Heat supply system based on isotope heat source and working method of heat supply system

Abstract

The application discloses a heat supply enthalpy-increasing chemical propulsion system based on an isotope heat source and a working method thereof, comprising a propellant tank, an isotope heat-electricity catalysis system, a Laval nozzle, an energy storage unit, an electric arc module and a fluid control valve. The system is divided into a main propulsion circuit and a pressure increasing circuit after the propellant tank is led out. The propellant in the main circuit enters a catalysis bed preheated by the isotope heat source, is decomposed, then enters the Laval nozzle and is heated by the electric arc module for enthalpy-increasing, is expanded and sprayed to generate thrust. The propellant in the pressure increasing circuit is branched into two bypasses, respectively flows through a pressure increasing heat exchanger to absorb the waste heat of the cold end of a thermoelectric generator assembly and a regenerative cooling channel of the nozzle, is vaporized after absorbing heat, and is converged to return to the upper part of the tank, so that self-pressurization without a gas cylinder is realized. The application realizes comprehensive utilization of isotope decay heat in heat standby, thermoelectric generation, self-pressurization and electric arc enthalpy-increasing, improves energy utilization efficiency and integration of the system, and is suitable for spaceflight tasks such as deep space exploration, orbit maneuvering and space transfer between the earth and the moon.

Description

Technical Field

[0001] This invention relates to the field of aerospace propulsion technology, specifically to a combined heat and power enthalpy-enhancing chemical propulsion system based on isotope heat sources and its operating method. Background Technology

[0002] With the development of deep space exploration, lunar transfer, and long-duration on-orbit missions, higher demands are being placed on the specific impulse, response speed, and dead weight of aerospace propulsion systems. Traditional monocomponent chemical propulsion systems have a simple structure, but their specific impulse is low due to the limitation of chemical energy; electric propulsion systems have extremely high specific impulse, but their thrust is too small to achieve rapid orbital maneuvers. In addition, existing space isotope heat sources are usually used only as a single power supply module and have not been deeply integrated with the work and pressurization processes of the propulsion system. Summary of the Invention

[0003] To address the problems existing in the prior art, the present invention aims to provide a combined heat and power (CHP) enthalpy-enhancing chemical propulsion system and its operating method based on isotope heat sources. This system constructs a propulsion architecture that coordinates the utilization of thermal, electrical, and chemical energy, establishing three interconnected energy chains: heat transfer, electrical conversion, and working fluid flow. This enables the cascaded utilization of isotope decay heat, improving system integration and propulsion performance without the need for traditional high-pressure gas cylinder pressurization.

[0004] To achieve the above objectives, the present invention adopts the following technical solution: A thermoelectric chemical propulsion system based on an isotope heat source and enthalpy-enhancing cogeneration includes an isotope thermoelectric catalytic system, a propellant tank 11, a Laval nozzle 12, a regeneration cooling channel 13, an energy storage unit 21, an anode 22, a cathode 23, a left-side return check valve 31 and a right-side return check valve 32, a left-side manifold check valve 33 and a right-side manifold check valve 34, a left-side bypass regulating valve 35 and a right-side bypass regulating valve 36, and a main propulsion valve 37. The isotope thermoelectric catalytic system has an axisymmetric coaxial structure, consisting of, from the geometric center outwards, a catalytic bed 1, a thermally conductive inner shell 6, an isotope heat source 2, a thermally conductive outer shell 7, a thermoelectric power generation component 3, a pressurized heat exchanger 5, and a structural outer shell 8; wherein the pressurized heat exchanger 5 has a spiral pressurized heat exchange channel 4 inside. The propellant tank 11 has two outlets: the main propulsion loop is connected to the catalyst bed 1 via the main propulsion valve 37, and the outlet of the catalyst bed 1 is connected to the Laval nozzle 12; the pressurization loop is divided into two branches via the left bypass regulating valve 35 and the right bypass regulating valve 36. The propellant in each branch enters the spiral pressurization heat exchange channel 4 to absorb the residual heat at the cold end, and enters the regeneration cooling channel 13 to absorb the residual heat at the nozzle, and then flows back to the upper gas phase space of the propellant tank 11 through the left return check valve 31 and the right return check valve 32, as well as the left merge check valve 33 and the right merge check valve 34. The decay heat released by the isotope heat source 2 is transferred to the catalyst bed 1 through the thermally conductive inner shell 6, and simultaneously to the thermoelectric generator 3 through the thermally conductive outer shell 7; the cold end of the thermoelectric generator 3 is in contact with the pressurization heat exchanger 5; the thermoelectric generator 3 is electrically connected to the energy storage unit 21 to provide power to the anode 22 and cathode 23 in the Laval nozzle 12. An arc discharge region is formed between the anode 22 and the cathode 23; the high-temperature working fluid generated by the catalytic bed 1 flows through the arc discharge region for secondary heating, which increases the total enthalpy of the working fluid and enhances the propulsion performance.

