A multifunctional aerospace heat pipe loop system

Abstract

The present invention relates to a multifunctional aerospace heat pipe loop system, which belongs to the technical fields of aerospace thermal control, aerospace power, and heat exchanger; the system comprises a propulsion system, which comprises a propellant storage tank and a thruster, and propellant is transported between the propellant storage tank and the thruster through a propellant pipeline assembly; the propellant pipeline assembly comprises a propulsion bypass pipeline, and the output end of the propulsion bypass pipeline is connected to the input port of the thruster; the system also comprises a heat dissipation condensation pipeline, a heat absorption evaporation pipeline and a three-way valve; the input end of the heat absorption evaporation pipeline is connected to the output end of the propellant storage tank, and the output end is connected to the three-way valve; the heat absorption evaporation pipeline passes through the heat absorption evaporation area; the input end of the heat dissipation condensation pipeline is connected to the three-way valve, and the output end is connected to the heat absorption evaporation pipeline; the heat dissipation condensation pipeline passes through the heat dissipation condensation area; the three-way valve is connected to the input end of the propulsion bypass pipeline; the propellant can be used as a heat flow carrier medium, and the active heating of the propellant pipeline can be reduced, thereby enhancing the gasification efficiency of the propellant.

Description

Technical Field

[0001] The present invention belongs to the technical fields of aerospace thermal control, aerospace power and heat exchanger, and in particular to a multifunctional aerospace heat pipe loop system. Background Art

[0002] Spacecraft have internal propulsion systems that provide specific propulsion. In spacecraft, especially satellites, the propulsion system is a system derived from this specific power supply and primarily consists of a propulsion system controller, propellant, propellant tanks, and corresponding valves and piping.

[0003] For propulsion systems powered by cold gas propellants, the propellant is a fluid medium, such as xenon, that absorbs heat and transforms from liquid to gas, ultimately being expelled from the spacecraft to provide specific propulsion power. The thrusters can expel the gaseous propellant medium to the outer spacecraft. If the propellant flowing through the thruster is not completely vaporized, the entire system will fail. Therefore, sufficient vaporization of the propellant is a key factor in ensuring the reliable and efficient operation of the propulsion system.

[0004] In common propulsion system solutions, propellant vaporization is primarily achieved through active heating using heaters. For example, Chinese Invention Patent Application No. CN 201911351525 discloses a liquid propellant supply assembly and electric propulsion system for electric propulsion, and Chinese Invention Patent Publication No. CN110697082A discloses an attitude control power system. Both utilize heating devices within the propulsion system pipelines to ensure propellant vaporization. Chinese Invention Patent Publication No. CN112918705A discloses a thermal control system and method for an integrated propulsion subsystem, which utilizes thermal control within the propellant tank. These active propellant vaporization methods are constrained by the space available for heater placement, leading to issues such as short propulsion times, poor propulsion capabilities, and thruster failure due to incomplete vaporization, as the propellant absorbs significant heat during vaporization. Summary of the Invention

[0005] The technical problem to be solved by the present invention is: to overcome the above-mentioned shortcomings of the existing technology and provide a multifunctional aerospace heat pipe loop system, which can use the heat consumption of the spacecraft's own equipment as a heat source to couple the heat pipe and propulsion pipeline circuit for vaporization and heating of the cold propellant. It can not only use the propellant phase change as the thermal control medium in the heat pipe, but also reduce the active heating of the propellant pipeline, enhance the vaporization efficiency of the propellant, thereby increasing the propulsion time of the thruster, directly enhancing the propulsion capability of the thruster, and reducing the risk of thruster failure due to incomplete vaporization.

