Pipeline structure for quickly filling cryogenic propellant

Abstract

The invention discloses a pipeline structure for rapid filling of a low-temperature propellant, and relates to the field of low-temperature engineering. The pipeline structure for rapid filling of the low-temperature propellant comprises a conveying pipeline used for conveying the low-temperature propellant; the low-heat-conduction coating is laid on the inner wall of the conveying pipeline; and the exhaust device is arranged on the conveying pipeline so as to exhaust gas generated by the low-temperature propellant in the conveying pipeline. When the low-temperature propellant is pre-cooled in the conveying pipeline, the low-heat-conduction coating can promote the low-temperature propellant to be converted from the liquid state to the gas state, so that the heat exchange intensity of fluid and the inner wall of the pipeline is improved, generated gas is exhausted from the exhaust device in the conversion process, and therefore fluctuation of flow and pressure in the pipeline is reduced, and the heat exchange efficiency is improved. And unstable phenomena such as vibration of a pipeline system are avoided.

Description

Technical Field

[0001] The present invention relates to the field of cryogenic engineering, and in particular to a pipeline structure for rapid filling of cryogenic propellant. Background Art

[0002] Cryogenic propellants, with their high specific impulse, high thrust, and non-toxicity, are considered the propellant of choice for future deep space exploration. However, their low saturation temperature and low latent heat of vaporization, coupled with a significant temperature difference from the ambient environment, make them susceptible to rapid vaporization during transportation and use. Therefore, low-flow pre-cooling is required before high-flow refueling, cooling the pipeline from room temperature to a low-temperature range.

[0003] The research on the mechanism of two-phase flow and heat transfer during the pipeline precooling process is not sufficient to guide the rapid filling in actual engineering. It still faces the following prominent problems: (1) Under the action of large temperature difference, the heat transfer that dominates the temperature drop of the pipe wall is mainly reverse annular film boiling. The annular gas film layer isolates the contact between the liquid and the wall, resulting in poor heat transfer effect and low heat transfer rate; (2) The transient change of flow pattern during the precooling process is likely to induce pressure shock and even resonance phenomenon, which takes a long time to calm down. Therefore, at this stage, the precooling of the pipeline from room temperature to the low temperature zone takes a long time, which leads to a long filling time.

[0004] Currently, research has shown that introducing a low-thermal-conductivity coating (a thin thermal resistance layer) on the inner surface of a pipeline can promote the onset of rewetting (intermittent solid-liquid contact) earlier, shortening pre-cooling time and reducing liquid consumption, thereby shortening pre-cooling time. However, when the low-thermal-conductivity coating is used to quickly pre-cool the pipeline, the heat exchange between the fluid and the inner wall of the pipeline is enhanced. Because heat exchange occurs when the cryogenic propellant converts from liquid to gas, it absorbs heat in the process, cooling the inner wall of the pipeline. This accelerated pre-cooling can lead to a rapid increase in gas volume within the pipeline, exacerbating fluctuations in flow and pressure within the pipeline, and thus causing instability such as vibration in the pipeline system. Summary of the Invention

[0005] In view of the defects in the prior art, the present invention solves the technical problem of how to reduce the fluctuation of flow and pressure in the pipeline.

[0006] To achieve the above objectives, in a first aspect, the present invention provides a pipeline structure for rapid filling of cryogenic propellants, comprising: a delivery pipeline for delivering cryogenic propellant; Low thermal conductivity coating, which is laid on the inner wall of the transmission pipeline; The exhaust device is arranged on the delivery pipeline to discharge the gas generated by the cryogenic propellant in the delivery pipeline.

[0007] By adopting the above technical solution, when the cryogenic propellant is pre-cooled in the transportation pipeline, the low thermal conductivity coating will promote the transformation of the cryogenic propellant from liquid to gas, thereby improving the heat exchange intensity between the fluid and the inner wall of the pipeline. During the transformation process, the generated gas is discharged from the exhaust device, thereby reducing the fluctuation of the flow and pressure in the pipeline, and avoiding instability such as vibration of the pipeline system.

