Liquid orbit control engine high-altitude simulation test real-time fault early warning system and method

Abstract

The present application relates to a kind of liquid attitude control engine high-altitude simulation test real-time fault early warning system and method, to solve the technical problem that personnel reaction speed is slow, operation time is long in the process of manual emergency shutdown by artificial monitoring water vapor generator system parameter change, easy to cause serious accident.The system includes real-time monitoring module containing real-time data acquisition unit and multiple measurement sensors, abnormal diagnosis module and fault early warning module.The method includes:1, obtaining the classifier of each operating phase, starting water vapor generator system;2, obtaining current parameter set data;3, calculating confidence, if confidence is greater than confidence threshold, continue monitoring;If confidence is less than or equal to confidence threshold, then judge whether three consecutive parameter set data are abnormal, if yes, then determine fault, shut down water vapor generator system, if not, then continue monitoring.

Description

Technical Field

[0001] The present invention relates to a liquid attitude and orbit control engine high altitude simulation test early warning system and method, and in particular to a liquid attitude and orbit control engine high altitude simulation test real-time fault early warning system and method. Background Art

[0002] Liquid attitude and orbit control rocket engines generally use self-igniting nitro-based substances (such as nitrogen tetroxide) and hydrazine-based substances (such as unsymmetrical dimethylhydrazine) as propellants. When operating in near-space or in space far from the ground, the engine propellant storage system often needs to operate under high vacuum conditions. The high-altitude simulation test system includes a vacuum chamber, a water vapor generator system, a diffuser, a tube bundle cooler, and a steam jet pump. The vacuum chamber is the workplace for high-altitude simulation tests of attitude and orbit control engines. The water vapor generator system uses liquid oxygen and alcohol combustion with softened water to produce water vapor at the required pressure and temperature. When using the high-altitude simulation test system to simulate the engine's operation in a near-space environment, the engine will eject a certain flow of gas at up to 2700°C from the combustion chamber per unit time. To maintain the vacuum level within the test system, the steam jet pump uses the water vapor generated by the water vapor generator as power to eject the engine gas within the vacuum chamber, creating and maintaining the vacuum environment within the vacuum chamber.

[0003] The steam injection system, comprising an igniter, a steam generator, a steam jet pump, and a water spray cooler, is a complex system. The steam generator system, a key component, generates the large quantities of high-temperature steam required for proper operation. The steam generator system typically uses the heat generated by the combustion of liquid oxygen and alcohol to instantly vaporize softened water into high-temperature dry steam. A malfunction in any part of the steam generator system can quickly deactivate the system's injection capabilities, disrupting the vacuum environment within the chamber and potentially damaging the rocket engine. Furthermore, since the steam generator system uses liquid oxygen and alcohol as both oxidizer and fuel, a malfunction can result in serious consequences such as explosions. Therefore, real-time status monitoring and diagnosis of the steam generator system is essential. Imminent system failure can be detected at the earliest sign of system parameter anomalies, sending a shutdown command to the rocket engine and shutting down the entire steam injection system.

[0004] Currently, steam injection system performance is monitored by manually observing all engineering parameters measured by a parameter acquisition system. When certain parameters exhibit significant anomalies, manual control is used to implement emergency engine shutdowns and emergency shutdowns of the high-altitude simulation system. However, the process from a steam generator system parameter anomaly to system failure typically occurs within a few seconds, such as a momentary loss of softened water flow, far less than the response time required for manual intervention. Manual monitoring and intervention fail to guarantee the safety of the injection system and could potentially cause a serious steam generator system accident. Furthermore, by the time an anomaly is detected, the high-altitude simulation system is no longer able to maintain the required operating environment for the engine, potentially leading to a rocket engine explosion. Summary of the Invention

[0005] The purpose of the present invention is to solve the technical problem that manual monitoring of water vapor generator system parameter changes and manual emergency shutdown take a long time and easily cause serious accidents. A real-time fault warning system and method for high-altitude simulation tests of liquid attitude and orbit control engines are proposed.

[0006] The technical solution provided by the present invention is:

[0007] A real-time fault warning system for high-altitude simulation tests of liquid attitude and orbit control engines is used to monitor the steam generator system in real time to monitor the working status of the ejection system. Its special features include: a real-time monitoring module, an abnormality diagnosis module, and a fault warning module;

[0008] The real-time monitoring module includes a real-time data acquisition unit and a plurality of measurement sensors connected to the steam generator system; the real-time data acquisition unit collects real-time data from each measurement sensor to obtain parameter set data and outputs it to the abnormality diagnosis module;

[0009] The abnormality diagnosis module performs data analysis on the parameter set data, judges the working state of the steam generator system in the current operation stage according to the data analysis result, and outputs a judgment signal;

[0010] The fault warning module is used to receive the abnormal diagnosis result of the abnormal diagnosis module and send an emergency shutdown signal.

