Ground test method and ground test system

Abstract

The present application provides a ground test method and a ground test system. This ground test method is applicable to liquid rocket engines and includes: igniting the liquid rocket engine during the ignition operating condition; the ignition pressure of the propellant provided to the liquid rocket engine during the ignition operating condition is less than the rated pressure; during the dynamic climb phase, gradually increasing the real-time operating condition of the liquid rocket engine from the ignition operating condition to the rated operating condition; and the real-time pressure of the propellant provided to the liquid rocket engine during the rated operating condition is equal to the rated pressure. The present application can obtain relatively complete parameters under the ignition operating condition and the parameters under the rated operating condition, while also avoiding the risk of direct ignition under the rated operating condition, resulting in excessive ignition shock or ignition failure.

Description

Technical Field

[0001] The present application relates to the field of liquid rocket engine testing technology, and more specifically, to a ground testing method and a ground testing system. 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 missiles (rocket) and spacecraft with the power they need 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 be damaged, and on the other hand, it can cause structural damage. Therefore, it is necessary to consider the problem of excessive ignition shock when conducting ground tests. Summary of the Invention

[0004] In view of the shortcomings of the existing methods, this application proposes a ground test method and a ground test system 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 method applicable to a liquid rocket engine, comprising:

[0006] In the ignition operating condition stage, the liquid rocket engine is ignited; under the ignition operating condition, the ignition pressure value of the propellant provided to the liquid rocket engine is less than the rated pressure value.

[0007] During the dynamic climb phase, the real-time operating condition of the liquid rocket engine is gradually increased from the ignition operating condition to the rated operating condition; the real-time pressure value of the propellant provided to the liquid rocket engine under the rated operating condition is equal to the rated pressure value.

[0008] In some embodiments, in the ignition phase, igniting the liquid rocket engine includes:

[0009] In the ignition operating stage, fuel at a first pressure value and an oxidizer at a second pressure value are supplied to the liquid rocket engine, and the liquid rocket engine is ignited; the first pressure value is less than a rated pressure value of the fuel, and the second pressure value is less than a rated pressure value of the oxidizer;

[0010] Furthermore, during the dynamic climb phase, gradually increasing the real-time operating condition of the liquid rocket engine from the ignition operating condition to the rated operating condition includes:

[0011] During the dynamic climb phase, according to the synchronous pressurization strategy, the pressurized gas system is used to gradually increase the real-time pressure value of the fuel provided to the liquid rocket engine from the first pressure value to the rated pressure value of the fuel, and at the same time, the real-time pressure value of the oxidizer provided to the liquid rocket engine is gradually increased from the second pressure value to the rated pressure value of the oxidizer.

[0012] In some embodiments, the synchronous boosting strategy includes: at least two first openings in a fuel orifice plate of a boosting gas system that participate in boosting regulation and a corresponding first design timing, and at least two second openings in an oxidant orifice plate of the boosting gas system that participate in boosting regulation and a corresponding second design timing;

[0013] The first design timing includes the switching timing of the first openings of any two adjacent area levels;

[0014] The second design timing includes the switching timing of the second openings of any two adjacent area levels.

[0015] In some embodiments, the synchronous boost strategy is predetermined by cold adjustment.

[0016] In some embodiments, using a pressurized gas system to gradually increase the real-time pressure value of the fuel provided to the liquid rocket engine from the first pressure value to the rated pressure value of the fuel, and simultaneously gradually increase the real-time pressure value of the oxidizer provided to the liquid rocket engine from the second pressure value to the rated pressure value of the oxidizer, comprises:

[0017] The plurality of first openings with increasing areas in the fuel orifice plate are opened one by one according to a first design sequence, and the plurality of second openings with increasing areas in the oxidant orifice plate are opened one by one according to a second design sequence; the pressurized gas system includes the fuel orifice plate and the oxidant orifice plate, the fuel orifice plate includes a plurality of first openings with gradually increasing areas, and the oxidant orifice plate includes a plurality of second openings with gradually increasing areas.

