A liquid rocket cryogenic propellant supply system and method

Abstract

This invention provides a cryogenic propellant supply system and method for liquid rockets, including a cryogenic propellant storage tank unit, a test liquid rocket engine, and a main pipeline. The cryogenic propellant storage tank unit includes a liquid cryogenic medium storage tank and a cryogenic propellant storage tank immersed in the liquid cryogenic medium storage tank. The test liquid rocket engine is connected to the cryogenic propellant outlet of the cryogenic propellant storage tank via the main pipeline. The cryogenic propellant storage tank unit further includes a cryogenic propellant delivery unit for supplying cryogenic propellant to the cryogenic propellant storage tank. The cryogenic propellant storage tank unit also includes a liquid cryogenic medium delivery unit for supplying liquid cryogenic medium to the liquid cryogenic medium storage tank. Through heat exchange between the liquid cryogenic medium and the cryogenic propellant, the propellant supplied to the test liquid rocket engine can be kept at a constant temperature.

Description

Technical Field

[0001] This invention relates to the field of liquid rocket testing, and more specifically to a cryogenic propellant supply system and method for liquid rockets. Background Technology

[0002] In the existing technology, when testing liquid rocket engines, the propellant supply system often uses conventional cryogenic propellant storage tanks. The inner tank is made of stainless steel, the outer tank is made of carbon steel, and the insulation layer is a vacuum + perlite structure. These tanks are typically used to store cryogenic liquids such as liquid oxygen, liquid hydrogen, and liquid methane. Furthermore, the operating pressure of cryogenic propellant storage tanks in the existing technology is generally around 10 MPa.

[0003] In the process of developing this invention, the applicant discovered at least the following problems in the prior art:

[0004] Existing cryogenic propellant storage tanks that only use vacuum jackets for insulation are costly and uneconomical; using simple insulation to cover the tank exterior results in poor insulation performance. Summary of the Invention

[0005] This invention provides a liquid rocket cryogenic propellant supply system and method, which can solve the technical problems in the prior art that "the existing cryogenic propellant storage tanks use only vacuum jackets for insulation, which is costly, uneconomical and expensive; and the simple method of covering the tank exterior with insulation has poor insulation effect".

[0006] To achieve the above objectives, in one aspect, embodiments of the present invention provide a liquid rocket cryogenic propellant supply system, including a cryogenic propellant storage tank unit, a test liquid rocket engine, and a main pipeline. The cryogenic propellant storage tank unit includes a liquid cryogenic medium storage tank and a cryogenic propellant storage tank immersed in the liquid cryogenic medium storage tank. The boiling point of the liquid cryogenic medium in the liquid cryogenic medium storage tank is lower than the boiling point of the cryogenic propellant in the cryogenic propellant storage tank, but higher than the freezing point of the cryogenic propellant, for maintaining the cryogenic propellant at a low temperature.

[0007] The test liquid rocket engine is connected to the cryogenic propellant outlet of the cryogenic propellant storage tank via the main pipeline;

[0008] The cryogenic propellant storage tank unit also includes a cryogenic propellant delivery unit connected to the cryogenic propellant storage tank for providing cryogenic propellant to the cryogenic propellant storage tank;

[0009] The cryogenic propellant storage tank unit also includes a liquid cryogenic medium delivery unit connected to the liquid cryogenic medium storage tank for providing liquid cryogenic medium to the liquid cryogenic medium storage tank.

[0010] On the other hand, embodiments of the present invention also provide a method for supplying cryogenic propellant to a liquid rocket. This method is implemented through a cryogenic propellant supply system, which includes a cryogenic propellant storage tank unit, a test liquid rocket engine, and a main pipeline. The cryogenic propellant storage tank unit includes a liquid cryogenic medium storage tank and a cryogenic propellant storage tank immersed in the liquid cryogenic medium storage tank. The boiling point of the liquid cryogenic medium in the liquid cryogenic medium storage tank is lower than the boiling point of the cryogenic propellant in the cryogenic propellant storage tank, but higher than the freezing point of the cryogenic propellant.

[0011] The test liquid rocket engine is connected to the cryogenic propellant outlet of the cryogenic propellant storage tank via the main pipeline;

[0012] The cryogenic propellant storage tank unit also includes a cryogenic propellant delivery unit connected to the cryogenic propellant storage tank for providing cryogenic propellant to the cryogenic propellant storage tank;

[0013] The cryogenic propellant storage tank unit also includes a liquid cryogenic medium delivery unit connected to the liquid cryogenic medium storage tank for providing liquid cryogenic medium to the liquid cryogenic medium storage tank.

[0014] The method for supplying cryogenic propellant for liquid rockets includes:

[0015] The cryogenic propellant is supplied to the cryogenic propellant storage tank through the cryogenic propellant delivery unit;

[0016] The liquid cryogenic medium is supplied to the liquid cryogenic medium storage tank through the liquid cryogenic medium delivery unit;

[0017] Before testing the liquid rocket engine for the test of the liquid rocket, the cryogenic propellant tank is immersed in the liquid cryogenic medium tank. Through heat exchange between the liquid cryogenic medium and the cryogenic propellant, the cryogenic propellant can be kept within a preset low temperature range.

[0018] During the testing of the test liquid rocket engine for the liquid rocket, cryogenic propellant in the cryogenic propellant storage tank is pushed into the test liquid rocket engine through the main pipeline.

[0019] The above technical solution has the following beneficial effects: When testing liquid rocket engines for liquid rocket testing, by immersing the cryogenic propellant tank in a liquid cryogenic medium tank, where the boiling point of the liquid cryogenic medium is lower than that of the cryogenic propellant but higher than its freezing point, heat exchange between the liquid cryogenic medium and the cryogenic propellant allows the cryogenic propellant to maintain its low temperature, ensuring that the propellant supplied to the test liquid rocket engine remains at a consistently low temperature. This solves the technical problems of "high cost and poor economy when using only vacuum jackets for insulation of cryogenic propellant tanks; and poor insulation effect when using simple insulation to cover the tank exterior." Furthermore, the heat exchange method reduces the high insulation performance requirements of the cryogenic propellant tank, thereby reducing the design difficulty and manufacturing cost. Finally, immersing the cryogenic propellant tank in a liquid cryogenic medium tank reduces the chance of the cryogenic propellant coming into contact with external flammable materials, lowering the risk of fire or explosion. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of a first liquid rocket cryogenic propellant supply system according to an embodiment of the present invention;

[0022] Figure 2 This is a schematic diagram of a second type of liquid rocket cryogenic propellant supply system according to an embodiment of the present invention.