[0005] The radioactive isotope used in the isotope heat source 2 is one or more of Po-210, Cm-242, Cm-244, and Pu-238.

[0006] The thermoelectric generator 3 is disposed between the thermally conductive outer shell 7 and the pressurized heat exchanger 5, with its hot end in contact with the thermally conductive outer shell 7 and its cold end in contact with the pressurized heat exchanger 5.

[0007] The pressurized heat exchanger 5 is a solid metal structure, and the spiral pressurized heat exchange channel 4 inside it is a spiral heat exchange channel structure. The spiral pressurized heat exchange channel 4 is arranged around the isotope thermoelectric catalytic system in a circumferential manner.

[0008] The thermally conductive inner shell 6 and the thermally conductive outer shell 7 are made of tungsten alloy, molybdenum alloy, tantalum alloy or iridium alloy.

[0009] The outer shell 8 is made of titanium alloy or carbon fiber composite material.

[0010] The propellant is a single-component green propellant system, employing one or more of hydroxylamine nitrate (HAN)-based propellants and dinitramide ammonium (ADN)-based propellants.

[0011] The energy storage unit 21 is a supercapacitor, a battery pack, or a combination of both.

[0012] A method for operating a combined heat and power (CHP) enthalpy-enhancing chemical propulsion system based on an isotope heat source is disclosed. Before system startup and during standby, the isotope heat source 2 continuously releases decay heat, transferring it to the catalytic bed 1 via a thermally conductive inner casing 6, maintaining the catalytic bed 1 in a thermal standby state. Simultaneously, heat is transferred via a thermally conductive outer casing 7 to the hot end of the thermoelectric generator 3, creating a temperature difference between the hot end of the thermoelectric generator 3 and the cold end of the pressurized heat exchanger 5. The thermoelectric generator 3 converts thermal energy into electrical energy, which is continuously output to the energy storage unit 21 for storage. When the propulsion system is operating, propellant is output from the propellant tank 11. Specifically, the propellant in the main propulsion loop enters the catalytic bed 1 via the main propulsion valve 37, undergoes a catalytic decomposition reaction under the action of the catalyst, generating a high-temperature, high-pressure working fluid, which then enters the Laval nozzle 12. During the flow of the working propellant through the Laval nozzle 12, the energy storage unit 21 supplies power to the anode 22 and cathode 23, forming an arc discharge region between the two electrodes. This process increases the enthalpy of the working propellant, raising its total enthalpy before it expands and is ejected through the nozzle to generate thrust. Simultaneously, a portion of the propellant in the pressurization circuit is diverted through the left bypass regulating valve 35 and the right bypass regulating valve 36, flowing through the spiral pressurization heat exchange channel 4 and the regeneration cooling channel 13 respectively, absorbing the residual heat from the pressurization heat exchanger 5 and the Laval nozzle 12. The heat-absorbed propellant then returns to the upper gas phase space of the propellant tank 11 through the left manifold check valve 33, the right manifold check valve 34, the left return check valve 31, and the right return check valve 32. This creates pressurized gas to maintain the pressure within the propellant tank 11, achieving self-pressurization of the propellant supply.

[0013] This invention addresses the problem of limited energy utilization efficiency in existing propulsion systems by proposing a combined heat and power (CHP) enthalpy-enhancing chemical propulsion system and its operating method based on an isotope heat source. The main advantages are as follows: 1. An isotope heat source is placed outside the catalytic bed, and long-term heating is achieved through an inner shell to maintain the high temperature of the catalytic bed. This design significantly improves the response rate of propellant catalytic decomposition, reduces the frequency of cold starts, and effectively extends catalyst life.