[0018] In some embodiments, the ground testing method includes at least one of the following:

[0019] Under the ignition condition, a first pressure value of the fuel supplied to the liquid rocket engine is greater than a second pressure value of the oxidizer;

[0020] Under the rated operating conditions, the rated pressure value of the fuel provided to the liquid rocket engine is less than the rated pressure value of the oxidizer.

[0021] In some embodiments, the ground testing method further comprises:

[0022] During the pressure relief shutdown stage, the real-time operating condition of the liquid rocket engine is gradually reduced from the rated operating condition to the shutdown condition, and the liquid rocket engine is controlled to shut down under the shutdown condition; during the pressure relief shutdown stage, the real-time pressure value of the propellant provided to the liquid rocket engine is less than the rated pressure value.

[0023] In some embodiments, the ground test method further includes obtaining test parameters of the liquid rocket engine under various operating conditions.

[0024] In a second aspect, an embodiment of the present application provides a ground test system suitable for a liquid rocket engine, comprising:

[0025] a tank system for storing propellant;

[0026] a propellant piping system configured to be connected between the tank system located above and the liquid rocket engine located below;

[0027] a pressurized gas system connected to the tank system via a pipeline;

[0028] a control system electrically connected to the pressurized gas system, and configured to, during an ignition operating condition, set the tank pressure of the tank system to an ignition pressure value via the pressurized gas system to provide propellant having the ignition pressure value to the liquid rocket engine, so that the liquid rocket engine ignites under the ignition operating condition, the ignition pressure value being less than a rated pressure value;

[0029] During the dynamic climb phase, the real-time tank pressure of the tank system is gradually increased to the rated pressure value through the pressurized gas system, so as to provide the liquid rocket engine with propellant whose real-time pressure value gradually increases from the ignition pressure value to the rated pressure value, so that the real-time operating condition of the liquid rocket engine gradually climbs from the ignition operating condition to the rated operating condition.

[0030] In some embodiments, the control system further includes a timer for controlling the pressurized gas system to stabilize the pressure according to a pressure stabilization procedure during the rated operating stage, so that the tank pressure of the tank system remains at the rated pressure value for a preset period of time; and for controlling the valve of the pressurized gas system to close and the exhaust valve of the tank system to open during the pressure relief stage, and sending a shutdown command to the liquid rocket engine after the exhaust valve of the tank system remains open for the pressure relief period.

[0031] The beneficial technical effects brought about by the technical solutions provided in the embodiments of the present application include:

[0032] During the ignition phase, the liquid rocket engine is ignited using a propellant at an ignition pressure value. Then, during the dynamic ramp phase, the real-time operating conditions of the liquid rocket engine are gradually increased from the ignition condition to the rated condition. The ignition pressure of the propellant is less than the rated pressure value under the rated condition. This indicates that by igniting the thrust chamber of the liquid rocket engine at a low operating condition and gradually ramping up to the rated condition, a more complete set of parameters under both the ignition condition and the rated condition can be obtained. This also avoids the risk of direct ignition under the rated condition, which could result in excessive ignition shock or ignition failure.

[0033] 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

[0034] 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:

[0035] Figure 1 A flow chart of a ground test method provided in an embodiment of the present application;

[0036] Figure 2 A timing diagram of a full-operation simulation test of a ground test method provided in an embodiment of the present application;

[0037] Figure 3 A schematic diagram of the framework of a ground test system provided in an embodiment of the present application.

[0038] Description of reference numerals:

[0039] 100-Ground test system;

[0040] 11-Tank system; 12-Propellant piping system; 13-Compressed gas system; 14-Liquid rocket engine; 15-Control system. DETAILED DESCRIPTION

[0041] 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.