[0023] The reference numerals in the attached figures are as follows:

[0024] 1. Cryogenic propellant storage tank unit; 2. Test liquid rocket engine; 3. Main pipeline; 4. Main valve for liquid supply; 5. Pressurized gas storage device; 6. Pressure control device; 7. First precooling device; 8. Jacketed pipeline; 9. Second precooling device;

[0025] 11. Liquid cryogenic medium storage tank; 12. Cryogenic propellant storage tank; 13. Liquid cryogenic medium conveying unit; 14. Cryogenic propellant conveying unit; 15. Propellant storage tank vent valve; 16. Propellant storage tank safety valve; 17. Liquid cryogenic medium storage tank vent valve;

[0026] 31. Supply fluid flow meter; 32. Supply fluid discharge valve;

[0027] 51. High-pressure booster cylinder; 52. Third pipeline; 53. High-pressure booster cylinder filling valve; 54. High-pressure booster cylinder exhaust valve; 55. High-pressure booster cylinder safety valve; 56. Sixth pipeline;

[0028] 61. Propellant storage tank inlet valve; 62. Pressure boosting control valve; 63. Pressure boosting circuit pressure reducing valve;

[0029] 71. Fourth pipeline; 72. Supply liquid precooling check valve; 73. Supply liquid precooling control valve;

[0030] 91. Fifth pipeline; 92. Interlayer control valve;

[0031] 131. Second pipeline; 132. Liquid cryogenic medium storage tank filling valve;

[0032] 141. First pipeline;

[0033] 142. Propellant tank filling valve; 143. Propellant tank filling filter. Detailed Implementation

[0034] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] like Figure 1 As shown in the figure, in conjunction with an embodiment of the present invention, a cryogenic propellant supply system for liquid rockets is provided, including a cryogenic propellant storage tank unit 1, a test liquid rocket engine 2, and a main pipeline 3. The cryogenic propellant storage tank unit 1 includes a liquid cryogenic medium storage tank 11 and a cryogenic propellant storage tank 12 immersed in the liquid cryogenic medium storage tank 11. The boiling point of the liquid cryogenic medium in the liquid cryogenic medium storage tank 11 is lower than the boiling point of the cryogenic propellant in the cryogenic propellant storage tank 12 and higher than the freezing point of the cryogenic propellant, for maintaining the cryogenic propellant at a low temperature. The test liquid rocket engine 2 is connected to the cryogenic propellant outlet of the cryogenic propellant storage tank 12 through the main pipeline 3. The cryogenic propellant storage tank unit 1 also includes a cryogenic propellant delivery unit 14 connected to the cryogenic propellant storage tank 12 for providing cryogenic propellant to the cryogenic propellant storage tank 12. The cryogenic propellant storage tank unit 1 also includes a liquid cryogenic medium delivery unit 13 connected to the liquid cryogenic medium storage tank 11 for providing liquid cryogenic medium to the liquid cryogenic medium storage tank 11.

[0036] During testing of the test liquid rocket engine 2, the cryogenic propellant storage tank 12 was immersed in the liquid cryogenic medium storage tank 11. The boiling point of the liquid cryogenic medium in the liquid cryogenic medium storage tank 11 was lower than the boiling point of the cryogenic propellant in the cryogenic propellant storage tank 12, but higher than the freezing point of the cryogenic propellant. Through heat exchange between the liquid cryogenic medium and the cryogenic propellant, the cryogenic propellant could be maintained within a preset low temperature range, ensuring that the propellant supplied to the test liquid rocket engine 2 remained at a consistently low temperature. This solved the technical problems of "high cost and poor economy when using only vacuum jacket insulation for cryogenic propellant storage tanks; and poor insulation effect when using simple insulation to cover the tank exterior." Furthermore, the heat exchange method can reduce the high insulation performance requirements of the cryogenic propellant storage tank 12, thereby reducing the design difficulty and manufacturing cost of the cryogenic propellant storage tank 12. Next, immersing the cryogenic propellant storage tank 12 in the liquid cryogenic medium storage tank 11 reduced the opportunity for the cryogenic propellant to come into contact with external flammable materials, reducing the risk of fire or explosion.

[0037] Preferably, such as Figure 2 As shown, the cryogenic propellant delivery unit 14 includes a first pipeline 141 for delivering propellant from the propellant source to the cryogenic propellant storage tank 12, and a propellant storage tank filling valve 142 and a propellant storage tank filling filter 143 provided on the first pipeline 141. When delivering propellant to the cryogenic propellant storage tank 12, the propellant storage tank filling valve 142 and the propellant storage tank filling filter 143 are opened, and the propellant is filtered through the propellant storage tank filling filter 143. The filtered propellant then enters the cryogenic propellant storage tank 12. The cryogenic propellant storage tank 12 is determined by specific design specifications to be either a single tank or a group of multiple parallel tanks.

[0038] The liquid cryogenic medium delivery unit 13 includes a second pipeline 131 for delivering the liquid cryogenic medium from the liquid cryogenic medium source to the liquid cryogenic medium storage tank 11, and a liquid cryogenic medium storage tank filling valve 132 provided on the second pipeline 131. Preferably, the liquid cryogenic medium storage tank 11 is a large-volume low-pressure storage tank for adding liquid cryogenic medium for heat exchange. The liquid cryogenic medium can be liquid nitrogen or the same cryogenic propellant, but no pressurization is required. When adding liquid cryogenic medium to the liquid cryogenic medium storage tank 11, the liquid cryogenic medium storage tank filling valve 132 provided on the second pipeline 131 is opened, and the liquid cryogenic medium from the liquid cryogenic medium source is delivered to the liquid cryogenic medium storage tank 11 through the second pipeline 131.

[0039] The liquid rocket cryogenic propellant supply system also includes a main supply valve 4 located on the main pipeline 3, which controls the opening and closing of the main pipeline 3. When cryogenic propellant is supplied from the cryogenic propellant storage tank 12 to the test liquid rocket engine 2, the main supply valve 4 is opened, and the main pipeline 3 is opened. Depending on the pressure and leakage requirements of the test liquid rocket engine 2, one or two main supply valves 4 can be connected in series, with the first located near the cryogenic propellant storage tank 12 and the second located on the main pipeline 3 before the test liquid rocket engine 2.

