Ground test system and ground test method

Abstract

The present application provides a ground test system and a ground test method. The ground test system includes a tank system, a pressurized gas system, a propellant pipeline system, and an exhaust system. The propellant pipeline system is constructed to connect between the tank system located above and the liquid rocket engine located below. The exhaust system is connected to the propellant pipeline system through a pipeline and is used to open the propellant discharge channel of the exhaust system before the ignition stage, so that the difference between the discharge flow rate of the propellant of the exhaust system and the target propellant flow rate of the liquid rocket engine is less than a preset threshold, so that the pressure of the propellant at the inlet of the liquid rocket engine reaches the required inlet pressure range. During the ignition stage, the propellant discharge channel of the exhaust system is closed, the main propellant pipeline of the liquid rocket engine is opened, and ignition is performed. The present application can reduce the risk of excessive ignition shock or ignition failure under rated operating conditions.

Description

Technical Field

[0001] The present application relates to the field of liquid rocket engine testing technology, and more specifically, to a ground testing system and a ground testing method. Background Art

[0002] Liquid rocket engines ignite and burn liquid propellant in the thrust chamber, generating a high-temperature, high-pressure airflow that is ejected from the nozzle at high speed to generate thrust, providing the power required for rockets and spacecraft to fly.

[0003] At the moment of ignition, there is a problem of excessive ignition shock. On the one hand, it can cause the measuring sensor to exceed the range and damage, and on the other hand, it can cause structural damage. Therefore, it is necessary to consider the problem of excessive ignition shock when designing the ground test system of the rocket engine. Summary of the Invention

[0004] In view of the shortcomings of the existing methods, this application proposes a ground test system and a ground test method to solve the technical problem of excessive ignition shock in related technologies.

[0005] In a first aspect, an embodiment of the present application provides a ground test system for a liquid rocket engine, comprising:

[0006] Tank systems for storing and supplying propellant;

[0007] a pressurized gas system connected to the tank system through a pipeline, and configured to pressurize the propellant to a target tank pressure so that the propellant can flow by overcoming a pressure equivalent to the flow resistance of the ground test system;

[0008] a propellant piping system configured to be connected between the tank system located above and the liquid rocket engine located below;

[0009] an exhaust system connected to the propellant piping system via a pipeline, and configured to, before the ignition phase, open a propellant discharge channel of the exhaust system so that the difference between the propellant discharge flow rate of the exhaust system and the target propellant flow rate of the liquid rocket engine is less than a preset threshold value, thereby ensuring that the propellant pressure at the inlet of the liquid rocket engine reaches within the required inlet pressure range; and, during the ignition phase, close the propellant discharge channel of the exhaust system, open the main propellant pipeline of the liquid rocket engine, and perform ignition.

[0010] In some embodiments, the liquid rocket engine includes a liquid oxygen main line pipeline, a liquid oxygen main line valve provided on the liquid oxygen main line pipeline, and a fuel main line pipeline, a fuel main line valve provided on the fuel main line pipeline;

[0011] The discharge system includes a liquid oxygen branch pipeline, a liquid oxygen branch valve, a liquid oxygen branch orifice plate, a fuel branch pipeline, a fuel branch valve and a fuel branch orifice plate. The liquid oxygen branch valve and the liquid oxygen branch orifice plate are arranged on the liquid oxygen branch pipeline, and the fuel branch valve and the fuel branch orifice plate are arranged on the fuel branch pipeline. The liquid oxygen branch pipeline and the liquid oxygen main pipeline are constructed to be connected to the liquid oxygen outlet of the tank system, and the fuel branch pipeline and the fuel main pipeline are constructed to be connected to the fuel outlet of the tank system.

[0012] In some embodiments, the ground test system further comprises:

[0013] a temperature sensor, provided at the inlet of the liquid oxygen main pipeline, for detecting the oxygen inlet temperature of the liquid oxygen main pipeline;

[0014] A control system is constructed to be electrically connected to the temperature sensor, the tank system, the propellant piping system, the exhaust system, and the liquid rocket engine, and is used to control the liquid oxygen valve and liquid oxygen exhaust valve of the tank system, the primary valve of the propellant piping system, the liquid oxygen branch valve of the exhaust system, and the pre-cooling discharge valve of the liquid rocket engine to be open during the pre-cooling stage before ignition, until the oxygen inlet temperature of the liquid oxygen main pipeline of the liquid rocket engine meets the inlet requirement, and then close the liquid oxygen branch valve of the exhaust system.

[0015] In some embodiments, the tank system includes a liquid oxygen tank and an exhaust valve provided on the liquid oxygen tank;

[0016] The propellant pipeline system includes a liquid oxygen pipeline configured to be connected between the liquid oxygen tank and a liquid oxygen main pipeline of the liquid rocket engine, and a primary valve provided on the liquid oxygen pipeline.

[0017] In some embodiments, the ground test system further comprises:

[0018] a control system electrically connected to the valve of the pressurized air system and configured to control the solenoid valve of the pressurized air system to increase the tank pressure of the tank system to a target tank pressure; the target tank pressure being determined based on the required inlet pressure of the liquid rocket engine, the flow resistance of the propellant piping system, and the hydraulic pressure difference of the propellant between the tank system and the liquid rocket engine.