[0042] Those skilled in the art will understand that, unless otherwise stated, the "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 described features, integers, steps, operations, 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. It should be understood that when we say that an element is "connected" or "coupled" to another element, the element can be directly connected or coupled to the other element, or it can refer to the establishment of a connection relationship between the element and the other element through an intermediate element. In addition, the "connection" or "coupling" used here can include wireless connection or wireless coupling. The term "and / or" used here 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".

[0043] 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.

[0044] 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.

[0045] To prevent damage to the thrust chamber walls of liquid rocket engines caused by oxygen-rich combustion, they typically use a rich-burn ignition system. This means that fuel enters the thrust chamber first, followed by the oxidizer in the header chamber. At this point, some fuel is already present inside the thrust chamber, 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's important to consider this issue during ground testing.

[0046] Furthermore, the ground testing methods used in related art for thrust chamber testing generally only conduct ignition tests under one or a few pressure conditions. This allows only ignition parameters to be obtained under these conditions, but not the thrust chamber's shift parameters, shutdown parameters, etc. This is especially true for newly developed thrust chambers, as they present risks of explosion due to high pressure and unstable combustion, potentially causing serious damage to the test bench. Therefore, conducting ground testing under rated conditions and obtaining the thrust chamber's rated parameters are difficult.

[0047] 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.

[0048] The present application embodiment provides a ground test method suitable for liquid rocket engines, such as Figure 1 As shown, the ground test method includes steps S11 to S12.

[0049] S11: In the ignition condition stage, the liquid rocket engine is ignited; the ignition pressure value of the propellant provided to the liquid rocket engine under the ignition condition is less than the rated pressure value.

[0050] In some embodiments, the ignition operating condition may be 30% of the rated operating condition, that is, the real-time pressure value of the propellant provided to the liquid rocket engine under the ignition operating condition may be 30% of the rated pressure value.

[0051] For example, the rated pressure value may be approximately 15 MPa (megapascals), and the real-time pressure value of the propellant supplied to the liquid rocket engine under ignition conditions may be 4.5 MPa.

[0052] S12: During the dynamic climb phase, the real-time operating condition of the liquid rocket engine is gradually increased from the ignition operating condition to the rated operating condition; the real-time pressure value of the propellant supplied to the liquid rocket engine under the rated operating condition is equal to the rated pressure value.

[0053] During the ignition phase, the liquid rocket engine is ignited using a propellant at an ignition pressure value. Then, during the dynamic ramp phase, the real-time operating conditions of the liquid rocket engine are gradually increased from the ignition condition to the rated condition. The ignition pressure of the propellant is less than the rated pressure value under the rated condition. This indicates that by igniting the thrust chamber of the liquid rocket engine at a low operating condition and gradually ramping up to the rated condition, a more complete set of parameters under both the ignition condition and the rated condition can be obtained. This also avoids the risk of direct ignition under the rated condition, which could result in excessive ignition shock or ignition failure.

[0054] Moreover, compared with the engine pump pressure type, the dynamic supercharging method takes longer to reach the rated operating conditions. The risks during the thrust chamber test are easy to identify, and the system can be stopped in time when there is a greater risk, avoiding serious damage to the test bench, reducing losses and risks during the development stage, and being more reliable and safer.

[0055] See also Figure 2In some embodiments, step S11 includes: in the ignition condition stage, providing fuel of a first pressure value and an oxidizer of a second pressure value to the liquid rocket engine, and igniting the liquid rocket engine; the first pressure value is less than the rated pressure value of the fuel, and the second pressure value is less than the rated pressure value of the oxidizer.

[0056] And, step S12 includes: in the dynamic climb phase, according to the synchronous pressurization strategy, using the pressurized gas system to gradually increase the real-time pressure value of the fuel provided to the liquid rocket engine from a first pressure value to the rated pressure value of the fuel, and at the same time, gradually increasing the real-time pressure value of the oxidizer provided to the liquid rocket engine from a second pressure value to the rated pressure value of the oxidizer.

[0057] That is, the first pressure value is the ignition pressure value of the fuel, and the second pressure value is the ignition pressure value of the oxidant.

