High-reliability long-life compensator for spacecraft thermal control and preparation method thereof

Abstract

The application discloses a high-reliability long-service-life compensator for spacecraft thermal control and a preparation method, relates to the field of space temperature control fluid loop compensators, and comprises a storage tank body, an upper cover and a bellows assembly. The upper cover is welded to one end of the storage tank body, and the bellows assembly is welded to the other end of the storage tank body. The bellows assembly is located inside the storage tank body and is used for connecting a thermal control fluid loop. A liquid cavity is formed in the bellows assembly, the liquid cavity is communicated with the thermal control fluid loop, and an air cavity is formed between the bellows assembly and the storage tank body. The main function of the compensator is to reduce fluid loop pressure fluctuation, prevent cavitation caused by excessively low inlet pressure of the loop pump, and compensate for the reduction of liquid working medium caused by long-term operation, maintenance and micro-leakage of the system. The product provided with a liquid level sensor also has a liquid level display function.

Description

Technical Field

[0001] This invention relates to the field of space temperature control fluid loop compensators, specifically to a high-reliability, long-life compensator for spacecraft thermal control and its manufacturing method. Background Technology

[0002] The space temperature-controlled fluid loop system is the primary means of active thermal control for spacecraft, playing a crucial role in the stable operation of the spacecraft. The compensator in the fluid loop balances pressure fluctuations caused by changes in ambient temperature, while also compensating for leaks due to loop malfunctions or natural leakage during long-term use. This ensures that the pump inlet pressure is higher than its cavitation pressure, thereby enabling the pump to operate stably over the long term.

[0003] In the past, compensators used in thermal control fluid loop systems had complex components, poor sealing, and low reliability, which could not meet the mission requirements of spacecraft for high reliability and long service life. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a high-reliability, long-life compensator for spacecraft thermal control, thus solving the reliability and lifespan problems of existing compensators.

[0005] The technical solution of this invention is:

[0006] A high-reliability, long-life compensator for spacecraft thermal control includes a tank body, a top cover, and a bellows assembly. The bellows assembly includes a bellows, a moving head assembly, and a nozzle head. The top cover is welded to one end of the tank body, and the nozzle head is welded to the other end of the tank body. One end of the bellows is welded to the nozzle head, and the other end is connected to the moving head assembly. The bellows and the moving head assembly are located inside the tank body. The nozzle head is used to connect to the thermal control fluid circuit.

[0007] A liquid cavity is formed inside the bellows assembly, which is connected to the thermal control fluid circuit through the nozzle end cap. An air cavity is formed between the bellows assembly and the inner wall of the tank.

[0008] The top cover is welded with a capillary tube for inflation. One end of the capillary tube is connected to the air chamber. After the air chamber is inflated to a certain pressure, the other end of the capillary tube is flattened and sealed to form a seal.

[0009] The top cover is welded with an electrical connector and a liquid level sensor. One end of the electrical connector is connected to an external power source and an output signal acquisition device, and the other end is welded to the wires of the liquid level sensor to provide power to the liquid level sensor and acquire voltage signals.

[0010] The liquid level sensor is fixed inside the top cover, and the pull cable head of the liquid level sensor is fixed to the bellows assembly. The movement of the bellows assembly drives the pull cable head to move, and the displacement of the pull cable head is converted into a voltage signal. The voltage signal is output to the monitoring system through the electrical connector.

[0011] The moving end cap assembly includes a connecting ring, an upper end cap, and a guide ring. The bellows consists of multiple diaphragms welded together in sequence. The end of the bellows away from the nozzle end cap is welded to the connecting ring as a single unit. The upper end cap is welded to the middle of the connecting ring to seal the end of the bellows away from the nozzle end cap. A stepped connecting ring groove is provided on the outer side of the connecting ring. The guide ring is fixedly connected to the connecting ring groove by bolts.

[0012] The guide ring is made of polytetrafluoroethylene.

[0013] There is a gap between the outer circle of the bellows and the inner side of the tank body; the gap between the guide ring and the inner side of the tank body is smaller than the gap between the outer circle of the bellows and the inner side of the tank body.