[0008] In combination with the first aspect, in one embodiment, the exhaust device includes an exhaust hole and an exhaust pipeline, a plurality of exhaust holes are opened on the delivery pipeline along its delivery direction, and the exhaust pipeline is arranged on one side of the delivery pipeline to enable the gas inside the delivery pipeline to be discharged into the interior of the exhaust pipeline through the exhaust holes.

[0009] By adopting the above technical solution, the gas inside the delivery pipeline is discharged into the exhaust pipeline through the exhaust hole, thereby preventing excessive cryogenic propellant from entering the exhaust pipeline; at the same time, the cryogenic propellant flows forward all the time and continuously generates gas, so multiple exhaust holes are opened along the delivery direction of the delivery pipeline to meet the exhaust work at different locations of the delivery pipeline and improve the exhaust efficiency.

[0010] In one embodiment, an exhaust pipe is provided on the exhaust hole, one end of the exhaust pipe is connected to the interior of the delivery pipeline, and the other end of the exhaust pipe is connected to the interior of the exhaust pipeline, and an exhaust valve is provided on the exhaust pipe.

[0011] By adopting the above technical solution, the exhaust valve can decide whether to exhaust according to demand.

[0012] In one embodiment, a first automatic adjustment component is provided on the exhaust valve, and the first automatic adjustment component includes a pressure sensor and a first regulator, so that when the air pressure inside the delivery pipeline exceeds a threshold value, the regulator opens the exhaust valve, and when the air pressure inside the delivery pipeline does not exceed the threshold value, the regulator closes the exhaust valve.

[0013] By adopting the above technical solution, the exhaust work is automated and the threshold is set according to actual needs. When the air pressure inside the delivery pipeline exceeds the threshold, the exhaust valve opens and exhaust is carried out. When the air pressure inside the delivery pipeline does not exceed the threshold, the exhaust valve closes and exhaust stops.

[0014] In one embodiment, a butterfly valve is provided at one end of the exhaust pipe that is connected to the interior of the delivery pipeline, and a second automatic adjustment component is provided on the butterfly valve. The second automatic adjustment component includes a temperature sensor and a second regulator, so that when the temperature of the inner wall of the delivery pipeline is not lower than the boiling point of the cryogenic propellant, the second regulator opens the butterfly valve, and when the temperature of the inner wall of the delivery pipeline is lower than the boiling point of the cryogenic propellant, the second regulator closes the butterfly valve.

[0015] By adopting the above technical solution, it is avoided that when the cryogenic propellant transportation work is carried out after pre-cooling, the flow of the cryogenic propellant generates pressure on the pressure sensor of the exhaust valve, thereby preventing misjudgment, and the first regulator controls the exhaust valve to open, causing a large amount of cryogenic propellant to enter the exhaust line.

[0016] In one embodiment, the butterfly valve includes a mounting frame, a rotating shaft and a baffle. The mounting frame is mounted on the end face of the exhaust pipe, and the baffle is mounted on the mounting frame through the rotating shaft, so that the baffle can block or unblock the end face of the exhaust pipe.

[0017] By adopting the above technical solution, the butterfly valve can be directly installed inside the exhaust pipe without taking up space in other pipelines, avoiding affecting pre-cooling, exhaust or transportation work; at the same time, this design structure can quickly switch the exhaust pipe between blocked or unobstructed states.

[0018] In one embodiment, one end of the exhaust pipe communicating with the interior of the delivery pipeline coincides with the exhaust hole, and the material of the baffle is the same as that of the low thermal conductivity coating.

[0019] By adopting the above technical solution, when the butterfly valve is closed, the baffle is flush with the low thermal conductivity coating, and the two are made of the same material, thereby reducing the transportation resistance of the cryogenic propellant during transportation.

[0020] In one embodiment, the cross-section of the exhaust pipeline is a semi-elliptical shape, and the cross-sectional area of ​​the exhaust pipeline is greater than half the cross-sectional area of ​​the delivery pipeline.

[0021] By adopting the above technical solution, both the exhaust effect and the maintenance of the vacuum distance are taken into consideration.