[0019] In some embodiments, the pressurized gas system includes a high-pressure gas cylinder, a connecting pipe connecting the high-pressure gas cylinder and the tank system, and a solenoid valve and a pressurized orifice plate provided on the connecting pipe;

[0020] The pressurizing orifice plate includes at least two holes with different diameters, and the diameter of each hole corresponds to the tank pressure level of the tank system.

[0021] In some embodiments, the ground test system further comprises:

[0022] a pressure sensor, provided at the inlet of the liquid rocket engine, for detecting the inlet pressure value of the liquid rocket engine;

[0023] A control system is electrically connected to the pressure sensor and the exhaust system, and is used to control the valve of the exhaust system to open when the inlet pressure value of the liquid rocket engine exceeds a preset pressure value; the preset pressure value is greater than the required inlet pressure.

[0024] In some embodiments, the ground test system also includes a control system, which is electrically connected to the exhaust system and the liquid rocket engine, and is used to close the liquid oxygen main valve of the liquid rocket engine on the basis of opening the liquid oxygen branch valve of the exhaust system during the shutdown phase.

[0025] In a second aspect, an embodiment of the present application provides a ground test method, which is applied to the above-mentioned ground test system, including:

[0026] During the pre-processing phase, the propellant discharge channel of the discharge system is opened so that the difference between the discharge flow rate of the propellant of the discharge system and the target flow rate of the propellant of the liquid rocket engine is less than a preset threshold value, thereby at least partially offsetting the flow resistance equivalent pressure and allowing the propellant at the inlet of the liquid rocket engine to approach or reach the required inlet pressure;

[0027] During the ignition phase, the propellant main pipeline of the liquid rocket engine is opened on the basis of closing the propellant discharge channel of the exhaust system.

[0028] In some embodiments, the ground testing method further comprises:

[0029] During the shutdown phase, after the auxiliary system of the liquid rocket engine is shut down, the liquid oxygen main valve of the liquid rocket engine is closed on the basis of opening the liquid oxygen branch valve of the exhaust system.

[0030] The beneficial technical effects brought about by the technical solutions provided in the embodiments of the present application include:

[0031] Pre-pressurization is achieved through the boost gas system, allowing the propellant to overcome the equivalent pressure of the flow resistance of the ground test system and flow normally, avoiding propellant flow problems. Before the ignition phase, the exhaust system is opened to release (outflow) the propellant. The propellant pressure decreases with the partial release, at least partially offsetting the effects of the process system's flow resistance, keeping the propellant pressure at the liquid rocket engine inlet near the required inlet pressure. Furthermore, because the propellant discharge flow rate from the exhaust system is equivalent to the target propellant flow rate of the liquid rocket engine, by first closing the exhaust system valve and then opening the main valve of the liquid rocket engine, the inlet pressure at ignition can be maintained near the required inlet pressure. This not only meets the pressure requirements for rocket ignition, but also reduces the ignition shock in the thrust chamber, maximizing the simulation of on-rocket ignition conditions.

[0032] Additional aspects and advantages of the present application will be given in part in the following description, which will become apparent from the following description, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0034] Figure 1 A schematic diagram of a framework of a ground test system provided in an embodiment of the present application;

[0035] Figure 2 A schematic diagram of the operation of an exhaust system of a ground test system provided in an embodiment of the present application;

[0036] Figure 3 A flow chart of a ground test method provided in an embodiment of the present application.

[0037] Description of reference numerals:

[0038] 100-Ground test system;

[0039] 11- Tank system;

[0040] 12-Booster gas system;

[0041] 13-Propellant piping system;

[0042] 14- exhaust system; 142- liquid oxygen branch orifice plate; 141- fuel branch orifice plate; 143- liquid oxygen collection container; 144- fuel collection container;

[0043] 15-Control system;

[0044] 16- Measurement system;

[0045] 200-Liquid rocket engine; 21-Liquid oxygen main path orifice plate; 22-Fuel main path orifice plate. DETAILED DESCRIPTION

[0046] The following describes the embodiments of the present application in conjunction with the accompanying drawings. It should be understood that the embodiments described below in conjunction with the accompanying drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0047] Those skilled in the art will understand that, unless otherwise stated, the terms "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of this application refers to the presence of the integers, elements and / or components, but does not exclude the implementation of other features, information, data, steps, operations, elements, components and / or their combinations supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" can be implemented as "A", or as "B", or as "A and B".

[0048] In order to make the objectives, technical solutions and advantages of this application clearer, the implementation methods of this application will be further described in detail below with reference to the accompanying drawings.

[0049] Liquid rocket engines typically undergo ground testing before they are put into actual operation. Ground testing is the primary means of verifying the product design and production process of liquid rocket engines. This includes determining the structural state of components, verifying system timing adjustment methods, and examining product performance.

[0050] The ground test system of the liquid rocket engine provides propellant that meets the pressure, temperature and flow requirements to the engine inlet through a pressurized delivery system, performs ignition tests according to a given timing through a control system, and finally obtains test data from measurement points on the engine through a measurement system.