[0006] In order to solve the above technical problems, the technical solution of the present invention is:

[0007] A multifunctional aerospace heat pipe loop system includes a propulsion system, the propulsion system including a propellant tank and a thruster, propellant being transported between the propellant tank and the thruster via a propellant pipeline assembly; the propellant pipeline assembly includes a propulsion bypass pipeline, the output end of the propulsion bypass pipeline being connected to the input port of the thruster, thereby supplying propellant to the thruster;

[0008] It also includes heat dissipation condensation pipes, heat absorption evaporation pipes and three-way valves;

[0009] The input end of the endothermic evaporation pipe is connected to the output end of the propellant storage tank, and the output end is connected to the three-way valve; the endothermic evaporation pipe passes through the endothermic evaporation zone, and the propellant therein absorbs heat and vaporizes in the endothermic evaporation zone;

[0010] The input end of the heat dissipation and condensation pipeline is connected to the three-way valve, and the output end is connected to the heat absorption and evaporation pipeline; the heat dissipation and condensation pipeline passes through the heat dissipation and condensation area, and the propellant in the heat dissipation and condensation pipeline dissipates heat and condenses in the heat dissipation and condensation area;

[0011] The three-way valve is also connected to the input end of the propulsion bypass pipe; when the propulsion system is working, the three-way valve is controlled to connect the propulsion bypass pipe and the heat absorption evaporation pipe and close the heat dissipation condensation pipe; when the propulsion system is not working, the three-way valve is controlled to connect the heat absorption evaporation pipe and the heat dissipation condensation pipe and close the propulsion bypass pipe.

[0012] In the above-mentioned multifunctional aerospace heat pipe loop system, in the heat absorbing and evaporating zone, the heat absorbing and evaporating pipe is in direct contact with the surface or mounting surface of the high heat consumption equipment for heat conduction; or a good thermal conductor is used to make the heat absorbing and evaporating pipe in indirect contact with the surface or mounting surface of the high heat consumption equipment for heat conduction.

[0013] In the above-mentioned multifunctional aerospace heat pipe loop system, the heat pipe loop utilizes a circulation pump or capillary force to drive the flow of the propellant.

[0014] In the above-mentioned multifunctional aerospace heat pipe loop system, the propulsion system further includes an air filter, which is arranged on the propulsion bypass pipeline and located between the three-way valve and the propeller, and has a heating plate inside the air filter.

[0015] In the above-mentioned multifunctional aerospace heat pipe loop system, a propulsion system fluid component is provided on the propulsion bypass pipeline for controlling the delivery of propellant.

[0016] In the above-mentioned multifunctional aerospace heat pipe loop system, the propulsion system fluid component includes a pressure reducing valve, a proportional control valve and a solenoid valve. The pressure reducing valve, the proportional control valve and the solenoid valve are arranged in sequence on the propulsion bypass pipeline, and the pressure reducing valve is located on the downstream side of the air filter.

[0017] In the above-mentioned multifunctional aerospace heat pipe loop system, a pressure measuring point is provided on the propulsion bypass pipeline, and the pressure measuring point is located between the pressure reducing valve and the proportional control valve.

[0018] In the above-mentioned multifunctional aerospace heat pipe loop system, ball valves are provided on the heat dissipation condensation pipe, the heat absorption evaporation pipe and the propulsion bypass pipe.

[0019] In the above-mentioned multifunctional aerospace heat pipe loop system, the propulsion system includes multiple thrusters and a group of propellant pipeline assemblies. The output end of the propulsion bypass pipeline can be connected to the input ports of the multiple thrusters, and the propulsion bypass pipeline can transport propellant to the multiple thrusters.

[0020] In the above-mentioned multifunctional aerospace heat pipe loop system, the propulsion system includes multiple thrusters and multiple groups of propellant pipeline assemblies, which are arranged in parallel and have consistent flow resistance; the propellant pipeline assemblies correspond one-to-one to the thrusters, and each group of propellant pipeline assemblies transports propellant to one thruster.

