A thermal control system for a spaceborne deployable phased array antenna
By designing thermal radiators on the deployable phased array antenna and combining them with loop heat pipes and distributed cold plates, the thermal control problem of the deployable phased array antenna was solved, achieving on-orbit temperature control and improved mechanical performance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- XIAN INSTITUE OF SPACE RADIO TECH
- Filing Date
- 2023-09-15
- Publication Date
- 2026-07-07
AI Technical Summary
Existing technologies cannot effectively solve the thermal control problem of deployable phased array antennas, especially when the heat dissipation requirements are difficult to meet during on-orbit operation. In addition, traditional devices are large in size and heavy in weight, which affects the reliability and mechanical design of the antenna.
A thermal control system for a spaceborne deployable phased array antenna was designed. The thermal radiator is arranged on the deployable arm using a deployable and locking device. Combined with a loop heat pipe and a distributed cold plate, efficient heat dissipation is achieved through the loop heat pipe pipeline and temperature control circuit, reducing thermal resistance and weight.
It achieves reasonable control of the on-orbit operating temperature of the deployable phased array antenna, reduces the size and weight of the thermal control device, improves heat transfer efficiency and mechanical resistance, and simplifies the design difficulty.
Smart Images
Figure CN117317569B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of thermal control of spaceborne phased array antennas, and relates to a thermal control system for a spaceborne deployable phased array antenna. Background Technology
[0002] With the increasing demands of spacecraft applications, the application forms of spaceborne phased array antennas are also undergoing new changes, evolving from traditional fixed installations on the satellite cabin to deployable phased array antennas. The main characteristic of deployable phased array antennas is that they are folded up on the satellite surface during launch and extended a certain distance from the satellite after entering orbit to avoid obstruction of the antenna's field of view. However, this poses a significant challenge to the antenna's thermal control. Due to the high heat flux density of phased array antennas and their long-term on-orbit operation, the antenna's surface area is insufficient for heat dissipation; furthermore, the deployed antenna is far from the satellite, making it impossible to utilize the satellite's surface heat dissipation capabilities. Therefore, a thermal control system needs to be designed for deployable phased array antennas that can meet the on-orbit thermal control requirements while also accommodating the antenna's deployable structure.
[0003] Chinese patent CN201811532714.1, entitled "A Spaceborne Phased Array Radar Payload Integrated with Satellite Platform Structure Thermal Control," discloses a thermal control device for a spaceborne phased array antenna. This device is located inside the satellite's cabin and utilizes the satellite platform's heat dissipation surface for cooling. However, this thermal control device is unusable over long heat transfer distances and fails to solve the thermal control problem of deployable phased array antennas. Chinese patent CN202210310685.4, entitled "A Dual-Fluid Loop Thermal Control System Suitable for High-Orbit Spacecraft," discloses a spacecraft heat exchange loop thermal control system. This system utilizes pump-valve assemblies to drive the flow of the heat exchange medium. It is heavy, bulky, and requires power and control circuits for the pumps and valves. When applied to deployable phased array antennas, it results in significant mechanical design challenges and a large deployment drag torque. Summary of the Invention
[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a thermal control system for a spaceborne deployable phased array antenna, providing a feasible thermal control scheme for deployable spaceborne phased array antennas and ensuring that the on-orbit operating temperature of high-power deployable phased array antennas is within a reasonable range.
[0005] The solution of the present invention is:
[0006] A spaceborne deployable phased array antenna thermal control system includes a phased array antenna body, a phased array antenna thermal control system, a deployment and locking device, and a satellite compartment panel. The satellite compartment panel is placed horizontally with its outer side wall facing upwards. The deployment and locking device is mounted on the outer side wall of the satellite compartment panel and has a folding structure. The root of the deployment and locking device is connected to the satellite compartment panel. The phased array antenna body is mounted at the head end of the deployment and locking device. The phased array antenna thermal control system is mounted on the side wall of the deployment and locking device.
[0007] In the aforementioned spaceborne deployable phased array antenna thermal control system, the deployment and locking device includes a deployment arm, a radiator support, and a locking device. The deployment arm is a two-bar folding structure, comprising a bottom bar and a top bar. The bottom end of the bottom bar is rotatably connected to the satellite module. The bottom end of the top bar is rotatably connected to the top end of the bottom bar. The phased array antenna body is mounted on the top end of the top bar. The radiator support is mounted on the side wall of the top bar. The phased array antenna thermal control system is connected to the top bar via the radiator support. The locking device is located on the outer side wall surface of the satellite module.
