuit is detected in the thermistor, the system switches to the backup temperature measurement point, increases the temperature monitoring frequency of adjacent equipment, and adjusts the heating strategy to ensure that the temperature of the satellite core equipment meets the requirements under fault conditions.

[0031] S3. Closed-loop control: This involves constraining the rate of temperature change in the rubidium atomic clock, controlling the uniform temperature of the mounting surface of the S / S antenna, maintaining the temperature range of the lithium-ion battery pack, smoothing temperature fluctuations in the Ka antenna using a phase-change device, and achieving high-precision temperature control for external equipment through multi-layer wrapping, heat amplification, and precise heating. The specifics of the closed-loop control are as follows: For rubidium atomic clocks, temperature change rate constraint control is implemented by dynamically adjusting the power of the heating element through a PID algorithm to ensure that its temperature change rate does not exceed ±1℃ / 24h. For S / S antennas, the temperature of each measuring point on the mounting surface is monitored in real time through the temperature equalization effect of the partitioned orthogonal heat pipe network to ensure that the temperature consistency is ≤8℃. For lithium-ion battery packs, heat dissipation is enhanced through a heat pipe network, and the temperature is monitored in real time to maintain the operating temperature within the range of 10℃ to 30℃. When the temperature is below 10℃, the heating power is increased, and when the temperature is above 30℃, the heating circuit is shut off. The Ka antenna uses a phase-change device to buffer temperature fluctuations. For the star sensors and flywheels outside the cabin, the heating power is adjusted in real time according to the changes in external heat flow through the coordinated work of shading, heat amplification and precise heating to ensure that their temperature is maintained within the operating temperature range.

[0032] If the temperature does not meet the preset threshold requirement, the thermal control strategy execution module immediately adjusts the switching status of the main and backup thermal control heating circuits until the temperature of each device and compartment stabilizes within the preset range, thus achieving closed-loop temperature control.

[0033] S4. Adaptive Adjustment: Real-time feedback of temperature data and dynamic adjustment of the heating circuit duty cycle to ensure stable and compliant temperature performance under various operating conditions.

[0034] The following specific embodiments further illustrate the multi-condition thermal control structure and temperature regulation method of this flat-panel satellite: 1. Thermal control system structure assembly 1.1 Installation of zoned orthogonal heat pipe network: +Z compartment plate is 25mm thick. Orthogonal aluminum ammonia channel heat pipes are installed in the pre-embedded groove of the compartment plate. The outer diameter of the heat pipe is 12mm and the spacing between adjacent heat pipes is 150mm. They are orthogonally distributed and cover the Ka antenna installation area and the S / S antenna active subarray installation surface. The heat pipes are fixed to the compartment plate with high thermal conductivity adhesive film. The outer surface of +Z compartment plate, antenna radiating surface and cold end area of ​​heat pipe are sprayed with thermal control white paint. - The Z-type compartment is 25mm thick and has three sets of aluminum-ammonia channel heat pipe networks, which correspond to the heat dissipation channels of the lithium-ion battery pack, rubidium atomic clock, and laser processor, respectively, thus isolating the battery pack, rubidium atomic clock, and laser processor to achieve zoned temperature control.

[0035] 1.2 Standardized antenna structure assembly: Externally mounted aluminum-ammonia channel heat pipes, 10mm in diameter, are arranged in eight evenly around the antenna mounting surface and are tightly fitted to the phase change device. The phase change device is a square box structure that matches the antenna mounting base. It is 10mm thick and filled with phase change material.

[0036] 1.3 Thermal control assembly of external equipment: Multi-layer thermal insulation components cover the star sensor's light shield; The heat spreader plate is bonded to the equipment housing using thermally conductive silicone grease; The precision heating module uses two thin-film heating elements (each with a power of 5W), which are respectively attached to the power module and the outer shell of the core components of the device.

[0037] Parts of the satellite are covered with 10-unit multi-layer thermal insulation components, and the satellite is equipped with a total of 106 graded heating circuits.

[0038] 2. Multi-condition temperature control process 2.1 Operating Condition Identification: Data is collected by satellite attitude sensors, external heat flow sensors, and equipment temperature sensors, and input into the operating condition identification model to achieve operating condition classification; 2.2 Strategy Execution: When identified as working condition: thermal control white paint naturally radiates heat to keep the cabin temperature ≤45℃; When the storage condition is identified: switch the storage thermal control mode, first start the 53 main heating circuits with a total power of 300W. If the temperature is still lower than the target temperature, start the 53 backup heating circuits with a total power of 200W. When a fault condition is identified (abnormal operating status of a certain device): switch to thermal control fault mode to save energy and troubleshoot the fault.

