Multi-path supercooling filling system and method for cryogenic propellant

Abstract

The invention discloses a multi-path supercooling filling system and method for low-temperature propellants, and belongs to the field of supercooling filling of the low-temperature propellants. Vacuumizing treatment is carried out on a negative pressure module of a two-stage supercooling device by utilizing an evacuating and decompressing device, so that the temperature of a coolant in a cold source tank car is reduced; a two-stage supercooling device is adopted to carry out supercooling treatment on the propellant in the propellant tank car stage by stage, so that the supercooling operation of the propellant is realized; the supercooled propellant is conveyed to the rocket storage tank through the ground storage tank or the combination of the ground storage tank and the negative pressure module, so that different filling requirements of medium and small flow filling and large flow filling are met; the output end of the rocket storage tank is connected with the input end of the rocket storage tank through the negative pressure module to form a propellant recooling loop, recooling treatment of propellants in the rocket storage tank is achieved, and therefore the filling requirement after a launching task is delayed is met; according to the system, continuous and efficient treatment of propellants is achieved, and the adaptability of the system to emergencies and special filling requirements is enhanced.

Description

Technical Field

[0001] The invention belongs to the field of cryogenic propellant supercooling filling, and in particular relates to a cryogenic propellant multi-path supercooling filling system and method. Background Art

[0002] Cryogenic propellants such as liquid hydrogen and liquid oxygen have excellent properties such as high specific impulse, non-toxicity and non-pollution, and have become the first choice for future deep space exploration missions. However, cryogenic propellants are extremely thermally sensitive, and space radiation heat invasion and structural heat leakage of the transportation system will cause the temperature of the cryogenic propellant to rise and evaporate. If supercooled cryogenic propellants are used for refueling, the heat leakage capacity of the liquid containment space can be improved, significantly extending the on-orbit storage period of cryogenic fuel.

[0003] The schemes for supercooling and refilling of propellant mainly adopt schemes such as supercooling first and then refilling, supercooling while refilling, and refilling first and then supercooling. For the scheme of supercooling first and then refilling, supercooling and refilling on the arrow are relatively independent, less affected by the refilling task and more maneuverable, but during the ground storage process, due to heat leakage from the external environment, a lot of high-quality supercooled propellant will be lost; for the scheme of refilling first and then supercooling, the loss of supercooled propellant during storage is reduced, and it has stronger adaptability to conditions such as delays in launch missions, but the launch pad needs to be modified and the launcher needs to be quickly and safely separated from the arrow body; for the scheme of supercooling and refilling at the same time, the structure is simple and does not require additional supercooling time, but the working performance requirements of the heat exchanger and vacuum device are higher.

[0004] At present, the cryogenic propellant filling system mainly adopts the scheme of supercooling first and then filling or supercooling supplement. In the above scheme, since the supercooling and filling are independent of each other, this will lead to a long overall filling time; and due to external heat leakage, the supercooled propellant is prone to lose some of its supercooling during the storage process; in addition, a single filling scheme is difficult to meet multiple filling needs, and there are problems such as weak adaptability to emergencies.

[0005] It can be seen that the existing cryogenic propellant filling system has low working efficiency and cannot meet various filling needs due to the independence of the two links of supercooling and filling. Summary of the invention

[0006] The present invention provides a cryogenic propellant multi-path supercooling filling system and method, so as to solve the technical problem that the existing cryogenic propellant filling system has low working efficiency and cannot meet various filling requirements due to the mutual independence of supercooling and filling.

[0007] In order to achieve the above object, the present invention adopts the following technical contents: A cryogenic propellant multi-path supercooling filling system, comprising a ground storage tank, a propellant tank truck, a cold source tank truck, a two-stage supercooling device and a rocket tank; The propellant tank truck, the two-stage supercooling device, the ground storage tank and the rocket tank are connected in sequence; The output end of the cold source tank truck is connected to the two-stage supercooling device, and the two-stage supercooling device is used to sequentially precool and supercool the propellant transported by the propellant tank truck; The two-stage supercooling device is connected to a vacuum pressure reducing device for vacuumizing the negative pressure module of the two-stage supercooling device; Wherein, the first output end of the two-stage supercooling device is connected to the ground storage tank, and the second output end is connected to the rocket tank; The output end of the rocket tank is connected to the input end of the rocket tank through a negative pressure module of a two-stage supercooling device to form a propellant re-supercooling loop.