[0008] In the aforementioned thermal control system for a spaceborne deployable phased array antenna, the bottom rod and top rod are rotated and folded to allow the deployable arm to be placed against the outer wall surface of the satellite compartment, and a locking device is used to lock and limit its position.
[0009] In the aforementioned spaceborne deployable phased array antenna thermal control system, the phased array antenna body includes a T / R assembly, a beam control and network assembly, a power supply assembly, and an antenna array; the power supply assembly, beam control and network assembly, T / R assembly, and antenna array are horizontally stacked from top to bottom; the sidewall of the beam control and network assembly is fixedly connected to the top of the deployable arm.
[0010] In the aforementioned spaceborne deployable phased array antenna thermal control system, the phased array antenna thermal control system includes a thermal radiator, a loop heat pipe evaporator, a loop heat pipe pipeline, a heat dissipation system, and a heating system. The thermal radiator is a plate-shaped structure, mounted on the side wall of the top rod in the deployable arm via a radiator bracket. The loop heat pipe evaporator is mounted on the side wall of the top rod head in the deployable arm. The loop heat pipe pipeline is attached to the side wall of the thermal radiator and arranged in a serpentine pattern within the thermal radiator. The heat dissipation system is located on the T / R assembly and the power supply assembly. The heating system is located on the T / R assembly, the power supply assembly, the loop heat pipe evaporator, and the thermal radiator.
[0011] In the aforementioned thermal control system for a spaceborne deployable phased array antenna, the heat dissipation system includes a first distributed cold plate and a second distributed cold plate; wherein, the first distributed cold plate is mounted on the T / R assembly; and the second distributed cold plate is mounted on the side wall of the power supply assembly.
[0012] In the aforementioned thermal control system for a spaceborne deployable phased array antenna, the input ends of both the first and second distributed cold plates are connected to a loop heat pipe evaporator, and the output ends of the first and second distributed cold plates are connected to a loop heat pipe pipeline. This enables the heat from the T / R components and power supply components to be transferred to the thermal radiator through the loop heat pipe pipeline via the driving medium driven by the loop heat pipe evaporator for heat dissipation.
[0013] In the aforementioned thermal control system for a spaceborne deployable phased array antenna, the T / R assembly includes n groups of T / R modules; each group of T / R modules includes m T / R modules placed face-to-face adjacent to each other; and a first distributed cold plate is installed between each pair of adjacent T / R modules in each group.
[0014] In the aforementioned thermal control system for a spaceborne deployable phased array antenna, the heating system includes a first temperature control loop, a second temperature control loop, a third temperature control loop, and a fourth temperature control loop. The first temperature control loop is symmetrically installed on both sides of each T / R module. The second temperature control loop is installed on the side wall of the power supply assembly. The third temperature control loop is installed on the side wall of the loop heat pipe evaporator. The fourth temperature control loop is installed on the side wall of the thermal radiator. The heating control of the T / R assembly, the power supply assembly, the loop heat pipe evaporator, and the thermal radiator is achieved through the first, second, third, and fourth temperature control loops.
[0015] In the aforementioned spaceborne deployable phased array antenna thermal control system, thermally conductive filler is coated between the T / R component and the wave control and network component; thermally conductive filler is coated between the wave control and network component and the power supply component.
[0016] The advantages of this invention compared to the prior art are:
[0017] (1) This invention provides a feasible thermal control scheme for deployable spaceborne phased array antennas, ensuring that the on-orbit operating temperature of high-power deployable phased array antennas remains within a reasonable range. The thermal control device deploys along with the antenna, eliminating the need to occupy the satellite's heat dissipation surface and reducing the heat transfer distance.
[0018] (2) The thermal radiator of the present invention is installed on the unfolding arm. When locked, it makes full use of the space inside the satellite fairing, solves the problem of excessive antenna envelope size during launch, and has a simple structure and high reliability.