[0014] The upper cover is provided with a limiting boss at its end. The outer diameter of the limiting boss is smaller than the outer diameter of the upper cover end. The outer diameter of the limiting boss is smaller than the inner diameter of the storage tank. The limiting boss is nested inside the storage tank. The outer sides of the ends where the upper cover and the storage tank are joined are provided with a first welding boss. The first welding boss melts after welding and forms a circumferential weld.

[0015] The inner diameter of the limiting boss is larger than the outer diameter of the connecting ring.

[0016] The spout end cap has an annular groove on its circumferential edge facing the bellows. Along the direction from the top cover to the spout end cap, the outer diameter of the bottom of the annular groove decreases to form a second welding boss. The outer diameter of the second welding boss is smaller than the inner diameter of the tank body so that the second welding boss is nested inside the tank body. The second welding boss is welded to the bellows assembly. The end edge of the spout end cap away from the top cover has a third welding boss, which is welded to the tank body.

[0017] The outer diameter of the second welding boss is 3-4 mm larger than the minimum outer diameter of the annular groove, and the thickness of the second welding boss is 1-1.5 times the thickness of the diaphragm of the bellows.

[0018] The nozzle end cap is provided with multiple raised reinforcing ribs to create a gap between the moving end cap and the nozzle end cap, thus preventing the outer arc surface of the moving end cap from being tightly fitted with the inner arc surface of the nozzle end cap.

[0019] A method for fabricating a high-reliability, long-life compensator for spacecraft thermal control includes:

[0020] S1: Weld the bellows, the moving head assembly, and the nozzle head into a whole to obtain the bellows assembly, and install the guide ring on the outside of the moving head assembly;

[0021] S2: Weld the electrical connector and liquid level sensor to the top cover, electrically connect the electrical connector to the liquid level sensor, and connect the zipper head of the liquid level sensor to the moving end cap assembly;

[0022] S3: Weld the top cover and nozzle end cap to the tank body;

[0023] S4: Weld the capillary tube to the top cover, and inflate the air chamber through the capillary tube; seal the capillary tube.

[0024] To obtain a high-reliability, long-life compensator for spacecraft thermal control as described above.

[0025] In summary, this application includes at least the following beneficial technical effects:

[0026] This invention provides a compensator with high reliability and long lifespan through a fully welded design. The invention uses a welded capillary structure for inflation, replacing the traditional inflation shut-off valve. The electrical connector is a welded type, connected to the compensator body via fusion welding. Welded sealing replaces O-ring sealing, reducing structural components and improving product reliability and sealing performance, eliminating the lifespan issues associated with O-ring seals. It features a simple and compact structure, small size, good sealing performance, long lifespan, and high reliability, meeting the high reliability and long lifespan requirements of spacecraft. The fully welded compensator of this application can operate continuously in orbit for 18 years or undergo more than 150,000 reciprocating cycles of the bellows assembly. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overall structure of the compensator;

[0028] Figure 2 This is a schematic diagram of the welded structure of the top cover;

[0029] Figure 3 A schematic diagram of the structure for welding the moving head;

[0030] Figure 4 A schematic diagram of the welding structure of the nozzle end cap;

[0031] Figure 5 This is a schematic diagram of the reinforcing ribs for the spout end cap.

[0032] Explanation of reference numerals in the attached drawings: 1. Bellows assembly; 2. Tank body; 3. Top cover; 4. Capillary tube; 5. Liquid level sensor; 6. Electrical connector;

[0033] 31. Limiting boss;

[0034] 8. Nozzle end cap; 81. Annular groove; 82. Second welding boss; 83. Third welding boss; 84. Reinforcing rib;

[0035] 11. Bellows; 12. Moving head assembly; 13. Guide ring; 121. Connecting ring; 122. Upper head; 123. Connecting ring groove. Detailed Implementation

[0036] The present application will now be described in further detail with reference to the accompanying drawings and specific embodiments:

[0037] This application discloses a high-reliability, long-life compensator for spacecraft thermal control. Its main function is to reduce pressure fluctuations in the fluid loop, prevent cavitation caused by excessively low inlet pressure of the loop pump, and compensate for the reduction of liquid working fluid due to long-term operation, maintenance, and micro-leakage. Products equipped with a liquid level sensor also have a liquid level display function.

