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 present invention relates to the technical field of cryogenic propellant testing, and particularly to a comprehensive testing device for cryogenic propellants. Background Art

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

[0003] However, before cryogenic propellants are officially put into use, strict tests must be carried out to ensure that their performance meets the requirements. Traditional cryogenic propellant testing devices have some limitations. For example, their functions are relatively single. Different tests (such as flow resistance test, heat leakage test, water hammer test, cavitation test, flow velocity 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 adjustment range of test conditions for these traditional devices is small, resulting in a limited amount of data obtained in a single test and a large consumption of the test medium (propellant), 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 testing device that can efficiently and safely transfer cryogenic propellants between different containers, and at the same time has a comprehensive monitoring function and an emergency pressure relief protection mechanism.

[0005] To solve the above technical problems, the technical solution provided by the present invention is as follows:

[0006] A comprehensive testing device for cryogenic propellants, comprising: a first container, a second container, a test pipeline, and a monitoring module;

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

[0008] The monitoring module is provided 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 be used interchangeably;

[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 are arranged in a geometric or arithmetic sequence.

[0013] Optionally, the arrangement of the plurality of sub-test pipelines includes at least one of vertical, horizontal or inclined forms, and two adjacent sub-test pipelines are connected by elbows.

[0014] Optionally, two adjacent sub-test pipelines are connected by flanges.

[0015] Optionally, at least one two-way sealing valve is provided on each sub-test pipeline.

[0016] Optionally, the two-way sealing valve adopts a pneumatic mode and has the ability to adjust its opening and closing speed through the supply air pressure or supply air speed, so as to simulate different water hammer pressures.

[0017] Optionally, it further includes two sets of independent container pressurization pipelines;

[0018] The inlets of the first container and the second container are respectively connected to one end of a container pressurization pipeline, and the other end of each container pressurization pipeline is connected to a pressurization container;

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

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

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

[0022] Optionally, it further includes a pressure relief buffer container;

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

[0024] The volume of the pressure relief buffer container is capable of accommodating the total pressure relief amount of the propellants in the first container and the second container.

[0025] Optionally, it further includes a controller;

[0026] A shut-off valve is provided on the connecting pipeline;

[0027] The controller is connected to the monitoring module and the shut-off valve;

[0028] When the test data detected by the monitoring module is greater than a preset value, the shut-off valve is controlled to open.

[0029] The technical solution provided by the present invention has the following technical effects:

[0030] 1. Monitoring modules are provided on the first container, the second container and the test pipeline, which can monitor various key parameters of the propellant during the test in real time, such as temperature, pressure, flow rate and liquid level, etc., 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 through the test pipeline, which can facilitate the transmission of the propellant, and at the same time, the presence of the monitoring module ensures the comprehensive grasp of the propellant state during the test process.

[0031] 2. The first container and the second container are the same and can be used interchangeably, which increases the flexibility of the test device, can easily switch the roles of the containers at different test stages, and improves the versatility and efficiency of the device. Since the containers can be interchanged, the test operation becomes simpler, reducing the extra operation steps caused by container differences, and saving time and resources.

[0032] 3. The test pipeline is composed of multiple sub-test pipelines, and the change of the pipe diameter can simulate the flow characteristics of the propellant in pipelines with different diameters, which is crucial for evaluating the performance of the propellant in actual applications. By changing the pipe diameter of the sub-test pipelines, the flow conditions under different working conditions can be simulated, thus expanding the application scope of the test device.

[0033] 4. The sub-test pipelines are vertically arranged 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 arrangement helps to reduce the flow resistance, and the elbow connection can simulate the behavior of the propellant at the turning point. At the same time, this design can simulate the flow characteristics of the propellant in the vertical direction, especially in the application of a rocket engine. This is very important for evaluating the performance of the propellant under complex flow conditions.

[0034] 5. Two adjacent sub-test pipelines are connected by flanges, which is convenient for disassembly and replacement, and is very beneficial for daily maintenance and inspection. The flange connection can provide good sealing performance, ensuring that there is no leakage during the test process, and improving the safety and reliability of the test device.

