Comprehensive test device for low-temperature propellants

Abstract

The invention provides a comprehensive test device for a low-temperature propellant, and relates to the technical field of low-temperature propellant tests. The test device comprises a first container, a second container, a test pipeline and a monitoring module, the first container and the second container are connected through a test pipeline; monitoring modules are arranged on the first container, the second container and the test pipeline. The monitoring modules are arranged on the first container, the second container and the test pipeline, various key parameters such as temperature, pressure, flow and liquid level height of the propellant in the test process can be monitored in real time, and therefore the accuracy of test data and the safety of the test process are ensured. The first container and the second container are connected through the test pipeline, so that the propellant can be conveniently transmitted, and meanwhile, the existence of the monitoring module ensures that the state of the propellant is comprehensively mastered in the test process.

Description

Technical Field

[0001] The invention relates to the technical field of cryogenic propellant testing, and in particular to a cryogenic propellant comprehensive testing device. Background Art

[0002] With the development of aerospace technology, cryogenic propellants (such as liquid hydrogen, liquid oxygen and methane) have been widely used in large launch vehicles due to their advantages such as non-toxicity, pollution-free, low cost, high specific impulse and high thrust. Compared with normal temperature propellants, cryogenic propellants can provide higher specific impulse (about 30% to 40% higher), thereby significantly improving the performance of rockets. In order to further improve the thermodynamic properties of cryogenic propellants, supercooling filling is usually adopted, that is, by lowering the temperature of the propellant to increase its sensible cooling capacity, effectively preventing the occurrence of two-phase flow phenomenon, reducing evaporation losses during storage, and reducing the volume of the tank by increasing the density of the propellant.

[0003] However, before cryogenic propellants are officially put into use, they must undergo rigorous testing to ensure that their performance meets the requirements. Traditional cryogenic propellant test equipment has some limitations, such as relatively single functions. Different tests (such as flow resistance test, heat leakage test, water hammer test, cavitation test, flow rate test, geyser test, etc.) often need to be carried out on independent devices, which means that only specific aspects can be tested each time. In addition, the test conditions of these traditional devices have a small adjustment range, resulting in a limited amount of data obtained in a single test, and the consumption of the test medium (propellant) is large, which is neither economical nor environmentally friendly. Summary of the invention

[0004] The main technical problem to be solved by the present invention is to provide a comprehensive test device that can realize the efficient and safe transfer of cryogenic propellants between different containers, and at the same time has a comprehensive monitoring function and an emergency pressure relief protection mechanism.

[0005] In order to solve the above technical problems, the technical solutions provided by the present invention are as follows:

[0006] A cryogenic propellant comprehensive test device comprises: a first container, a second container, a test pipeline and a monitoring module;

[0007] The first container and the second container are connected via the test pipeline;

[0008] The monitoring module is disposed on the first container, the second container and the test pipeline.

[0009] Optionally, the first container and the second container are the same and can use roles with each other;

[0010] When the first container is a supply container, the second container is a receiving container; when the second container is a supply container, the first container is a receiving container.

[0011] Optionally, the test pipeline includes a plurality of sub-test pipelines connected in sequence;

[0012] The diameters of the plurality of sub-test pipelines gradually increase or decrease.

[0013] Optionally, a plurality of the sub-test pipelines are vertically arranged, and two adjacent sub-test pipelines are connected via an elbow.

[0014] Optionally, two adjacent sub-test pipelines are connected via a flange.

[0015] Optionally, at least one bidirectional sealing valve is provided on each of the sub-test pipelines.

[0016] Optionally, the bidirectional sealing valve adopts a pneumatic mode and has the ability to adjust its switching speed by air supply pressure or air supply speed to achieve simulation of different water hammer pressures.