[0011] Furthermore, the abnormality diagnosis module includes an I / O board relay and a three-out-of-two voting circuit connected in series with the I / O board relay, the three-out-of-two voting circuit being used to receive an output signal of the I / O board relay and perform a three-out-of-two voting;

[0012] The three-out-of-two voting circuit includes a first double-pole double-throw switch, a second double-pole double-throw switch, and a third double-pole double-throw switch. The input end of the first double-pole double-throw switch and the first channel input end of the second double-pole double-throw switch are both connected to the power supply end. The output end of the first double-pole double-throw switch is connected to the second channel input end of the second double-pole double-throw switch and the second channel input end of the third double-pole double-throw switch. The second channel output end of the second double-pole double-throw switch is connected to the second channel output end of the third double-pole double-throw switch and is connected to the input end of the fault warning module for outputting a signal to the fault warning module. The control ends of the first double-pole double-throw switch, the second double-pole double-throw switch, and the third double-pole double-throw switch are all connected to the I / O board relay to receive the output signal of the I / O board relay.

[0013] The first channel output end of the second double-pole double-throw switch is connected to the first channel input end of the third double-pole double-throw switch, and the first channel output end of the third double-pole double-throw switch is connected to the input end of the fault warning module.

[0014] Furthermore, the fault warning module includes an audible and visual alarm device, a fault warning control relay, and an emergency stop button; the input end of the fault warning control relay is connected to the output end of the three-out-of-two voting circuit, and one output end of the fault warning control relay is connected to the emergency stop button; the fault warning control relay is used to receive the judgment signal output by the abnormal diagnosis module, and control the emergency stop button to be turned on or off according to the judgment signal, so as to control the injection system and the engine system to be turned on or off;

[0015] Another output terminal of the fault warning control relay is connected to an audible and visual alarm device for issuing an early warning through an audible and visual alarm.

[0016] Furthermore, the measuring sensor is a high-precision sensor, and the accuracy of the measuring sensor is better than 2‰.

[0017] Furthermore, the operation stage includes an igniter starting stage, a softened water entering stage, a steam generator starting stage and a steam generator stabilization stage.

[0018] Furthermore, the abnormality diagnosis module is connected to an external server to make the access to the real-time fault warning system of the liquid attitude and orbit control engine high-altitude simulation test lightweight.

[0019] The present invention also provides a method for real-time fault warning during a high-altitude simulation test of a liquid attitude and orbit control engine. The method is special in that it uses the above-mentioned real-time fault warning system during a high-altitude simulation test of a liquid attitude and orbit control engine, and includes the following steps:

[0020] S1. Obtain classifiers for each operating stage

[0021] Using existing simulation test data, the existing simulation test data is divided into corresponding training sets according to the operation stage, and the training sets are trained using anomaly detection algorithms to obtain classifiers corresponding to each operation stage;

[0022] S2, start the steam generator system;

[0023] S3. Using the real-time monitoring module to collect data from each measurement sensor in real time to obtain the parameter set data at the current moment;

[0024] S4, based on the anomaly detection algorithm, using the anomaly diagnosis module, select the corresponding classifier according to the operation stage corresponding to the current moment parameter set data, input the current moment parameter set data in step S3 into the corresponding classifier, and the classifier calculates the credibility C of the current moment parameter set data. θ (x), the calculation formula is as follows:

[0025] C θ (x) = f θ (x 1 ) f θ (x 2 ) …f θ (x n )

[0026] Among them, θ is the probability density parameter after training, n is the number of data in the parameter set data at the current moment, and f θ (x) is the probability density function of each data in the current parameter time set data;

[0027] If C θ (x)>λ, then the parameter set data at the current moment is normal, and step S7 is executed;

[0028] If C θ (x)≤λ, then the parameter set data at the current moment is abnormal, and step S5 is executed; λ is the confidence threshold of the classifier after training corresponding to the parameter set data at the current moment;

[0029] S5. If the parameter set data are abnormal for three consecutive times, it is determined that the steam generator system is faulty, and a fault signal is sent to the fault warning module, and step S6 is executed; if the number of consecutive abnormal parameter set data is less than 3, step S7 is executed;

[0030] S6, the fault warning module shuts down the ejection system and the engine system in an emergency according to the fault signal;

[0031] S7. Return to step S3 and monitor the operation of the steam generator system in real time until the test is completed.