[0035] 6. At least one two-way sealing valve is provided on each sub-test pipeline, which can precisely 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 protection for the test device.

[0036] 7. The container pressurization pipeline can increase the pressure inside the container, promote the flow of the propellant, and ensure that the propellant can smoothly transfer 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

[0037] The above and other features and advantages of the present invention will become more apparent by referring to the accompanying drawings and describing its exemplary embodiments in detail.

[0038] Figure 1 FIG. 12 is a first schematic structural diagram of a cryogenic propellant comprehensive test device provided in an embodiment of the present invention;

[0039] Figure 2 FIG. 16 is a second schematic structural diagram of a cryogenic propellant comprehensive test device provided in an embodiment of the present invention.

[0040] DESCRIPTION OF THE REFERENCE NUMERALS:

[0041] 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. Connection pipeline, 9. Shut-off valve, 10. Pressurization container;

[0042] 31. Sub-test pipeline;

[0043] 81. Mother connection pipeline, 82. Sub-connection pipeline. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0044] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, the exemplary embodiments can be implemented in various forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. Like reference numerals in the figures denote the same or similar structures, and thus their detailed descriptions will be omitted.

[0045] The terms "a", "an", "the", and "said" are used to denote the presence of one or more elements / components / etc.; the terms "comprising" and "having" are used to mean an open inclusion and mean that in addition to the listed elements / components / etc., there may be additional elements / components / etc.

[0046] Figure 1 It is the first structural schematic diagram of a cryogenic propellant comprehensive test device provided in an embodiment of the present invention; Figure 2 It is the second structural schematic diagram of a cryogenic propellant comprehensive test device provided in an embodiment of the present invention. The above schematic diagrams only show the structural relationships related to the inventive points and do not represent the actual proportions of actual products.

[0047] As Figure 1 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.

[0048] Among them, 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 fracture or deformation.

[0049] The first container 1 and the second container 2 can be designed in a cylindrical shape 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 the test requirements to adapt to different magnitudes of propellants.

[0050] An insulating layer can be provided inside and / or outside the first container 1 and the second container 2 to reduce the influence of the external environment on the cryogenic propellant and keep the propellant at the required working temperature.

[0051] Necessary interfaces are provided on the first container 1 and the second container 2 for connecting the test pipeline 3 and other auxiliary devices, such as a pressurization pipeline and the monitoring module 4, etc.

[0052] The first container 1 and the second container 2 are connected through the test pipeline 3, and the monitoring module 4 is provided on both the first container 1, the second container 2, and the test pipeline 3.

[0053] When the first container 1 serves as a supply container, it is responsible for providing cryogenic propellant to the second container 2 (which serves as a receiving container at this time). During this period, the propellant in the first container 1 will be transferred to the second container 2 through the test pipeline 3, and this process will be closely monitored by the monitoring module 4.

[0054] When the second container 2 serves as a supply container, its role is interchanged with that of the first container 1. At this time, 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.

[0055] The monitoring module 4 is installed on both the first container 1, the second container 2, and the test pipeline 3, which can real-time monitor key parameters such as temperature, pressure, flow rate, and liquid level height. These data are crucial for evaluating the state of the propellant and ensuring the safety of the test.

[0056] Before the start of the test, 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 the receiving container. Test process: During the transfer of the 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.

[0057] 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 the supply container, the second container 2 is the receiving container; when the second container 2 is the supply container, the first container 1 is the receiving container. The first container 1 and the second container 2 are designed to be interchangeable, which means they have the same structural and functional characteristics and can flexibly switch roles as the supply container or the receiving container according to different stages of the test.

[0058] In the cryogenic propellant comprehensive test device, the container pressurization pipeline 6, as one of the core subsystems, undertakes the key tasks of pressure regulation, propellant flow drive, and high-pressure working condition simulation. By connecting two independent container pressurization pipelines 6 to the first container 1 and the second container 2 respectively, combined with the pressurization container 10, control valves, and the monitoring module 4, precise control of the pressure inside the container during the test is achieved.