[0017] Optionally, it also includes a container pressurization pipeline;

[0018] The inlet of the first container and the inlet of the second container are respectively connected to a container pressurizing pipeline;

[0019] When the first container is a supply container, the pressurizing pipeline on the second container is used for pressure relief;

[0020] When the second container is a supply container, the pressurizing pipeline on the first container is used for pressure relief.

[0021] Optionally, the monitoring module includes at least one of the following: a temperature detection module, a pressure detection module, a flow detection module, a liquid level detection module, a vibration detection module, a strain detection module, a gas leakage detection module, and a sound pressure detection module.

[0022] Optionally, a pressure relief buffer container is also included;

[0023] The test pipeline is connected to the pressure relief buffer container through a connecting pipeline.

[0024] Optionally, a controller is also included;

[0025] A shut-off valve is arranged on the connecting pipeline;

[0026] The controller is connected to the monitoring module and the shut-off valve;

[0027] When the test data detected by the monitoring module is greater than a preset value, the shut-off valve is controlled to open.

[0028] The technical solution provided by the present invention has the following technical effects:

[0029] 1. Monitoring modules are set on the first container, the second container and the test pipeline, which can monitor the key parameters of the propellant in the test process in real time, such as temperature, pressure, flow rate and liquid level, so as to ensure the accuracy of the test data and the safety of the test process. The first container and the second container are connected by the test pipeline, which can facilitate the transmission of the propellant. At the same time, the existence of the monitoring module ensures a comprehensive grasp of the propellant status during the test.

[0030] 2. The first container and the second container are identical and can be used interchangeably, which increases the flexibility of the test device and allows the role of the container to be easily switched at different test stages, thus improving the versatility and efficiency of the device. Since the containers are interchangeable, the test operation becomes simpler, reducing the extra operation steps caused by container differences, saving time and resources.

[0031] 3. The test pipeline is composed of multiple sub-test pipelines. The change of pipe diameter can simulate the flow characteristics of propellants in pipes of different diameters, which is crucial for evaluating the performance of propellants in practical applications. By changing the diameter of the sub-test pipeline, the flow conditions under different working conditions can be simulated, thereby expanding the application range of the test device.

[0032] 4. The sub-test pipeline is set vertically and connected by elbows, which can better simulate the flow path of the propellant in actual use, especially in the combustion chamber of a rocket engine. The vertical setting helps to reduce flow resistance, while the elbow connection can simulate the behavior of the propellant at the bend. At the same time, this design can simulate the flow characteristics of the propellant in the vertical direction, especially in the application of rocket engines. This is very important for evaluating the performance of the propellant under complex flow conditions.

[0033] 5. The two adjacent sub-test pipelines are connected by flanges, which is convenient for disassembly and replacement, which is very beneficial for daily maintenance and inspection. The flange connection can provide good sealing, ensuring that no leakage occurs during the test, and improving the safety and reliability of the test device.

[0034] 6. At least one two-way sealing valve is set on each sub-test pipeline to accurately control the flow direction and speed of the propellant, enhancing the control flexibility during the test. The two-way sealing valve helps prevent accidental backflow and provides additional safety for the test device.

[0035] 7. The container pressurization line can increase the pressure inside the container, promote the flow of propellant, and ensure that the propellant can be smoothly transferred from one container to another. By injecting pressurized gas into the container, the behavior of the propellant under high pressure conditions can be simulated, which is crucial for evaluating the performance of the propellant under actual working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The above and other features and advantages of the present invention will become more apparent by describing in detail exemplary embodiments thereof with reference to the attached drawings.

[0037] Figure 1 It is a first structural schematic diagram of a cryogenic propellant comprehensive test device provided in an embodiment of the present invention;

[0038] Figure 2 It is a second structural schematic diagram of a cryogenic propellant comprehensive test device provided in an embodiment of the present invention.