[0008] Further, the two-stage supercooling device comprises a connected normal pressure heat exchanger and a negative pressure heat exchanger, wherein the negative pressure module adopts a negative pressure heat exchanger; The cold source tank truck is connected to a cold source input end of a normal pressure heat exchanger and a cold source input end of a negative pressure heat exchanger; The vacuum decompression device is connected to the negative pressure heat exchanger; The first propellant input end of the atmospheric heat exchanger is connected to the propellant tank truck, and the second propellant input end is connected to the ground storage tank; The first propellant input end of the negative pressure heat exchanger is connected to the normal pressure heat exchanger, and the second propellant input end is connected to the output end of the rocket tank; The first output end of the negative pressure heat exchanger is connected to the ground storage tank, and the second output end is connected to the input end of the rocket tank.

[0009] Furthermore, an eleventh cryogenic regulating valve and a third cryogenic pump are provided between the second propellant input end of the negative pressure heat exchanger and the output end of the rocket tank.

[0010] Furthermore, a seventh low-temperature regulating valve, a second filter and a second flow meter are provided between the first output end of the negative pressure heat exchanger and the ground storage tank.

[0011] Furthermore, a fifth cryogenic regulating valve and a second cryogenic pump are provided between the propellant tank truck and the input end of the atmospheric pressure heat exchanger.

[0012] Furthermore, a first filling branch is formed between the ground storage tank and the input end of the rocket tank; a second filling branch is formed between the second output end of the negative pressure heat exchanger and the input end of the rocket tank; the first filling branch and the second filling branch merge to form a main filling passage; and a first filter and a first flow meter are provided on the main filling passage.

[0013] Furthermore, the ground storage tank is connected to the input end of the rocket tank through a third cryogenic regulating valve and a first cryogenic pump, or through a fourth cryogenic regulating valve.

[0014] Furthermore, the propellant tank truck is connected to the ground storage tank; the ground storage tank and the propellant tank truck are both connected to the two-stage supercooling device via a second cryogenic pump.

[0015] Furthermore, the ground storage tank adopts composite material insulation; the rocket tank adopts polyurethane foam insulation; the evacuation and decompression device adopts a vacuum pump or an ejector.

[0016] A working method of a multi-path cryogenic propellant supercooling filling system, comprising: The first working condition: starting the vacuum pressure reducing device to vacuum the negative pressure module of the two-stage supercooling device to reduce the temperature of the coolant in the negative pressure module; A two-stage supercooling device is used to supercool the propellant transported by the propellant tank truck step by step; The supercooled propellant is stored in a ground tank and the rocket tank is filled with the supercooled propellant from the ground tank before launch; The second working condition: During the process of the first working condition, the propellant in the propellant tank truck is supercooled by a two-stage supercooling device and then directly transported to the rocket tank; The third working condition: re-supercooling the supercooled propellant in the rocket tank, specifically including: Starting the vacuum decompression device to evacuate the negative pressure module of the two-stage supercooling device to reduce the temperature of the coolant in the negative pressure module; The propellant in the rocket tank is transported to the negative pressure module of the two-stage supercooling device, and then transported back to the rocket tank after being supercooled by the negative pressure module.