[0021] Compared with the prior art, the present invention has the following advantages:

[0022] 1) The multifunctional aerospace heat pipe loop system disclosed in the present invention utilizes the heat consumption of spacecraft equipment as a heat source to provide heat for propellant vaporization. The vaporized propellant is discharged from the spacecraft through the thrusters to provide power for the spacecraft. This technical solution reduces the active heating of the propellant coil valve in conventional technologies and fully utilizes the waste heat of spacecraft equipment to fully vaporize the propellant, thereby improving waste heat utilization, reducing active thermal control power consumption, increasing the thruster's propulsion time, directly enhancing the thruster's propulsion capability, and reducing the risk of thruster failure due to incomplete vaporization.

[0023] 2) When the thrusters are not in operation, the propellant can act as a heat flux carrier in the heat pipe, dissipating heat for spacecraft equipment. This technical solution has good thermal cycling and high adaptability, providing thermal control for spacecraft.

[0024] 3) In general technical solutions, the heat pipe loop and propulsion are independent technologies and lack connection. In the technical solution proposed by the present invention, the heat pipe loop and propulsion technology are coupled with each other. The propellant can be fully vaporized by the heat consumption of the heat absorption zone equipment in the heat pipe technology, and the heat pipe can form a recyclable heat flow carrier with the help of the propellant, thus complementing each other.

[0025] 4) This technical solution differs from other technical solutions in that it enhances the allocation of spacecraft thermal resources. It uses heat pipe loop technology to utilize the waste heat generated by high-heat consumption equipment during operation to provide heat for propellant vaporization. This is a passive heating method, supplemented by a small amount of active heating to achieve full vaporization of the propellant, extend the working time of the thruster, and reduce the risk of permanent damage to valves and thrusters caused by liquid propellant residue. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is the schematic diagram of the multifunctional aerospace heat pipe loop system;

[0027] Figure 2 This is an axial schematic diagram of an embodiment of a multifunctional aerospace heat pipe loop system;

[0028] Figure 3 It is a front view schematic diagram of an embodiment of a multifunctional aerospace heat pipe loop system;

[0029] Figure 4 It is a right side schematic diagram of an embodiment of a multifunctional aerospace heat pipe loop system;

[0030] Figure 5 This is an axial schematic diagram of an embodiment of a multifunctional aerospace heat pipe loop system after removing the cabin plate and the fluid component mounting plate;

[0031] Figure 6 It is a rear view schematic diagram of an embodiment of a multifunctional aerospace heat pipe loop system with the cabin plate and the fluid component mounting plate removed;

[0032] Figure 7 This is an axial schematic diagram of the propulsion bypass pipe, heat dissipation condensation pipe, heat absorption evaporation pipe, propulsion system fluid components and thruster in an embodiment of a multifunctional aerospace heat pipe loop system.

[0033] In the picture:

[0034] 101-rear deck; 102-right deck; 103-lower deck; 104-front deck; 105-upper deck;

[0035] 2-propellant tank; 201-tank bracket;

[0036] 3-Fluid component mounting plate;

[0037] 4-air filter; 401-heating plate;

[0038] 5-pressure reducing valve; 6-proportional regulating valve; 7-pressure measuring point; 8-solenoid valve; 9-thruster; 10-propulsion system controller; 11-integrated electronics; 12-battery; 13-thermal pad; 14-three-way valve; 15-circulation pump; 16-ball valve;

[0039] 1a- propulsion bypass pipe; 1b- heat dissipation condensation pipe; 1c- heat absorption evaporation pipe. DETAILED DESCRIPTION

[0040] The present invention will be further described below in conjunction with the embodiments.

[0041] The present invention proposes a multifunctional aerospace heat pipe loop system, in which a propulsion system is combined with a propellant pipeline assembly. The heat-absorbing evaporation pipeline 1c, the heat-dissipating condensation pipeline 1b and the three-way valve 14 form a heat pipe loop. The heat pipe loop uses the propellant provided by the propellant storage tank 2 as a heat flow carrier source to achieve heat dissipation of high heat consumption equipment; the propulsion bypass pipeline 1a, the heat-absorbing evaporation pipeline 1c and the three-way valve 14 form a propulsion passage, which can not only achieve temperature control of high heat consumption equipment, but also fully vaporize the propellant to expand the capacity of the thruster 9.