[0022] In one embodiment, a vacuum tube is provided on the periphery of the delivery pipeline and the exhaust device, a vacuum cavity is formed between the outer wall of the delivery pipeline and the inner wall of the vacuum tube, and a vacuum cavity is formed between the outer wall of the exhaust device and the inner wall of the vacuum tube.

[0023] By adopting the above technical solution, the temperature inside and outside the conveying pipeline is isolated, preventing the external temperature from affecting the pre-cooling and conveying work.

[0024] In a second aspect, the present invention provides a method for rapid filling of cryogenic propellant, comprising the following steps: Providing the pipeline structure for rapid filling of cryogenic propellant; Fill the delivery pipeline with cryogenic propellant for pre-cooling; The air pressure inside the delivery pipeline is detected by the pressure sensor. If the air pressure inside the delivery pipeline exceeds the threshold, the exhaust valve opens; otherwise, the exhaust valve closes. The temperature of the inner wall of the delivery pipeline is detected by the temperature sensor. If the temperature of the inner wall of the delivery pipeline is not lower than the boiling point of the cryogenic propellant, the butterfly valve opens until the temperature of the inner wall of the delivery pipeline is lower than the boiling point of the cryogenic propellant. When the temperature of the inner wall of the delivery pipeline is lower than the boiling point of the cryogenic propellant, pre-cooling is completed and the cryogenic propellant is added to the delivery pipeline to carry out the delivery of the cryogenic propellant.

[0025] By adopting the above technical solution, when the cryogenic propellant is pre-cooled in the transportation pipeline, the low thermal conductivity coating will promote the transformation of the cryogenic propellant from liquid to gas, thereby improving the heat exchange intensity between the fluid and the inner wall of the pipeline. During the transformation process, the generated gas is discharged from the exhaust device, thereby reducing the fluctuation of the flow and pressure in the pipeline, and avoiding instability such as vibration of the pipeline system.

[0026] In summary, the present invention includes at least one of the following beneficial technical effects: 1. When the cryogenic propellant is pre-cooled in the delivery pipeline, the low thermal conductivity coating will promote the conversion of the cryogenic propellant from liquid to gas, thereby improving the heat exchange intensity between the fluid and the inner wall of the pipeline. During the conversion process, the generated gas is discharged from the exhaust device, thereby reducing the fluctuation of the flow and pressure in the pipeline, and avoiding instability such as vibration of the pipeline system; 2. The design of the exhaust valve and butterfly valve in the exhaust device improves the automation level of the pipeline structure in the pre-cooling and transportation of cryogenic propellants; 3. The design of the exhaust valve on the exhaust pipe can ensure normal exhaust work during pre-cooling, prevent fluid from entering the exhaust pipe during transportation, and reduce the transportation resistance of cryogenic propellant during transportation. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic structural diagram of a pipeline structure for rapid filling of cryogenic propellant according to an embodiment of the present invention; Figure 2 for Figure 1 AA section view; Figure 3 for Figure 2 A magnified view of part B; Figure 4 This is a structural schematic diagram of a butterfly valve in an open state according to an embodiment of the present invention; Figure 5 This is a structural schematic diagram of a butterfly valve in a closed state according to an embodiment of the present invention.

[0028] In the figure: 1-transport pipeline, 2-low thermal conductivity coating, 3-exhaust pipeline, 4-vacuum tube, 41-vacuum chamber, 5-exhaust hole, 6-exhaust pipe, 7-exhaust valve, 8-butterfly valve, 81-mounting frame, 82-rotating shaft, 83-baffle. DETAILED DESCRIPTION

[0029] The embodiments of the present invention are further described in detail below with reference to the accompanying drawings.