[0032] Furthermore, in step S1, each operation stage includes an igniter starting stage, a softened water entering stage, a steam generator starting stage, and a steam generator stabilization stage;

[0033] The classifiers include an igniter starting section classifier, a softened water entering section classifier, a steam generator starting section classifier, and a steam generator stabilization section classifier.

[0034] The present invention also provides a computer-readable storage medium on which a computer program is stored. The special feature of the computer program is that when the computer program is executed by a processor, the real-time fault warning method for the high-altitude simulation test of the liquid attitude and orbit control engine is implemented.

[0035] The present invention also provides an electronic device, including a processor and a memory, wherein the memory is used to store executable instructions of the processor. The special feature of the electronic device is that the processor executes the executable instructions to implement the above-mentioned real-time fault warning method for high-altitude simulation tests of liquid attitude and orbit control engines.

[0036] Beneficial effects of the present invention:

[0037] 1. The anomaly detection algorithm adopted by the present invention uses the state parameter data of various parts of the existing simulation test system as the training set. According to the various process segments of the system operation, a classifier is trained on the key parameters of each process segment. The credibility of the trained classifier output will be used as the diagnostic criterion for each working process segment. Compared with manual judgment based on historical experience, this criterion is faster and more accurate.

[0038] 2. The abnormality diagnosis module in the present invention calculates the credibility of the key parameter set collected for three consecutive moments. Only when the credibility is abnormal for more than or equal to three consecutive times, the generator is judged to be abnormal. Therefore, it can avoid signal interference of the collected data and misjudgment caused by abnormal key parameter collection to the greatest extent, thereby causing incorrect shutdown.

[0039] 3. The method provided by the present invention can immediately detect the fault at the very beginning of the fault, thus avoiding serious consequences such as explosion of the ejection system caused by untimely response based on human experience.

[0040] 4. The fault alarm module used in the real-time fault warning system of the present invention uses a relay driven by an I / O board. When the fault diagnosis server issues a shutdown command, the I / O board switch in the fault alarm chassis triggers and drives the relay within 3-5ms, controlling the time from fault detection to emergency shutdown and system shutdown to milliseconds. In contrast, using a manual method, limited by human reaction time, it takes 10 seconds or even longer from the commander's discovery of the anomaly to the issuance of the emergency shutdown command and then to its execution. The fault shutdown response time of the present invention is improved by orders of magnitude.

[0041] 5、The abnormal diagnosis module of the real-time fault early warning system of the liquid attitude orbit control engine high-altitude simulation test uses a two-out-of-three direct current protection circuit, which avoids the false shutdown caused by the false triggering of the I / O board switch after being disturbed, and ensures the reliability of the system.

[0042] 6、The abnormal diagnosis module of the real-time fault early warning system of the liquid attitude orbit control engine high-altitude simulation test has a special fault diagnosis server, so that the access software for fault diagnosis is lightweight and can be directly accessed by a browser, and multiple computers can be logged in at the same time. BRIEF DESCRIPTION OF DRAWINGS

[0043] Figure 1 It is a schematic diagram of the real-time fault early warning system of the liquid attitude orbit control engine high-altitude simulation test of the application;

[0044] Figure 2 It is a schematic diagram of the fault early warning module in the embodiment of the application;

[0045] Figure 3 It is a schematic diagram of the three-voting circuit in the embodiment of the application;

[0046] Figure 4 It is a schematic diagram of the real-time fault early warning method flow of the liquid attitude orbit control engine high-altitude simulation test of the application;

[0047] Figure 5 It is the credibility acquisition process in the embodiment of the application. DETAILED DESCRIPTION

[0048] As shown in the drawings, Figure 1 The embodiment provides a real-time fault early warning system for liquid attitude orbit control engine high-altitude simulation test, which is used for real-time monitoring of a water vapor generator system, and further realizes monitoring of the working state of an injection system, and the system comprises a real-time monitoring module, an abnormal diagnosis module and a fault early warning module.

[0049] The real-time monitoring module comprises a real-time data acquisition unit and a plurality of measurement sensors connected with the water vapor generator system, the measurement sensors are connected with each engineering position of the water vapor generator system to receive real-time parameter information of each engineering, and the real-time data acquisition unit acquires real-time data of each measurement sensor to obtain parameter set data and outputs the parameter set data to the abnormal diagnosis module; the measurement sensor used in the embodiment is a high-precision sensor, and the precision of the measurement sensor is better than 2 ‰, so as to improve the sampling precision in the monitoring process.