[0039] Description of reference numerals:

[0040] 1. First container, 2. Second container, 3. Test pipeline, 4. Monitoring module, 5. Two-way sealing valve, 6. Container pressurization pipeline, 7. Pressure relief buffer container, 8. Connecting pipeline, 9. Shut-off valve;

[0041] 31. Sub-test pipeline;

[0042] 81. mother connecting pipeline, 82. child connecting pipeline. DETAILED DESCRIPTION

[0043] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in a variety of forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that the present invention will be comprehensive and complete and fully convey the concepts of the example embodiments to those skilled in the art. The same reference numerals in the figures represent the same or similar structures, and thus their detailed description will be omitted.

[0044] The terms "a", "an", "the", and "said" are used to indicate the presence of one or more elements / components / etc.; the terms "comprising" and "having" are used to express an open-ended inclusive meaning and mean that additional elements / components / etc. may be present in addition to the listed elements / components / etc.

[0045] Figure 1 It is a first structural schematic diagram of a cryogenic propellant comprehensive test device provided in an embodiment of the present invention; Figure 2This is a second structural schematic diagram of a cryogenic propellant comprehensive test device provided in an embodiment of the present invention. The above schematic diagram is only to show the structural relationship related to the invention point and is not to be used as the actual proportion of the actual product.

[0046] like Figure 1 As shown, a cryogenic propellant comprehensive test device in this embodiment includes: a first container 1, a second container 2, a test pipeline 3 and a monitoring module 4;

[0047] The first container 1 and the second container 2 are usually made of low-temperature resistant materials, such as stainless steel or other alloy materials, which can withstand extremely low temperatures without brittle cracking or deformation.

[0048] The first container 1 and the second container 2 can be designed to be cylindrical or other suitable shapes to ensure good thermodynamic performance and structural stability. The sizes of the first container 1 and the second container 2 need to be determined according to test requirements to accommodate different levels of propellants.

[0049] The first container 1 and the second container 2 may be provided with a heat insulating layer inside and / or outside to reduce the influence of the external environment on the cryogenic propellant and keep the propellant at the required working temperature.

[0050] Necessary interfaces are provided on the first container 1 and the second container 2 for connecting the test pipeline 3 and other auxiliary equipment, such as a booster pipeline and a monitoring module 4 .

[0051] The first container 1 and the second container 2 are connected via a test pipeline 3 , and monitoring modules 4 are disposed on the first container 1 , the second container 2 and the test pipeline 3 .

[0052] When the first container 1 is used as a supply container, it is responsible for providing cryogenic propellant to the second container 2 (which is now used as a receiving container). During this period, the propellant in the first container 1 will be transferred to the second container 2 through the test line 3, and this process will be closely monitored by the monitoring module 4.

[0053] When the second container 2 is used as a supply container, its role is exchanged with the first container 1, and the second container 2 will provide propellant to the first container 1. This design allows the test device to operate in different configurations, thereby increasing the flexibility and efficiency of the test.

[0054] The first container 1, the second container 2 and the test pipeline 3 are all equipped with a monitoring module 4, which can monitor key parameters such as temperature, pressure, flow rate and liquid level in real time. These data are crucial for evaluating the state of the propellant and ensuring the safety of the test.

[0055] Before the test begins, one of the containers will be filled with cryogenic propellant, while the other container will be empty or contain a small amount of propellant as a receiving container. Test process: During the transfer of propellant between the two containers, data is collected through the test pipeline 3 and the monitoring module 4 to evaluate the performance and behavior of the propellant and the performance of the pipeline.

[0056] In one embodiment, the first container 1 and the second container 2 are the same and can be used interchangeably; when the first container 1 is a supply container, the second container 2 is a receiving container; when the second container 2 is a supply container, the first container 1 is a receiving container. The first container 1 and the second container 2 are designed to be interchangeable, which means that they have the same structural and functional characteristics and can flexibly switch between the roles of supply container or receiving container according to different stages of the experiment.