[0042] like Figure 1-7 As shown, the multifunctional aerospace heat pipe loop system includes a propulsion system, which primarily comprises a propulsion system controller 10, a propellant tank 2, an air filter 4, a propulsion system fluid assembly, and a thruster 9. Propellant is transported between the propellant tank 2 and the thruster 9 via a propellant pipeline assembly. The propellant pipeline assembly includes a propulsion bypass pipeline 1a, the output end of which communicates with the input port of the thruster 9, supplying propellant to the thruster 9. Propellant from the propellant tank 2 flows through the air filter 4 before being delivered to the thruster 9. The propulsion system fluid assembly is distributed along the propulsion bypass pipeline 1a, downstream of the air filter 4, and controls the delivery of propellant. The air filter 4 includes a heating plate 401 for heating unvaporized propellant to fully vaporize it. The propulsion system controller 10 primarily controls the operation of the thruster 9 and the propulsion system fluid assembly, which is conventional technology.

[0043] like Figure 4 As shown, the spacecraft has a rear deck 101, a right deck 102, a lower deck 103, a front deck 104, an upper deck 105, and a left deck (not shown in the figure), which is the prior art.

[0044] The thruster 9 is installed outside the right cabin panel 102, that is, fixedly installed on the right cabin panel 102 and located in the external space of the spacecraft.

[0045] A fluid assembly mounting plate 3 is fixedly mounted on the inside of the right cabin panel 102, and the propulsion system fluid assembly is mounted on this plate. This mounting plate 3 is located within the spacecraft cabin, on the side of the right cabin panel 102 facing the interior. The propulsion system fluid assembly includes a pressure reducing valve 5, a proportional control valve 6, a solenoid valve 8, and other components. The propulsion bypass line 1a sequentially connects the propellant tank 2, the air filter 4, the pressure reducing valve 5, the proportional control valve 6, the solenoid valve 8, and the thruster 9. A pressure measuring point 7 is also provided on the propulsion bypass line 1a, located between the pressure reducing valve 5 and the proportional control valve 6.

[0046] According to actual needs, the propulsion system fluid component can also be provided with or apply other fluid control mechanisms such as valve bodies.

[0047] A tank bracket 201 is fixedly mounted on the inner side of the lower deck 103 , and the propellant tank 2 is placed on the tank bracket 201 .

[0048] The propulsion system controller 10 is installed on the lower deck 103 of the spacecraft and is located inside the cabin of the spacecraft. The propulsion system controller 10 is a high-heat consumption device. When a high-heat consumption device is in operation, a large amount of heat will be generated, and heat dissipation is required to ensure the normal operation of the device. Depending on the needs, different equipment will be carried inside the spacecraft, such as integrated electronics 11, batteries 12 and other high-heat consumption equipment. The installation location of the propulsion system controller 10, integrated electronics 11, batteries 12 and other high-heat consumption equipment is set to the heat absorption evaporation zone. Figure 2 and Figure 3 As shown, the integrated electronics 11 and battery 12 are mounted on the lower deck 103. The area corresponding to the lower deck 103, the propulsion system controller 10, the integrated electronics 11, and the battery 12 is the heat absorption and evaporation zone. Similarly, if high-heat consumption equipment is mounted on the upper deck 105 according to actual needs, the area corresponding to the high-heat consumption equipment installation location on the upper deck 105 is also the heat absorption and evaporation zone.

[0049] It also includes a heat dissipation condensation pipe 1b, a heat absorption evaporation pipe 1c and a three-way valve 14.