[0017] Compared with the prior art, the present invention has the following beneficial effects: The present invention provides a multi-path supercooling and filling system for low-temperature propellant. The system utilizes an evacuation and decompression device to perform a vacuum treatment on a negative pressure module of a two-stage supercooling device, thereby reducing the temperature of the coolant in a cold source tank truck; a two-stage supercooling device is used to perform a step-by-step supercooling treatment on the propellant in the propellant tank truck, thereby realizing a propellant supercooling operation; the supercooled propellant is transported to a rocket tank through a ground storage tank or a combination of a ground storage tank and a negative pressure module, thereby meeting different filling requirements of small and medium flow filling and large flow filling; the output end of the rocket tank is connected to the input end of the rocket tank through a negative pressure module to form a propellant re-supercooling circuit, thereby realizing a re-supercooling treatment of the propellant in the rocket tank, thereby meeting the filling requirement after the launch mission is postponed; the system designs a variety of filling paths, closely combines the supercooling and filling links, realizes continuous and efficient processing of the propellant, and enhances the system's adaptability to emergencies and special filling requirements.

[0018] Preferably, in the present invention, the two-stage supercooling device adopts a normal pressure heat exchanger and a negative pressure heat exchanger; the negative pressure heat exchanger can use an evacuation and decompression device to evacuate the interior thereof, and reduce the internal coolant to a temperature near the triple point; since the temperature of liquid nitrogen at normal boiling point is much lower than the saturation temperature of liquid oxygen at normal pressure, the normal pressure heat exchanger is used to pre-cool the propellant before the negative pressure heat exchanger is supercooled, thereby reducing the consumption of liquid nitrogen, reducing the scale and energy consumption of the evacuation and decompression device, and improving the supercooling capacity. The design of the two-stage supercooling device ensures the supercooling effect and reduces the consumption of cold source working fluid and system energy consumption.

[0019] Further preferably, in the present invention, a cryogenic regulating valve and a cryogenic pump are arranged between the second propellant input end of the negative pressure heat exchanger and the output end of the rocket tank, which can accurately control the propellant flow rate returning from the rocket tank to the negative pressure heat exchanger, further improving the accuracy and efficiency of the re-supercooling treatment.

[0020] Further preferably, in the present invention, a low-temperature regulating valve, a filter and a flow meter are arranged between the first output end of the negative pressure heat exchanger and the ground storage tank, which can ensure the quality of the propellant delivered to the ground storage tank, and at the same time facilitate monitoring and control of the flow to ensure stable operation of the system.

[0021] Further preferably, in the present invention, a low-temperature regulating valve and a low-temperature pump are arranged between the propellant tank truck and the input end of the atmospheric pressure heat exchanger, so as to accurately control the flow rate of the propellant transported from the propellant tank truck to the atmospheric pressure heat exchanger, thereby providing stable input conditions for subsequent supercooling treatment.

[0022] Further preferably, in the present invention, by designing a first filling branch and a second filling branch and merging them to form a main filling passage, the flexibility and redundancy of the system are increased; at the same time, a filter and a flow meter are arranged on the main filling passage to ensure the quality and flow control of the propellant during the filling process.

[0023] Preferably, the present invention provides a variety of connection methods between the ground storage tank and the rocket tank, including connection through a cryogenic pump and a cryogenic regulating valve, or directly connecting through a cryogenic regulating valve. Filling can be achieved by a pump or by utilizing a pressure difference. This design enables the system to flexibly select the filling method according to actual needs, thereby improving the adaptability and flexibility of the system.

[0024] Preferably, in the present invention, the propellant tank truck and the ground storage tank are connected to realize the circulation of the propellant between the propellant tank truck and the ground storage tank, thereby improving the circulation performance of the system; and, both the ground storage tank and the propellant tank truck are connected to the two-stage supercooling device through a second cryogenic pump, thereby further improving the circulation capacity of the system and reducing the energy loss of the system.

[0025] Preferably, in the present invention, the ground storage tank adopts high vacuum multi-layer insulation; the rocket tank adopts polyurethane foam insulation; the evacuation and decompression device adopts a vacuum pump or an ejector; this helps to reduce system heat loss and improve the energy efficiency and stability of the system.