[0051] In the prior art, for liquid rocket engines, the thrust chamber is typically ignited at tank pressure. This is followed by a timed sequence of turbopump spin-up, gas generator relay, and thrust chamber stage change, ultimately leading to shutdown. Ground-based propellant delivery systems typically have a much greater flow resistance than onboard booster delivery systems (the sum of the booster delivery system's longitudinal and local flow resistances, which is proportional to the square of the flow rate). Consequently, the inlet pressure of a liquid rocket engine is higher than the required inlet pressure before thrust chamber ignition. The greater the process system's flow resistance, the greater the difference between the inlet pressure and the required inlet pressure of the liquid rocket engine, resulting in a significant ignition shock within the thrust chamber at the moment of ignition. Excessive ignition shock can cause measurement sensors to exceed their range and potentially damage the structure. Therefore, it is important to consider the issue of excessive ignition shock when designing ground test systems.

[0052] Furthermore, ground-based testing of the system required meeting the inlet temperature requirements of liquid rocket engines. In related technologies, liquid rocket engines are typically pre-cooled and discharged through a pre-cooling drain, typically located on the outlet branch of the oxygen circuit venturi in the liquid rocket engine's auxiliary system. Due to the low flow rate in the liquid rocket engine's auxiliary system, the venturi in these systems is typically small, resulting in a long pre-cooling time. Therefore, shortening the oxygen circuit pre-cooling time was a technical challenge that needed to be addressed.

[0053] In addition, when the main valve of a liquid rocket engine is shut down unexpectedly, the inlet pressure of the liquid rocket engine will increase abnormally, thereby affecting the safety of the test bench. This is also a problem that needs to be solved.

[0054] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above-mentioned technical problems with specific embodiments. It should be noted that the following embodiments can refer to, draw on, or combine with each other, and the same terms, similar features, and similar implementation steps in different embodiments will not be repeated.

[0055] The present application embodiment provides a ground test system for liquid rocket engines, such as Figure 1 As shown, the ground test system 100 includes a tank system 11 , a pressurized gas system 12 , a propellant piping system 13 and an exhaust system 14 .

[0056] The tank system 11 is used to store and supply propellant.

[0057] The pressurized gas system 12 is connected to the tank system 11 through a pipeline, and is used to pressurize the propellant to a target tank pressure so that the propellant can flow at a pressure equivalent to the flow resistance of the ground test system 100 .

[0058] The propellant piping system 13 is configured to be connected between the tank system 11 located above and the liquid rocket engine 200 located below.

[0059] The exhaust system 14 is connected to the propellant piping system 13 through a pipeline, and is used to open the propellant discharge channel of the exhaust system 14 before the ignition stage, so that the difference between the propellant discharge flow rate of the exhaust system 14 and the propellant target flow rate of the liquid rocket engine 200 is less than a preset threshold value, so that the propellant pressure at the inlet of the liquid rocket engine 200 reaches the required inlet pressure range; during the ignition stage, the propellant discharge channel of the exhaust system 14 is closed, the propellant main pipeline of the liquid rocket engine 200 is opened, and ignition is performed.

[0060] Pre-pressurization is achieved through the pressurized gas system 12, allowing the propellant to overcome the equivalent pressure of the flow resistance of the ground test system and flow normally, thus preventing propellant flow obstruction. Prior to the ignition phase, the exhaust system is opened to release (outflow) the propellant. The propellant pressure decreases with the partial release, at least partially offsetting the effects of the process system's flow resistance, thereby controlling the propellant pressure at the inlet of the liquid rocket engine 200 near the desired inlet pressure. Furthermore, because the propellant discharge flow rate from the exhaust system 14 is comparable to the target propellant flow rate of the liquid rocket engine 200, by first closing the valve of the exhaust system 14 and then opening the main valve of the liquid rocket engine 200, the inlet pressure during ignition can be maintained near the desired inlet pressure. This not only meets the pressure requirements for rocket ignition, but also reduces the ignition shock in the thrust chamber, maximizing the simulation of on-rocket ignition conditions.

[0061] Since the propellant piping system 13 is constructed to be connected between the tank system 11 located above and the liquid rocket engine 200 located below, that is, the propellant piping system 13 is designed to have an overall downward slope from the bottom of the tank to the inlet of the liquid rocket engine 200, it can ensure that the gas in the pipeline of the propellant piping system 13 during the pre-cooling process can freely flow upward and be discharged through the exhaust valve on the tank.

[0062] It should be noted that Figure 1 The connection of the liquid circuit is represented by a solid line, that is, the solid line represents the connection through the pipeline; the connection of the circuit is represented by a dot-dashed line, that is, the dot-dashed line represents the electrical connection or communication connection.

[0063] See also Figure 2 In some embodiments, the liquid rocket engine 200 includes a liquid oxygen main pipeline, a liquid oxygen main valve Y provided on the liquid oxygen main pipeline, a fuel main pipeline, and a fuel main valve R provided on the fuel main pipeline.