[0030] The pipeline structure for rapid filling of cryogenic propellant in the embodiment of the present invention is shown in FIG. Figure 1 As shown, the pipeline structure for rapid refueling of cryogenic propellant includes a delivery pipeline 1, which is used to transport cryogenic propellant. The delivery pipeline 1 can be a metal pipeline; the inner wall of the delivery pipeline 1 is paved with a low thermal conductivity coating 2, which is used to promote the transition from film boiling to transition boiling earlier, so as to improve the heat exchange intensity between the cryogenic propellant fluid and the wall of the delivery pipeline 1. The low thermal conductivity coating 2 can be made of thermal barrier coating or polytetrafluoroethylene material; an exhaust device is provided on the delivery pipeline 1 to discharge the gas generated by the cryogenic propellant in the delivery pipeline 1.

[0031] It can be seen from this that before transporting the cryogenic propellant, the present invention pre-cools the delivery pipeline 1 with a small amount of cryogenic propellant. The low thermal conductivity coating 2 promotes the conversion of the cryogenic propellant from liquid to gas, thereby improving the heat exchange intensity between the fluid and the inner wall of the pipeline. The faster the conversion rate, the faster the rate of gas generation. During the conversion process, the generated gas is discharged from the exhaust device, thereby reducing the fluctuation of the flow and pressure in the pipeline, and avoiding instability such as vibration of the pipeline system.

[0032] Preferably, see Figure 2 、 3 As shown, there is provided a specific structure of the exhaust device; The exhaust device includes an exhaust hole 5 and an exhaust pipeline 3. A plurality of exhaust holes 5 are opened on the delivery pipeline 1 along its delivery direction. The exhaust pipeline 3 is arranged on one side of the delivery pipeline 1 to enable the gas inside the delivery pipeline 1 to be discharged into the exhaust pipeline 3 through the exhaust holes 5.

[0033] Specifically, a plurality of exhaust holes 5 are provided on the delivery pipeline 1, and the exhaust holes 5 are distributed along the delivery direction of the delivery pipeline 1. The spacing between two adjacent exhaust holes 5 is 350 to 500 mm, and 400 mm is most preferred. The exhaust pipeline 3 is arranged close to the delivery pipeline 1. When the cryogenic propellant is converted from liquid to gas, the gas inside the delivery pipeline 1 is discharged from the exhaust holes 5 into the exhaust pipeline 3, thereby preventing excessive cryogenic propellant from entering the exhaust pipeline 3. At the same time, the cryogenic propellant flows forward all the time and continuously generates gas. Therefore, a plurality of exhaust holes 5 are provided along the delivery direction of the delivery pipeline 1 to meet the exhaust work at different locations of the delivery pipeline 1 and improve the exhaust efficiency.

[0034] For further information, see Figure 2 、 3As shown, an exhaust pipe 6 is provided on the exhaust hole 5 , one end of the exhaust pipe 6 is connected to the interior of the delivery pipeline 1 , and the other end thereof is connected to the interior of the exhaust pipeline 3 , and an exhaust valve 7 is provided on the exhaust pipe 6 .

[0035] Specifically, an exhaust pipe 6 is inserted into the exhaust hole 5, ensuring a tight seal between the exhaust hole 5 and the exhaust pipe 6. The exhaust pipe 6 connects the delivery pipeline 1 and the exhaust pipeline 3. When exhaust is required, the exhaust valve 7 on the exhaust pipe 6 is opened, and when exhaust is stopped, the exhaust valve 7 on the exhaust pipe 6 is closed. Therefore, exhaust can be determined based on demand, improving the applicability of the pipeline structure.

[0036] Furthermore, a first automatic adjustment component is provided on the exhaust valve 7, and the first automatic adjustment component includes a pressure sensor and a first regulator, so that when the air pressure inside the delivery pipeline 1 exceeds the threshold, the regulator opens the exhaust valve 7, and when the air pressure inside the delivery pipeline 1 does not exceed the threshold, the regulator closes the exhaust valve 7.

[0037] Specifically, when the air pressure inside the delivery pipeline 1 rises, the air pressure will pass through the exhaust pipe 6 and squeeze the pressure sensor. Therefore, the air pressure inside the delivery pipeline 1 can be measured by the pressure sensor, and the measured air pressure data signal is sent to the control center. The control center determines whether the measured air pressure exceeds the threshold. When the air pressure inside the delivery pipeline 1 exceeds the threshold, the control center sends a signal to the first regulator, and the first regulator controls the exhaust valve 7 to open and exhaust. When the air pressure inside the delivery pipeline 1 does not exceed the threshold, the control center sends a signal to the first regulator, and the first regulator controls the exhaust valve 7 to close and stop exhausting.