[0026] The present invention also provides a multi-path supercooling filling system for cryogenic propellants. Based on the above-mentioned multi-path supercooling filling system for cryogenic propellants, this method is implemented for a variety of working conditions, specifically including three implementation processes: supercooling first and then filling, supercooling first and then filling with supercooling and filling simultaneously, and filling first and then supercooling. The specific links of various filling routes are clarified to achieve the mission requirements of different filling situations. Compared with a single propellant filling system, it has stronger adaptability to conditions such as rapid launch and launch delays, which is beneficial to improving the filling efficiency and reducing the evaporation loss of supercooled propellant. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 A schematic diagram of the structure of a cryogenic propellant multi-path supercooling filling system provided by the present invention; Figure 2 A schematic diagram of the system operation of a cryogenic propellant multi-path supercooling filling system under a first working condition provided by the present invention; Figure 3 A schematic diagram of the system operation of a cryogenic propellant multi-path supercooling filling system under a second working condition provided by the present invention; Figure 4 A schematic diagram of the system operation of a cryogenic propellant multi-path supercooling filling system under the third working condition provided by the present invention.

[0028] Reference numerals: Ground storage tank-1, first safety valve-2, first cryogenic regulating valve-3, second cryogenic regulating valve-4, third cryogenic regulating valve-5, first cryogenic pump-6, fourth cryogenic regulating valve-7, first filter-8, first flowmeter-9, propellant tank truck-10, fifth cryogenic regulating valve-11, second cryogenic pump-12, second safety valve-13, normal pressure heat exchanger-14, third safety valve-15, negative pressure heat exchanger-16, sixth cryogenic regulating valve-17, vacuum pressure reducing device-18, seventh cryogenic regulating valve-19, second filter-20, second flowmeter-21, cold source tank truck-22, eighth cryogenic regulating valve-23, ninth cryogenic regulating valve-24, tenth cryogenic regulating valve-25, cryogenic gate valve-26, fourth safety valve-27, rocket tank-28, eleventh cryogenic regulating valve-29, third cryogenic pump-30. DETAILED DESCRIPTION

[0029] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention more clearly understood, the present invention is further described in detail in the following specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0030] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0031] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0032] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0033] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use, it is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0034] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0035] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0036] The present invention is further described in detail below in conjunction with the accompanying drawings: Example 1 As described in the background technology above, the traditional cryogenic propellant filling system mainly adopts the scheme of supercooling first and then filling or supercooling supplement. In the above scheme, since the two links of supercooling and filling are independent of each other, this will lead to a long overall filling time; and due to external heat leakage, the supercooled propellant is prone to lose some supercooling during the storage process; in addition, a single filling scheme is difficult to meet multiple filling needs and has weak adaptability to emergencies.

[0037] In order to solve the above problems, the present embodiment provides a cryogenic propellant multi-path supercooled filling system. The system can provide suitable filling solutions for different filling tasks and launch situations, so as to solve the problems of the existing cryogenic propellant filling system, such as long filling time, easy loss of high-quality supercooled propellant, and weak adaptability to emergencies. like Figure 1 As shown, this embodiment provides a cryogenic propellant multi-path supercooling filling system, comprising: Ground tank 1: used to store supercooled propellant.

[0038] Propellant tanker 10: transports raw propellant from outside to the filling site.

[0039] Cold source tank truck 22: carries a low-temperature cold source and provides necessary cooling medium for the two-stage supercooling device.

[0040] The two-stage supercooling device comprises a normal pressure heat exchanger 14 and a negative pressure heat exchanger 16, which respectively perform precooling and deep supercooling treatment on the propellant in the propellant tank car 10.

[0041] Rocket tank 28: finally receives and stores supercooled propellant for use in rocket launch.