[0040] Preferably, such as Figure 2 As shown, the liquid rocket cryogenic propellant supply system further includes a supply flow meter 31 and a supply discharge valve 32 installed on the main pipeline 3. The supply flow meter 31 is located between the main supply valve 4 and the test liquid rocket engine 2. During the process of supplying cryogenic propellant from the cryogenic propellant storage tank 12 to the test liquid rocket engine 2, the supply flow meter 31 measures the flow rate of the cryogenic propellant in the main pipeline 3. The supply discharge valve 32 is located between the supply flow meter 31 and the test liquid rocket engine 2 and is used to discharge the cryogenic propellant in the main pipeline 3.

[0041] Preferably, such as Figure 2 As shown, the cryogenic propellant storage tank unit 1 also includes a propellant storage tank safety valve 16 connected to the cryogenic propellant storage tank 12. The propellant storage tank safety valve 16 is used to detect the pressure inside the cryogenic propellant storage tank 12. When the pressure rises abnormally to the limit of the propellant storage tank safety valve 16, the mechanical propellant storage tank safety valve 16 will automatically open to release pressure, which is used to prevent the cryogenic propellant in the cryogenic propellant storage tank 12 from vaporizing and causing the internal pressure to rise excessively and be damaged.

[0042] The cryogenic propellant storage tank unit 1 further includes a propellant tank vent valve 15 connected to the cryogenic propellant storage tank 12. The propellant tank vent valve 15 can be composed of a single valve or a group of valves in parallel, specifically determined according to the operating pressure and volume of the cryogenic propellant storage tank 12. The propellant tank vent valve 15 is remotely controlled and can actively vent and depressurize according to test requirements, discharging the remaining high-pressure pressurized gas in the cryogenic propellant storage tank 12 to achieve pressure control; and can also be used to discharge the remaining high-pressure pressurized gas in the cryogenic propellant storage tank 12 after the test is completed. Preferably, the propellant tank vent valve 15 is a pneumatic valve or a solenoid valve. In this embodiment of the invention, all vent valves are remotely controlled by a remote control system.

[0043] The cryogenic propellant storage tank unit 1 also includes a cryogenic medium storage tank exhaust valve 17 connected to the cryogenic medium storage tank 11. During the heat exchange process between the cryogenic medium storage tank 11 and the cryogenic propellant storage tank 12, the cryogenic medium in the cryogenic medium storage tank 11 continuously evaporates and vaporizes to form a gaseous medium, thus increasing the gas pressure inside the cryogenic medium storage tank 11. Therefore, the pressure inside the cryogenic medium storage tank 11 and the boiling point and thermal equilibrium temperature of the cryogenic medium can be controlled remotely by opening and closing the cryogenic medium storage tank exhaust valve 17, thereby achieving the required temperature regulation for the cryogenic propellant storage tank 12. In addition, when the gas pressure inside the cryogenic medium storage tank 11 is detected to have risen to a set threshold, the cryogenic medium storage tank exhaust valve 17 is opened remotely to discharge the gaseous medium, preventing the cryogenic medium storage tank 11 from exceeding the limit due to pressure increase.

[0044] Preferably, such as Figure 2 As shown, the liquid rocket cryogenic propellant supply system further includes a pressurized gas storage device 5. The pressurized gas storage device 5 includes a high-pressure pressurized gas cylinder 51 and a third pipeline 52 connecting the high-pressure pressurized gas cylinder 51 and the cryogenic propellant storage tank 12. The high-pressure pressurized gas cylinder 51 provides pressurized gas with a pressure higher than the cryogenic propellant pressure inside the cryogenic propellant storage tank 12 via the third pipeline 52. The high-pressure pressurized gas cylinder 51 is an all-metal or composite material cylinder, and can be a single cylinder or a group of cylinders. The high-pressure pressurized gas cylinder 51 stores high-pressure pressurized gas, and the stored high-pressure pressurized gas pressure is higher than the cryogenic propellant pressure inside the cryogenic propellant storage tank 12. By forcing the high-pressure pressurized gas into the cryogenic propellant storage tank 12 through the third pipeline 52, the cryogenic propellant inside the cryogenic propellant storage tank 12 is squeezed and enters the main pipeline 3, thereby providing cryogenic propellant that meets the pressure requirements for the test liquid rocket engine 2.

[0045] Preferably, such as Figure 2 As shown, the booster gas storage device 5 further includes a sixth pipeline 56 for conveying booster gas from the booster gas source to the high-pressure booster gas cylinder 51 and a high-pressure booster gas cylinder filling valve 53 provided on the sixth pipeline 56. The sixth pipeline 56 is connected to the high-pressure booster gas cylinder 51. After the high-pressure booster gas cylinder filling valve 53 is opened, the high-pressure booster gas from the high-pressure booster gas source can be filled into the high-pressure booster gas cylinder 51 and filled to a specified pressure. Preferably, the high-pressure booster gas cylinder filling valve 53 is a pneumatic valve or a solenoid valve.

[0046] The pressurized gas storage device 5 also includes a high-pressure pressurized gas cylinder safety valve 55 connected to the high-pressure pressurized gas cylinder 51, which is used to detect the pressure of the high-pressure pressurized gas in the high-pressure pressurized gas cylinder 51. When the pressure of the high-pressure pressurized gas is higher than the pressurized gas pressure threshold, the mechanical high-pressure pressurized gas cylinder safety valve 55 will automatically open to release pressure, thereby protecting the high-pressure pressurized gas cylinder 51.

[0047] The pressurized gas storage device 5 also includes a high-pressure pressurized gas cylinder exhaust valve 54 connected to the high-pressure pressurized gas cylinder 51. The high-pressure pressurized gas cylinder exhaust valve 54 can be composed of a single valve or a group of valves in parallel, specifically determined by the operating pressure and volume of the high-pressure pressurized gas cylinder 51. According to test requirements, the high-pressure pressurized gas cylinder exhaust valve 54 can be opened remotely or automatically to release pressure and discharge high-pressure pressurized gas, thus achieving pressure control. The high-pressure pressurized gas cylinder exhaust valve 54 can be a pneumatic valve or a solenoid valve.

[0048] Preferably, such as Figure 2 As shown, the liquid rocket cryogenic propellant supply system further includes a pressure control device 6 installed on the third pipeline 52. The pressure control device 6 includes a propellant tank inlet valve 61 and a pressure control valve 62 installed on the third pipeline 52. The propellant tank inlet valve 61 is located near the cryogenic propellant tank 12, and the pressure control valve 62 is located near the high-pressure booster cylinder 51. The propellant tank inlet valve 61 is used to isolate or supply high-pressure booster gas from the high-pressure booster cylinder 51 to the cryogenic propellant tank 12. The pressure control valve 62 is used to depressurize the high-pressure gas from the high-pressure booster cylinder 51 to a specified pressure range, so that the pressure of the high-pressure booster gas entering the cryogenic propellant tank 12 is stable. This ensures that after the high-pressure booster gas enters the cryogenic propellant tank 12, it can deliver the cryogenic propellant into the main pipeline 3, further ensuring that the cryogenic propellant entering the test liquid rocket engine 2 meets the pressure requirements. Among them, the pressurization control valve 62 is a pneumatic valve or a solenoid valve, and the propellant storage tank inlet valve 61 is a pneumatic valve or a solenoid valve.