[0059] The container pressurization pipeline 5 is composed of two completely independent pipelines, which are respectively connected to the inlet ends of the first container 1 and the second container 2. One end of each pipeline is fixedly connected to the corresponding container, and the other end is connected to the pressurization container 10. The container pressurization pipeline 5 is made of low-temperature and high-pressure resistant materials (such as 316L stainless steel or Inconel alloy) to ensure stability in extreme environments such as liquid hydrogen (-253 °C) or liquid oxygen (-183 °C). Flange or clamp sealing structures are usually used at the joints, supplemented with metal wound gaskets or low-temperature special sealants to prevent gas or propellant leakage.

[0060] The container pressurization pipeline 6 is a special pipeline system used to introduce cryogenic propellant or pressurized gas into the first container 1 and the second container 2 to increase the pressure inside the container, thereby promoting the flow of cryogenic propellant or simulating the behavior of the propellant under high-pressure conditions. A container pressurization pipeline 6 is respectively 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 the supply container, the pressurization pipeline 6 on the second container 2 is used for pressure relief; when the second container 1 is the supply container, the pressurization pipeline 6 on the first container 2 is used for pressure relief.

[0061] By pressurizing the first container 1 and the second container 2, the flow of cryogenic propellant can be promoted to ensure that the propellant can smoothly transfer 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 a rocket engine combustion chamber. The container pressurization pipeline 6 can help achieve this goal. By precisely controlling the pressure inside the container, the accuracy of the test can be improved to ensure more reliable test results.

[0062] The pressurizing gas is usually an inert gas, such as nitrogen or helium, to avoid reacting with the cryogenic propellant, or it can also be additional cryogenic propellant. The pressurization pipeline is connected to a pressurizing container, which can be a compressor or a gas storage tank, for providing the required pressurizing gas. Control valves are provided on the container pressurization pipeline 6 for regulating the gas flow rate and pressure entering the container. A monitoring module 4 should also be provided on the container pressurization pipeline 6 for monitoring the pressure and flow rate of the pressurizing gas to ensure the stability of the pressure inside the container.

[0063] When it is necessary to transfer the propellant from one container to another, pressurizing gas can be injected into the supply container, and the pressure difference is used to drive the flow of the propellant. When simulating the high-pressure environment in a rocket engine combustion chamber, high-pressure gas can be injected into the container through the pressurization pipeline to simulate the actual working conditions. By pressurizing the container and monitoring the pressure change within a certain period of time, the tightness of the container and the pipeline system can also be checked.

[0064] 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 are arranged in a geometric or arithmetic sequence, which can be that the diameters gradually increase or gradually decrease.

[0065] The test pipeline 3 is composed of a series of sub-test pipelines 31, and each sub-test pipeline 31 is an independent pipe segment, which are connected in a certain order in sequence to form the complete test pipeline 3. The diameters of the respective sub-test pipelines 31 can gradually increase or gradually decrease according to a specific design pattern. This change can simulate various pipeline conditions encountered by the propellant during actual use, such as nozzles, diffusers, or narrow channels, etc.

[0066] By changing the pipe diameter, the flow characteristics of the propellant in pipelines with 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 velocity, pressure drop, and turbulence degree, etc. By testing the performance of the propellant under different pipe diameters, data support can be provided for the design of rocket engines to help optimize the performance and efficiency of the engines.

[0067] If the pipe diameter gradually increases, the flow of the propellant in the diffuser can be simulated. For example, the pressure recovery and turbulent characteristics of the propellant can be studied. If the pipe diameter gradually decreases, the flow of the propellant in the nozzle can be simulated. For example, the injection characteristics of the propellant, such as the injection angle, injection velocity, etc. By combining the changes in different pipe diameters, more complex flow conditions can be simulated, such as the flow of the propellant in the combustion chamber of a rocket engine.

[0068] The through-diameter of the sub-test pipeline 31 covers common nominal through-diameters.

[0069] Adjacent sub-test pipelines 31 can be connected by elbows, flanges or other connectors to ensure that the fluid flows smoothly through the entire test pipeline 3.