[0042] The specific connection relationship is as follows: The cold source tanker 22 is connected to the atmospheric pressure heat exchanger 14 through the eighth low temperature regulating valve 23, and is connected to the negative pressure heat exchanger 16 through the ninth low temperature regulating valve 24; The normal pressure heat exchanger 14 is provided with a second safety valve 13, the negative pressure heat exchanger 16 is provided with a third safety valve 15, and is also connected to a sixth low temperature regulating valve 17 and an evacuation and pressure reducing device 18; The propellant tanker 10 is connected to the normal pressure heat exchanger 14 and the negative pressure heat exchanger 16 in sequence through the fifth cryogenic regulating valve 11 and the second cryogenic pump 12; The first output end of the negative pressure heat exchanger 16 is connected to the ground storage tank 1 through the seventh low temperature regulating valve 19, the second filter 20 and the second flow meter 21. The ground storage tank 1 is provided with a first safety valve 2; The second output end of the negative pressure heat exchanger 16 is connected to the rocket tank 28 through the tenth low temperature regulating valve 25; The ground storage tank 1 and the rocket tank 28 are connected via the third cryogenic regulating valve 5 and the first cryogenic pump 6, and the filling process is realized by the cryogenic pump; the two can also be connected via the fourth cryogenic regulating valve 7, and the filling is realized by the pressure difference; The first filling branch formed between the ground storage tank 1 and the rocket tank 28 merges with the second filling branch formed between the negative pressure heat exchanger 16 and the rocket tank 28 to form a main filling passage, and a first filter 8 and a first flow meter 9 are arranged on the main filling passage; a cryogenic gate valve 26 and a fourth safety valve 27 are arranged on the rocket tank 28; In this embodiment, the second input end of the negative pressure heat exchanger 16 is also connected to the output end of the rocket tank through the eleventh cryogenic regulating valve 29 and the third cryogenic pump 30, thereby realizing the operation of filling and then subcooling.

[0043] In this embodiment, the ground storage tank 1 is insulated with a composite material, preferably a high vacuum multi-layer, and the rocket tank 28 is insulated with polyurethane foam.

[0044] The evacuation and decompression device 18 adopts a vacuum pump or an ejector.

[0045] This embodiment also provides the working principle of the multi-path cryogenic propellant supercooling filling system, which is divided into three working conditions, i.e., three paths, as follows: The first working condition: Figure 2 As shown, for the filling of small and medium flow rates, a scheme of first supercooling and then filling is adopted, and the propellant supercooling adopts a two-stage supercooling operation. For example, for liquid oxygen supercooling filling, the normal boiling point temperature of liquid nitrogen is about 77.4K, which can be reduced to near the triple point temperature of liquid nitrogen 63.2K by evacuation to achieve 66K supercooled liquid oxygen production. However, since the normal boiling point temperature of liquid nitrogen is much lower than the saturation temperature of liquid oxygen at normal pressure, the normal pressure heat exchanger 14 can be used to pre-cool the propellant before the negative pressure heat exchanger 16, thereby reducing the consumption of liquid nitrogen, reducing the energy consumption of the evacuation and decompression device, and improving the supercooling capacity. Before the propellant is supercooled, the eighth low-temperature regulating valve 23, the ninth low-temperature regulating valve 24, and the sixth low-temperature regulating valve 17 are opened, and the coolant in the cold source tank truck 22 is transported to the atmospheric pressure heat exchanger 14 and the negative pressure heat exchanger 16, and the vacuum pressure reducing device 18 is started to evacuate the coolant in the negative pressure heat exchanger 16 to a temperature near the triple point. It should be noted that the filling system can also achieve supercooling filling in different temperature zones by changing the vacuum pressure, for example, liquid nitrogen can be reduced to a triple point of 66K or 73K, etc.; by adjusting the vacuum pressure, not only the supercooling temperature can be accurately controlled, but also the evaporation rate of the coolant liquid nitrogen can be more effectively controlled, thereby reducing unnecessary losses, thereby improving the supercooling efficiency and significantly reducing the operating cost. Open the flow path of the propellant to be supercooled, that is, open the fifth cryogenic regulating valve 11 and the ninth cryogenic regulating valve 19. The propellant in the propellant tank truck 10 is first pumped to the atmospheric heat exchanger 14 through the first cryogenic pump 12 to exchange heat with the saturated coolant; then it is transported to the negative pressure heat exchanger 16 to exchange heat with the supercooled coolant. The supercooled propellant is transported to the ground storage tank 1 through the second filter 20 and the second flowmeter 21. Before the propellant is filled, open the third cryogenic regulating valve 5 or the fourth cryogenic regulating valve 7. The supercooled propellant in the ground storage tank 1 is pumped by the first cryogenic pump 6 or transported by pressure difference. The propellant is filled into the rocket tank 28 after passing through the first filter 8 and the first flowmeter 9.