[0038] like Figure 1 As shown, the compensator includes a bellows assembly 1, a tank body 2, and a top cover 3. The bellows assembly 1 includes a bellows 11, a moving end cap assembly 12, and a nozzle end cap 8. The tank body 2 is a cylindrical thin-walled metal structure. The top cover 3 is connected to the top of the tank body 2, and the nozzle end cap 8 is connected to the bottom of the tank body 2. The bellows assembly 1 is located inside the tank body 2. One end of the bellows 11 is welded to the nozzle end cap 8, and the other end is welded to the moving end cap assembly, thus sealing the end of the bellows 11 by the moving end cap assembly. The moving end cap assembly can move within the tank body 2. The bellows assembly 1 isolates relatively independent gas and liquid chambers. The sealed space formed by the inner side of the tank body 2 and the outer side of the bellows assembly 1 is the gas chamber, which is filled with a helium-nitrogen mixture at a certain pressure (helium concentration 10% or less). The internal space of the bellows assembly 1 is the liquid chamber, which is connected to the thermal control fluid circuit to be compensated through the nozzle end cap 8.

[0039] As above Figure 1As shown, the upper cover 3 is welded with an inflation capillary tube 4, a liquid level sensor 5, and an electrical connector 6. First, one end of the capillary tube is inserted into the capillary tube protrusion of the upper cover 3 by approximately 5mm or more, and then the two are welded together. Next, mixed gas is injected into the compensator's gas chamber through the capillary tube 4. Then, the other end of the capillary tube 4 is flattened and sealed, forming a closed space within the gas chamber. After leak detection, the capillary tube 4 is protected with a sleeve, and adhesive is filled into the gap between the sleeve and the capillary tube for protection. During inflation, to control the amount of gas injected, the gas and liquid chambers are simultaneously inflated to ensure consistent pressure on the inner and outer sides of the bellows 11, keeping the bellows 11 in a free state at its upper limit. After reaching a certain pressure, the gas chamber is sealed, and the gas in the liquid chamber is released. The electrical connector 6 is a welded sealing type, connected to the upper cover 3 by fusion welding. The electrical connector 6 is welded into the electrical connector socket of the upper cover 3. One end of the electrical connector 6 has pins connected to an external power source and output signal acquisition device via a cable. The other end of the connector 6 has a solder cup soldered to the wires of the level sensor 5, providing power to the level sensor 5 and acquiring voltage signals. The level sensor 5 is fixed to the inside of the upper cover 3 via a connecting plate, and the cable head of the level sensor 5 is fixed to the connector of the moving end cap assembly of the bellows assembly 1 via a cotter pin. When the bellows assembly reciprocates, it drives the cable head to move, and the displacement of the cable is converted into a change in voltage signal. The voltage signal is output to the monitoring system through the electrical connector, thereby monitoring the working fluid level in the compensator's liquid chamber.

[0040] like Figure 2 As shown, a limiting boss 31 is provided at the end of the upper cover 3, and the outer diameter of the limiting boss 31 is smaller than the outer diameter of the end of the upper cover 3. The outer diameter of the limiting boss 31 is smaller than the inner diameter of the tank body 2, forming an upper limit for the bellows assembly 1. A first welding boss is provided on the outer side of the joint ends of the upper cover 3 and the tank body 2. The first welding boss melts after welding and forms a circumferential weld. After the limiting boss 31 is engaged inside the tank body 2, welding is performed on the outer side between the upper cover 3 and the tank body 2 to complete the connection between the upper cover 3 and the tank body 2.

[0041] like Figure 3 As shown, the moving head assembly 12 includes a connecting ring 121, an upper head 122, a guide ring 13, and a connector. The top end of the bellows 11 is welded integrally with the welding boss of the connecting ring 121. The upper head 122 is welded to the middle of the connecting ring 121 to seal the top of the bellows. A connecting ring groove 123 is provided on the outer circumference of the connecting ring. The connecting ring groove 123 is a stepped groove used for assembling the guide ring 13. The guide ring 13 is fixedly connected to the connecting ring groove 123 by bolts. The guide ring 13 includes multiple arc-shaped segments, and guide ring pads are provided between the multiple arc-shaped segments. The guide ring 13 is made of polytetrafluoroethylene material, which has a self-lubricating effect and can ensure that the bellows assembly 1 moves smoothly back and forth in the tank without jamming.