[0014] 2. The system utilizes isotope heat sources to generate electricity through thermoelectricity, storing the generated energy in an energy storage unit rather than directly driving an electric arc. During propulsion system operation, the energy storage unit releases a high-frequency, high-current stream into the Laval nozzle to create an arc discharge zone, which reheats the decomposed working fluid, further increasing the total enthalpy of the working fluid and enhancing propulsion performance.

[0015] 3. The high-pressure helium cylinder and pressure reducing valve of the traditional system are eliminated. A small portion of the bypass propellant absorbs the waste heat from the cold end of the thermoelectric generator and the Laval nozzle in the spiral pressurization heat exchange channel and the regeneration cooling channel, respectively. After vaporization, it returns to the upper part of the propellant tank for pressurization, which reduces the dead weight of the system and improves the waste heat utilization rate.

[0016] 4. By multi-level distribution and comprehensive utilization of the decay heat of isotope heat sources, synergistic effects are achieved in catalytic heating, energy conversion, self-pressurization and working fluid enthalpy increase, forming a coupled utilization system between thermal energy, electrical energy and chemical energy, thereby constructing a multi-energy synergistic propulsion architecture and improving the overall energy utilization efficiency and integration of the system. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the enthalpy-enhancing chemical propulsion system and its working method based on isotope heat sources according to the present invention. Detailed Implementation

[0018] The present invention will now be further described with reference to examples and accompanying drawings: like Figure 1As shown, this invention is a thermoelectric chemical propulsion system based on an isotope heat source, comprising an isotope thermoelectric catalytic system, a propellant tank 11, a Laval nozzle 12, a regeneration cooling channel 13, an energy storage unit 21, an anode 22, a cathode 23, a left-side reflux check valve 31, a right-side reflux check valve 32, a left-side manifold check valve 33, a right-side manifold check valve 34, a left-side bypass regulating valve 35, a right-side bypass regulating valve 36, and a main propulsion valve 37; the isotope thermoelectric catalytic system includes a catalyst bed 1, an isotope heat source, and a chemical propulsion system. The system comprises: source 2, thermoelectric generator 3, spiral pressurized heat exchange channel 4, pressurized heat exchanger 5, thermally conductive inner shell 6, thermally conductive outer shell 7, and structural outer shell 8; the catalytic bed 1 is located in the central region of the isotope thermoelectric catalytic system, and the Laval nozzle 12 is connected to the outlet of the catalytic bed 1; the isotope heat source 2 is arranged around the outside of the catalytic bed 1, and exchanges heat with the catalytic bed 1 through the thermally conductive inner shell 6, and with the thermoelectric generator 3 through the thermally conductive outer shell 7; the thermoelectric generator 3 is arranged outside the isotope heat source 2, and its cold end is in contact with the pressurized heat exchanger 5; The pressurized heat exchanger 5 has a spiral heat exchange channel 4 inside, arranged inside the outer shell 8; the propellant tank 11 is connected to the inlet of the catalyst bed 1 through the main propulsion valve 37 to form the main propulsion loop; the propellant tank 11 is connected to the pressurization loop through the left bypass regulating valve 35 and the right bypass regulating valve 36, the pressurization loop including the spiral pressurized heat exchange channel 4 set inside the pressurized heat exchanger 5 and the regeneration cooling channel 13 set inside the wall of the Laval nozzle 12; the propellant is distributed through the left bypass regulating valve 35 and the right bypass regulating valve 36. The system consists of two branches, with the propellant in each branch entering the spiral pressurization heat exchange channel 4 and the regeneration cooling channel 13, respectively. A one-way valve is installed at the outlet of the spiral pressurization heat exchange channel 4 to prevent the high-temperature and high-pressure working fluid in the regeneration cooling channel 13 from flowing back into the spiral pressurization heat exchange channel 4. After the two working fluids absorb heat, they merge and return to the upper gas phase space of the propellant tank 11 through the left return one-way valve 31, the right return one-way valve 32, the left merge one-way valve 33, and the right merge one-way valve 34 to maintain the pressurization of the propellant tank. Thermoelectric generator 3 generates electricity by utilizing the temperature difference between isotope heat source 2 and pressurized heat exchanger 5, and outputs the electricity to energy storage unit 21 for storage. Energy storage unit 21 is connected to anode 22 and cathode 23 to provide electricity to anode 22 and cathode 23. Anode 22 is located on the inner wall of Laval nozzle 12, and cathode 23 is located at the upper center of Laval nozzle 12. An arc discharge region is formed between anode 22 and cathode 23. The high-temperature working fluid generated by catalytic bed 1 flows through the arc discharge region for secondary heating, which increases the total enthalpy of the working fluid and enhances propulsion performance.