[0064] The discharge system 14 includes a liquid oxygen branch pipeline, a liquid oxygen branch valve Y1, a liquid oxygen branch orifice plate 142, a fuel branch pipeline, a fuel branch valve R1 and a fuel branch orifice plate 141. The liquid oxygen branch valve Y1 and the liquid oxygen branch orifice plate 142 are arranged on the liquid oxygen branch pipeline, and the fuel branch valve R1 and the fuel branch orifice plate 141 are arranged on the fuel branch pipeline. The liquid oxygen branch pipeline and the liquid oxygen main pipeline are constructed to be connected to the liquid oxygen outlet of the tank system 11, and the fuel branch pipeline and the fuel main pipeline are constructed to be connected to the fuel outlet of the tank system 11.

[0065] The flow rate of liquid oxygen discharged through the liquid oxygen branch valve Y1 is adjusted by the liquid oxygen branch orifice plate 142 , and the flow rate of fuel discharged through the fuel branch valve R1 is adjusted by the fuel branch orifice plate 141 .

[0066] Before the ignition stage, open the liquid oxygen branch valve Y1 and the fuel branch valve R1, and adjust the liquid oxygen branch orifice plate 142 and the fuel branch orifice plate 141 so that the difference between the flow in the oxygen branch pipeline and the flow in the oxygen main pipeline is less than a preset threshold, and the difference between the flow in the fuel branch pipeline and the flow in the fuel main pipeline is less than a preset threshold; and, in the ignition stage, before opening the oxygen main valve Y and the fuel main valve R, close the oxygen branch valve Y1 and the fuel branch valve R1.

[0067] It should be noted that by adjusting the liquid oxygen branch orifice plate 142 and the fuel branch orifice plate 141, the flow rates within the oxygen branch pipeline and the flow rate within the main oxygen pipeline can be adjusted, respectively, thereby adapting to different operating conditions and achieving more accurate simulation of rocket operating conditions. Furthermore, by configuring the liquid oxygen branch orifice plate 142 and the fuel branch orifice plate 141, the exhaust system 14 can adapt to a variety of ignition conditions, thereby simulating the ignition conditions of different rocket engines, and achieving greater versatility.

[0068] Continue to see Figure 2 In some embodiments, the ground test system 100 further includes a liquid oxygen collection container 143 disposed at the end of the liquid oxygen branch pipeline, and a fuel collection container 144 disposed at the end of the fuel branch pipeline.

[0069] In practical applications, the liquid rocket engine 200 may further include a main liquid oxygen orifice plate 21 disposed on the main liquid oxygen pipeline, and a main fuel orifice plate 22 disposed on the main fuel pipeline, which cooperate with the branch liquid oxygen orifice plate 142 and the branch fuel orifice plate 141, respectively. The main liquid oxygen orifice plate 21 regulates the flow of liquid oxygen into the thrust chamber of the liquid rocket engine 200, while the main fuel orifice plate 22 regulates the flow of fuel into the thrust chamber of the liquid rocket engine 200.

[0070] See also Figure 1 In some embodiments, the ground test system 100 further includes a temperature sensor (corresponding to the measurement system 16 ) and a control system 15 .

[0071] The temperature sensor is installed at the inlet of the liquid oxygen main pipeline and is used to detect the oxygen inlet temperature of the liquid oxygen main pipeline.

[0072] The control system 15 is constructed to be electrically connected to the temperature sensor, the tank system 11, the propellant piping system 13, the exhaust system 14 and the liquid rocket engine 200. It is used to control the liquid oxygen valve and liquid oxygen exhaust valve of the tank system 11, the primary valve of the propellant piping system 13, the liquid oxygen branch valve Y1 of the exhaust system 14, and the pre-cooling discharge valve of the liquid rocket engine 200 to be open during the pre-cooling stage before ignition, until the oxygen inlet temperature of the liquid oxygen main pipeline of the liquid rocket engine 200 meets the inlet requirement, and then the liquid oxygen branch valve Y1 of the exhaust system 14 is closed.

[0073] Liquid oxygen from the tank system 11 flows through the piping of the entire ground test system 100 (sequentially passing through the liquid oxygen valve and the primary valve) and is discharged through the liquid oxygen branch valve Y1 of the exhaust system 14 and the pre-cooling discharge valve of the liquid rocket engine 200, thereby achieving cooling of the oxygen circuit. In other words, coordinated discharge through the exhaust system 14 and the pre-cooling discharge of the liquid rocket engine 200 accelerates pre-cooling and shortens pre-cooling time.

[0074] It should be noted that, for the fuel path, the exhaust system 14 can also be used to coordinate the exhaust of the pre-cooling discharge path of the liquid rocket engine 200, which will not be described in detail here.

[0075] In some embodiments, the tank system 11 includes a liquid oxygen tank and an exhaust valve provided on the liquid oxygen tank.

[0076] The propellant piping system 13 includes a liquid oxygen piping configured to be connected between the liquid oxygen tank and the liquid oxygen main pipeline of the liquid rocket engine 200 , and a primary valve provided on the liquid oxygen piping.

[0077] The primary valve of the propellant piping system 13 is used to cut off the liquid oxygen between the liquid oxygen tank and the main liquid oxygen pipeline of the liquid rocket engine 200. The liquid oxygen exhaust valve of the tank system 11 is used to exhaust the liquid oxygen tank to maintain the internal and external pressure balance of the liquid oxygen tank.