[0019] (3) This invention utilizes a loop heat pipe and a distributed cold plate scheme to reduce the thermal resistance between the antenna and the thermal radiator, requiring a smaller thermal radiator area, thereby reducing the weight of the thermal control device. Simultaneously, the compensation power of the antenna under low-temperature operating conditions can be reduced by controlling the on / off state of the loop heat pipe;
[0020] (4) The present invention connects the antenna body and the heat radiator through a smooth inner wall transmission pipe, which improves the mechanical resistance of the heat transfer pipe and reduces the difficulty of the overall mechanical resistance design of the antenna. Attached Figure Description
[0021] Figure 1 This is a schematic diagram of the phased array antenna thermal control system of the present invention in its folded state;
[0022] Figure 2 This is a schematic diagram of the deployed state of the phased array antenna thermal control system of the present invention;
[0023] Figure 3 This is a detailed schematic diagram of the phased array antenna body and the phased array antenna thermal control system of the present invention;
[0024] Figure 4 This is a schematic diagram of the T / R module of the present invention;
[0025] Figure 5 This is a schematic diagram of the heat dissipation system and heating system of the present invention. Detailed Implementation
[0026] The present invention will be further described below with reference to the embodiments.
[0027] This patent proposes a thermal control system for a spaceborne deployable phased array antenna. Its basic principle is as follows: utilizing the antenna layout space, the thermal radiator is arranged on the deployable arm, allowing the thermal control system to deploy along with the antenna, shortening the heat transfer path. The thermal control system uses a loop heat pipe to connect the antenna and the thermal radiator, achieving high coupling with the antenna structure, improving heat transfer efficiency. This allows the weight and volume of the thermal control system to be controlled within a small range, reducing the difficulty of antenna mechanical design and deployable structure design.
[0028] The thermal control system for spaceborne deployable phased array antennas, such as Figure 1-2 As shown, the device includes a phased array antenna body 100, a phased array antenna thermal control system 200, an unfolding and locking device 300, and a satellite module 400. The satellite module 400 is placed horizontally with its outer side wall facing upward. The unfolding and locking device 300 is mounted on the outer side wall of the satellite module 400. The unfolding and locking device 300 has a folding structure. The root of the unfolding and locking device 300 is connected to the satellite module 400. The phased array antenna body 100 is mounted at the head end of the unfolding and locking device 300. The phased array antenna thermal control system 200 is mounted on the side wall of the unfolding and locking device 300.
[0029] like Figure 3As shown, the unfolding and locking device 300 includes an unfolding arm 301, a radiator support 302, and a locking device 303. The unfolding arm 301 is a two-bar folding structure, comprising a bottom bar and a top bar. The bottom end of the bottom bar is rotatably connected to the satellite module 400; the bottom end of the top bar is rotatably connected to the top end of the bottom bar. The phased array antenna body 100 is mounted on the top end of the top bar; the radiator support 302 is mounted on the side wall of the top bar; the phased array antenna thermal control system 200 is connected to the top bar via the radiator support 302; and the locking device 303 is disposed on the outer side wall surface of the satellite module 400. After the bottom bar and top bar are folded, the unfolding arm 301 rests against the outer side wall surface of the satellite module 400, and is locked and limited by the locking device 303.
[0030] like Figure 3 As shown, the phased array antenna body 100 includes a T / R assembly 101, a beam control and network assembly 102, a power supply assembly 103, and an antenna array 104; the power supply assembly 103, the beam control and network assembly 102, the T / R assembly 101, and the antenna array 104 are horizontally stacked from top to bottom; the sidewall of the beam control and network assembly 102 is fixedly connected to the top of the deployable arm 301. Thermally conductive filler is coated between the T / R assembly 101 and the beam control and network assembly 102; thermally conductive filler is coated between the beam control and network assembly 102 and the power supply assembly 103.
[0031] The phased array antenna thermal control system 200 includes a thermal radiator 201, a loop heat pipe evaporator 202, a loop heat pipe duct 203, a heat dissipation system, and a heating system. The thermal radiator 201 is a plate-shaped structure, mounted on the side wall of the top rod in the deployable arm 301 via a radiator bracket 302. The loop heat pipe evaporator 202 is mounted on the side wall of the top rod head in the deployable arm 301. The loop heat pipe duct 203 is attached to the side wall of the thermal radiator 201 and arranged in a serpentine pattern within the thermal radiator 201. The heat dissipation system is mounted on the T / R assembly 101 and the power supply assembly 103. The heating system is mounted on the T / R assembly 101, the power supply assembly 103, the loop heat pipe evaporator 202, and the thermal radiator 201.