[0046] The second working condition: Figure 3As shown, for the case of large flow filling, the operations of supercooling first and then filling and supercooling and filling are carried out simultaneously, and the flow rate can be flexibly adjusted. The supercooled propellant in the ground storage tank 1 is pumped by the first cryogenic pump 6 or directly transported by pressure difference, and then filled into the rocket tank 28 after passing through the first filter 8 and the first flowmeter 9; at the same time, the eighth cryogenic regulating valve 23, the ninth cryogenic regulating valve 24, and the sixth cryogenic regulating valve 17 are opened, and the coolant in the cold source tank car 22 is transported to the atmospheric pressure heat exchanger 14 and the negative pressure heat exchanger 16, and the vacuum pressure reducing device 18 is started to evacuate the coolant in the negative pressure heat exchanger 16 to a preset pressure. The propellant flow path to be supercooled is opened, that is, the fifth cryogenic regulating valve 11 and the tenth cryogenic regulating valve 25 are opened, and the propellant in the propellant tank car 10 is first pumped to the atmospheric pressure heat exchanger 14 by the second cryogenic pump 12 to exchange heat with the saturated cold source working fluid, and then transported to the negative pressure heat exchanger 16 to exchange heat with the supercooled coolant. The supercooled propellant passes through the first filter 8 and the first flow meter 9 and is then filled into the rocket tank 28 .

[0047] The third working condition: Figure 4 As shown, in the case where the propellant is overcooled again after the launch mission is postponed, the essence is to fill it first and then overcool it. After the launch mission is postponed, although the temperature of the propellant in the rocket tank 28 increases, the temperature is lower than that of the saturated propellant, and it is only necessary to use the negative pressure heat exchanger 16 for overcooling. Before the propellant in the rocket tank 28 is overcooled, the sixth low-temperature regulating valve 17 and the ninth low-temperature regulating valve 24 are opened, and the coolant in the cold source tank truck 22 is transported to the negative pressure heat exchanger 16, and the vacuum pressure reducing device 18 is started to reduce the pressure of the coolant in the negative pressure heat exchanger 16 to a preset pressure; the tenth low-temperature regulating valve 25 and the eleventh low-temperature regulating valve 29 are opened, and the propellant in the rocket tank 28 is pumped to the negative pressure heat exchanger 16 through the third low-temperature pump 30 to exchange heat with the overcooled coolant. The overcooled propellant passes through the first filter 8 and the first flowmeter 9 and then is filled into the rocket tank 28.

[0048] It can be seen that the present embodiment provides a multi-path cryogenic propellant supercooling filling system, the system includes three propellant supercooling filling paths, and each filling path is connected to the rocket tank; the three filling paths are respectively a propellant supercooling and then filling route, a propellant supercooling and then filling and real-time supercooling filling parallel route, and a propellant first filling and then supercooling route, which can meet the requirements of different propellant filling flow rates and filling tasks, is conducive to improving the filling efficiency, reducing the evaporation loss of supercooled propellant, and has strong adaptability to sudden situations such as launch delays and cancellations.