[0057] It also includes a container pressurization pipeline 6; a container pressurization pipeline 6 is connected to the inlet of the first container 1 and the second container 2 respectively. The container pressurization pipeline 6 is a special pipeline system, which is used to introduce cryogenic propellant or pressurized gas into the first container 1 and the second container 2 to increase the pressure in the container, thereby promoting the flow of cryogenic propellant or simulating the behavior of propellant under high pressure conditions. A container pressurization pipeline 6 is connected to the inlet of each container (i.e., the first container 1 and the second container 2), so that cryogenic propellant or pressurized gas can be injected into the container when needed. When the first container 1 is a supply container, the pressurization pipeline 6 on the second container 2 is used for pressure relief; when the second container 1 is a supply container, the pressurization pipeline 6 on the first container 2 is used for pressure relief.

[0058] By increasing the pressure in the first container 1 and the second container 2, the flow of the cryogenic propellant can be promoted, ensuring that the propellant can be smoothly transferred from one container to another. In some tests, it is necessary to simulate the behavior of the propellant under high pressure conditions, such as in the combustion chamber of a rocket engine. The container pressurization pipeline 6 can help achieve this goal. By accurately controlling the pressure in the container, the accuracy of the test can be improved, ensuring that the test results are more reliable.

[0059] The pressurized gas is usually an inert gas, such as nitrogen or helium, to avoid reaction with cryogenic propellants. The pressurized pipeline is connected to a pressurized device, which can be a compressor or a gas tank, to provide the required pressurized gas. A control valve is provided on the pressurized pipeline to adjust the gas flow and pressure entering the container. A monitoring module 4 should also be provided on the container pressurized pipeline 6 to monitor the pressure and flow of the pressurized gas to ensure the stability of the pressure in the container.

[0060] When it is necessary to transfer propellant from one container to another, the pressure difference can be used to push the propellant flow by injecting pressurized gas into the supply container. When simulating the high-pressure environment in the combustion chamber of a rocket engine, high-pressure gas can be injected into the container through the pressurization pipeline to simulate actual working conditions. By pressurizing the container and monitoring the pressure change over a certain period of time, the sealing of the container and piping system can also be checked.

[0061] The test pipeline 3 includes a plurality of sub-test pipelines 31 connected in sequence; the diameters of the plurality of sub-test pipelines 31 gradually increase or decrease.

[0062] The test pipeline 3 is composed of a series of sub-test pipelines 31, each of which is an independent pipe section, which are connected in sequence in a certain order to form a complete test pipeline 3. The diameter of each sub-test pipeline 31 can be gradually increased or gradually reduced according to a specific design mode. This change can simulate various pipeline conditions encountered by propellants in actual use, such as nozzles, diffusers or narrow channels.

[0063] By changing the pipe diameter, the flow characteristics of the propellant in pipes of different diameters can be simulated, which is crucial for evaluating the performance of the propellant in an actual rocket engine. The change in pipe diameter can help researchers understand the physical properties of the propellant under different flow conditions, such as flow rate, pressure drop, turbulence, etc. By testing the performance of propellants under different pipe diameters, data support can be provided for the design of rocket engines to help optimize the performance and efficiency of the engine.

[0064] If the tube diameter is gradually increased, the flow of the propellant in the diffuser can be simulated. For example, the pressure recovery and turbulence characteristics of the propellant can be studied. If the tube diameter is gradually decreased, the flow of the propellant in the nozzle can be simulated. For example, the injection characteristics of the propellant, such as injection angle, injection velocity, etc. By combining the changes in different tube diameters, more complex flow conditions can be simulated, such as the flow of propellant in the combustion chamber of a rocket engine.

[0065] The diameter of the sub-test pipeline 31 covers commonly used nominal diameters.

[0066] Adjacent sub-test pipelines 31 may be connected via elbows, flanges or other connectors to ensure that the fluid passes through the entire test pipeline 3 smoothly.