[0038] Preferably, see Figure 3 As shown, a butterfly valve 8 is provided at one end of the exhaust pipe 6 communicating with the interior of the delivery pipeline 1. A second automatic regulating component is provided on the butterfly valve 8. The second automatic regulating component includes a temperature sensor and a second regulator. When the temperature of the inner wall of the delivery pipeline 1 is not lower than the boiling point of the cryogenic propellant, the second regulator opens the butterfly valve 8. When the temperature of the inner wall of the delivery pipeline 1 is lower than the boiling point of the cryogenic propellant, the second regulator closes the butterfly valve 8.

[0039] Specifically, a butterfly valve 8 and an exhaust valve 7 are sequentially arranged along the exhaust direction of the gas in the exhaust pipe 6. A temperature sensor measures the temperature of the inner wall of the delivery pipe 1 and sends the measured temperature data signal to the control center. The control center determines whether the measured temperature exceeds the boiling point of the cryogenic propellant. When the temperature of the inner wall of the delivery pipe 1 is not lower than the boiling point of the cryogenic propellant, the control center sends a signal to the second regulator, which controls the butterfly valve 8 to open. When the temperature of the inner wall of the delivery pipe 1 is lower than the boiling point of the cryogenic propellant, the control center sends a signal to the second regulator, which controls the butterfly valve 8 to close. Therefore, the design of the exhaust valve 7 and butterfly valve 8 in the exhaust device improves the automation level of the pipeline structure in the pre-cooling and transportation of cryogenic propellant. At the same time, it prevents the flow of cryogenic propellant from exerting pressure on the pressure sensor of the exhaust valve 7 during the transportation of cryogenic propellant after pre-cooling is completed, thereby preventing the first regulator from controlling the exhaust valve 7 to open and causing a large amount of cryogenic propellant to enter the exhaust pipe 3.

[0040] For further information, see Figure 4 、 5 As shown, a specific structure of a butterfly valve 8 is provided: The butterfly valve 8 includes a mounting frame 81, a rotating shaft 82 and a baffle 83. The mounting frame 81 is installed on the end face of the exhaust pipe 6. The baffle 83 is installed on the mounting frame 81 through the rotating shaft 82 to enable the baffle 83 to block or unblock the end face of the exhaust pipe 6.

[0041] Specifically, mounting bracket 81 is mounted on the end face of exhaust pipe 6, perpendicular to the axis of exhaust pipe 6. A rotating shaft 82 is mounted on mounting bracket 81, and a baffle 83 is fixedly mounted on rotating shaft 82, so that rotating shaft 82 can drive baffle 83 to rotate relative to mounting bracket 81. The butterfly valve 8 can be installed directly inside exhaust pipe 6, without occupying space in other pipelines and thus avoiding any impact on pre-cooling, exhaust, or transportation operations. Furthermore, this design structure can quickly switch the exhaust pipe 6 between a blocked and unobstructed state.

[0042] Furthermore, one end of the exhaust pipe 6 communicating with the interior of the delivery pipeline 1 coincides with the exhaust hole 5 , and the material of the baffle 83 is the same as that of the low thermal conductivity coating 2 .

[0043] Specifically, after the pipeline is pre-cooled, cryogenic propellant transportation is required. At this time, the butterfly valve 8 is closed. Through the above design, the baffle 83 is flush with the low thermal conductivity coating 2, and the two are made of the same material, thereby reducing the transportation resistance of the cryogenic propellant during transportation. If the two are not flush, the cryogenic propellant will move toward the groove or convex body where the butterfly valve 8 is provided when being transported along the low thermal conductivity coating 2, thereby increasing the resistance. If the two are made of different materials, the same problem will occur.