[0042] To allow the bellows 11 to move flexibly along the inner side of the storage tank 2, a certain gap exists between the outer circle of the bellows 11 and the inner side of the storage tank 2. Considering the flexibility of the bellows 11 itself, a guide ring 13 made of polytetrafluoroethylene is provided at one end of the bellows 11. The guide ring 13 is embedded in the connecting ring groove 123 of the moving head 12. Multiple bolts are arranged in the circumferential direction to connect the guide ring 13 and the connecting ring. The gap between the guide ring 13 and the inner side of the storage tank 2 is smaller than the gap between the outer circle of the bellows 11 and the inner side of the storage tank 2. This can reduce mechanical damage caused by the contact between the bellows 11 and the inner side of the shell during testing, installation and transportation. When the connecting ring of the moving head assembly 12 of the bellows 11 contacts the top cover 3, the bellows 11 is in a free state, avoiding it from being in a stretched state, so as to improve the service life of the bellows 11.

[0043] As above Figure 1 and Figure 4 As shown, the nozzle end cap 8 is a single integral part, machined from bar stock by milling. The nozzle end cap 8 is fitted inside the storage tank 2. An annular groove 81 is provided on the edge of the nozzle end cap 8 facing the bellows 11. Along the direction from the top cover 3 towards the nozzle end cap 8, the outer diameter of the bottom of the annular groove 81 decreases, forming a second welding boss 82. The outer diameter of the second welding boss 82 is smaller than the inner diameter of the storage tank 2, so that the second welding boss 82 is nested inside the storage tank 2. The second welding boss 82 is welded to the bellows assembly 1. Another part of the second welding boss 82 is a wedge-shaped portion, which is adapted to the end of the diaphragm of the bellows 11. A third welding boss 83 is provided on the end edge of the nozzle end cap 8 away from the top cover 3, and the third welding boss 83 is welded to the storage tank 2. The outer diameter of the second welding boss 82 is 3-4 mm larger than the minimum outer diameter of the annular groove 81, and the thickness of the second welding boss 82 is 1-1.5 times the thickness of the diaphragm of the bellows 11.

[0044] like Figure 5 As shown, the liquid chamber is connected to the thermal control fluid circuit through the opening of the nozzle end cap 8. The inner arc surface of the nozzle end cap 8 acts as a lower limit for the moving end cap assembly of the bellows assembly 1, preventing excessive compression of the bellows 11 and plastic deformation of the diaphragm of the welded bellows 11. At the same time, multiple raised reinforcing ribs 84 are provided on the nozzle end cap 8 to ensure that there is a gap between the upper end cap 122 and the nozzle end cap 8. This prevents the outer arc surface of the upper end cap 122 from being tightly fitted with the inner arc surface of the nozzle end cap 8 when the bellows 11 is in the lower limit position, thus avoiding the formation of a dead cavity that would affect the leakage of the working fluid from the liquid chamber and thus preventing the bellows assembly from being opened for an extended period of time.

[0045] Except for the guide ring 13, the compensator is made of 316L stainless steel. 316L stainless steel has a small coefficient of linear expansion, a large thermal conductivity, a high temperature endurance limit, good toughness, and good corrosion resistance. The same material makes the welding performance between different parts good and can avoid electrochemical corrosion between dissimilar materials.

[0046] The capillary tube and the top cover 3, the tank body 2 and the top cover 3, the tank body 2 and the nozzle end cap 8, the adjacent diaphragms of the bellows 11, the bellows 11 and the moving end cap 12, and the bellows 11 and the nozzle end cap 8 are all welded together using the same material.

[0047] The gas chamber is a closed space filled with an inert gas at a certain pressure (in this example, a helium-nitrogen mixture, with 10% helium, to facilitate product sealing tests). The liquid chamber is connected to the thermal control fluid circuit through the opening of the nozzle end cap 8. The pressure in the compensator's liquid chamber is the working fluid pressure of the connected thermal control fluid circuit. This compensator is mainly based on the compressibility of the gas and the axial deformation capability of the bellows 11, relying on the energy of the pressurized gas filled in the gas chamber to achieve real-time pressure balance between the gas and liquid chambers.

[0048] Product assembly sequence:

[0049] 1. Bellows assembly welding, which involves welding the bellows, moving head assembly, and nozzle head into a single unit.

[0050] 2. Install the guide ring and guide ring pad into the connecting ring groove of the moving head.