[0049] Preferably, such as Figure 2 As shown, the pressure control device 6 also includes a booster pressure reducing valve 63 located on the third pipeline 52. The booster pressure reducing valve 63 is located between the propellant tank inlet valve 61 and the booster control valve 62. The booster pressure reducing valve 63 is an electrically controlled pressure reducing valve used to isolate or supply high-pressure booster gas.

[0050] Preferably, such as Figure 2As shown, the liquid rocket cryogenic propellant supply system further includes a first precooling device 7 connected to the main pipeline 3 for precooling the main pipeline 3. The first precooling device 7 includes a fourth pipeline 71 for conveying the precooled cryogenic medium from the precooled cryogenic medium source to the main pipeline 3, and a supply liquid line precooling check valve 72 and a supply liquid line precooling control valve 73 provided on the fourth pipeline 71. Before the cryogenic propellant in the cryogenic propellant storage tank 12 is supplied to the test liquid rocket engine 2, the supply liquid line precooling check valve 72 and the supply liquid line precooling control valve 73 are opened, and the precooled cryogenic medium from the precooled cryogenic medium source is conveyed to the main pipeline 3 through the fourth pipeline 71. The boiling point of the precooled cryogenic medium is much lower than the recommended boiling point for cryogenic conditions, so it can remove the heat in the main pipeline 3, thereby reducing the temperature of the main pipeline 3 to below the recommended boiling point for cryogenic conditions in advance, and achieving precooling of the main pipeline 3. In the process of passing the cryogenic propellant in the cryogenic propellant storage tank 12 through the test liquid rocket engine 2 of the main pipeline 3, the disadvantages of pre-cooling the main pipeline 3 by directly using the cryogenic propellant in the cryogenic propellant storage tank 12 in advance, which would result in a decrease in the consumption of cryogenic propellant and a shortening of the formal working time of the test liquid rocket engine 2, or increasing the volume of the cryogenic propellant storage tank 12 to overcome the disadvantage of large cryogenic propellant loss, which would increase the difficulty and cost of tank manufacturing.

[0051] Preferably, such as Figure 2 As shown, the liquid rocket cryogenic propellant supply system further includes a jacketed pipe 8 fitted onto the outer surface of the main pipeline 3; the liquid rocket cryogenic propellant supply system also includes a second precooling device 9 for precooling the jacketed pipe 8. The second precooling device 9 includes a fifth pipe 91 for conveying the precooled cryogenic medium from the precooled cryogenic medium source to the jacketed pipe 8 and a jacketed pipe control valve 92 provided on the fifth pipe 91. Before the cryogenic propellant in the cryogenic propellant storage tank 12 is supplied to the test liquid rocket engine 2, the jacketed pipe control valve 92 on the fifth pipe 91 is opened, and the precooled cryogenic medium from the precooled cryogenic medium source is conveyed to the jacketed pipe 8 through the fifth pipe 91. The flow of the precooled cryogenic medium in the jacketed pipe 8 further removes the heat from the outer wall of the cooling main pipeline 3, thereby further reducing the temperature of the main pipeline 3 and improving the precooling effect of the main pipeline 3. During the process of transferring the cryogenic propellant from the cryogenic propellant storage tank 12 to the test liquid rocket engine 2, the vaporization of the cryogenic propellant and the resulting waste are avoided. Furthermore, the pre-cooling cryogenic medium source used in the second pre-cooling device 9 is the same as that used in the second pre-cooling device 7; one branch of the pre-cooling cryogenic medium source is connected to the second pre-cooling device 7, and the other branch is connected to the second pre-cooling device 9.

[0052] Preferably, in conjunction with embodiments of the present invention, a method for supplying cryogenic propellant to a liquid rocket is provided. This method is implemented through a cryogenic propellant supply system, which includes a cryogenic propellant storage tank unit 1, a test liquid rocket engine 2, and a main pipeline 3. The cryogenic propellant storage tank unit 1 includes a liquid cryogenic medium storage tank 11 and a cryogenic propellant storage tank 12 immersed in the liquid cryogenic medium storage tank 11. The boiling point of the liquid cryogenic medium in the liquid cryogenic medium storage tank 11 is lower than the boiling point of the cryogenic propellant in the cryogenic propellant storage tank 12, but higher than the freezing point of the cryogenic propellant.

[0053] The test liquid rocket engine 2 is connected to the cryogenic propellant outlet of the cryogenic propellant storage tank 12 via the main pipeline 3;

[0054] The cryogenic propellant storage tank unit 1 further includes a cryogenic propellant delivery unit 14 connected to the cryogenic propellant storage tank 12 and used to provide cryogenic propellant to the cryogenic propellant storage tank 12;

[0055] The cryogenic propellant storage tank unit 1 further includes a liquid cryogenic medium delivery unit 13 connected to the liquid cryogenic medium storage tank 11 and used to provide liquid cryogenic medium to the liquid cryogenic medium storage tank 11.

[0056] The method for supplying cryogenic propellant for liquid rockets includes:

[0057] The cryogenic propellant is supplied to the cryogenic propellant storage tank 12 through the cryogenic propellant delivery unit 14;

[0058] The liquid cryogenic medium is supplied to the liquid cryogenic medium storage tank 11 through the liquid cryogenic medium delivery unit 13;

[0059] Before testing the liquid rocket engine 2 for the test of the liquid rocket, the cryogenic propellant tank 12 is immersed in the liquid cryogenic medium tank 11. Through heat exchange between the liquid cryogenic medium and the cryogenic propellant, the cryogenic propellant can be kept within a preset low temperature range.

[0060] During the test of the liquid rocket engine 2 for the test of the liquid rocket, the cryogenic propellant in the cryogenic propellant storage tank 12 is pushed into the test liquid rocket engine 2 through the main pipeline 3.