[0019] In a preferred embodiment of the present invention, the material of the isotope heat source 2 is selected from one or more of Po-210, Cm-242, Cm-244, and Pu-238. Based on this selection, a continuous and stable external energy source can be provided for the thruster throughout its life cycle, meeting the long-term requirements of system thermoelectric conversion and thermal backup.

[0020] In a preferred embodiment of the present invention, the thermoelectric power generation component 3 is disposed between the heat-conducting outer shell 7 and the pressurized heat exchanger 5, with its hot end in contact with the heat-conducting outer shell 7 and its cold end in contact with the pressurized heat exchanger 5. Based on this selection, it is beneficial to establish a stable temperature difference and improve the power generation efficiency of the thermoelectric power generation component 3.

[0021] In a preferred embodiment of the present invention, the pressurized heat exchanger 5 is a solid metal structure, and the spiral pressurized heat exchange channel 4 inside it is a spiral heat exchange channel structure. The spiral pressurized heat exchange channel 4 is arranged around the isotope thermoelectric catalytic system in a circumferential manner. Based on this selection, the spiral channel effectively increases the heat exchange area and fluid residence time, which not only ensures the heat sink effect of the cold end of the thermoelectric power generation component 3, but also ensures that the bypass propellant can fully absorb the waste heat to complete part or all of the vaporization.

[0022] In a preferred embodiment of the present invention, the thermally conductive inner shell 6 and the thermally conductive outer shell 7 are made of tungsten alloy, molybdenum alloy, tantalum alloy or iridium alloy. Based on this selection, refractory metals have excellent high-temperature thermal conductivity and structural stability, which can efficiently conduct the decay heat of the isotope heat source 2 to the catalyst bed 1 for thermal standby, and can also effectively isolate the heat source from the catalyst particles.

[0023] In a preferred embodiment of the present invention, the material of the outer shell 8 is titanium alloy or carbon fiber composite material. Based on this selection, it is possible to ensure that the outermost layer of the system has extremely high specific strength.

[0024] In a preferred embodiment of the present invention, the propellant is a single-component green propellant system, employing one or more of hydroxylamine nitrate (HAN)-based propellants and dinitramide ammonium (ADN)-based propellants. Based on this selection, the propellant is matched with the catalytic bed, and can achieve stable catalytic decomposition and generate high-temperature fuel gas after entering the catalytic bed.

[0025] In a preferred embodiment of the present invention, the energy storage unit 21 is a supercapacitor, a battery pack, or a combination of both. Based on this selection, the electrical energy generated by the thermoelectric generator can be stored and the power supply can be stably supplied during the arc enthalpy increase process.

[0026] In a preferred embodiment of the present invention, the anode 22 is disposed on the conductive inner wall surface of the Laval nozzle 12, and the cathode 23 is disposed at the upper center of the Laval nozzle 12. An arc discharge region is formed between the anode 22 and the cathode 23. Based on this selection, the gas density in this region is moderate and is in a state of full expansion, which can efficiently convert electrical energy into the high internal energy of the working fluid.

[0027] In a preferred embodiment of the present invention, the valve body materials of the left return check valve 31 and the right return check valve 32, the left manifold check valve 33 and the right manifold check valve 34, the left bypass regulating valve 35 and the right bypass regulating valve 36, and the main propulsion valve 37 are silicon carbide-based composite materials or molybdenum alloys. Based on this selection, the chemical corrosion of the single-component propellant can be effectively resisted, and the structural strength and sealing reliability can be maintained in the phase change vaporization and high-temperature working environment.