[0058] In some embodiments, the tank system includes a fuel tank and an oxidizer tank, and the pressurized gas system includes a first gas cylinder and a second gas cylinder. The first gas cylinder is connected to the fuel tank via a first pipe, and the second gas cylinder is connected to the oxidizer tank via a second pipe. A first pressurizing system is provided on the first pipe, and the first pressurizing system includes a fuel orifice plate and a first solenoid valve. A second pressurizing system is provided on the second pipe, and the second pressurizing system includes an oxidizer orifice plate and a second solenoid valve.

[0059] By adjusting the fuel orifice plate and the oxidizer orifice plate, the pressure values of the fuel and oxidizer supplied to the liquid rocket engine are adjusted respectively.

[0060] See also Figure 2 In some embodiments, the synchronous boost strategy includes: at least two first openings in the fuel orifice plate of the boost gas system that participate in boost regulation and a corresponding first design timing, and at least two second openings in the oxidizer orifice plate of the boost gas system that participate in boost regulation and a corresponding second design timing.

[0061] The first design timing includes the switching timing of the first openings of any two adjacent area levels; the second design timing includes the switching timing of the second openings of any two adjacent area levels.

[0062] In some embodiments, the synchronous boost strategy is predetermined by cold tuning.

[0063] Cold commissioning is debugging without ignition. The other conditions are the same as those during hot testing (i.e. ground testing). For example, the propellant supply during cold commissioning is the same as the propellant supply during the ignition operating condition stage and the rated operating condition stage.

[0064] In other words, cold commissioning can be understood as a rehearsal before hot commissioning. It ensures that the cylinder pressure matches the orifice plate size and the boost sequence is correct. Typically, cold commissioning involves multiple adjustments, ultimately determining the cylinder pressure, orifice plate size, and boost sequence based on these adjustments. Hot commissioning is then conducted based on these finalized values.

[0065] In other words, before the ground test, the boost orifice plates and boost strategies of the fuel and oxidizer circuits can be determined through cold adjustment. After the tank pressures of the fuel and oxidizer meet their respective target tank pressure values, the program is switched to the pressure stabilization program, and the pressure stabilization control is performed according to the pressure control band accuracy to avoid serious deviations in the mixing ratio of the fuel and oxidizer during the boosting process. The synchronization of the fuel and oxidizer boosting is guaranteed through cold adjustment verification.

[0066] In some embodiments, using a pressurized gas system to gradually increase a real-time pressure value of fuel provided to a liquid rocket engine from a first pressure value to a rated pressure value of the fuel, and simultaneously gradually increase a real-time pressure value of an oxidizer provided to the liquid rocket engine from a second pressure value to the rated pressure value of the oxidizer, comprises:

[0067] The multiple first openings with increasing areas in the fuel orifice plate are opened one by one according to a first design sequence, and at the same time, the multiple second openings with increasing areas in the oxidant orifice plate are opened one by one according to a second design sequence; the pressurized gas system includes a fuel orifice plate and an oxidant orifice plate, the fuel orifice plate includes a multiple first openings with increasing areas, and the oxidant orifice plate includes a multiple second openings with increasing areas.

[0068] See also Figure 2 In some embodiments, the ground test method includes at least one of the following:

[0069] Under ignition conditions, a first pressure value of the fuel provided to the liquid rocket engine is greater than a second pressure value of the oxidizer.

[0070] Under rated operating conditions, the rated pressure of the fuel supplied to the liquid rocket engine is less than the rated pressure of the oxidizer.

[0071] Since under the ignition condition, the first pressure value of the fuel provided to the liquid rocket engine is greater than the second pressure value of the oxidizer, that is, the ignition condition is a low mixture ratio (rich fuel condition), the problem of thrust chamber ablation that is prone to occur during ignition under oxygen-rich conditions can be improved, the ignition shock is smaller, and the equipment safety is higher.