[0050] The heat-absorbing evaporation pipe 1c passes through the spacecraft's heat-absorbing evaporation zone, where the high-heat-consuming equipment contacts the heat-absorbing evaporation pipe 1c for heat transfer. In the heat-absorbing evaporation zone, the heat-absorbing evaporation pipe 1c can directly contact the surface or mounting surface of the high-heat-consuming equipment for heat transfer, or it can indirectly contact the surface or mounting surface of the high-heat-consuming equipment using a good thermal conductor such as a thermal pad 13 or thermally conductive silicone rubber.

[0051] The area of ​​the spacecraft's deck that dissipates heat to the cold space outside the spacecraft can be designated as a heat dissipation condensation zone, with the heat dissipation condensation pipe 1b passing through the spacecraft's heat dissipation condensation zone. For example, if the rear deck 101 is designated as the heat dissipation surface, a portion of the heat dissipation condensation pipe 1b is mounted on the rear deck 101. This allows the heat dissipation of the gaseous propellant within the heat dissipation condensation pipe 1b to the outside.

[0052] One port of three-way valve 14 is connected to the propulsion bypass pipe 1a, located upstream of the air filter 4. The other two ports are connected to the heat-absorbing evaporation pipe 1c and the heat-dissipating condensation pipe 1b, respectively. Specifically, the output end of heat-absorbing evaporation pipe 1c is connected to three-way valve 14, while the input end of heat-dissipating condensation pipe 1b is connected to three-way valve 14.

[0053] The output end of the heat-dissipating condensing pipe 1b is connected to the input end of the heat-absorbing evaporating pipe 1c. Thus, the heat-absorbing evaporating pipe 1c, the heat-dissipating condensing pipe 1b, and the three-way valve 14 form a heat pipe loop. This heat pipe loop can be driven by a circulating pump 15, which is located on the heat-dissipating condensing pipe 1b. Alternatively, it can be a capillary loop, where capillary forces drive the flow of the fluid.

[0054] The output port of the propellant storage tank 2 is communicated with the heat absorbing evaporation pipe 1 c, and the propellant is input into the heat absorbing evaporation pipe 1 c.

[0055] A ball valve 16 can also be provided on the propulsion bypass pipe 1a, the heat dissipation condensation pipe 1b, and the heat absorption evaporation pipe 1c. The ball valve 16 is a gas replacement switch. Before the gas cylinder tank is connected to the pipeline or before the thruster works, a gaseous medium identical to the working propellant is connected to replace the gas in the pipeline. After the pipeline is filled with the working medium, the system starts working again.

[0056] A spacecraft is typically equipped with multiple thrusters 9. The propellant required by these multiple thrusters 9 can be delivered by a single set of propellant pipe assemblies. The output end of the propulsion bypass pipe 1a is connectable to the input ports of multiple thrusters 9, and a single propulsion bypass pipe 1a can deliver propellant to multiple thrusters 9. Alternatively, delivery can be achieved by multiple sets of parallel propellant pipe assemblies, which are arranged in parallel and have consistent flow resistance. There is a one-to-one correspondence between each propellant pipe assembly and each thruster 9, with each set delivering propellant to one thruster 9. That is, one propulsion bypass pipe 1a delivers propellant to one thruster 9.

[0057] Working principle of the multifunctional aerospace heat pipe loop system:

[0058] When the propulsion system is not operating, the propulsion system controller 10 first controls the three-way valve 14 to connect the heat-absorbing evaporation pipe 1c with the heat-dissipating condensation pipe 1b, closing the propulsion bypass pipe 1a and forming a heat pipe loop. Propellant is supplied to the heat pipe loop by the propellant tank 2. The propellant functions as the heat transfer medium in the heat pipe loop. Initially in liquid form upon exiting the propellant tank 2, the liquid medium flows along the heat-absorbing evaporation pipe 1c to the heat-absorbing evaporation zone. The heat-absorbing evaporation pipe 1c directly contacts and conducts heat to high-heat-consuming devices in the heat-absorbing evaporation zone, such as the propulsion system controller 10, integrated electronics 11, and batteries 12, or indirectly contacts and conducts heat via thermal pads 13. This allows waste heat generated by these high-heat-consuming devices to be transferred to the heat-absorbing evaporation pipe 1c. The liquid medium in the heat-absorbing evaporation pipe 1c absorbs heat and evaporates, removing heat from the high-heat-consuming devices and forming a gaseous medium, thereby dissipating heat for these devices. Then, the gaseous medium flows through the three-way valve 14 to the heat dissipation condensation pipe 1b connected to the heat absorption evaporation pipe 1c. The heat dissipation condensation pipe 1b is arranged in the rear cabin 101, that is, the heat dissipation surface of the spacecraft. The heat dissipation condensation pipe 1b is in direct contact with the cold space outside the spacecraft or indirectly in contact with the cabin through heat conduction. The gaseous medium inside the heat dissipation condensation pipe 1b can dissipate heat to the outside. The gaseous medium dissipates heat and condenses to form a liquid medium, which is then driven by the circulation pump 15 to flow back to the heat absorption evaporation pipe 1c. The entire process can realize heat transfer to high heat consumption equipment and achieve continuous thermal control for high heat consumption equipment.

[0059] When the propulsion system is operating—that is, when it needs to provide specific power to the spacecraft—the propulsion system controller 10 first controls three-way valve 14, connecting heat-absorbing evaporation pipe 1c to the propulsion bypass pipe 1a and closing heat-dissipating condensation pipe 1b to form the propulsion path. Propellant is supplied by propellant tank 2, which serves as the propulsion system's motive force. Initially, the motive force is liquid upon exiting tank 2. The liquid flows through the heat pipe loop along heat-absorbing evaporation pipe 1c to the heat-absorbing evaporation zone, where it absorbs heat and evaporates to form a gaseous medium, dissipating heat for high-heat-consuming equipment. Then, the gaseous medium flows through the three-way valve 14 to the propulsion bypass pipe 1a connected to the heat absorption evaporation pipe 1c, and flows along the propulsion bypass pipe 1a to the air filter 4 and the propulsion system fluid component; in order, first through the air filter 4 equipped with a heating plate 401, the air filter 4 can filter out the liquid medium carried by the gaseous medium in the propulsion bypass pipe 1a, and the residual liquid medium can be completely vaporized by supplementary heating by the heating plate 401 in heat conduction contact with the air filter 4; secondly, it passes through the pressure reducing valve 5 to reduce the high-pressure gaseous medium to the design pressure, and then passes through the pressure measuring point 7 for a pressure measurement feedback and then flows to the proportional control valve 6. The proportional control valve 6 is controlled by the propulsion system controller 10 to adjust the flow rate according to the pressure difference between the front and back of the valve. After adjustment by the proportional control valve 6, the gaseous medium parameters can meet the design requirements of the propeller 9 for the power medium, and then passes through the solenoid valve 8 controlled by the propulsion system controller 10 to control the switch, and finally is discharged from the propeller 9 to the outside of the spacecraft.

[0060] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications 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 scope of protection of the technical solutions of the present invention.