[0070] At least one two-way sealing valve 5 can be set on each sub-test pipeline 31 to control the flow direction and velocity of the propellant, so as to facilitate more refined test control. The two-way sealing valve 5 adopts a pneumatic mode and has the ability to adjust its opening and closing speed through the supply air pressure or supply air velocity, so as to simulate different water hammer pressures.

[0071] In the cryogenic propellant comprehensive test device, the structure and layout of the test pipeline 3 are crucial for simulating the actual flow characteristics of the propellant. In this embodiment, the test pipeline 3 is composed of a plurality of sub-test pipelines 31 connected in series, and its layout covers at least one of the vertical, horizontal or inclined forms, and adjacent sub-test pipelines 31 are connected by elbows. The following elaborates on this technical solution in detail from three aspects: design principle, function realization and practical application.

[0072] 1. Layout of the sub-test pipeline 31 and simulation of fluid characteristics

[0073] The layout form of the sub-test pipeline 31 is directly related to the simulation accuracy of the propellant flow state. According to the test requirements, the pipeline can be designed in a vertical, horizontal or inclined form, or even a combination of multiple directions to reproduce complex flow paths. For example:

[0074] Vertical layout: The sub-test pipelines 31 are arranged in the vertical direction, which can simulate the vertical transportation path of the propellant from the fuel tank to the combustion chamber in a rocket engine. The flow in the vertical direction needs to overcome the influence of gravity, and this design can effectively test the flow velocity stability, liquid level fluctuation and gas-liquid two-phase distribution characteristics of the propellant under the action of gravity.

[0075] Horizontal layout: It is suitable for simulating the parallel transmission scenario between ground transportation pipelines or storage tanks, and can study the pressure gradient, turbulent intensity and phase change behavior of the propellant in horizontal flow.

[0076] Inclined arrangement: By setting a specific inclination angle (such as 30°, 45°, or 60°), the flow characteristics of the propellant during the inclined flight stage of the rocket body can be simulated, or the sealing performance and shock resistance of the pipeline at non-standard angles can be verified.

[0077] 2. Design advantages and functional realization of elbow connection

[0078] Adjacent sub-test pipelines 31 are connected by elbows, and its core function is to simulate the change in the flow behavior of the propellant due to pipeline turning in actual applications. Specific design features include:

[0079] Flow path simulation: Elbows usually use standard angles of 90° or 45°, which can reproduce the flow turning at key parts such as the inlet of the rocket engine combustion chamber and the fuel distribution manifold. By adjusting the elbow curvature radius (such as short-radius or long-radius elbows), the local pressure loss, vortex generation, and phase separation phenomena of the propellant in sharp-turn and gentle-turn regions can be further studied.

[0080] Structural compatibility: The elbows and sub-test pipelines 31 are connected by flanges or welding to ensure that the interface sealing performance meets the requirements of low-temperature and high-pressure working conditions. Flange connection also supports quick disassembly, facilitating the replacement of elbows at different angles to adapt to diverse test requirements.

[0081] Flow resistance optimization: When the vertically arranged sub-test pipeline 31 changes direction through an elbow, its streamlined inner wall design can reduce the generation of turbulence and lower the flow resistance, thus being closer to the optimized pipeline system in actual engineering.

[0082] 3. Actual application scenarios and test verification

[0083] Taking the vertically arranged sub-test pipeline 31 as an example, when simulating the vertical filling process of the rocket engine, the test device realizes function verification through the following steps:

[0084] Flow initialization: The first container 1 serves as the supply container. After internal pressurization, the propellant flows through the sub-test pipeline 31 to the second container 2. The monitoring module 4 real-time collects flow rate, pressure, and temperature data to analyze the flow stability under gravity drive.

[0085] Elbow effect test: When the propellant flows through the elbow, a high-speed camera and a pressure sensor synchronously record the flow field pattern and local pressure fluctuations to evaluate whether cavitation or water hammer phenomena occur at the elbow.

[0086] Multi-condition comparison: By replacing elbows at different angles or adjusting the pipeline inclination angle, repeating the test to obtain multiple groups of data, establishing a flow model of the propellant under different turning conditions, and providing a basis for the design of the engine pipeline.