[0039] 3. Performance Verification In this embodiment, the flat-panel satellite is equipped with a Ka-band antenna, an active S / S antenna subarray (heat dissipation 249.2W), a rubidium atomic clock, a lithium-ion battery pack, and other equipment. During its on-orbit operation: The temperature uniformity of the S / S antenna mounting surface is ≤5.8℃, which meets the requirement of ≤8℃; The temperature change rate of the rubidium atomic clock is ≤ ±0.8℃ / 24h, which is better than the design target of ±1℃ / 24h; The lithium-ion battery pack operates at a temperature of 12℃ to 28℃, covering the requirement of 10℃ to 30℃. Under extreme storage conditions, the maximum compensated heating power is 480W, which meets the satellite's energy constraints.

[0040] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A multi-mission thermal control structure for a satellite platform, characterized in that, It includes a partitioned orthogonal heat pipe network, coupling of the orthogonal heat pipe network with a pre-embedded phase change energy storage device, a precision temperature control universal adaptable thermal control structure, a dedicated thermal control module for external equipment, multi-layer thermal insulation components, a graded heating circuit, a thermal control white paint radiant heat dissipation surface, and an intelligent temperature control unit. The partitioned orthogonal heat pipe network enables heat dissipation in high heat flux areas and separate temperature control for isolated equipment heat dissipation channels. The orthogonal heat pipe network is coupled with the pre-embedded phase change energy storage device to enable long-distance heat transfer and storage when the high-power antenna is turned on. At the same time, the phase change energy storage device relies on the orthogonal heat pipe network to achieve timely heat dissipation. The precision temperature control universal adaptable thermal control structure consists of an externally attached aluminum-ammonia channel heat pipe and a phase change device, and is compatible with two types of high heat dissipation antennas. The dedicated thermal control module for extravehicular equipment is equipped with a combined structure of "multi-layer heat insulation components covered by a light shield + heat dissipation plate + precision heating components" and is used for the extravehicular equipment of the star sensor. The thermal control white paint is sprayed on the outer surface of the +Z compartment plate, the radiation surface of the active subarray of the S / S antenna, the radiation heat dissipation surface of the Ka antenna, and the extended radiation area of ​​the cold end of the orthogonal heat pipe of the +Z compartment plate. The intelligent temperature control unit includes a temperature acquisition module, an operating condition identification module, and a thermal control strategy execution module. The temperature acquisition module collects temperature data from various satellite devices and cabins. The operating condition identification module switches according to the satellite's on-orbit operating conditions. The thermal control strategy execution module matches the corresponding thermal control strategy according to the identified operating conditions, controls the working status of the graded heating circuit and multi-layer thermal insulation components, and executes the corresponding thermal control temperature threshold based on the operating condition identification results.

2. The flat panel satellite multi-mission thermal control structure of claim 1, wherein, In the aforementioned precision temperature control universal adaptable thermal control structure, the phase change device is filled with a phase change working fluid.

3. The multi-condition thermal control structure for flat-panel satellites according to claim 1, characterized in that, In the dedicated thermal control module for extravehicular equipment, the outer surface of the star-sensor light shield is covered with multiple layers of heat insulation components, the heat expansion plate is an aluminum alloy structure, and the precision heating component uses heating elements and temperature sensors.

4. The multi-condition thermal control structure for flat-panel satellites according to claim 1, characterized in that, The intelligent temperature control unit has 106 circuits in the graded heating circuit, including the main heating circuit and the backup heating circuit. It uses polyimide copper foil heating elements and combines PID and PWM to achieve precise temperature control. The main heating circuit corresponds to each device, and the backup heating circuit is shared by multiple devices. The multi-layer heat insulation component has 10 units, which are composed of alternating layers of aluminized film and polyester mesh, and have excellent heat insulation performance under vacuum.