[0032] like Figure 4-5 As shown, the heat dissipation system includes a first distributed cold plate 2041 and a second distributed cold plate 2042; wherein, the first distributed cold plate 2041 is mounted on the T / R assembly 101; and the second distributed cold plate 2042 is mounted on the side wall of the power supply assembly 103.
[0033] The input ends of the first distributed cold plate 2041 and the second distributed cold plate 2042 are both connected to the loop heat pipe evaporator 202, and the output ends of the first distributed cold plate 2041 and the second distributed cold plate 2042 are connected to the loop heat pipe 203; thereby realizing the transfer of heat from the T / R component 101 and the power component 103 to the heat radiator 201 through the loop heat pipe 203 via the driving medium of the loop heat pipe evaporator 202 for heat dissipation.
[0034] like Figure 4 As shown, the T / R assembly 101 includes n groups of T / R modules 1011; each group of T / R modules 1011 includes m T / R modules 1011 placed face-to-face; and a first distributed cold plate 2041 is installed between each pair of adjacent T / R modules 1011 in each group.
[0035] like Figure 5 As shown, the heating system includes a first temperature control circuit 2051, a second temperature control circuit 2052, a third temperature control circuit 2053, and a fourth temperature control circuit 2054. The first temperature control circuit 2051 is symmetrically installed on both side walls of each T / R module 1011. The second temperature control circuit 2052 is installed on the side wall of the power supply assembly 103. The third temperature control circuit 2053 is installed on the side wall of the loop heat pipe evaporator 202. The fourth temperature control circuit 2054 is installed on the side wall of the radiant heat pump 201. The heating control of the T / R assembly 101, the power supply assembly 103, the loop heat pipe evaporator 202, and the radiant heat pump 201 is achieved through the first temperature control circuit 2051, the second temperature control circuit 2052, the third temperature control circuit 2053, and the fourth temperature control circuit 2054.
[0036] Example
[0037] See Figure 1 This example provides a thermal control system for a spaceborne deployable phased array antenna in its state before antenna deployment. The thermal control system 200, along with the phased array antenna body 100 and the deployment and locking device 300, is fixed to the outside of the satellite module 400 via the locking device 303. The thermal radiator 201 in the thermal control system 200 is perpendicular to the satellite module 400, ensuring that the thermal radiator 201 remains within the rocket fairing envelope when retracted. The height of the thermal radiator 201 is limited by the fairing envelope.
[0038] See Figure 2This example provides the thermal control system of a spaceborne deployable phased array antenna in the state after the antenna is deployed. The thermal control system 200 deploys together with the phased array antenna body 100 and the deployment and locking device 300. After deployment, the deployment arm 301 forms an angle of approximately 90° with the satellite panel 400. After deployment, the antenna body 100, thermal control system 200, deployment arm 301, and other components are all in a fixed state and no longer move. After deployment, the normal of the thermal radiator 201 points towards the cold air. Its direction is affected by the position of the satellite panel 400. Where possible, the normal of the thermal radiator 201 should be aligned with the ±Y direction of the satellite, taking into account the specific satellite attitude.
[0039] See Figure 3 , Figure 4 and Figure 5 This example provides a thermal control system for a spaceborne deployable phased array antenna, including a thermal radiator 201, a loop heat pipe evaporator 202, a loop heat pipe 203, a first distributed cold plate 2041, a second distributed cold plate 2042, a first temperature control circuit 2051, a second temperature control circuit 2052, a third temperature control circuit 2053, a fourth temperature control circuit 2054, a germanium-coated solar screen, a thermal control multilayer, and thermally conductive fillers, etc.
[0040] The heat radiator 201 is fixed to one side of the unfolding arm 301 by the radiator bracket 302, and both sides of the heat radiator 201 are sprayed with ACR-1G thermal control white paint.
[0041] The loop heat pipe evaporator 202 is installed at one end of the deployable arm 301 near the antenna body.