[0028] The working principle of this invention is as follows: Before the propulsion system starts up and during the standby phase, the isotope heat source 2 continuously releases decay heat and transfers heat to the catalytic bed 1 through the thermally conductive inner shell 6, keeping the catalytic bed 1 in a hot standby state. Simultaneously, heat is transferred through the thermally conductive outer shell 7 to the hot end of the thermoelectric generator 3, creating a temperature difference between the hot end of the thermoelectric generator 3 and the cold end of the pressurized heat exchanger 5. The thermoelectric generator 3 converts thermal energy into electrical energy and continuously outputs it to the energy storage unit 21 for storage. When the propulsion system is working, the propellant is output from the propellant tank 11. The propellant in the main propulsion loop enters the catalytic bed 1 through the main propulsion valve 37, undergoes a catalytic decomposition reaction under the action of the catalyst, generates a high-temperature, high-pressure working fluid, and enters the Laval nozzle 12. During the flow of the working fluid through the Laval nozzle 12, the energy storage unit 21 supplies power to the anode 22 and cathode 23, forming an arc discharge region between the two electrodes, which performs secondary enthalpy enhancement on the working fluid. After increasing the total enthalpy of the working fluid, it expands and is ejected through the nozzle to generate thrust. Meanwhile, a portion of the propellant in the pressurization circuit is diverted through the left bypass regulating valve 35 and the right bypass regulating valve 36, flowing through the spiral pressurization heat exchange channel 4 and the regeneration cooling channel 13 respectively, absorbing the residual heat from the pressurization heat exchanger 5 and the Laval nozzle 12. The heat-absorbing propellant then returns to the upper gas phase space of the propellant tank 11 through the left manifold check valve 33, the right manifold check valve 34, the left return check valve 31, and the right return check valve 32, forming pressurized gas to maintain the pressure inside the propellant tank 11, thus achieving self-pressurized propellant supply.

Claims

1. A combined heat and power enthalpy-enhancing chemical propulsion system based on an isotope heat source, characterized in that: The system includes an isotope thermoelectric catalytic system, a propellant tank (11), a Laval nozzle (12), a regeneration cooling channel (13), an energy storage unit (21), an anode (22), a cathode (23), a left-side return check valve (31), a right-side return check valve (32), a left-side manifold check valve (33), a right-side manifold check valve (34), a left-side bypass regulating valve (35), a right-side bypass regulating valve (36), and a main propulsion valve (37); the isotope thermoelectric catalytic system includes a catalyst bed (1), an isotope heat source (2), a thermoelectric power generation component (3), a spiral pressurized heat exchange channel (4), a pressurized heat exchanger (5), a thermally conductive inner shell (6), a thermally conductive outer shell (7), and a structural outer shell (8); the catalyst bed (1) Located in the central region of the isotope thermoelectric catalytic system, the Laval nozzle (12) is connected to the outlet of the catalyst bed (1); the isotope heat source (2) is arranged around the outside of the catalyst bed (1) and exchanges heat with the catalyst bed (1) through the heat-conducting inner shell (6), and exchanges heat with the thermoelectric generator assembly (3) through the heat-conducting outer shell (7); the thermoelectric generator assembly (3) is arranged outside the isotope heat source (2), and its cold end is in contact with the pressurized heat exchanger (5); the pressurized heat exchanger (5) is provided with a spiral heat exchange channel (4) inside, which is arranged inside the structural shell (8); the propellant tank (11) is connected to the inlet of the catalyst bed (1) through the main propulsion valve (37) to form the main propulsion loop; the propellant tank (11) is connected to the left bypass regulating valve (35) The right bypass regulating valve (36) is connected to the booster circuit, which includes a spiral booster heat exchange channel (4) located inside the booster heat exchanger (5) and a regeneration cooling channel (13) located inside the wall of the Laval nozzle (12). The propellant is divided into two branches by the left bypass regulating valve (35) and the right bypass regulating valve (36). The propellant in each branch enters the spiral booster heat exchange channel (4) and the regeneration cooling channel (13) respectively. A one-way valve is provided at the outlet of the spiral booster heat exchange channel (4) to prevent the high-temperature and high-pressure working fluid in the regeneration cooling channel (13) from flowing back into the spiral booster heat exchange channel (4). After the two propellant working fluids are split, they absorb heat and merge, passing through the left return one-way valve (31) and the right... The side return check valve (32), the left manifold check valve (33), and the right manifold check valve (34) return to the upper gas phase space of the propellant tank (11) to maintain the pressurization of the propellant tank; the thermoelectric generator (3) generates electrical energy by utilizing the temperature difference between the isotope heat source (2) and the pressurization heat exchanger (5), and outputs the electrical energy to the energy storage unit (21) for storage; the energy storage unit (21) is connected to the anode (22) and the cathode (23) to provide electrical energy to the anode (22) and the cathode (23); wherein the anode (22) is set on the inner wall of the Laval nozzle (12), the cathode (23) is set at the upper center of the Laval nozzle (12), and an arc discharge area is formed between the anode (22) and the cathode (23);The high-temperature working fluid generated by the catalytic bed (1) undergoes secondary heating in the arc discharge region, increasing the total enthalpy of the working fluid and enhancing its propulsion performance.