Claims

1. A multifunctional aerospace heat pipe loop system, comprising a propulsion system, wherein the propulsion system comprises a propellant storage tank (2) and a thruster (9), and propellant is transported between the propellant storage tank (2) and the thruster (9) via a propellant pipeline assembly; characterized in that: The propellant pipeline assembly comprises a propulsion bypass pipeline (1a), the output end of the propulsion bypass pipeline (1a) is connected to the input port of the propeller (9), and the propellant is input to the propeller (9); It also includes a heat dissipation condensation pipe (1b), a heat absorption evaporation pipe (1c) and a three-way valve (14); The input end of the endothermic evaporation pipe (1c) is in communication with the output end of the propellant storage tank (2), and the output end is in communication with the three-way valve (14); the endothermic evaporation pipe (1c) passes through the endothermic evaporation zone, and the propellant therein absorbs heat and vaporizes in the endothermic evaporation zone; The input end of the heat dissipation and condensation pipeline (1b) is in communication with a three-way valve (14), and the output end is in communication with a heat absorption and evaporation pipeline (1c); the heat dissipation and condensation pipeline (1b) passes through a heat dissipation and condensation zone, and the propellant therein dissipates heat and condenses in the heat dissipation and condensation zone; The three-way valve (14) is also connected to the input end of the propulsion bypass pipe (1a); when the propulsion system is working, the three-way valve (14) is controlled to connect the propulsion bypass pipe (1a) and the heat absorption evaporation pipe (1c), and close the heat dissipation condensation pipe (1b); when the propulsion system is not working, the three-way valve (14) is controlled to connect the heat absorption evaporation pipe (1c) and the heat dissipation condensation pipe (1b), and close the propulsion bypass pipe (1a).

2. The multifunctional aerospace heat pipe loop system according to claim 1, characterized in that: In the heat absorbing evaporation zone, the heat absorbing evaporation pipe (1c) is in direct contact with the surface or mounting surface of the high heat consumption equipment for heat conduction; or a good heat conductor is used to make the heat absorbing evaporation pipe (1c) in indirect contact with the surface or mounting surface of the high heat consumption equipment for heat conduction.

3. The multifunctional aerospace heat pipe loop system according to claim 1, characterized in that: The heat pipe loop utilizes a circulation pump (15) or capillary force to drive the flow of the propellant.

4. The multifunctional aerospace heat pipe loop system according to claim 1, characterized in that: The propulsion system further comprises an air filter (4), which is arranged on the propulsion bypass pipeline (1a) and located between the three-way valve (14) and the propeller (9), and a heating plate (401) is provided in the air filter (4).

5. The multifunctional aerospace heat pipe loop system according to claim 4, characterized in that: A propulsion system fluid component is provided on the propulsion bypass pipe (1a) for controlling the delivery of propellant.

6. The multifunctional aerospace heat pipe loop system according to claim 5, characterized in that: The propulsion system fluid component comprises a pressure reducing valve (5), a proportional regulating valve (6) and a solenoid valve (8), wherein the pressure reducing valve (5), the proportional regulating valve (6) and the solenoid valve (8) are sequentially arranged on the propulsion bypass pipeline (1a), and the pressure reducing valve (5) is located on the downstream side of the air filter (4).

7. The multifunctional aerospace heat pipe loop system according to claim 6, characterized in that: A pressure measuring point (7) is provided on the propulsion bypass pipeline (1a), and the pressure measuring point (7) is located between the pressure reducing valve (5) and the proportional regulating valve (6).

8. The multifunctional aerospace heat pipe loop system according to claim 4, characterized in that: The heat dissipation condensation pipe (1b), the heat absorption evaporation pipe (1c) and the propulsion bypass pipe (1a) are all provided with ball valves (16).

9. The multifunctional aerospace heat pipe loop system according to claim 1, characterized in that: The propulsion system comprises a plurality of thrusters (9) and a group of propellant pipeline components. The output end of the propulsion bypass pipeline (1a) can be connected to the input ports of the plurality of thrusters (9), and the propulsion bypass pipeline (1a) can transport propellant to the plurality of thrusters (9).

10. The multifunctional aerospace heat pipe loop system according to claim 1, characterized in that: The propulsion system comprises a plurality of thrusters (9) and a plurality of groups of propellant pipeline assemblies, wherein the plurality of groups of propellant pipeline assemblies are arranged in parallel and have the same flow resistance; the propellant pipeline assemblies correspond one to one with the thrusters (9), and each group of propellant pipeline assemblies delivers propellant to one thruster (9).

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