[0072] Because under rated operating conditions, the rated pressure value of the fuel supplied to the liquid rocket engine is lower than the rated pressure value of the oxidizer, it can ensure the full combustion of the fuel and provide sufficient power for the rocket and spacecraft.

[0073] See also Figure 2 In some embodiments, the ground test method may further include:

[0074] During the pressure relief shutdown stage, the real-time operating conditions of the liquid rocket engine are gradually reduced from the rated operating conditions to the shutdown conditions, and the liquid rocket engine is controlled to shut down under the shutdown conditions; during the pressure relief shutdown stage, the real-time pressure value of the propellant provided to the liquid rocket engine is less than the rated pressure value.

[0075] That is to say, during the pressure relief shutdown stage, the pressurized gas system stops pressurizing and stabilizing the pressure, and the tank system opens the exhaust valve to start pressure relief. Compared with the direct shutdown solution, by first releasing pressure and then shutting down, the inlet pressure of the liquid rocket engine can be reduced, and the shutdown water hammer of the liquid rocket engine valve can be reduced, thereby extending the service life of the liquid rocket engine valve.

[0076] In some embodiments, the ground test method may further include: during the rated operating condition phase, maintaining the real-time operating condition of the liquid rocket engine at the rated operating condition for a preset period of time.

[0077] By igniting at low operating conditions, dynamically climbing to rated operating conditions, and maintaining rated operating conditions for a preset period of time, it is possible to carry out ground tests under rated operating conditions while ensuring safety, obtain the rated parameters of the thrust chamber, and better assess the chamber pressure, thrust, mixture ratio, and cooling performance of the thrust chamber.

[0078] In some embodiments, the ground test method further includes obtaining test parameters of the liquid rocket engine under full operating conditions.

[0079] Among them, the test parameters may include real-time pressure, real-time temperature, etc.

[0080] For example, obtain the ignition parameters of the liquid rocket engine under the ignition condition (i.e., the thrust chamber starting performance data); obtain the stage transfer parameters of the liquid rocket engine during the process of gradually climbing from the ignition condition to the rated condition; obtain the pressure relief parameters of the liquid rocket engine during the process of gradually descending from the rated condition to the shutdown condition; obtain the shutdown parameters of the liquid rocket engine during the shutdown process.

[0081] Through the above-mentioned full-operating condition ground test method, ignition, stage change, rating, pressure relief, shutdown can be completed in one test run, and the test parameters of the liquid rocket engine under full operating conditions can be obtained, which can save time, manpower and material resources in ground testing.

[0082] See also Figure 2 The ground test method for simulating the full working conditions of the thrust chamber proposed in the embodiment of the present application mainly includes the following stages:

[0083] 1) Ignition stage: pressurize the tank system to the oxidizer ignition condition pressure P by manual (or automatic) pre-pressurization. 0Y , fuel fire working pressure P 0R , trigger T0 ignition, after ignition lasts for t1, obtain the ignition parameters of the liquid rocket engine under the ignition condition.

[0084] Among them, the oxidant ignition pressure P 0Y Less than the rated working pressure P of the oxidizer 1Y , fuel ignition pressure P 0R Less than the fuel rated working pressure P 1R .

[0085] 2) Dynamic climbing stage: The tank system is pressurized by the booster gas system according to the boosting program, so that the tank pressure of the oxidizer tank of the tank system is gradually increased to the rated working pressure of the oxidizer P 1Y The fuel tank pressure of the tank system gradually increases to the fuel rated working pressure P 1R , the boost time lasts for t2.

[0086] During the dynamic climb, according to the characteristics of the tanks, the consistency of the fuel tank and the oxidizer tank pressurization is allowed to deviate. In order to avoid a serious deviation in the mixture ratio during the pressurization process, the pressurization orifice plates and pressurization strategies of the oxidizer and fuel lines can be determined by cold adjustment before the ground test. The cold adjustment verification ensures the synchronization of the fuel tank and the oxidizer tank pressurization, and the tank pressure meets the target tank pressure value (i.e., the rated operating pressure P of the oxidizer). 1Y , fuel rated operating pressure P 1R ) and then switches to the voltage stabilization program and performs voltage stabilization control according to the pressure control band accuracy.