[0042] T / R module 1011 is located inside the frame of T / R assembly 101. Each first distributed cold plate 2041 is installed between two adjacent rows of T / R modules 1011, and thermally conductive filler is coated on the mounting interface. The number of first distributed cold plates 2041 is determined according to the number of rows of T / R modules 1011; in this case, there are 8 plates. Second distributed cold plates 2042 are installed on the side of power assembly 103, and thermally conductive filler is coated on the mounting interface.
[0043] The loop heat pipe 203 connects the heat radiator 201, the loop heat pipe evaporator 202, multiple first dispersed cold plates 2041, and second dispersed cold plates 2042 in series to form a loop, creating a heat circulation pipeline. To increase the heat exchange area, the loop heat pipe 203 is arranged in a serpentine pattern on the heat radiator 201. The loop heat pipe 203 is fixed to an adjacent structural component.
[0044] The first temperature control circuit 2051 is located on the T / R module 1011, with one branch of the first temperature control circuit 2051 arranged for every two rows of T / R modules 1011. The second temperature control circuit 2052 is located on the side of the power supply assembly 103, installed on the side not where the second distributed cold plate 2042 is mounted. The third temperature control circuit 2053 is located on the side of the loop heat pipe evaporator 202. The fourth temperature control circuit 2054 is located on the side of the heat radiator 201 away from the unfolding arm 301.
[0045] A germanium-coated solar screen is applied to the outer surface of the antenna array 104 to reduce sunlight intake.
[0046] The thermal control multilayer is wrapped around the outer surface of the T / R component 101 frame, the outer surface of the wave control and network component 102, the outer surface of the power supply component 103 and the second distributed cold plate 2042, the outer surface of the loop heat pipe evaporator 202, the outer surface of the expansion arm 301 and the outer surface of the radiator support 302.
[0047] Thermally conductive filler is applied between the T / R component 101 and the beam control and network component 102, and thermally conductive filler is applied between the beam control and network component 102 and the power supply component 103.
[0048] This invention provides a feasible thermal control scheme for deployable spaceborne phased array antennas, ensuring that the on-orbit operating temperature of high-power deployable phased array antennas remains within a reasonable range. The thermal control device deploys along with the antenna, eliminating the need to occupy the satellite's heat dissipation surface and reducing the heat transfer distance.
[0049] The thermal radiator of this invention is mounted on the deployable arm, and when locked, it makes full use of the space inside the satellite fairing, solving the problem of excessive antenna envelope size during launch. It also has a simple structure and high reliability.
[0050] This invention utilizes a loop heat pipe and distributed cold plate design to reduce the thermal resistance between the antenna and the thermal radiator, requiring a smaller thermal radiator area and thus reducing the weight of the thermal control device. Simultaneously, the compensation power of the antenna under low-temperature operating conditions can be reduced by controlling the on / off state of the loop heat pipe.
[0051] This invention connects the antenna body and the heat radiator through a heat transfer pipe with a smooth inner wall, which improves the mechanical resistance of the heat transfer pipe and reduces the difficulty of the overall mechanical design of the antenna.
[0052] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.
Claims
1. A thermal control system for a spaceborne deployable phased array antenna, characterized in that: It includes a phased array antenna body (100), a phased array antenna thermal control system (200), an deployment and locking device (300), and a satellite compartment panel (400). The satellite module (400) is placed horizontally with its outer side wall facing upwards; an unfolding and locking device (300) is installed on the outer side wall of the satellite module (400); the unfolding and locking device (300) has a folding structure; the root of the unfolding and locking device (300) is connected to the satellite module (400); the phased array antenna body (100) is installed at the head end of the unfolding and locking device (300); the phased array antenna thermal control system (200) is installed on the side wall of the unfolding and locking device (300); the unfolding and locking device (300) includes an unfolding arm (301), a radiator support (302), and a locking device (303); the phased array antenna body (100) includes a T / R assembly (101) and a beam control and network assembly (102). The power supply assembly (103) and antenna array (104) are included; the phased array antenna thermal control system (200) includes a thermal radiator (201), a loop heat pipe evaporator (202), a loop heat pipe (203), a heat dissipation system and a heating system; the thermal radiator (201) is mounted on the side wall of the top rod in the deployable arm (301) via a radiator bracket (302); the loop heat pipe evaporator (202) is mounted on the side wall of the top rod head in the deployable arm (301); the loop heat pipe (203) is attached to the side wall of the thermal radiator (201); the heat dissipation system is provided on the T / R assembly (101) and the power supply assembly (103); the heating system is provided on the T / R assembly (101), the power supply assembly (103), the loop heat pipe evaporator (202) and the thermal radiator (201).