[0087] 4. Technical expansion and safety guarantee

[0088] Material selection: The sub-test pipeline 31 and elbows are made of austenitic stainless steel or nickel-based alloy to ensure toughness and sealing performance at extreme low temperatures such as liquid hydrogen (-253 °C) or liquid oxygen (-183 °C).

[0089] Redundant design: A strain detection module is added at the key elbow joints to monitor the deformation of the pipeline in real time and prevent structural failure caused by low-temperature shrinkage or pressure shock.

[0090] Dynamic adjustment: Combining with the pneumatic control function of the two-way seal valve 5, the transient flow changes at the elbows are simulated by adjusting the valve opening and closing speed to further refine the water hammer pressure test scenario.

[0091] As Figure 2 shown, in another embodiment, a pressure relief buffer container 7 is further 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, preventing 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 operators. The pressure relief buffer container 7 can also play a buffering role, absorbing sudden pressure fluctuations and reducing 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 key positions of the test pipeline 3, such as near the outlet of the container or in the high-pressure area of the test pipeline 3. By adding the pressure relief buffer container 7 to the cryogenic propellant comprehensive test device, the safety of the test can be greatly improved, and it is ensured that measures can be taken quickly in case of abnormal situations to prevent potential risks.

[0092] The connecting pipeline 8 is composed of a female connecting pipeline 81 and multiple sub-connecting pipelines 82. One end of each sub-connecting pipeline 82 communicates with the middle part of a sub-test pipeline 31, the other ends of the multiple sub-connecting pipelines 82 are connected to one end of the female connecting pipeline 81, and the other end of the female connecting pipeline 81 is connected to the pressure relief buffer container 7. The sub-connecting pipeline 82 is a branch pipe led out from the middle part of each sub-test pipeline 31. One end of each sub-connecting pipeline 82 is connected to the middle part of a sub-test pipeline 31, and the other end is connected to the female connecting pipeline 81. One end of each sub-connecting pipeline 82 is connected to the middle part 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 female connecting pipeline 81 is a main pipeline, which is used to collect the fluid from multiple sub-connecting pipelines 82 and finally guide it to the pressure relief buffer container 7.

[0093] 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, or rather, the volume of the pressure relief buffer container 7 is such that it can accommodate the total amount of propellant discharged from 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 propellant in the first container 1 and the second container 2 needs to be released into the pressure relief buffer container 7, the container has sufficient capacity to hold this propellant, thus avoiding overflow and potential safety risks. Usually, a certain safety margin is left in the volume of the pressure relief buffer container 7 to cope with unexpected situations or calculation errors. In addition, a safety valve is also provided on the pressure relief buffer container 7 itself, which can quickly discharge when overpressure occurs.

[0094] It also includes a controller; a shut-off valve 9 is provided 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 a preset value, the shut-off valve 9 is controlled to open.

[0095] The controller is an electronic device used to receive data from the monitoring module 4 and make corresponding control decisions based on this data. In this embodiment, the controller is connected to the monitoring module 4 and the shut-off valve 9.

[0096] The monitoring module 4 includes at least one of the following: a temperature detection module, a pressure detection module, a flow detection module, a liquid level detection module. These modules are used to monitor the key parameters in the test pipeline 3 in real time.

[0097] Among them, the pressure detection module has the characteristic of high-speed acquisition, and the sampling frequency is greater than 5 kHz. Optionally, a vibration detection module, a strain detection module, a gas leakage detection module, and a sound pressure detection module can also be configured.

[0098] The shut-off valve 9 is installed on the connecting pipeline 8 and is used to control the flow of propellant or gas.

[0099] When the test data (such as temperature, pressure, flow rate, 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 rate in the test pipeline 3 and prevent safety accidents from occurring.

[0100] The controller communicates with the monitoring module 4 and the shut-off valve 9 via 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 of the test and safety standards and are used to trigger the actions of the controller. These preset values are usually set by the operator or engineer before the test. In case of 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.

[0101] 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.

[0102] If an abnormal increase in temperature is detected, the controller will also control the shut-off valve 9 to open to avoid safety problems caused by excessive temperature.