[0061] By exchanging heat between the cryogenic medium and the cryogenic propellant, the cryogenic propellant can be maintained within a preset cryogenic range, ensuring that the propellant supplied to the test liquid rocket engine 2 remains at a consistently low temperature. This solves the technical problems of "high cost and poor economy when using only vacuum jackets for insulation of cryogenic propellant tanks; and poor insulation effect when using simple insulation to cover the tank exterior." Furthermore, the heat exchange method reduces the high insulation performance requirements of the cryogenic propellant tank 12, thereby reducing the design difficulty and manufacturing cost of the cryogenic propellant tank 12. Next, immersing the cryogenic propellant tank 12 in the cryogenic medium tank 11 reduces the chance of the cryogenic propellant coming into contact with external flammable materials, lowering the risk of fire or explosion.

[0062] Preferably, the cryogenic propellant delivery unit 14 includes a first pipeline 141 for delivering propellant from the propellant source to the cryogenic propellant storage tank 12, and a propellant storage tank filling valve 142 and a propellant storage tank filling filter 143 provided on the first pipeline 141;

[0063] The liquid cryogenic medium delivery unit 13 includes a second pipeline 131 for delivering the liquid cryogenic medium from the liquid cryogenic medium source to the liquid cryogenic medium storage tank 11, and a liquid cryogenic medium storage tank filling valve 132 provided on the second pipeline 131;

[0064] The liquid rocket cryogenic propellant supply system also includes a main supply valve 4 located on the main pipeline 3.

[0065] The method for supplying cryogenic propellants for liquid rockets further includes:

[0066] When supplying propellant to the cryogenic propellant storage tank 12, the propellant storage tank filling valve 142 and the propellant storage tank filling filter 143 on the first pipeline 141 are opened, and the propellant is filtered through the propellant storage tank filling filter 143. The filtered propellant then enters the cryogenic propellant storage tank 12. The cryogenic propellant storage tank 12 is determined by specific design specifications to be either a single tank or a group of multiple parallel tanks.

[0067] When adding liquid cryogenic medium to the liquid cryogenic medium storage tank 11, the liquid cryogenic medium storage tank filling valve 132 located on the second pipeline 131 is opened, and the liquid cryogenic medium in the liquid cryogenic medium source is transported to the liquid cryogenic medium storage tank 11 through the second pipeline 131. The liquid cryogenic medium storage tank 11 is a large-volume low-pressure storage tank used to add liquid cryogenic medium for heat exchange. The liquid cryogenic medium can be liquid nitrogen or the same cryogenic propellant, but no pressurization is required.

[0068] The cryogenic propellant in the cryogenic propellant storage tank 12 is pushed into the test liquid rocket engine 2 through the main pipeline 3, including:

[0069] Opening the main valve 4 of the supply fluid creates a passage in the main pipeline 3, allowing the cryogenic propellant in the cryogenic propellant storage tank 12 to be pushed into the test liquid rocket engine 2 through the main pipeline 3.

[0070] Based on the pressure and leakage requirements of the propellant for the test liquid rocket engine 2, one or two main supply valves 4 can be connected in series. The first one is located near the end of the cryogenic propellant storage tank 12, and the second one is located on the main pipeline 3 before the test liquid rocket engine 2.

[0071] Preferably, the cryogenic propellant supply system for the liquid rocket further includes a supply liquid flow meter 31 and a supply liquid discharge valve 32 disposed on the main pipeline 3. The supply liquid flow meter 31 is disposed between the main supply liquid valve 4 and the test liquid rocket engine 2, and the supply liquid discharge valve 32 is disposed between the supply liquid flow meter 31 and the test liquid rocket engine 2.

[0072] The method for supplying cryogenic propellants for liquid rockets further includes:

[0073] During the process of supplying cryogenic propellant from the cryogenic propellant storage tank 12 to the test liquid rocket engine 2, the flow rate of the cryogenic propellant in the main pipeline 3 is measured by the supply flow meter 31;

[0074] The cryogenic propellant in the main pipeline 3 can be discharged as needed through the supply fluid discharge valve 32.

[0075] Preferably, the cryogenic propellant storage tank unit 1 further includes a propellant storage tank vent valve 15 connected to the cryogenic propellant storage tank 12;

[0076] The cryogenic propellant storage tank unit 1 also includes a propellant storage tank safety valve 16 connected to the cryogenic propellant storage tank 12;

[0077] The cryogenic propellant storage tank unit 1 also includes a liquid cryogenic medium storage tank exhaust valve 17 connected to the liquid cryogenic medium storage tank 11.

[0078] The method for supplying cryogenic propellants for liquid rockets further includes:

[0079] The pressure inside the cryogenic propellant tank 12 is detected by the propellant tank safety valve 16. When the pressure rises abnormally to the limit of the propellant tank safety valve 16, the propellant tank safety valve 16 automatically opens and automatically releases pressure.

[0080] According to the test requirements, the propellant tank vent valve 15 is opened by a remote control system to actively vent and depressurize the cryogenic propellant tank 12; pressure control is achieved by releasing the remaining high-pressure pressurized gas in the cryogenic propellant tank 12; and the remaining high-pressure pressurized gas in the cryogenic propellant tank 12 is released after the test. Preferably, the propellant tank vent valve 15 is a pneumatic valve or a solenoid valve, which can be composed of a single valve or a group of valves in parallel, specifically determined according to the operating pressure and volume of the cryogenic propellant tank 12. In this embodiment of the invention, all vent valves are remotely controlled by a remote control system.

[0081] The method for supplying cryogenic propellants for liquid rockets further includes:

[0082] The cryogenic propellant storage tank unit 1 also includes a cryogenic medium storage tank exhaust valve 17 connected to the cryogenic medium storage tank 11. During the heat exchange process between the cryogenic medium storage tank 11 and the cryogenic propellant storage tank 12, the cryogenic medium in the cryogenic medium storage tank 11 continuously evaporates and vaporizes to form a gaseous medium, thus increasing the gas pressure inside the cryogenic medium storage tank 11. Therefore, the opening and closing of the cryogenic medium storage tank exhaust valve 17 can be remotely controlled by a remote control system to control the pressure inside the cryogenic medium storage tank 11 and the boiling point and thermal equilibrium temperature of the cryogenic medium, thereby achieving the required temperature regulation for the cryogenic propellant storage tank 12. In addition, when the gas pressure inside the cryogenic medium storage tank 11 is detected to have risen to a set threshold, the cryogenic medium storage tank exhaust valve 17 is opened remotely to discharge the gaseous medium, preventing the cryogenic medium storage tank 11 from exceeding the limit due to pressure increase.