[0050] The abnormal diagnosis module performs data analysis on the parameter set data, judges the working state of the current running stage of the water vapor generator system according to the data analysis result, and outputs a judgment signal; the running stage mentioned here includes an igniter starting section, a softened water entering section, a water vapor generator starting section and a water vapor generator stabilizing section.

[0051] See also Figure 3 The abnormal diagnosis module includes an I / O board relay and a three-out-of-two voting circuit connected in series with the I / O board relay. The three-out-of-two voting circuit is used to receive the output signal of the I / O board relay and perform three-out-of-two voting; the three-out-of-two voting circuit includes a first double-pole double-throw switch, a second double-pole double-throw switch and a third double-pole double-throw switch. The input end of the first double-pole double-throw switch and the first channel input end of the second double-pole double-throw switch are both connected to the power supply end, the output end of the first double-pole double-throw switch is connected to the second channel input end of the second double-pole double-throw switch and the second channel input end of the third double-pole double-throw switch, the second channel output end of the second double-pole double-throw switch is connected to the second channel output end of the third double-pole double-throw switch, and is connected to the input end of the fault warning module for outputting a signal to the fault warning module; the control ends of the first double-pole double-throw switch, the second double-pole double-throw switch and the third double-pole double-throw switch are all connected to the I / O board relay to receive the output signal of the I / O board relay.

[0052] The first channel output end of the second double-pole double-throw switch is connected to the first channel input end of the third double-pole double-throw switch, and the first channel output end of the third double-pole double-throw switch is connected to the input end of the fault warning module. Figure 3 As shown, J1 is the channel of the first double-pole double-throw switch, which has one channel. J2-1 and J2-2 are the first channel and the second channel of the second double-pole double-throw switch, respectively. J3-1 and J3-2 are the first channel and the second channel of the third double-pole double-throw switch, respectively. See Table 1 for the truth table of the three-out-of-two voting circuit, where the channel of the first double-pole double-throw switch and the second channel of the second double-pole double-throw switch form path A, the channel of the first double-pole double-throw switch and the second channel of the third double-pole double-throw switch form path B, and the first channel of the second double-pole double-throw switch and the first channel of the third double-pole double-throw switch form path C.

[0053] Table 1 Truth table of three voting circuits

[0054]

[0055] As shown in Table 1, when the I / O board is in the untriggered state, an interference signal appears in a single relay channel, and when it changes from 0 to 1, the output result remains 0; when it is in the triggered state, an interference signal appears in a single relay channel, and when it changes from 1 to 0, the output result remains 1.

[0056] The abnormal diagnosis module is connected to an external server, which can realize the lightweight real-time fault warning system of the liquid attitude and orbit control engine high-altitude simulation test. It can be directly accessed by the browser to meet the needs of multiple computers logging in at the same time.

[0057] The fault warning module is used to receive the abnormal diagnosis results of the abnormal diagnosis module and send an emergency shutdown signal to the control console of the steam generator system and the control console of the liquid attitude and orbit control engine.

[0058] See also Figure 2 The fault warning module includes an audible and visual alarm device, a fault warning control relay and an emergency stop button; the input end of the fault warning control relay is connected to the output end of the three-out-of-two voting circuit, and one output end of the fault warning control relay is connected to the emergency stop button; the fault warning control relay is used to receive the judgment signal output by the abnormal diagnosis module, and control the emergency stop button to be turned on or off according to the judgment signal, so as to control the opening or closing of the injection system and the engine system; the other output end of the fault warning control relay is connected to the audible and visual alarm device, which is used to issue a warning through the audible and visual alarm to facilitate the operator to perform fault troubleshooting.

[0059] The fault warning module uses a rising edge trigger instruction to control the console of the steam generator system and the console of the engine system to achieve emergency shutdown.

[0060] This embodiment of the real-time fault warning system uses a classifier trained using existing simulation test data. During system operation, the abnormality diagnosis module performs real-time analysis and diagnosis of key system parameters at different operating stages. This module performs segmented assessments of key parameters at different times, including during the igniter startup phase, softened water inlet phase, steam generator startup phase, and steam generator stabilization phase. If the abnormality diagnosis module determines a system fault has occurred, it issues a fault warning within 30 milliseconds. The module then sends an automatic emergency shutdown command to both the steam generator system console and the engine system console, triggering an audible and visual alarm system to alert the test commander to prepare for subsequent actions.