[0044] Preferably, a vacuum tube 4 is provided on the periphery of the delivery pipeline 1 and the exhaust device, a vacuum cavity 41 is formed between the outer wall of the delivery pipeline 1 and the inner wall of the vacuum tube 4 , and a vacuum cavity 41 is formed between the outer wall of the exhaust device and the inner wall of the vacuum tube 4 .

[0045] Specifically, a vacuum chamber 41 is formed between the conveying pipeline 1 and the outside, and a vacuum chamber 41 is formed between the exhaust device and the outside, thereby isolating the temperature inside and outside the conveying pipeline 1 to prevent the external temperature from affecting the pre-cooling and conveying work.

[0046] Preferably, the cross section of the exhaust pipeline 3 is a semi-elliptical shape, and the cross-sectional area of ​​the exhaust pipeline 3 is greater than half the cross-sectional area of ​​the delivery pipeline 1 .

[0047] Specifically, the inner wall of the semi-elliptical exhaust pipe 3 has no sharp edges, and the cross-sectional area of ​​the exhaust pipe 3 is larger than half of the cross-sectional area of ​​the delivery pipe 1, thereby improving the exhaust effect. At the same time, the distance between the exhaust pipe 3 and the vacuum tube 4 is ensured, that is, the thickness of the vacuum chamber 41 between the two, so as to ensure that the external temperature does not affect the effect of pre-cooling and delivery. Preferably, the distance between the exhaust pipe 3 and the vacuum tube 4 is greater than 30 mm.

[0048] The method for rapidly filling a cryogenic propellant in an embodiment of the present invention comprises the following steps: Providing the pipeline structure for rapid filling of cryogenic propellant; Filling the delivery pipeline 1 with cryogenic propellant for pre-cooling; The air pressure inside the delivery pipeline 1 is detected by a pressure sensor. If the air pressure inside the delivery pipeline 1 exceeds a threshold, the exhaust valve 7 is opened; otherwise, the exhaust valve 7 is closed. The temperature of the inner wall of the delivery pipeline 1 is detected by the temperature sensor. If the temperature of the inner wall of the delivery pipeline 1 is not lower than the boiling point of the cryogenic propellant, the butterfly valve 8 is opened until the temperature of the inner wall of the delivery pipeline 1 is lower than the boiling point of the cryogenic propellant. When the temperature of the inner wall of the delivery pipeline 1 is lower than the boiling point of the cryogenic propellant, pre-cooling is completed, and the cryogenic propellant is added into the delivery pipeline 1 to carry out the delivery of the cryogenic propellant.

[0049] It can be seen from this that before transporting the cryogenic propellant, the present invention pre-cools the delivery pipeline 1 with a small amount of cryogenic propellant. The low thermal conductivity coating 2 promotes the conversion of the cryogenic propellant from liquid to gas, thereby improving the heat exchange intensity between the fluid and the inner wall of the pipeline. The faster the conversion rate, the faster the rate of gas generation. During the conversion process, the generated gas is discharged from the exhaust device, thereby reducing the fluctuation of the flow and pressure in the pipeline, and avoiding instability such as vibration of the pipeline system.

[0050] The foregoing is merely a list of specific embodiments of the present application, intended to enable those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application is not limited to the embodiments shown herein, but is intended to conform to the broadest scope consistent with the principles and novel features of the present application.

Claims

1. A pipeline structure for rapid filling of cryogenic propellant, characterized in that: It includes: A delivery pipeline (1) for delivering cryogenic propellant; A low thermal conductivity coating (2) is laid on the inner wall of the delivery pipeline (1); An exhaust device is provided on the delivery pipeline (1) to discharge gas generated by the cryogenic propellant in the delivery pipeline (1).

2. The pipeline structure for rapid filling of cryogenic propellant according to claim 1, characterized in that: The exhaust device comprises an exhaust hole (5) and an exhaust pipeline (3). The delivery pipeline (1) is provided with a plurality of exhaust holes (5) along its delivery direction. The exhaust pipeline (3) is arranged on one side of the delivery pipeline (1) so that the gas inside the delivery pipeline (1) is discharged into the interior of the exhaust pipeline (3) through the exhaust holes (5).