[0087] 3) Rated working condition stage: The tank pressure of the tank system reaches the target tank pressure value under rated working condition (the tank pressure of the oxidizer tank is the oxidizer rated working condition pressure P 1Y The fuel tank pressure is the fuel rated working pressure), and the boost system is stabilized according to the pressure stabilization procedure. 1R The stable working time under rated conditions lasts for t3.

[0088] 4) Pressure relief shutdown stage: The boost gas system stops pressurizing and stabilizing, and the tank system opens the exhaust valve to start pressure relief; when the inlet pressure of the liquid rocket engine (equal to the tank pressure of the tank system) drops to the specified value, the auxiliary system of the liquid rocket engine executes the shutdown command and completes the shutdown.

[0089] In actual applications, the time required for the oxidizer tank and fuel tank pressures to reach the specified value may differ. Therefore, the fuel tank vent valve and the oxidizer tank vent valve may be opened sequentially to begin pressure relief. When the fuel tank pressure drops to the specified value, the fuel tank vent valve is closed. When the oxidizer tank pressure drops to the specified value, the oxidizer tank vent valve is closed. After both the fuel tank vent valve and the oxidizer tank vent valve are closed (pressure relief is complete for both the fuel and oxidizer tanks), the liquid rocket engine's auxiliary systems execute a shutdown command.

[0090] During the entire process (all operating conditions) described above, the measurement system is responsible for collecting real-time sensor data and obtaining the test parameters of the liquid rocket engine under all operating conditions; the control system performs valve control according to a predetermined timing to achieve control of the pressure values of the oxidizer and fuel lines.

[0091] The beneficial technical effects brought about by the technical solutions provided in the embodiments of the present application include:

[0092] Since the thrust chamber of the liquid rocket engine is ignited under low operating conditions and gradually climbs to the rated operating conditions, it is possible to obtain more complete parameters under the ignition conditions and the parameters under the rated operating conditions. At the same time, it can avoid the risk of direct ignition under the rated conditions, which may lead to excessive ignition shock or ignition failure. Moreover, compared with the engine pump pressure type, the dynamic supercharging method takes longer to reach the rated operating conditions. The risks during the thrust chamber test are easy to judge, and the system can be stopped in time when there is a greater risk, avoiding serious damage to the test bench, reducing losses and risks in the development stage, and being more reliable and safer.

[0093] In addition, compared with the direct shutdown solution, the method of first releasing pressure and then shutting down can reduce the inlet pressure of the liquid rocket engine and reduce the shutdown water hammer of the liquid rocket engine valve, thereby extending the service life of the liquid rocket engine valve.

[0094] Through the above-mentioned full-operating condition ground test method, ignition, stage change, rating, pressure relief, shutdown can be completed in one test run, and the test parameters of the liquid rocket engine under full operating conditions can be obtained, which can save time, manpower and material resources in ground testing.

[0095] Based on the same inventive concept, the embodiment of the present application provides a ground test system suitable for liquid rocket engines, such as Figure 3 As shown, the ground test system 100 includes a tank system 11 , a propellant piping system 12 and a pressurized gas system 13 .

[0096] The tank system 11 is used to store propellant.

[0097] The propellant piping system 12 is configured to connect between the tank system 11 located above and the liquid rocket engine 14 located below.

[0098] The pressurized gas system 13 is connected to the tank system 11 through a pipeline;

[0099] The control system 15 is electrically connected to the pressurized gas system 13 and is used to:

[0100] During the ignition operating condition, the tank pressure of the tank system 11 is set to the ignition pressure value through the pressurized gas system 13 to provide propellant with the ignition pressure value to the liquid rocket engine 14, so that the liquid rocket engine 14 ignites under the ignition operating condition, and the ignition pressure value is less than the rated pressure value.