2. The thermal control system for a spaceborne deployable phased array antenna according to claim 1, characterized in that: The deployable arm (301) is a two-bar folding structure; the deployable arm (301) includes a bottom bar and a top bar; the bottom end of the bottom bar is rotatably connected to the satellite cabin panel (400); the bottom end of the top bar is rotatably connected to the top end of the bottom bar; the phased array antenna body (100) is installed at the top end of the top bar; the radiator bracket (302) is installed on the side wall of the top bar; the phased array antenna thermal control system (200) is connected to the top bar through the radiator bracket (302); the locking device (303) is set on the outer side wall surface of the satellite cabin panel (400).
3. The thermal control system for a spaceborne deployable phased array antenna according to claim 2, characterized in that: After the bottom rod and top rod are rotated and folded, the unfolding arm (301) is placed on the outer wall surface of the satellite compartment (400) and locked and limited by the locking device (303).
4. The thermal control system for a spaceborne deployable phased array antenna according to claim 2, characterized in that: The power supply assembly (103), the beam control and network assembly (102), the T / R assembly (101), and the antenna array (104) are stacked horizontally from top to bottom; the sidewall of the beam control and network assembly (102) is fixedly connected to the top of the deployable arm (301).
5. The thermal control system for a spaceborne deployable phased array antenna according to claim 4, characterized in that: The heat radiator (201) has a plate-like structure; the loop heat pipe (203) is arranged in a serpentine pattern on the heat radiator (201).
6. The thermal control system for a spaceborne deployable phased array antenna according to claim 5, characterized in that: The heat dissipation system includes a first distributed cold plate (2041) and a second distributed cold plate (2042); wherein the first distributed cold plate (2041) is mounted on the T / R assembly (101); and the second distributed cold plate (2042) is mounted on the side wall of the power supply assembly (103).
7. The thermal control system for a spaceborne deployable phased array antenna according to claim 6, characterized in that: The input ends of the first distributed cold plate (2041) and the second distributed cold plate (2042) are both connected to the loop heat pipe evaporator (202), and the output ends of the first distributed cold plate (2041) and the second distributed cold plate (2042) are connected to the loop heat pipe (203); thereby realizing the transfer of heat from the T / R component (101) and the power component (103) to the heat radiator (201) through the loop heat pipe (203) via the driving medium of the loop heat pipe evaporator (202) for heat dissipation.
8. The thermal control system for a spaceborne deployable phased array antenna according to claim 6, characterized in that: The T / R assembly (101) includes n groups of T / R modules (1011); each group of T / R modules (1011) includes m T / R modules (1011) placed face to face; and a first distributed cold plate (2041) is installed between each pair of adjacent T / R modules (1011).
9. The thermal control system for a spaceborne deployable phased array antenna according to claim 8, characterized in that: The heating system includes a first temperature control circuit (2051), a second temperature control circuit (2052), a third temperature control circuit (2053), and a fourth temperature control circuit (2054). The first temperature control circuit (2051) is symmetrically installed on both sides of each T / R module (1011). The second temperature control circuit (2052) is installed on the side wall of the power supply assembly (103). The third temperature control circuit (2053) is installed on the side wall of the loop heat pipe evaporator (202). The fourth temperature control circuit (2054) is installed on the side wall of the radiator (201). The heating control of the T / R assembly (101), the power supply assembly (103), the loop heat pipe evaporator (202), and the radiator (201) is realized through the first temperature control circuit (2051), the second temperature control circuit (2052), the third temperature control circuit (2053), and the fourth temperature control circuit (2054).
10. The thermal control system for a spaceborne deployable phased array antenna according to claim 4, characterized in that: Thermally conductive filler is applied between the T / R assembly (101) and the beam control and network assembly (102); thermally conductive filler is applied between the beam control and network assembly (102) and the power supply assembly (103).