[0083] Preferably, the system further includes a pressurized gas storage device 5, which includes a high-pressure pressurized gas cylinder 51 and a third pipeline 52 connecting the high-pressure pressurized gas cylinder 51 and the cryogenic propellant storage tank 12. The high-pressure pressurized gas cylinder 51 is used to provide pressurized gas with a pressure higher than that of the cryogenic propellant in the cryogenic propellant storage tank 12 through the third pipeline 52. The high-pressure pressurized gas cylinder 51 is an all-metal or composite material cylinder, and can be a single cylinder or a group of multiple cylinders.

[0084] The method for supplying cryogenic propellants for liquid rockets further includes:

[0085] The high-pressure booster gas is stored in the high-pressure booster gas cylinder 51, and the pressure of the stored high-pressure booster gas is higher than the pressure of the cryogenic propellant in the cryogenic propellant storage tank 12.

[0086] By pressurizing high-pressure gas into the cryogenic propellant storage tank 12 through the third pipeline 52, the cryogenic propellant in the cryogenic propellant storage tank 12 is squeezed and enters the main pipeline 3, thereby providing cryogenic propellant that meets the pressure requirements for the test liquid rocket engine 2.

[0087] Preferably, the booster gas storage device 5 further includes a sixth pipeline 56 for conveying the booster gas in the booster gas source to the high-pressure booster gas cylinder 51 and a high-pressure booster gas cylinder filling valve 53 provided on the sixth pipeline 56, wherein the sixth pipeline 56 is connected to the high-pressure booster gas cylinder 51;

[0088] The pressurized gas storage device 5 also includes a high-pressure pressurized gas cylinder exhaust valve 54 and a high-pressure pressurized gas cylinder safety valve 55, which are respectively connected to the high-pressure pressurized gas cylinder 51.

[0089] The method for supplying cryogenic propellants for liquid rockets further includes:

[0090] After the high-pressure booster gas cylinder filling valve 53 is opened, the high-pressure booster gas from the high-pressure booster gas source is filled into the high-pressure booster gas cylinder 51 through the sixth pipeline 56 and filled to the specified pressure; preferably, the high-pressure booster gas cylinder filling valve 53 is a pneumatic valve or a solenoid valve.

[0091] The pressure of the high-pressure booster gas in the high-pressure booster gas cylinder 51 is detected by the safety valve 55 of the high-pressure booster gas cylinder. When the pressure of the high-pressure booster gas is higher than the pressure threshold of the booster gas, the mechanical high-pressure booster gas cylinder safety valve 55 will automatically open to release pressure, thereby protecting the high-pressure booster gas cylinder 51.

[0092] According to the test requirements, the high-pressure booster cylinder exhaust valve 54 is remotely controlled to actively open via a remote control system. The high-pressure booster cylinder exhaust valve 54 automatically releases pressure, discharging the high-pressure boosted gas to the outside, thus achieving pressure control. The high-pressure booster cylinder exhaust valve 54 is either a pneumatic valve or a solenoid valve. The high-pressure booster cylinder exhaust valve 54 can consist of a single valve or a parallel valve group, specifically determined by the operating pressure and volume of the high-pressure booster cylinder 51.

[0093] Preferably, the liquid rocket cryogenic propellant supply system further includes a pressure control device 6 disposed on the third pipeline 52. The pressure control device 6 includes a propellant tank inlet valve 61 and a pressure control valve 62 disposed on the third pipeline 52. The propellant tank inlet valve 61 is located near the end of the cryogenic propellant tank 12, and the pressure control valve 62 is located near the end of the high-pressure pressurization cylinder 51.

[0094] Preferably, the liquid rocket cryogenic propellant supply method further includes:

[0095] The propellant storage tank inlet valve 61 isolates or supplies high-pressure booster gas from the high-pressure booster gas cylinder 51 to the cryogenic propellant storage tank 12;

[0096] Then, the pressure control valve 62 depressurizes the high-pressure gas from the high-pressure booster cylinder 51 to a specified pressure range, stabilizing the pressure of the high-pressure booster gas entering the cryogenic propellant storage tank 12. This ensures that the high-pressure booster gas, after entering the cryogenic propellant storage tank 12, can deliver the cryogenic propellant into the main pipeline 3, further guaranteeing that the cryogenic propellant entering the test liquid rocket engine 2 meets the pressure requirements. The pressure control valve 62 is either a pneumatic valve or a solenoid valve, and the propellant storage tank inlet valve 61 is also either a pneumatic valve or a solenoid valve.

[0097] Preferably, the pressure control device 6 further includes a booster pressure reducing valve 63 disposed on the third pipeline 52, the booster pressure reducing valve 63 being disposed between the propellant storage tank inlet valve 61 and the booster control valve 62.

[0098] The method for supplying cryogenic propellants for liquid rockets further includes:

[0099] The pressure control device 6 also includes a pressure reducing valve 63 on the third pipeline 52.

[0100] The pressure reducing valve 63 is located between the propellant storage tank inlet valve 61 and the pressure control valve 62, and the high-pressure boosting gas is isolated or supplied through the pressure reducing valve 63.

[0101] Preferably, the liquid rocket cryogenic propellant supply system further includes a first precooling device 7 connected to the main pipeline 3 for precooling the main pipeline 3. The first precooling device 7 includes a fourth pipeline 71 for conveying the precooled cryogenic medium in the precooled cryogenic medium source to the main pipeline 3, and a supply liquid line precooling check valve 72 and a supply liquid line precooling control valve 73 provided on the fourth pipeline 71.

[0102] Preferably, the liquid rocket cryogenic propellant supply method further includes:

[0103] Before supplying the cryogenic propellant from the cryogenic propellant storage tank 12 to the test liquid rocket engine 2, the supply liquid line precooling check valve 72 and the supply liquid line precooling control valve 73 are opened. The precooled cryogenic medium from the precooled cryogenic medium source is then transported to the main pipeline 3 through the fourth pipeline 71. The boiling point of the precooled cryogenic medium is much lower than the recommended boiling point for cryogenic use, thus removing heat from the main pipeline 3 and precooling it below the recommended boiling point. This process avoids the drawbacks of directly using the cryogenic propellant from the storage tank 12 to precool the main pipeline 3, which would result in increased cryogenic propellant consumption and shortened operating time of the test liquid rocket engine 2. It also avoids the drawback of increasing the volume of the cryogenic propellant storage tank 12 to overcome the high cryogenic propellant loss and increased manufacturing difficulty and cost.

[0104] Preferably, the liquid rocket cryogenic propellant supply system further includes a jacketed pipe 8 fitted onto the outer surface of the main pipe 3; the liquid rocket cryogenic propellant supply system also includes a second precooling device 9 for precooling the jacketed pipe 8.