[0067] At least one two-way sealing valve 5 can be provided on each sub-test pipeline 31 to control the flow direction and speed of the propellant, so as to facilitate more precise test control. The two-way sealing valve 5 adopts a pneumatic mode and has the ability to adjust its opening and closing speed by the air supply pressure or air supply speed to achieve simulation of different water hammer pressures.

[0068] In one embodiment, a plurality of sub-test pipelines 31 are vertically arranged, and two adjacent sub-test pipelines 31 are connected via an elbow.

[0069] Multiple sub-test pipes 31 are arranged vertically, which means that they are arranged in the vertical direction rather than the horizontal direction. This design can simulate the flow characteristics of the propellant in the vertical direction, especially in the application of rocket engines. Two adjacent sub-test pipes 31 are connected by an elbow. An elbow is a pipe fitting used to change the flow direction of the fluid, usually for an angle change of 90 degrees or 45 degrees. This connection method can also simulate the behavior of the propellant at a turn, such as the change in the flow path in the combustion chamber of a rocket engine.

[0070] The sub-test line 31 can be set to a specific direction to simulate a real usage scenario.

[0071] like Figure 2 As shown, in another embodiment, a pressure relief buffer container 7 is also included; the test pipeline 3 is connected to the pressure relief buffer container 7 through a connecting pipeline 8. The pressure relief buffer container 7 is an important safety component, which is used to provide a safe pressure relief path when the pressure in the test pipeline 3 exceeds the safety threshold to prevent accidents caused by overpressure. When the pressure in the test pipeline 3 is too high, the pressure can be released through the pressure relief buffer container 7 to protect the safety of the test device and the operator. The pressure relief buffer container 7 can also play a buffering role, absorb sudden pressure fluctuations, and reduce the impact on the entire test device. The test pipeline 3 is connected to the pressure relief buffer container 7 through a dedicated connecting pipeline 8. This connecting pipeline 8 should be strong enough to withstand high pressure and have good sealing performance. The connecting pipeline 8 is usually installed at a key position of the test pipeline 3, such as near the outlet of the container or in the high-pressure area in the test pipeline 3. By adding a pressure relief buffer container 7 to the cryogenic propellant comprehensive test device, the safety of the test can be greatly improved, and it can be ensured that measures can be taken quickly in the event of an abnormal situation to prevent potential risks.

[0072] The connecting pipeline 8 is composed of a mother connecting pipeline 81 and a plurality of sub-connecting pipelines 82. One end of each sub-connecting pipeline 82 is connected to the middle of a sub-test pipeline 31, and the other ends of the plurality of sub-connecting pipelines 82 are connected to one end of the mother connecting pipeline 81. The other end of the mother connecting pipeline 81 is connected to the pressure relief buffer container 7. The sub-connecting pipeline 82 is a branch pipe drawn from the middle of each sub-test pipeline 31. One end of each sub-connecting pipeline 82 is connected to the middle of a sub-test pipeline 31, and the other end is connected to the mother connecting pipeline 81. One end of each sub-connecting pipeline 82 is connected to the middle of a sub-test pipeline 31, so as to ensure that the propellant or gas can be released from any sub-test pipeline 31 when needed. The mother connecting pipeline 81 is a trunk pipeline used to collect fluids from a plurality of sub-connecting pipelines 82 and finally guide them to the pressure relief buffer container 7.

[0073] Here, the volume of the pressure relief buffer container 7 is larger than the sum of the volumes of the first container 1 and the second container 2. The volume of the pressure relief buffer container 7 is designed to be larger than the total volume of the first container 1 and the second container 2. This is to ensure that in an emergency, even if all the propellants in the first container 1 and the second container 2 need to be released into the pressure relief buffer container 7, the container has enough capacity to accommodate these propellants, thereby avoiding overflow and possible safety risks. Usually, the volume of the pressure relief buffer container 7 will leave a certain safety margin to deal with unexpected situations or calculation errors. In addition, the pressure relief buffer container 7 is also equipped with a safety valve, which can be quickly discharged when overpressure occurs.