[0103] 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.

[0104] Specifically, a shut-off valve 9 is provided on the main connection pipeline 81. The shut-off valve 9 is arranged on the main connection pipeline 81 at the position between the convergence of multiple sub-connection pipelines 82 and the pressure relief buffer container 7. Arranging the shut-off valve 9 on the main connection pipeline 81 means that the fluid from 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, simplifying the design of the control system. By centrally arranging the shut-off valve 9 on the main 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 at the position between the convergence of multiple sub-connection pipelines 82 and the pressure relief buffer container 7, which can ensure that all fluids can safely enter the pressure relief buffer container 7, avoiding fluid leakage 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 main connection pipeline 81, without modifying or adding shut-off valves 9, which makes the system easier to expand.

[0105] Among them, the shut-off valve 9 includes a gate valve, a globe valve, a ball valve and a butterfly valve. Since the controller is required to control the opening or closing of the shut-off valve 9, an electromagnetic shut-off valve 9 needs to be selected.

[0106] In the embodiments of the present invention, the term "a plurality of" refers to two or more, unless otherwise clearly defined. Terms such as "installed", "connected", "fixed", etc. shall be understood in a broad sense. For example, "connected" 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.

[0107] In the description of the embodiments of the present invention, it should be understood that the orientation or positional relationship indicated by terms such as "upper", "lower", etc. is based on the orientation or positional relationship shown in the drawings. It is 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 should not be construed as a limitation to the embodiments of the present invention.

[0108] In the description of this specification, the description of terms such as "an embodiment", "a preferred embodiment", etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the embodiments of the present invention. In this specification, the schematic representations of the above terms do 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.

[0109] The above are only the preferred embodiments of the embodiments of the present invention and are not used to limit the embodiments of the present invention. For those skilled in the art, the embodiments of the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the embodiments of the present invention shall be included within the protection scope of the embodiments of the present invention.

Claims

1. A comprehensive test device for cryogenic propellants, characterized in that, Comprising: 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 through the test pipeline (3); The monitoring module (4) is provided on the first container (1), the second container (2), and the test pipeline (3).

2. The integrated test device for cryogenic propellants according to claim 1, wherein The first container (1) and the second container (2) are the same and can interchange roles; 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. The comprehensive test device for cryogenic propellants according to claim 1 or 2, characterized in that 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) are arranged in a geometric or arithmetic sequence.

4. The integrated test device for cryogenic propellants according to claim 3, wherein, The arrangement mode of the plurality of sub-test pipelines (31) includes at least one of vertical, horizontal, or inclined forms, and two adjacent sub-test pipelines (31) are connected by elbows.

5. The comprehensive test device for cryogenic propellants according to claim 3 or 4, characterized in that, Two adjacent sub-test pipelines (31) are connected by flanges.

6. The integrated test device for cryogenic propellants according to claim 3, wherein, At least one two-way sealing valve (5) is provided on each sub-test pipeline (31).

7. The integrated test device for cryogenic propellants according to claim 6, characterized in that, The two-way sealing valve (5) adopts a pneumatic mode and has the ability to adjust its opening and closing speed through the supply air pressure or supply air speed to simulate different water hammer pressures.

8. A comprehensive test device for cryogenic propellants according to claim 1, characterized in that It also includes two sets of independent container pressurization pipelines (6); The inlets of the first container (1) and the second container (2) are respectively connected to one end of a container pressurization pipeline (6), and the other end of each container pressurization pipeline (6) is connected to a pressurization container (10); 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.

9. The comprehensive test device for cryogenic propellants according to claim 1, wherein It also includes a pressure relief buffer container (7); The test pipeline (3) is connected to the pressure relief buffer container (7) through a connection pipeline (8); The volume of the pressure relief buffer container (7) is capable of accommodating the total discharge amount of the propellants in the first container (1) and the second container (2).

10. The integrated test device for cryogenic propellants according to claim 9, wherein It also includes a controller; A shut-off valve (9) is provided on the connection 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 a preset value, the shut-off valve (9) is controlled to open.

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