5. A multi-condition thermal control temperature regulation method for flat-panel satellites, based on claim 1.

4. The thermal control structure according to any one of the claims, characterized in that, Includes the following steps: S1. Operating Condition Identification: Determine the operating condition, storage condition, orbit control condition, or fault condition based on the satellite orbit, attitude, and equipment operating status. S2. Match thermal control temperature threshold strategy according to working condition identification results: The working condition relies on the thermal control white paint of the +Z compartment plate and antenna area to enhance radiation heat dissipation; the storage condition starts the storage mode temperature control threshold and combines multi-layer heat insulation components to keep the heat; the fault condition switches to emergency thermal control mode to prioritize the temperature stability of core equipment. S3, Closed-loop control: The rubidium atomic clock is subjected to temperature change rate constraint control, the mounting surface of the S / S antenna is subjected to uniform temperature control, the lithium-ion battery pack is subjected to temperature range maintenance, the Ka antenna is subjected to temperature fluctuation smoothing through a phase change device, and the external equipment is subjected to high-precision temperature control through shading, heat expansion and precise heating. S4. Adaptive Adjustment: Real-time feedback of temperature data, dynamic adjustment of heating power and heat dissipation path, ensuring stable and compliant temperature performance under various operating conditions.

6. The multi-condition thermal control temperature regulation method for flat-panel satellites according to claim 5, characterized in that, In S1, the designed temperature control threshold is adapted to different working modes and takes into account the high and low temperature conditions under different working modes. It is controlled by the satellite service software. When the satellite service software switches between different working modes, the temperature control threshold also switches simultaneously with the working mode.

7. The multi-condition thermal control temperature regulation method for flat-panel satellites according to claim 5, characterized in that, In S1, the high and low temperature conditions under each working mode have been considered in the detailed design, and the temperature control threshold only changes with the switching of the working mode of the spacecraft software. The high and low temperature conditions are determined by the magnitude of the average external heat flux experienced by the spacecraft during its on-orbit service life and the heat consumption under each working mode.

8. The multi-condition thermal control temperature regulation method for flat-panel satellites according to claim 5, characterized in that, In S2, the specific thermal control strategy is as follows: Operating conditions: The satellite software switches the temperature control threshold to the working mode, relying on the inorganic white paint on the outer surface of the +Z panel to enhance radiation heat dissipation. Through the partitioned orthogonal heat pipe network, the concentrated heat dissipation of the high heat flux load of the Ka antenna and S / S antenna is quickly conducted to the satellite heat dissipation surface. The phase change device with a universal and adaptable thermal control structure is used to buffer temperature fluctuations and ensure that the temperature of each device does not exceed its upper limit of operating temperature. Storage mode: The satellite maintenance software switches the temperature control threshold to storage mode, reducing heat loss through the 10-unit multi-layer thermal insulation components of the satellite surface, lithium-ion battery pack, and propulsion subsystem. The lithium-ion battery pack is an important unit on the platform with a narrow temperature control range. Through the tiered temperature control on the panel and the unit itself, the temperature is maintained between 10°C and 30°C. When the unit is not in operation, its storage temperature requirements are lower. At this time, the temperature control threshold is lower, which can reduce the duty cycle of the platform heater and save onboard energy. This ensures that the maximum compensation heating power meets the satellite's power resource requirements under extreme low temperature storage conditions. Orbit control mode: The satellite software switches the temperature control threshold to orbit control mode. The Ka antenna, laser system payload and other equipment do not work. Their temperature control threshold requirements are lower to save satellite energy and ensure the working temperature requirements of the Hall propulsion unit. Other platform equipment maintains the conventional temperature control strategy. Fault Condition: When a satellite malfunctions, the satellite management software switches the temperature control threshold to fault mode. In order to reduce the loss of platform energy, only some important working units are kept powered on, while the rest are shut down. Temperature is controlled according to the stored temperature control threshold to ensure that the temperature of the satellite's core equipment meets the requirements under fault conditions.

9. The multi-condition thermal control temperature regulation method for flat-panel satellites according to claim 5, characterized in that, In S3, the closed-loop control is specifically as follows: For rubidium atomic clocks, the power of the heating element is dynamically adjusted using a PID algorithm to ensure that its temperature change rate does not exceed ±1℃ / 24h; For S / S antennas, the temperature of each measuring point on the mounting surface is monitored in real time through the temperature equalization effect of the partitioned orthogonal heat pipe network to ensure that the temperature consistency is ≤8℃. For lithium-ion battery packs, heat dissipation is enhanced through a heat pipe network, and the temperature is monitored in real time. When the temperature is below 10°C, the heating power is increased, and when the temperature is above 30°C, the heating circuit is shut off, thereby achieving effective temperature control. For the star sensor and flywheel outside the cabin, the duty cycle of the heating circuit will be adjusted according to the change of external heat flow to ensure that its temperature is maintained within the operating temperature range. If the temperature does not meet the preset threshold requirement, the ground can send a command, and the thermal control strategy execution module will immediately adjust the execution parameters of the thermal control strategy until the temperature of each device and panel stabilizes within the preset range, thus achieving closed-loop temperature control.

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