[0049] Example 2 Another example Figure 1 and Figure 2As shown, this embodiment provides another cryogenic propellant multi-path supercooling filling system, which is basically the same as the solution of Example 1. The specific difference is that this embodiment is optimized and improved on the basis of Example 1, specifically including: A branch of the propellant tank truck 10 is connected to the atmospheric pressure heat exchanger 14 and the negative pressure heat exchanger 16 in sequence through the fifth cryogenic regulating valve 11 and the second cryogenic pump 12; the other branch is connected to the ground storage tank 1 through the first cryogenic regulating valve 3; and the ground storage tank 1 is merged with a branch of the propellant tank truck 10 through the second cryogenic regulating valve 4, and is connected to the atmospheric pressure heat exchanger 14 through the second cryogenic pump 12, thereby realizing the propellant in the ground storage tank 1 first filling and then supercooling cycle, ensuring that the temperature of the supercooled propellant in the ground storage tank 1 meets the requirements.

[0050] The present invention provides a cryogenic propellant multi-path supercooling filling system and method. Compared with existing filling measures, the system has the following advantages: First, efficient supercooling treatment: By introducing a two-stage supercooling device (normal pressure heat exchanger and negative pressure heat exchanger), pre-cooling and deep supercooling treatment of the propellant are achieved, which significantly improves the cooling efficiency of the propellant and helps to improve the combustion efficiency and thrust performance of the rocket engine.

[0051] Second, multi-path filling flexibility: The system is designed with a variety of filling paths, including the conventional filling path directly through the ground storage tank to the rocket tank, and the deep-cold filling path that passes through a two-stage supercooling device and then enters the rocket tank, which increases the flexibility and adaptability of filling, and the optimal filling plan can be selected according to actual needs.

[0052] Third, negative pressure treatment: The negative pressure heat exchanger combined with the vacuum pressure reduction device effectively maintains the negative pressure environment during the supercooling process and reduces the evaporation loss of the propellant.

[0053] Fourth, precise control and monitoring: The system is equipped with multiple low-temperature regulating valves, filters, flow meters and other components to achieve precise control and real-time monitoring of the propellant flow, ensuring the stability and safety of the filling process.

[0054] Fifth, efficient insulation design: The ground storage tank uses composite material insulation, and the rocket tank uses polyurethane foam insulation, which effectively reduces the heat loss of the propellant during storage and transportation, maintains its low temperature state, and extends its service life.

[0055] Sixth, modularity and scalability: The system components are designed to be modular, which is easy to maintain, upgrade and expand. They can be flexibly configured according to different rocket models and launch requirements, improving the versatility and adaptability of the system.

[0056] In summary, the multi-path cryogenic propellant supercooling filling system provided by the present invention has designed a variety of filling routes to meet the needs of different filling flow rates and filling tasks, and has clarified the specific links of various filling routes to achieve the task requirements of different filling situations. Compared with a single propellant filling system, it has stronger adaptability to conditions such as rapid launch and launch delays, which is beneficial to improving the filling efficiency and reducing the evaporation loss of supercooled propellant.

[0057] The above embodiment is only one of the implementation methods that can realize the technical solution of the present invention. The scope of protection claimed by the present invention is not limited only to this embodiment, but also includes changes, replacements and other implementation methods that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention.

Claims

1. A cryogenic propellant multi-path supercooling filling system, characterized in that: It comprises a ground storage tank (1), a propellant tank truck (10), a cold source tank truck (22), a two-stage supercooling device and a rocket tank (28); The propellant tank truck (10), the two-stage supercooling device, the ground storage tank (1) and the rocket tank (28) are connected in sequence; The output end of the cold source tank truck (22) is connected to the two-stage supercooling device, and the two-stage supercooling device is used to sequentially perform precooling and supercooling treatment on the propellant transported by the propellant tank truck (10); The two-stage supercooling device is connected to a vacuuming and decompression device (18) for performing a vacuuming process on the negative pressure module of the two-stage supercooling device; Wherein, the first output end of the two-stage supercooling device is connected to the ground storage tank (1), and the second output end is connected to the rocket tank (28); The output end of the rocket tank (28) is connected to the input end of the rocket tank (28) via a negative pressure module of a two-stage supercooling device, thereby forming a propellant re-supercooling loop.