[0051] 3. Weld the electrical connector to the liquid level sensor;

[0052] Specifically, first weld the electrical connector to the top cover, and then fix the liquid level sensor to the inner wall of the top cover;

[0053] 4. Welding of the bellows assembly nozzle end cap to the tank body;

[0054] 5. Connect the liquid level sensor cable head to the connecting piece of the moving end cap of the bellows assembly;

[0055] 6. The top cover is welded to the storage tank;

[0056] 7. The capillary tube is welded to the top cover;

[0057] 8. Inflate the compensator's air chamber through a capillary tube;

[0058] 9. Capillary sealing;

[0059] 10. A protective sleeve is attached to the outside of the capillary tube.

[0060] The implementation principle of this application is as follows:

[0061] The compensator connected to the thermal control fluid circuit has its liquid chamber connected to the thermal control fluid circuit. The sealed gas chamber is pre-filled with inert gas at a certain pressure. The gas chamber electrical connector 6 outputs a voltage signal in real time to provide feedback on the position information of the moving head 12. When the fluid circuit pressure drops due to working fluid leakage or temperature drop (working fluid contraction), the compensator liquid chamber pressure drops, the gas volume in the gas chamber expands, and the moving head 12 moves in the compression direction of the bellows 11, squeezing the working fluid in the compensator liquid chamber into the circuit. Since the gas chamber is a closed space, according to the ideal gas law, the gas pressure in the gas chamber drops as the volume expands. After the moving head 12 moves a certain distance, the gas and liquid sides of the compensator reach equilibrium at the new pressure and the new position of the moving head 12. The new pressure is slightly less than the original pressure but higher than the pump cavitation pressure, avoiding failure caused by the circuit pressure dropping to the pump cavitation pressure due to working fluid leakage or temperature drop.

[0062] When the pressure in the circuit increases due to factors such as temperature rise, the gas in the gas chamber is compressed, and the moving head 12 moves in the direction of restoring the bellows 11 to its free state. The working fluid in the fluid circuit flows into the compensator's liquid chamber, and the circuit pressure drops. The system reaches equilibrium under the new pressure and the position of the moving head 12. The new pressure is slightly higher than the original pressure, but the liquid pressure drops rapidly with the release of volume, thus avoiding damage to pipeline components caused by excessive pressure of the working fluid in the circuit.

[0063] The entire compensator, except for the guide ring 13 of the gas chamber which is made of polytetrafluoroethylene (PTFE), is made of metal. The guide ring 13 is located inside the gas chamber, so it does not affect the compensator's sealing performance and has minimal wear, meeting the requirements for long service life. All other components of the compensator are connected by welding, ensuring good sealing and eliminating the risk of failure due to expired parts. It effectively balances circuit pressure and compensates for working fluid losses caused by leakage. It also features real-time signal output for convenient monitoring of circuit operation. With its excellent sealing, high reliability, and long service life, it meets the high reliability and long service life requirements of spacecraft missions.

[0064] 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 without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope defined in the claims of the present invention.

Claims

1. A high-reliability, long-life compensator for spacecraft thermal control, characterized in that: The system includes a tank body (2), a top cover (3), and a bellows assembly (1). The bellows assembly (1) includes a bellows (11), a moving head assembly, and a nozzle head (8). The top cover (3) is welded to one end of the tank body (2), and the nozzle head (8) is welded to the other end of the tank body (2). One end of the bellows (11) is welded to the nozzle head (8), and the other end is connected to the moving head assembly. The bellows (11) and the moving head assembly are located inside the tank body. The nozzle head (8) is used to connect the thermal control fluid circuit. A liquid cavity is formed inside the bellows assembly (1), and the liquid cavity is connected to the thermal control fluid circuit through the nozzle end cap (8). An air cavity is formed between the bellows assembly (1) and the inner wall of the tank body (2). The upper cover (3) is welded with an electrical connector (6) and a liquid level sensor (5). One end of the electrical connector (6) is connected to an external power source and an output signal acquisition device, and the other end of the connector is welded to the wire of the liquid level sensor (5) to provide power to the liquid level sensor (5) and acquire voltage signals. The liquid level sensor (5) is fixed inside the top cover (3). The cable head of the liquid level sensor (5) is fixed to the bellows assembly (1). The movement of the bellows assembly (1) drives the cable head to move. The displacement of the cable head is converted into a voltage signal. The voltage signal is output to the monitoring system through the electrical connector (6). The upper cover (3) is provided with a limiting boss (31) at its end. The outer diameter of the limiting boss (31) is smaller than the outer diameter of the upper cover (3) end. The outer diameter of the limiting boss (31) is smaller than the inner diameter of the storage tank (2). The limiting boss (31) is nested inside the storage tank (2). The outer sides of the ends where the upper cover (3) and the storage tank (2) meet are provided with a first welding boss. The first welding boss melts after welding and forms a circumferential weld. The nozzle end cap (8) is provided with an annular groove (81) on the circumferential edge facing the bellows (11). Along the direction from the top cover (3) to the nozzle end cap (8), the bottom outer diameter of the annular groove (81) decreases to form a second welding boss (82). The outer diameter of the second welding boss (82) is smaller than the inner diameter of the tank body (2) so that the second welding boss (82) is nested inside the tank body (2). The second welding boss (82) is welded to the bellows assembly (1). The end edge of the nozzle end cap (8) away from the top cover (3) is provided with a third welding boss, which is welded to the tank body (2).