[0078] See also Figure 1 In some embodiments, the ground test system 100 further includes a control system 15, which is electrically connected to the valve of the pressurized air system 12 and is used to control the solenoid valve of the pressurized air system 12 to increase the tank pressure of the tank system 11 to a target tank pressure; the target tank pressure is determined based on the required inlet pressure of the liquid rocket engine, the flow resistance of the propellant pipeline system, and the hydraulic pressure difference of the propellant between the tank system and the liquid rocket engine.

[0079] In some embodiments, the target tank pressure = + -P1, where is the required inlet pressure of the liquid rocket engine 200, is the flow resistance of the propellant piping system 13 , and P1 is the hydraulic pressure difference of the propellant between the tank system 11 and the liquid rocket engine 200 .

[0080] During the ground test, the propellant in the propellant pipeline is approximated as an ideal fluid. The Bernoulli equation for the ideal fluid between the tank and the outlet of the propellant pipeline is as follows:

[0081]

[0082] Due to the flow rate in the propellant pipe during ground testing It is generally 5~10m / s. Considering that the cross section of the tank is much larger than that of the propellant pipe, the following formula can be used for approximate estimation in practice:

[0083]

[0084] Among them, ρgH is the aforementioned P1, is the density of the propellant, g is the acceleration due to gravity, It is the height difference from the liquid level in the tank to the outlet of the propellant pipeline.

[0085] In some embodiments, the pressurized gas system 12 includes a high-pressure gas cylinder, a connecting pipe connecting the high-pressure gas cylinder and the tank system 11, and a solenoid valve and a pressurization orifice plate provided on the connecting pipe.

[0086] The pressurization orifice plate includes at least two holes with different diameters, and the diameter of each hole corresponds to the tank pressure level of the tank system 11 .

[0087] High-pressure gas cylinders provide a stable, sufficient gas source for tank pressurization. The pressurization system typically consists of a boost solenoid valve and a boost orifice plate. The boost orifice plate regulates the flow of gas delivered from the high-pressure gas cylinder to the tank system 11. Multiple sets of boost solenoid valves and boost orifice plates are used in parallel to form a boost orifice plate matrix, providing both boost and pressure stabilization for the propellant tanks according to a pre-defined schedule.

[0088] In some embodiments, the tank system 11 includes a fuel tank and a liquid oxygen tank, and the pressurized gas system 12 includes a first gas cylinder and a second gas cylinder. The first gas cylinder is connected to the fuel tank via a first pipeline, and the second gas cylinder is connected to the liquid oxygen tank via a second pipeline. A first pressurizing system is provided on the first pipeline, comprising a fuel orifice plate and a first solenoid valve. A second pressurizing system is provided on the second pipeline, comprising a liquid oxygen orifice plate and a second solenoid valve.

[0089] In some embodiments, the fuel orifice plate includes a plurality of first openings with gradually increasing areas, and the liquid oxygen orifice plate includes a plurality of second openings with gradually increasing areas.

[0090] By aligning multiple first openings in the fuel orifice plate with the fuel pipeline one by one according to the first design sequence, the real-time pressure value of the fuel provided to the liquid rocket engine 200 can be gradually increased from the first pressure value to the rated pressure value of the fuel using the pressurized gas system 12.

[0091] By aligning multiple second openings in the liquid oxygen orifice plate with the liquid oxygen pipeline one by one according to the second design sequence, the real-time pressure value of the liquid oxygen provided to the liquid rocket engine 200 can be gradually increased from the second pressure value to the rated pressure value of the liquid oxygen using the pressurized gas system 12.

[0092] In practical applications, the tank system 11 may further include a first exhaust valve provided on the fuel tank and a second exhaust valve provided on the liquid oxygen tank.

[0093] The propellant piping system 13 includes a delivery pipeline (and accessories), a flowmeter, and a primary valve. The delivery pipeline is capable of delivering propellant at a specific pressure and flow rate to the inlet of the liquid rocket engine 200. The flowmeter measures the propellant flowing in the delivery pipeline in real time, typically in terms of volumetric or mass flow rate. The primary valve, typically a pneumatic valve, shuts off the propellant flow between the ground test system 100 and the liquid rocket engine 200.

[0094] In some embodiments, the ground test system 100 further includes a measurement system 16 and a control system 15. The measurement system 16 is composed of sensors (e.g., temperature sensors, pressure sensors), cables, and an acquisition system, and is used to collect parameters such as pressure, temperature, and vibration of the liquid rocket engine 200. The control system 15 can be composed of a PLC (Programmable Logic Controller) and a host computer, and is used to control the valve operation of the ground test system 100 and complete the valve operation of the liquid rocket engine 200 according to a given time sequence.

[0095] See also Figure 1 In some embodiments, the ground test system 100 further includes a pressure sensor (corresponding to the measurement system 16 ) and a control system 15 .

[0096] The pressure sensor is provided at the inlet of the liquid rocket engine 200 and is used to detect the inlet pressure value of the liquid rocket engine 200 .

[0097] The control system 15 is electrically connected to the pressure sensor and the exhaust system 14, and is used to control the valve of the exhaust system 14 to open when the inlet pressure value of the liquid rocket engine 200 exceeds a preset pressure value; the preset pressure value is greater than the required inlet pressure.