[0074] It also includes a controller; a shut-off valve 9 is arranged on the connecting pipeline 8; the controller is connected to the monitoring module 4 and the shut-off valve 9; when the test data detected by the monitoring module 4 is greater than the preset value, the shut-off valve 9 is controlled to open.

[0075] The controller is an electronic device used to receive data from the monitoring module 4 and make corresponding control decisions based on the data. In this embodiment, the controller is connected to the monitoring module 4 and the shut-off valve 9.

[0076] The monitoring module 4 includes at least one of the following: a temperature detection module, a pressure detection module, a flow detection module, and a liquid level detection module. These modules are used to monitor key parameters in the test pipeline 3 in real time.

[0077] The pressure detection module has the characteristics of high-speed acquisition, and the sampling frequency is greater than 5kHZ. Optionally, vibration detection module, strain detection module, gas leakage detection module, and sound pressure detection module can also be configured.

[0078] A shut-off valve 9 is installed on the connecting pipeline 8 to control the flow of the propellant or gas.

[0079] When the test data (such as temperature, pressure, flow or liquid level) detected by the monitoring module 4 is greater than the preset value, the controller will receive this signal and control the opening of the shut-off valve 9 according to the preset logic. Once the shut-off valve 9 is opened, the propellant or gas in the test pipeline 3 will enter the pressure relief buffer container 7 through the connecting pipeline 8 to reduce the pressure or flow in the test pipeline 3 to prevent safety accidents.

[0080] The controller communicates with the monitoring module 4 and the shut-off valve 9 through electrical signals or digital signals to ensure the accuracy of data transmission and the timely execution of control instructions. The preset values ​​are set according to the specific requirements and safety standards of the test and are used to trigger the actions of the controller. These preset values ​​are usually set by operators or engineers before the test. In an emergency, when the data detected by the monitoring module 4 exceeds the safety threshold, the controller will respond quickly and control the shut-off valve 9 to open to ensure the safety of the test device.

[0081] If the monitoring module 4 detects that the pressure in the test pipeline 3 exceeds the preset safety threshold, the controller will immediately control the shut-off valve 9 to open and introduce the propellant or gas into the pressure relief buffer container 7 to reduce the pressure and protect the test device from damage.

[0082] If an abnormal temperature rise is detected, the controller will also control the shut-off valve 9 to open to avoid safety problems caused by excessive temperature.

[0083] When the flow rate exceeds the preset maximum value, the controller will also control the shut-off valve 9 to open to prevent excessive propellant or gas from entering the system.

[0084] Specifically, a shut-off valve 9 is provided on the mother connection pipeline 81. The shut-off valve 9 is provided on the mother connection pipeline 81, and is located between the pressure relief buffer container 7 after the multiple sub-connection pipelines 82 are collected. The shut-off valve 9 is provided on the mother connection pipeline 81, which means that the fluid from the multiple sub-test pipelines 31 can be centrally controlled. This means that once emergency pressure relief is required, the fluid discharge of all sub-test pipelines 31 can be controlled by a single shut-off valve 9, which simplifies the design of the control system. By centrally arranging the shut-off valves 9 on the mother connection pipeline 81, the number of shut-off valves 9 can be reduced, thereby reducing costs. If a shut-off valve 9 is provided on each sub-connection pipeline 82, the entire system will require more valves and related control components, which will increase the complexity and cost of the system. The shut-off valve 9 is located between the pressure relief buffer container 7 after the multiple sub-connection pipelines 82 are collected, which can ensure that all fluids can safely enter the pressure relief buffer container 7, avoiding leakage of fluids at any position in the system, thereby improving the safety of the system. Through centralized control, the possibility of operator misoperation is reduced. If each sub-connection pipeline 82 has its own shut-off valve 9, the operator may cause unnecessary safety problems due to misoperation. If more sub-test pipelines 31 need to be added in the future, only new sub-connection pipelines 82 need to be added to the mother connection pipeline 81 without modifying or adding the shut-off valve 9, which makes the system easier to expand.