3. The pipeline structure for rapid filling of cryogenic propellant according to claim 2, characterized in that: An exhaust pipe (6) is provided on the exhaust hole (5), one end of the exhaust pipe (6) is connected to the interior of the delivery pipeline (1), and the other end is connected to the interior of the exhaust pipeline (3), and an exhaust valve (7) is provided on the exhaust pipe (6).

4. The pipeline structure for rapid filling of cryogenic propellant according to claim 3, characterized in that: The exhaust valve (7) is provided with a first automatic adjustment component, which includes a pressure sensor and a first regulator, so that when the air pressure inside the delivery pipeline (1) exceeds a threshold value, the regulator opens the exhaust valve (7); when the air pressure inside the delivery pipeline (1) does not exceed the threshold value, the regulator closes the exhaust valve (7).

5. The pipeline structure for rapid filling of cryogenic propellant according to claim 3, characterized in that: A butterfly valve (8) is provided at one end of the exhaust pipe (6) that is in communication with the interior of the delivery pipeline (1). A second automatic regulating component is provided on the butterfly valve (8). The second automatic regulating component includes a temperature sensor and a second regulator, so that when the temperature of the inner wall of the delivery pipeline (1) is not lower than the boiling point of the low-temperature propellant, the second regulator opens the butterfly valve (8); when the temperature of the inner wall of the delivery pipeline (1) is lower than the boiling point of the low-temperature propellant, the second regulator closes the butterfly valve (8).

6. The pipeline structure for rapid filling of cryogenic propellant according to claim 5, characterized in that: The butterfly valve (8) comprises a mounting frame (81), a rotating shaft (82) and a baffle (83), wherein the mounting frame (81) is mounted on the end face of the exhaust pipe (6), and the baffle (83) is mounted on the mounting frame (81) via the rotating shaft (82), so that the baffle (83) blocks or clears the end face of the exhaust pipe (6).

7. The pipeline structure for rapid filling of cryogenic propellant according to claim 6, characterized in that: One end of the exhaust pipe (6) that is in communication with the interior of the delivery pipeline (1) coincides with the exhaust hole (5), and the material of the baffle (83) is the same as that of the low thermal conductivity coating (2).

8. The pipeline structure for rapid filling of cryogenic propellant according to claim 2, characterized in that: The cross section of the exhaust pipeline (3) is a semi-ellipse, and the cross-sectional area of ​​the exhaust pipeline (3) is greater than half the cross-sectional area of ​​the delivery pipeline (1).

9. The pipeline structure for rapid filling of cryogenic propellant according to claim 1, characterized in that: The outer peripheries of the delivery pipeline (1) and the exhaust device are sheathed with a vacuum tube (4); a vacuum cavity (41) is formed between the outer wall of the delivery pipeline (1) and the inner wall of the vacuum tube (4); and a vacuum cavity (41) is formed between the outer wall of the exhaust device and the inner wall of the vacuum tube (4).

10. A method for rapid filling of cryogenic propellant, characterized in that: It includes the following steps: Providing a pipeline structure for rapid filling of cryogenic propellant according to any one of claims 1 to 9; Filling the delivery pipeline (1) with cryogenic propellant for pre-cooling; The air pressure inside the delivery pipeline (1) is detected by a pressure sensor. If the air pressure inside the delivery pipeline (1) exceeds a threshold value, the exhaust valve (7) is opened; otherwise, the exhaust valve (7) is closed; The temperature of the inner wall of the delivery pipe (1) is detected by a temperature sensor. If the temperature of the inner wall of the delivery pipe (1) is not lower than the boiling point of the cryogenic propellant, the butterfly valve (8) is opened until the temperature of the inner wall of the delivery pipe (1) is lower than the boiling point of the cryogenic propellant. When the temperature of the inner wall of the delivery pipeline (1) is lower than the boiling point of the cryogenic propellant, pre-cooling is completed, and the cryogenic propellant is added into the delivery pipeline (1) to carry out the delivery of the cryogenic propellant.

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