2. The multi-path cryogenic propellant supercooling filling system according to claim 1, characterized in that: The two-stage supercooling device comprises a connected normal pressure heat exchanger (14) and a negative pressure heat exchanger (16), wherein the negative pressure module adopts a negative pressure heat exchanger (16); The cold source tank car (22) is connected to a cold source input end of the normal pressure heat exchanger (14) and a cold source input end of the negative pressure heat exchanger (16); The evacuation and decompression device (18) is connected to the negative pressure heat exchanger (16); The first propellant input end of the atmospheric heat exchanger (14) is connected to the propellant tank truck (10), and the second propellant input end is connected to the ground storage tank (1); The first propellant input end of the negative pressure heat exchanger (16) is connected to the normal pressure heat exchanger (14), and the second propellant input end is connected to the output end of the rocket tank (28); The first output end of the negative pressure heat exchanger (16) is connected to the ground storage tank (1), and the second output end is connected to the input end of the rocket tank (28).

3. The multi-path cryogenic propellant supercooling filling system according to claim 2, characterized in that: An eleventh cryogenic regulating valve (29) and a third cryogenic pump (30) are provided between the second propellant input end of the negative pressure heat exchanger (16) and the output end of the rocket tank (28).

4. The multi-path cryogenic propellant supercooling filling system according to claim 2, characterized in that: A seventh low-temperature regulating valve (19), a second filter (20) and a second flow meter (21) are provided between the first output end of the negative pressure heat exchanger (16) and the ground storage tank (1).

5. The multi-path cryogenic propellant supercooling filling system according to claim 2, characterized in that: A fifth cryogenic regulating valve (11) and a second cryogenic pump (12) are provided between the propellant tank truck (10) and the input end of the atmospheric pressure heat exchanger (14).

6. The multi-path cryogenic propellant supercooling filling system according to claim 2, characterized in that: A first filling branch is formed between the ground storage tank (1) and the input end of the rocket tank (28); a second filling branch is formed between the second output end of the negative pressure heat exchanger (16) and the input end of the rocket tank (28); the first filling branch and the second filling branch merge to form a main filling passage; a first filter (8) and a first flow meter (9) are provided on the main filling passage.

7. The multi-path cryogenic propellant supercooling filling system according to claim 1, characterized in that: The ground storage tank (1) is connected to the input end of the rocket tank (28) via a third cryogenic regulating valve (5) and a first cryogenic pump (6), or is connected via a fourth cryogenic regulating valve (7).

8. The multi-path cryogenic propellant supercooling filling system according to claim 1, characterized in that: The propellant tank truck (10) is connected to the ground storage tank (1); the ground storage tank (1) and the propellant tank truck (10) are both connected to the two-stage supercooling device via a second cryogenic pump (12).

9. The multi-path cryogenic propellant supercooling filling system according to claim 1, characterized in that: The ground storage tank (1) is insulated by composite materials; the rocket tank (28) is insulated by polyurethane foam; and the evacuation and decompression device (18) is insulated by a vacuum pump or an ejector.

10. A working method of a multi-path cryogenic propellant supercooling filling system, characterized in that: include: The first working condition: starting the vacuum pressure reducing device (18) to perform vacuum processing on the negative pressure module of the two-stage supercooling device to reduce the temperature of the coolant in the negative pressure module; A two-stage supercooling device is used to perform a step-by-step supercooling treatment on the propellant transported by the propellant tank truck (10); storing supercooled propellant in a ground storage tank (1), and filling the rocket tank (28) with the supercooled propellant in the ground storage tank (1) before launch; Second working condition: During the first working condition, the propellant in the propellant tank car (10) is supercooled by a two-stage supercooling device and then directly transported to the rocket tank (28); The third working condition: the supercooled propellant in the rocket tank (28) is subjected to a re-supercooling treatment, which specifically includes: Starting the vacuum decompression device (18) to evacuate the negative pressure module of the two-stage supercooling device to reduce the temperature of the coolant in the negative pressure module; The propellant in the rocket tank (28) is transported to the negative pressure module of the two-stage supercooling device, and then transported back to the rocket tank (28) after being supercooled by the negative pressure module.

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