[0105] The second precooling device 9 includes a fifth pipeline 91 for conveying the precooling cryogenic medium in the precooling cryogenic medium source to the interlayer pipeline 8 and an interlayer pipeline control valve 92 provided on the fifth pipeline 91.

[0106] The method for supplying cryogenic propellants for liquid rockets further includes:

[0107] Before supplying the cryogenic propellant from the cryogenic propellant storage tank 12 to the test liquid rocket engine 2, the jacket control valve 92 on the fifth pipeline 91 is opened. This allows the pre-cooled cryogenic medium from the pre-cooled cryogenic medium source to be transported through the fifth pipeline 91 to the jacket pipeline 8. The flow of the pre-cooled cryogenic medium in the jacket pipeline 8 further removes heat from the outer wall of the cooling main pipeline 3, thereby further reducing the temperature of the main pipeline 3 and improving the pre-cooling effect. This process of supplying the cryogenic propellant from the cryogenic propellant storage tank 12 to the test liquid rocket engine 2 avoids the vaporization of the cryogenic propellant and the resulting waste.

[0108] In summary, the cryogenic propellant storage tank 12 is a cryogenic storage tank with a large volume (≥500L) and high pressure (≥35MPa) or ultra-high pressure (≥100MPa). There are no cryogenic storage tanks with such a large volume and withstanding such high pressure (10MPa in the prior art) in the existing technology. In this invention, the cryogenic propellant storage tank 12 is placed in the liquid cryogenic medium storage tank 11 by immersion heat exchange. The cryogenic propellant is stored in the cryogenic propellant storage tank 12, and the liquid cryogenic medium is added to the liquid cryogenic medium storage tank 11. The boiling point of the liquid cryogenic medium is lower than that of the cryogenic propellant but higher than that of the cryogenic propellant, which ensures that the cryogenic propellant in the cryogenic propellant storage tank 12 is in a cryogenic liquid state. By controlling the pressure in the liquid cryogenic medium storage tank 11, the boiling point and thermal equilibrium temperature of the liquid cryogenic medium in the liquid cryogenic medium storage tank 11 can be changed, thereby achieving the required temperature regulation of the cryogenic propellant storage tank 12. The cryogenic propellant system for liquid rocket engines (including engine components) requires high thermal insulation performance from the storage tank. Alternatively, a simple insulation layer can be applied to the exterior of the cryogenic medium storage tank 11; of course, leaving it uncovered will not affect the cooling requirements for the cryogenic propellant.

[0109] The liquid rocket cryogenic propellant supply system of this invention is a compression test system. The cryogenic propellant in the cryogenic propellant storage tank 12 is compressed by the high-pressure pressurized gas entering the cryogenic propellant storage tank 12, so that the cryogenic propellant entering the inlet of the test liquid rocket engine 2 is in a high-pressure state. In order to be suitable for high-pressure supply, all equipment in the system (except for the liquid cryogenic medium storage tank 11) can withstand high pressure.

[0110] The test liquid rocket engine 2 corresponds to a cryogenic liquid rocket engine (propellant such as liquid oxygen / methane). Before starting, the propellant delivery system and combustion chamber components of the engine (e.g., a liquid oxygen / methane engine) need to be pre-cooled to a cryogenic state of -180°C to -160°C. Therefore, if the propellant delivery system and combustion chamber components are not sufficiently pre-cooled, the propellant will vaporize during engine (e.g., liquid oxygen / methane engine) operation, causing problems such as propellant flow fluctuations and deviations in the working mixture ratio from the rated operating conditions, which may lead to start-up failure. In this embodiment of the invention, the pre-cooled cryogenic medium circulation removes the heat capacity of the pipeline, allowing the pipeline structure to reach a thermal equilibrium state and avoiding a series of problems caused by propellant vaporization during engine (e.g., liquid oxygen / methane engine) operation.

[0111] The volume of the high-pressure booster cylinder 51, the volume of the cryogenic propellant storage tank 12, and the diameter of various valves are determined according to the specific specifications and test indicators of the test liquid rocket engine 2.

[0112] It should be understood that in the above detailed description, various features are combined together in a single embodiment to simplify this disclosure. This approach to disclosure should not be construed as reflecting an intention that embodiments of the claimed subject matter require more features than are explicitly stated in each claim. Rather, as reflected in the appended claims, the invention is presented with fewer features than all the features of a single disclosed embodiment. Therefore, the appended claims are hereby explicitly incorporated into the detailed description, wherein each claim stands alone as a preferred embodiment of the invention.

[0113] The disclosed embodiments have been described above to enable any person skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be applied to other embodiments without departing from the spirit and scope of this disclosure. Therefore, this disclosure is not limited to the embodiments given herein, but is consistent with the broadest scope of the principles and novel features disclosed in this application.

[0114] The foregoing description includes examples of one or more embodiments. It is certainly impossible to describe all possible combinations of components or methods in order to describe the above embodiments, but those skilled in the art will recognize that further combinations and arrangements of the various embodiments are possible. Therefore, the embodiments described herein are intended to cover all such changes, modifications, and variations that fall within the scope of the appended claims. Furthermore, the term "comprising" as used in the specification or claims is interpreted in a manner similar to the term "including," as interpreted when used as a conjunction in the claims. Additionally, the use of any term "or" in the specification of the claims is intended to mean "non-exclusive or."

[0115] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A liquid rocket cryogenic propellant supply system, characterized in that, The system includes a cryogenic propellant storage tank unit (1), a test liquid rocket engine (2), and a main pipeline (3). The cryogenic propellant storage tank unit (1) includes a liquid cryogenic medium storage tank (11) and a cryogenic propellant storage tank (12) immersed in the liquid cryogenic medium storage tank (11). The boiling point of the liquid cryogenic medium in the liquid cryogenic medium storage tank (11) is lower than the boiling point of the cryogenic propellant in the cryogenic propellant storage tank (12) and higher than the freezing point of the cryogenic propellant. The test liquid rocket engine (2) is connected to the cryogenic propellant outlet of the cryogenic propellant storage tank (12) via the main pipeline (3); The cryogenic propellant storage tank unit (1) further includes a cryogenic propellant delivery unit (14) connected to the cryogenic propellant storage tank (12) for providing cryogenic propellant to the cryogenic propellant storage tank (12), and the cryogenic propellant delivery unit (14) includes a first pipeline (141) for delivering propellant in the propellant source to the cryogenic propellant storage tank (12); The cryogenic propellant storage tank unit (1) further includes a liquid cryogenic medium delivery unit (13) connected to the liquid cryogenic medium storage tank (11) for providing liquid cryogenic medium to the liquid cryogenic medium storage tank (11); the liquid cryogenic medium delivery unit (13) includes a second pipeline (131) for delivering liquid cryogenic medium from the liquid cryogenic medium source to the liquid cryogenic medium storage tank (11); The liquid rocket cryogenic propellant supply system further includes a pressurizing gas storage device (5) that provides pressurizing gas with a pressure higher than that of the cryogenic propellant in the cryogenic propellant storage tank (12).