[0098] By establishing an interlocking function between the overpressure relief of the liquid rocket engine 200 and the pneumatic valve of the exhaust system 14, the safety hazard of overpressure on the test bench caused by accidental shutdown of the main valve of the liquid rocket engine 200 can be avoided.

[0099] See also Figure 1 and Figure 2In some embodiments, the ground test system 100 further includes a control system 15, which is electrically connected to the exhaust system 14 and the liquid rocket engine 200, and is configured to close the liquid oxygen main valve Y of the liquid rocket engine 200 while opening the liquid oxygen branch valve Y1 of the exhaust system 14 during the shutdown phase.

[0100] By opening the liquid oxygen branch valve Y1 of the exhaust system 14 in advance during the shutdown phase, the shutdown water hammer of the liquid oxygen main valve Y of the liquid rocket engine 200 can be reduced to a certain extent, thereby extending the service life of the valve of the liquid rocket engine 200.

[0101] The beneficial technical effects brought about by the technical solutions provided in the embodiments of the present application include:

[0102] Pre-pressurization is achieved through the pressurized gas system 12, allowing the propellant to overcome the equivalent pressure of the flow resistance of the ground test system and flow normally, thus preventing propellant flow obstruction. Prior to the ignition phase, the exhaust system is opened to release (outflow) the propellant. The propellant pressure decreases with the partial release, at least partially offsetting the effects of the process system's flow resistance, thereby controlling the propellant pressure at the inlet of the liquid rocket engine 200 near the desired inlet pressure. Furthermore, because the propellant discharge flow rate from the exhaust system 14 is comparable to the target propellant flow rate of the liquid rocket engine 200, by first closing the valve of the exhaust system 14 and then opening the main valve of the liquid rocket engine 200, the inlet pressure during ignition can be maintained near the desired inlet pressure. This not only meets the pressure requirements for rocket ignition, but also reduces the ignition shock in the thrust chamber, maximizing the simulation of on-rocket ignition conditions.

[0103] Liquid oxygen from the tank system 11 flows through the piping of the entire ground test system 100 (sequentially passing through the liquid oxygen valve and the primary valve) and is discharged through the liquid oxygen branch valve Y1 of the exhaust system 14 and the pre-cooling discharge valve of the liquid rocket engine 200, thereby achieving cooling of the oxygen circuit. In other words, coordinated discharge through the exhaust system 14 and the pre-cooling discharge of the liquid rocket engine 200 accelerates pre-cooling and shortens pre-cooling time.

[0104] By establishing an interlocking function between the overpressure relief of the liquid rocket engine 200 and the pneumatic valve of the exhaust system 14, the safety hazard of overpressure on the test bench caused by accidental shutdown of the main valve of the liquid rocket engine 200 can be avoided.

[0105] By opening the liquid oxygen branch valve Y1 of the exhaust system 14 in advance during the shutdown phase, the shutdown water hammer of the liquid oxygen main valve Y of the liquid rocket engine 200 can be reduced to a certain extent, thereby extending the service life of the valve of the liquid rocket engine 200.

[0106] Based on the same inventive concept, the embodiment of the present application provides a ground test method, which is applied to the above-mentioned ground test system, such as Figure 2 As shown, the ground test method includes steps S11 to S12.

[0107] S11: In the pretreatment stage, the propellant discharge channel of the exhaust system is opened so that the difference between the discharge flow rate of the propellant of the exhaust system and the target flow rate of the propellant of the liquid rocket engine is less than a preset threshold value, so as to at least partially offset the flow resistance equivalent pressure, so that the propellant at the inlet of the liquid rocket engine approaches or reaches the required inlet pressure.

[0108] S12: During the ignition phase, the propellant main pipeline of the liquid rocket engine is opened on the basis of closing the propellant discharge channel of the exhaust system.

[0109] By opening the exhaust system to discharge during the pretreatment stage, the discharge flow rate of the exhaust system to the propellant is made equivalent to the target propellant flow rate of the liquid rocket engine, so as to at least partially offset the influence of the flow resistance of the process system, so that the liquid pressure at the inlet of the liquid rocket engine is controlled near the required inlet pressure, thereby reducing the ignition shock of the thrust chamber and simulating the ignition condition on the rocket to the greatest extent.

[0110] See also Figure 2 In some embodiments, the ground test method may further include: during the shutdown phase, after the auxiliary system of the liquid rocket engine is shut down, the liquid oxygen main valve of the liquid rocket engine is closed on the basis of opening the liquid oxygen branch valve of the exhaust system.

[0111] Among them, the auxiliary system of the liquid rocket engine refers to the gas generator of the liquid rocket engine, which is mainly used to generate a certain amount of low-temperature gas to drive the turbine.

[0112] By opening the liquid oxygen branch valve of the exhaust system in advance after the auxiliary system of the liquid rocket engine is shut down, the shutdown water hammer of the liquid oxygen main valve of the liquid rocket engine can be reduced to a certain extent, and the service life of the liquid rocket engine valve can be extended.