[0101] During the dynamic climb phase, the real-time tank pressure of the tank system 11 is gradually increased to the rated pressure value through the pressurized gas system 13, so as to provide the liquid rocket engine 14 with propellant whose real-time pressure value gradually increases from the ignition pressure value to the rated pressure value, so that the real-time operating condition of the liquid rocket engine 14 gradually climbs from the ignition operating condition to the rated operating condition.

[0102] Continue to see Figure 3 In some embodiments, the control system 15 further includes a timer for controlling the pressurized gas system to stabilize the pressure according to the pressure stabilization program during the rated operating stage, so that the tank pressure of the tank system 11 remains at the rated pressure value for a preset period of time; during the pressure relief stage, controlling the valve of the pressurized gas system 13 to close and the exhaust valve of the tank system 11 to open, and sending a shutdown command to the liquid rocket engine 14 after the exhaust valve of the tank system 11 remains in the open state for the pressure relief period.

[0103] In practical applications, the tank system 11 includes a propellant tank and an exhaust valve. The propellant tank can hold a certain volume and pressure of propellant; the exhaust valve is used to exhaust the propellant tank to maintain a balance of pressure inside and outside the propellant tank.

[0104] The pressurized gas system 13 includes high-pressure gas cylinders and a pressurization system. The high-pressure gas cylinders provide a stable and sufficient gas source for tank pressurization. The pressurization system generally consists of a pressurization solenoid valve and a pressurization orifice plate. Multiple sets of these valves and plates are used in parallel to form a pressurization orifice plate matrix, which can provide pressurization and pressure stabilization for the propellant tank according to a predetermined program.

[0105] In other words, the boost system consists of a parallel matrix of multiple boost solenoid valves and boost orifice plates, also known as an orifice matrix. Each branch contains a boost solenoid valve and a boost orifice plate. In each branch, a control sequence controls the opening and closing of the boost solenoid valve, which in turn controls the opening and closing of the orifice plate. The opening and closing of each boost solenoid valve corresponds to a corresponding upper and lower limit for the tank pressure.

[0106] The propellant piping system 12 includes a delivery pipeline (and accessories), a flowmeter, and a primary valve. The delivery pipeline can deliver propellant at a certain pressure and flow rate to the inlet of the liquid rocket engine. The flowmeter is used to measure the propellant flowing in the delivery pipeline in real time, generally in terms of volume flow or mass flow. The primary valve is generally a pneumatic valve that shuts off the propellant between the ground test system and the liquid rocket engine.

[0107] The measurement and control system includes a measurement system and a control system 15. The measurement system, consisting of sensors, cables, and an acquisition system, is used to collect parameters such as pressure, temperature, and vibration of the liquid rocket engine. The control system 15, which can be composed of a programmable logic controller (PLC) and a host computer, is used to control the valves of the ground test system and to complete the valve movements of the liquid rocket engine according to a given time sequence.

[0108] This embodiment is a system embodiment corresponding to the aforementioned ground test method. Specific technical details and technical effects can be found in the aforementioned description and will not be repeated here.

[0109] 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.

[0110] 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.

[0111] 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.

[0112] 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.

[0113] 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.

[0114] 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 method, applicable to liquid rocket engines, characterized in that: include: In an ignition operating state, fuel at a first pressure value and an oxidizer at a second pressure value are supplied to the liquid rocket engine, and the liquid rocket engine is ignited; the first pressure value is less than a rated pressure value of the fuel, and the second pressure value is less than a rated pressure value of the oxidizer; in the ignition operating state, the first pressure value of the fuel supplied to the liquid rocket engine is greater than the second pressure value of the oxidizer; During the dynamic climb phase, according to the synchronous pressurization strategy, the pressurized gas system is used to gradually increase the real-time pressure value of the fuel provided to the liquid rocket engine from the first pressure value to the rated pressure value of the fuel, and at the same time, the real-time pressure value of the oxidizer provided to the liquid rocket engine is gradually increased from the second pressure value to the rated pressure value of the oxidizer; under rated operating conditions, the rated pressure value of the fuel provided to the liquid rocket engine is less than the rated pressure value of the oxidizer.