2. The liquid rocket cryogenic propellant supply system according to claim 1, characterized in that, The cryogenic propellant delivery unit (14) further includes a propellant tank filling valve (142) and a propellant tank filling filter (143) provided on the first pipeline (141); The liquid cryogenic medium transport unit (13) also includes a liquid cryogenic medium storage tank filling valve (132) provided on the second pipeline (131); The liquid rocket cryogenic propellant supply system also includes a main supply valve (4) located on the main pipeline (3).

3. The liquid rocket cryogenic propellant supply system according to claim 2, characterized in that, It also includes a supply liquid flow meter (31) and a supply liquid discharge valve (32) installed on the main pipeline (3). The supply liquid flow meter (31) is located between the supply liquid main valve (4) and the test liquid rocket engine (2). The supply liquid discharge valve (32) is located between the supply liquid flow meter (31) and the test liquid rocket engine (2).

4. The liquid rocket cryogenic propellant supply system according to claim 1, characterized in that, The cryogenic propellant storage tank unit (1) also includes a propellant storage tank exhaust valve (15) connected to the cryogenic propellant storage tank (12); The cryogenic propellant storage tank unit (1) also includes a propellant storage tank safety valve (16) connected to the cryogenic propellant storage tank (12); The cryogenic propellant storage tank unit (1) also includes a liquid cryogenic medium storage tank exhaust valve (17) connected to the liquid cryogenic medium storage tank (11).

5. The liquid rocket cryogenic propellant supply system according to claim 1, characterized in that, The pressurized gas storage device (5) includes a high-pressure pressurized gas cylinder (51) and a third pipeline (52) connected to the high-pressure pressurized gas cylinder (51) and the cryogenic propellant storage tank (12). The high-pressure pressurized gas cylinder (51) is used to provide pressurized gas with a pressure higher than that of the cryogenic propellant in the cryogenic propellant storage tank (12) through the third pipeline (52).

6. The liquid rocket cryogenic propellant supply system according to claim 5, characterized in that, The pressurized gas storage device (5) further includes a sixth pipeline (56) for conveying pressurized gas in the pressurized gas source to the high-pressure pressurized gas cylinder (51) and a high-pressure pressurized gas cylinder filling valve (53) provided on the sixth pipeline (56), wherein the sixth pipeline (56) is connected to the high-pressure pressurized gas cylinder (51). The pressurized gas storage device (5) also includes a high-pressure pressurized gas cylinder exhaust valve (54) and a high-pressure pressurized gas cylinder safety valve (55) respectively connected to the high-pressure pressurized gas cylinder (51).

7. The liquid rocket cryogenic propellant supply system according to claim 5, characterized in that, It also includes a pressure control device (6) provided on the third pipeline (52), the pressure control device (6) including a propellant tank inlet valve (61) and a pressure control valve (62) provided on the third pipeline (52), the propellant tank inlet valve (61) being located near the cryogenic propellant tank (12), and the pressure control valve (62) being located near the high-pressure pressurization cylinder (51).

8. The liquid rocket cryogenic propellant supply system according to claim 7, characterized in that, The pressure control device (6) further includes a booster pressure reducing valve (63) provided on the third pipeline (52), which is located between the propellant tank inlet valve (61) and the booster control valve (62).

9. The liquid rocket cryogenic propellant supply system according to claim 1, characterized in that, It also includes a first precooling device (7) connected to the main pipeline (3) for precooling the main pipeline (3).

10. The liquid rocket cryogenic propellant supply system according to claim 9, characterized in that, The first precooling device (7) includes a fourth pipeline (71) for conveying the precooling low temperature medium in the precooling low temperature medium source to the main pipeline (3), and a supply liquid line precooling check valve (72) and a supply liquid line precooling control valve (73) provided on the fourth pipeline (71).

11. The liquid rocket cryogenic propellant supply system according to claim 9, characterized in that, It also includes a sandwiched pipe (8) fitted onto the outer surface of the main pipe (3); The liquid rocket cryogenic propellant supply system also includes a second precooling device (9) for precooling the interlayer pipeline (8).

12. A method for supplying cryogenic propellant to a liquid rocket, characterized in that, The liquid rocket cryogenic propellant supply method is implemented by any of the liquid rocket cryogenic propellant supply systems described in claims 1-11. The liquid rocket cryogenic propellant supply system includes a cryogenic propellant storage tank unit (1), a test liquid rocket engine (2), and a main pipeline (3). The cryogenic propellant storage tank unit (1) includes a liquid cryogenic medium storage tank (11) and a cryogenic propellant storage tank (12) immersed in the liquid cryogenic medium storage tank (11). The boiling point of the liquid cryogenic medium in the liquid cryogenic medium storage tank (11) is lower than the boiling point of the cryogenic propellant in the cryogenic propellant storage tank (12) and higher than the freezing point of the cryogenic propellant. The test liquid rocket engine (2) is connected to the cryogenic propellant outlet of the cryogenic propellant storage tank (12) via the main pipeline (3); The cryogenic propellant storage tank unit (1) further includes a cryogenic propellant delivery unit (14) connected to the cryogenic propellant storage tank (12) for providing cryogenic propellant to the cryogenic propellant storage tank (12); The cryogenic propellant storage tank unit (1) also includes a liquid cryogenic medium delivery unit (13) connected to the liquid cryogenic medium storage tank (11) for providing liquid cryogenic medium to the liquid cryogenic medium storage tank (11); The method for supplying cryogenic propellant for liquid rockets includes: Cryogenic propellant is supplied to the cryogenic propellant storage tank (12) through the cryogenic propellant delivery unit (14); The liquid cryogenic medium is supplied to the liquid cryogenic medium storage tank (11) through the liquid cryogenic medium delivery unit (13); Before testing the liquid rocket engine (2) for the test of the liquid rocket, the cryogenic propellant tank (12) is immersed in the liquid cryogenic medium tank (11), and the cryogenic propellant is kept in a preset low temperature range through heat exchange between the liquid cryogenic medium and the cryogenic propellant. During the test of the test liquid rocket engine (2) of the liquid rocket, the cryogenic propellant in the cryogenic propellant tank (12) is pushed into the test liquid rocket engine (2) through the main pipeline (3).

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