[0113] In some embodiments, the ground test method may further include: during at least part of the test phase, when the inlet pressure value of the liquid rocket engine exceeds a preset pressure value, opening the propellant discharge channel of the exhaust system, the preset pressure value being greater than the inlet required pressure.

[0114] When an abnormality occurs in the main circuit of a liquid rocket engine—for example, an abnormal drop in pressure in the main valve control gas circuit, a short circuit or open circuit, or a valve failure causing the valve to abnormally close—while the turbopump is still operating, the inlet pressure of the liquid rocket engine can overpressure, even exceeding the system design pressure (typically 1.6 MPa). By interlocking the liquid rocket engine's overpressure relief with the pneumatic valves in the exhaust system, the safety hazard of test bench overpressure caused by the unexpected shutdown of the liquid rocket engine's main circuit valve can be avoided.

[0115] As an example, the implementation sequence of a ground test system during a ground test may include:

[0116] 1) Oxygen Line Precooling: After the blow-out replacement is complete and the oxygen line dew point meets the precooling requirements, the liquid oxygen valve and exhaust valve of the tank system, the primary valve of the propellant piping system, the liquid oxygen branch valve of the exhaust system, and the precooling relief valve of the liquid rocket engine are all controlled to open, utilizing the hydrostatic pressure within the tank for precooling. Once the oxygen inlet temperature of the liquid oxygen main line of the liquid rocket engine meets the inlet requirements, the liquid oxygen branch valve of the exhaust system is closed.

[0117] The exhaust system is coordinated with the pre-cooling discharge path of the liquid rocket engine to accelerate the pre-cooling speed and shorten the pre-cooling time.

[0118] Nitrogen is typically used as the displacement gas for blow-out replacement. Nitrogen's uses include: 1. Removing flammable gases from pipes or containers. Before use, nitrogen is introduced to displace existing air or other gases to prevent dangerous reactions during subsequent operations. 2. Maintaining system pressure balance. During the precooling process, nitrogen can be used to regulate system pressure and ensure a stable supply of oxidizer and fuel.

[0119] 2) Fuel line filling: Fill the fuel (such as kerosene) and ensure the filling effect of the fuel line by observing the full flow of the outlet of the fuel discharge valve of the liquid rocket engine.

[0120] 3) Pre-pressurization: Use the booster gas system to manually (or automatically) pre-pressurize the tank system to increase the tank pressure to the target tank pressure. .

[0121] Specifically, the tank pressure of the liquid oxygen tank is increased to the target tank pressure of the liquid oxygen. The fuel tank pressure is increased to the target fuel tank pressure. , where the target liquid oxygen tank pressure is , fuel target tank pressure According to the target box pressure The calculation formula is obtained.

[0122] 4) Opening the discharge: Open the liquid oxygen branch valve Y1 and the fuel branch valve R1 of the discharge system for a duration of t, and adjust the first orifice plate provided on the liquid oxygen branch pipeline and the second orifice plate provided on the fuel branch pipeline so that the discharge flow rate of the propellant of the discharge system is equivalent to the target propellant flow rate of the liquid rocket engine. At this time, the inlet pressure of the liquid rocket engine is the required inlet pressure.

[0123] 5) Connecting the main line ignition: According to the debugging sequence, close the liquid oxygen branch valve Y1 and the fuel branch valve R1, and at the same time open the liquid oxygen main line valve Y and the fuel main line valve R, and use the thrust chamber igniter to complete the thrust chamber ignition.

[0124] 6) Carry out the test phases of spin-up (turbine pneumatics, turbo pump pneumatics), auxiliary system relay (gas generator pneumatics, continuing to drive the turbine), thrust chamber stage change (thrust chamber operation to main stage operation), and shutdown in a timed sequence.

[0125] During the shutdown phase, after the auxiliary systems of the liquid rocket engine are shut down, first open the liquid oxygen branch valve Y1, and then close the liquid oxygen main valve Y. This can effectively reduce the shutdown water hammer of the liquid oxygen main valve of the liquid rocket engine and extend the service life of the liquid rocket engine valve.

[0126] This embodiment is an embodiment of a ground test method corresponding to the aforementioned ground test system. Specific technical details and technical effects can be found in the aforementioned embodiments and will not be repeated here.

[0127] Those skilled in the art will appreciate that the steps, measures, and schemes in the various operations, methods, and processes discussed in this application may be interchanged, modified, combined, or deleted. Furthermore, other steps, measures, and schemes in the various operations, methods, and processes discussed in this application may also be interchanged, modified, rearranged, decomposed, combined, or deleted. Furthermore, steps, measures, and schemes in the related art that are similar to those disclosed in this application may also be interchanged, modified, rearranged, decomposed, combined, or deleted.

[0128] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0129] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. Throughout this application, unless otherwise specified, "plurality" means two or more.

[0130] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to direct connections, indirect connections through an intermediate medium, or internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0131] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0132] The above is only part of the implementation methods of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the solution of the present application, other similar implementation methods based on the technical ideas of the present application also fall within the protection scope of the embodiments of the present application.