2. The high-reliability, long-life compensator for spacecraft thermal control according to claim 1, characterized in that: The upper cover (3) is welded with a capillary tube (4) for inflation. One end of the capillary tube (4) is connected to the air chamber. After the air chamber is inflated to a certain pressure, the other end of the capillary tube (4) is flattened and sealed to form a seal.

3. A high-reliability, long-life compensator for spacecraft thermal control according to claim 1, characterized in that: The moving end cap assembly includes a connecting ring (121), an upper end cap (122), and a guide ring (13). The bellows (11) is formed by welding multiple diaphragms in sequence. The end of the bellows (11) away from the nozzle end cap (8) is welded to the connecting ring (121) as a whole. The upper end cap (122) is welded to the middle of the connecting ring (121) to seal the end of the bellows (11) away from the nozzle end cap (8). A stepped connecting ring groove (123) is provided on the outer side of the connecting ring (121). The guide ring (13) is fixedly connected to the connecting ring groove (123) by bolts.

4. A high-reliability, long-life compensator for spacecraft thermal control according to claim 3, characterized in that: The guide ring (13) is made of polytetrafluoroethylene.

5. A high-reliability, long-life compensator for spacecraft thermal control according to claim 3, characterized in that: There is a gap between the outer circle of the corrugated pipe (11) and the inner side of the tank body (2); the gap between the guide ring (13) and the inner side of the tank body (2) is smaller than the gap between the outer circle of the corrugated pipe (11) and the inner side of the tank body (2).

6. A high-reliability, long-life compensator for spacecraft thermal control according to claim 3, characterized in that: The inner diameter of the limiting boss (31) is larger than the outer diameter of the connecting ring (121).

7. A high-reliability, long-life compensator for spacecraft thermal control according to claim 1, characterized in that: The outer diameter of the second welding boss (82) is 3-4 mm larger than the minimum outer diameter of the annular groove (81), and the thickness of the second welding boss (82) is 1-1.5 times the thickness of the diaphragm of the bellows (11).

8. A high-reliability, long-life compensator for spacecraft thermal control according to claim 1, characterized in that: The nozzle end cap (8) is provided with multiple raised reinforcing ribs (84) to ensure that there is a gap between the moving end cap (12) and the nozzle end cap (8), and to prevent the outer arc surface of the moving end cap (12) from being tightly fitted with the inner arc surface of the nozzle end cap (8).

9. A method for manufacturing a high-reliability, long-life compensator for spacecraft thermal control, characterized in that, include: S1: Weld the bellows (11), the moving head assembly and the nozzle head (8) into a whole to obtain the bellows assembly (1), and install the guide ring (13) on the outside of the moving head assembly; S2: Weld the electrical connector (6) and the liquid level sensor (5) to the top cover (3), connect the electrical connector (6) to the liquid level sensor (5), and connect the zipper head of the liquid level sensor (5) to the moving end cap assembly; S3: Weld the top cover (3) and the nozzle end cap (8) to the tank body; S4: Weld the capillary tube (4) to the top cover (3), and inflate the air chamber through the capillary tube (4), and seal the capillary tube (4); Obtain a high-reliability, long-life compensator for spacecraft thermal control as described in any one of claims 1-8.

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