2. The ground test method according to claim 1, characterized in that: The synchronous supercharging strategy includes: at least two first openings in a fuel orifice plate of a supercharging system that participate in supercharging regulation and a corresponding first design timing, and at least two second openings in an oxidant orifice plate of a supercharging system that participate in supercharging regulation and a corresponding second design timing; The first design timing includes the switching timing of the first openings of any two adjacent area levels; The second design timing includes the switching timing of the second openings of any two adjacent area levels.

3. The ground test method according to claim 2, characterized in that: The synchronous supercharging strategy is determined in advance through cold adjustment.

4. The ground test method according to claim 1, characterized in that: The method comprises: gradually increasing the real-time pressure value of the fuel supplied to the liquid rocket engine from the first pressure value to the rated pressure value of the fuel by using the pressurized gas system, and gradually increasing the real-time pressure value of the oxidizer supplied to the liquid rocket engine from the second pressure value to the rated pressure value of the oxidizer. The plurality of first openings with increasing areas in the fuel orifice plate are opened one by one according to a first design sequence, and the plurality of second openings with increasing areas in the oxidant orifice plate are opened one by one according to a second design sequence; the pressurized gas system includes the fuel orifice plate and the oxidant orifice plate, the fuel orifice plate includes a plurality of first openings with gradually increasing areas, and the oxidant orifice plate includes a plurality of second openings with gradually increasing areas.

5. The ground test method according to claim 1, characterized in that: Also includes: During the pressure relief shutdown stage, the real-time operating condition of the liquid rocket engine is gradually reduced from the rated operating condition to the shutdown condition, and the liquid rocket engine is controlled to shut down under the shutdown condition; during the pressure relief shutdown stage, the real-time pressure value of the propellant provided to the liquid rocket engine is less than the rated pressure value.

6. The ground test method according to claim 5, characterized in that: It also includes obtaining test parameters of the liquid rocket engine under all working conditions.

7. A ground test system for a liquid rocket engine, characterized in that: include: a tank system for storing propellant; a propellant piping system configured to be connected between the tank system located above and the liquid rocket engine located below; a pressurized gas system connected to the tank system via a pipeline; a control system electrically connected to the pressurized gas system, and configured to, during an ignition operating state, set the tank pressure of the tank system to an ignition pressure value via the pressurized gas system to provide the liquid rocket engine with fuel at a first pressure value and oxidizer at a second pressure value, thereby igniting the liquid rocket engine, wherein the first pressure value is less than a rated pressure value of the fuel, and the second pressure value is less than a rated pressure value of the oxidizer; During the dynamic climb phase, the real-time tank pressure of the tank system is gradually increased to the rated pressure value through the pressurized gas system, so as to gradually increase the real-time pressure value of the fuel supplied to the liquid rocket engine from the first pressure value to the rated pressure value of the fuel, and at the same time, gradually increase the real-time pressure value of the oxidizer supplied to the liquid rocket engine from the second pressure value to the rated pressure value of the oxidizer, so that the real-time operating condition of the liquid rocket engine gradually climbs from the ignition operating condition to the rated operating condition; under the rated operating condition, the rated pressure value of the fuel supplied to the liquid rocket engine is less than the rated pressure value of the oxidizer.

8. The ground test system according to claim 7, characterized in that: The control system further includes a timer for controlling the pressurized gas system to stabilize the pressure according to a pressure stabilization program during the rated operating phase, so that the tank pressure of the storage tank system remains at the rated pressure value for a preset period of time; During the pressure relief phase, the valve of the pressurized gas system is controlled to close and the exhaust valve of the tank system is controlled to open. After the exhaust valve of the tank system remains open for the pressure relief period, a shutdown command is sent to the liquid rocket engine.

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