Claims

1. A ground test system for a liquid rocket engine, comprising a liquid oxygen main line pipeline, a liquid oxygen main line valve provided on the liquid oxygen main line pipeline, and a fuel main line pipeline, a fuel main line valve provided on the fuel main line pipeline, characterized in that: The ground test system includes: Tank systems for storing and supplying propellant; a pressurized gas system connected to the tank system through a pipeline, and configured to pressurize the propellant to a target tank pressure so that the propellant can flow by overcoming a pressure equivalent to the flow resistance of the ground test system; a propellant piping system configured to be connected between the tank system located above and the liquid rocket engine located below; The discharge system is connected to the propellant pipeline system through a pipeline, and the discharge system includes a liquid oxygen branch pipeline, a liquid oxygen branch valve, a liquid oxygen branch orifice plate, a fuel branch pipeline, a fuel branch valve and a fuel branch orifice plate. The liquid oxygen branch valve and the liquid oxygen branch orifice plate are arranged on the liquid oxygen branch pipeline, and the fuel branch valve and the fuel branch orifice plate are arranged on the fuel branch pipeline. The liquid oxygen branch pipeline and the liquid oxygen main pipeline are constructed to be connected to the liquid oxygen outlet of the tank system via the propellant pipeline system. The fuel branch pipeline and the fuel main pipeline are connected to the liquid oxygen outlet of the tank system via the propellant pipeline system. The pipelines are configured to be connected to the fuel outlet of the tank system via the propellant piping system. The discharge system is configured to open the propellant discharge channel of the discharge system before the ignition phase, so that the difference between the discharge flow rate of the propellant of the discharge system and the target propellant flow rate of the liquid rocket engine is less than a preset threshold value, so that the pressure of the propellant at the inlet of the liquid rocket engine reaches within the required inlet pressure range. During the ignition phase, the propellant discharge channel of the discharge system is closed, the main propellant pipeline of the liquid rocket engine is opened, and ignition is performed. A control system is electrically connected to the exhaust system and the liquid rocket engine, and is used to close the liquid oxygen main valve of the liquid rocket engine on the basis of opening the liquid oxygen branch valve of the exhaust system during the shutdown phase.

2. The ground test system according to claim 1, characterized in that: Also includes: a temperature sensor, provided at the inlet of the liquid oxygen main pipeline, for detecting the oxygen inlet temperature of the liquid oxygen main pipeline; A control system is constructed to be electrically connected to the temperature sensor, the tank system, the propellant piping system, the exhaust system, and the liquid rocket engine, and is used to control the liquid oxygen valve and liquid oxygen exhaust valve of the tank system, the primary valve of the propellant piping system, the liquid oxygen branch valve of the exhaust system, and the pre-cooling discharge valve of the liquid rocket engine to be open during the pre-cooling stage before ignition, until the oxygen inlet temperature of the liquid oxygen main pipeline of the liquid rocket engine meets the inlet requirement, and then close the liquid oxygen branch valve of the exhaust system.

3. The ground test system according to claim 2, characterized in that: The tank system includes a liquid oxygen tank and an exhaust valve provided on the liquid oxygen tank; The propellant pipeline system includes a liquid oxygen pipeline configured to be connected between the liquid oxygen tank and a liquid oxygen main pipeline of the liquid rocket engine, and a primary valve provided on the liquid oxygen pipeline.

4. The ground test system according to claim 1, characterized in that: Also includes: a control system electrically connected to the valve of the pressurized gas system and configured to control the solenoid valve of the pressurized gas system to increase the tank pressure of the storage tank system to a target tank pressure; The target tank pressure is determined based on the required inlet pressure of the liquid rocket engine, the flow resistance of the propellant piping system, and the hydraulic pressure difference of the propellant between the tank system and the liquid rocket engine.

5. The ground test system according to claim 4, characterized in that: The pressurized gas system includes a high-pressure gas cylinder, a connecting pipe connecting the high-pressure gas cylinder and the tank system, and a solenoid valve and a pressurized orifice plate provided on the connecting pipe; The pressurizing orifice plate includes at least two holes with different diameters, and the diameter of each hole corresponds to the tank pressure level of the tank system.

6. The ground test system according to claim 1, characterized in that: Also includes: a pressure sensor, provided at the inlet of the liquid rocket engine, for detecting the inlet pressure value of the liquid rocket engine; A control system is electrically connected to the pressure sensor and the exhaust system, and is used to control the valve of the exhaust system to open when the inlet pressure value of the liquid rocket engine exceeds a preset pressure value; the preset pressure value is greater than the required inlet pressure.

7. A ground test method, applied to the ground test system according to any one of claims 1 to 6, characterized in that: include: During the pre-processing phase, the propellant discharge channel of the discharge system is opened so that the difference between the discharge flow rate of the propellant of the discharge system and the target flow rate of the propellant of the liquid rocket engine is less than a preset threshold value, thereby at least partially offsetting the flow resistance equivalent pressure and allowing the propellant at the inlet of the liquid rocket engine to approach or reach the required inlet pressure; During the ignition phase, the propellant main pipeline of the liquid rocket engine is opened after closing the propellant discharge channel of the exhaust system; During the shutdown phase, after the auxiliary system of the liquid rocket engine is shut down, the liquid oxygen main valve of the liquid rocket engine is closed on the basis of opening the liquid oxygen branch valve of the exhaust system.

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