[0085] The shutoff valve 9 includes a gate valve, a stop valve, a ball valve and a butterfly valve. Since a controller is needed to control the opening or closing of the shutoff valve 9, an electromagnetic shutoff valve 9 needs to be selected.

[0086] In the embodiments of the present invention, the term "plurality" refers to two or more than two, unless otherwise clearly defined. The terms "installation", "connection", "fixation" and the like should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific circumstances.

[0087] In the description of the embodiments of the present invention, it needs to be understood that the directions or positional relationships indicated by the terms "upper" and "lower" are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present invention and simplifying the description, rather than indicating or implying that the device or unit referred to must have a specific direction, be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation on the embodiments of the present invention.

[0088] In the description of this specification, the description of the terms "one embodiment", "a preferred embodiment", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiment of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0089] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A cryogenic propellant comprehensive test device, characterized in that: include: A first container (1), a second container (2), a test pipeline (3) and a monitoring module (4); The first container (1) and the second container (2) are connected via the test pipeline (3); The monitoring module (4) is arranged on the first container (1), the second container (2) and the test pipeline (3).

2. A cryogenic propellant comprehensive test device according to claim 1, characterized in that: The first container (1) and the second container (2) are identical and can be used interchangeably; When the first container (1) is a supply container, the second container (2) is a receiving container; when the second container (2) is a supply container, the first container (1) is a receiving container.

3. A cryogenic propellant comprehensive test device according to claim 1 or 2, characterized in that: The test pipeline (3) comprises a plurality of sub-test pipelines (31) connected in sequence; The diameters of the plurality of sub-test pipelines (31) gradually increase or decrease.

4. A cryogenic propellant comprehensive test device according to claim 3, characterized in that: A plurality of the sub-test pipelines (31) are arranged vertically, and two adjacent sub-test pipelines (31) are connected via an elbow.

5. A cryogenic propellant comprehensive test device according to claim 3, characterized in that: Two adjacent sub-test pipelines (31) are connected via a flange.

6. A cryogenic propellant comprehensive test device according to claim 3, characterized in that: At least one bidirectional sealing valve (5) is arranged on each of the sub-test pipelines (31).

7. A cryogenic propellant comprehensive test device according to claim 6, characterized in that: The bidirectional sealing valve (5) adopts a pneumatic mode and has the ability to adjust its opening and closing speed by means of air supply pressure or air supply speed, thereby achieving simulation of different water hammer pressures.

8. A cryogenic propellant comprehensive test device according to claim 1, characterized in that: Also included is a container pressurizing pipeline (6); The inlet of the first container (1) and the inlet of the second container (2) are respectively connected to a container pressurizing pipeline (6); When the first container (1) is a supply container, the pressurizing pipeline (6) on the second container (2) is used for pressure relief; When the second container (1) is a supply container, the pressurizing pipeline (6) on the first container (2) is used for pressure relief.

9. A cryogenic propellant comprehensive test device according to claim 1, characterized in that: The monitoring module (4) comprises at least one of the following: a temperature detection module, a pressure detection module, a flow detection module, a liquid level detection module, a vibration detection module, a strain detection module, a gas leakage detection module, and a sound pressure detection module.

10. A cryogenic propellant comprehensive test device according to claim 1, characterized in that: It also includes a pressure relief buffer container (7); The test pipeline (3) is connected to the pressure relief buffer container (7) via a connecting pipeline (8).

11. A cryogenic propellant comprehensive test device according to claim 10, characterized in that: Also includes a controller; The connecting pipeline (8) is provided with a shut-off valve (9); The controller is connected to the monitoring module (4) and the shut-off valve (9); When the test data detected by the monitoring module (4) is greater than a preset value, the shut-off valve (9) is controlled to open.

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