2. The combined heat and power enthalpy-enhancing chemical propulsion system based on an isotope heat source according to claim 1, characterized in that: The isotopic heat source (2) is selected from one or more of Po-210, Cm-242, Cm-244, and Pu-238.

3. The combined heat and power enthalpy-enhancing chemical propulsion system based on an isotope heat source according to claim 1, characterized in that: The thermoelectric generator component (3) is disposed between the thermally conductive outer shell (7) and the pressurized heat exchanger (5), with its hot end in contact with the thermally conductive outer shell (7) and its cold end in contact with the pressurized heat exchanger (5).

4. The combined heat and power enthalpy-enhancing chemical propulsion system based on an isotope heat source according to claim 1, characterized in that: The pressurized heat exchanger (5) is a solid metal structure, and the spiral pressurized heat exchange channel (4) inside it is a spiral heat exchange channel structure. The spiral pressurized heat exchange channel (4) is arranged around the isotope thermoelectric catalytic system in a circumferential manner.

5. The combined heat and power enthalpy-enhancing chemical propulsion system based on an isotope heat source according to claim 1, characterized in that: The thermally conductive inner shell (6) and the thermally conductive outer shell (7) are made of tungsten alloy, molybdenum alloy, tantalum alloy or iridium alloy.

6. The combined heat and power enthalpy-enhancing chemical propulsion system based on an isotope heat source according to claim 1, characterized in that: The material of the outer shell (8) is titanium alloy or carbon fiber composite material.

7. The combined heat and power enthalpy-enhancing chemical propulsion system based on an isotope heat source according to claim 1, characterized in that: The propellant is a single-component green propellant system, employing one or more of hydroxylamine nitrate-based propellants and dinitramide ammonium-based propellants.

8. The combined heat and power enthalpy-enhancing chemical propulsion system based on an isotope heat source according to claim 1, characterized in that: The energy storage unit (21) is a supercapacitor, a battery pack, or a combination of both.

9. The operating method of the combined heat and power enthalpy-enhancing chemical propulsion system based on an isotope heat source according to any one of claims 1 to 8, characterized in that: Before the propulsion system is started and during the standby phase, the isotope heat source (2) continuously releases decay heat and transfers heat to the catalyst bed (1) through the thermally conductive inner shell (6), keeping the catalyst bed (1) in a hot standby state. At the same time, the heat is transferred to the hot end of the thermoelectric generator (3) through the thermally conductive outer shell (7), forming a temperature difference between the hot end of the thermoelectric generator (3) and the cold end of the pressurized heat exchanger (5). The thermoelectric generator (3) converts thermal energy into electrical energy and continuously outputs it to the energy storage unit (21) for storage. When the propulsion system is working, the propellant is output from the propellant tank (11); the propellant in the main propulsion loop enters the catalyst bed (1) through the main propulsion valve (37), and undergoes a catalytic decomposition reaction under the action of the catalyst to generate a high-temperature and high-pressure working fluid, which then enters the Laval nozzle (12); during the process of the working fluid flowing through the Laval nozzle (12), the energy storage unit (21) supplies power to the anode (22) and cathode (23), forming an arc discharge area between the two electrodes, which performs secondary enthalpy enhancement on the working fluid, and after increasing the total enthalpy of the working fluid, it expands and is ejected through the Laval nozzle (12) to generate thrust; at the same time, the pressurized return Part of the propellant in the path is diverted through the left bypass regulating valve (35) and the right bypass regulating valve (36), and flows through the spiral pressurization heat exchange channel (4) and the regeneration cooling channel (13) respectively to absorb the residual heat of the pressurization heat exchanger (5) and the Laval nozzle (12). After absorbing heat, the propellant returns to the top gas phase space of the propellant tank (11) through the left manifold check valve (33), the right manifold check valve (34), the left return check valve (31), and the right return check valve (32). By forming pressurized gas, the pressure inside the propellant tank (11) is maintained, and the self-pressurization supply of propellant is realized.

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