[0061] See also Figure 4 The working process of the above-mentioned liquid attitude and orbit control engine high-altitude simulation test real-time fault warning system includes the following steps:

[0062] S1. Obtain classifiers for each operating stage

[0063] The existing simulation test data is used, and the data comes from the state parameter data of each operation stage in the existing test data of the high-altitude simulation test of the liquid attitude and orbit control engine; the data is divided into corresponding training sets according to the operation stage, and the training sets are trained to obtain the classifiers corresponding to each operation stage; specifically, each operation stage includes the igniter starting stage, the softened water entering stage, the steam generator starting stage and the steam generator stabilization stage, and the state parameter data of each operation stage in the existing test data are divided into corresponding training sets according to the four control intervals of [0s,3s), [3s,5s), [5s,10s), and [10s,+∞). For each operation stage The classifier training is performed based on the key parameters of the igniter. The obtained classifiers include an igniter starting segment classifier, a softened water inlet segment classifier, a steam generator starting segment classifier, and a steam generator stable segment classifier. In this embodiment, the interval [0s, 3s) is used to judge the three parameters of oxygen pre-spray pressure, ignition alcohol pre-spray pressure, and ignition alcohol flow rate. The interval [3s, 5s) is used to judge the three parameters of softened water pre-spray pressure, softened water flow rate, and steam temperature. The interval [5s, 10s) is used to judge the four parameters of liquid oxygen pre-spray pressure, alcohol pre-spray pressure, steam pressure, and steam temperature. The interval [10s, +∞) is used to judge the three parameters of softened water flow rate, softened water pre-spray pressure, and steam temperature.

[0064] S2. Start the liquid attitude and orbit control engine and the steam generator system;

[0065] S3, using the real-time monitoring module to collect data from each measurement sensor in real time to obtain the current moment parameter set data;

[0066] S4, see Figure 5 Based on the anomaly detection algorithm, the anomaly diagnosis module is used to select the corresponding classifier according to the operation stage corresponding to the current parameter set data. The current parameter set data in step S3 is input into the corresponding classifier, and the classifier calculates the credibility C of the current parameter set data. θ (x), the calculation formula is as follows:

[0067] C θ (x) = f θ (x 1 )f θ (x 2 ) …f θ (x n )

[0068] Among them, θ is the probability density parameter after training, n is the number of data in the parameter set data at the current moment, and f θ (x) is the probability density function of each data in the current parameter time set data;

[0069] If C θ(x)>λ, then the parameter set data at the current moment is normal, and step S7 is executed;

[0070] If C θ (x)≤λ, then the parameter set data at the current moment is abnormal, and step S5 is executed; λ is the confidence threshold of the classifier after training corresponding to the parameter set data at the current moment;

[0071] S5. If the parameter set data are abnormal for three consecutive times, it is determined that the steam generator system is faulty, and a fault signal is sent to the fault warning module, and step S6 is executed; if the number of consecutive abnormal parameter set data is less than 3, return to step S3;

[0072] S6, the fault warning module shuts down the ejection system and liquid attitude and orbit control engine in an emergency according to the fault signal;

[0073] S7. Return to step S3 and monitor the operation of the steam generator system in real time until the test is completed.

[0074] This embodiment also provides a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the method for real-time fault warning of a high-altitude simulation test of a liquid attitude and orbit control engine is implemented. An electronic device is also provided, including a processor and a memory. The memory is used to store executable instructions of the processor, and the processor executes the executable instructions to implement the method for real-time fault warning of a high-altitude simulation test of a liquid attitude and orbit control engine.

Claims

1. A real-time fault warning system for high-altitude simulation tests of liquid attitude and orbit control engines, used to monitor the steam generator system in real time to monitor the working status of the ejection system, characterized by: Including real-time monitoring module, abnormal diagnosis module and fault warning module; The real-time monitoring module includes a real-time data acquisition unit and a plurality of measurement sensors connected to the steam generator system; the real-time data acquisition unit collects real-time data from each measurement sensor to obtain parameter set data and outputs it to the abnormality diagnosis module; The abnormality diagnosis module performs data analysis on the parameter set data, selects a corresponding classifier according to the corresponding operation stage, and uses the abnormality detection algorithm to calculate the credibility of the parameter set data at the current moment, compares it with the credibility threshold of the trained classifier corresponding to the parameter set data at the current moment, and outputs a judgment signal; the operation stage includes the igniter startup stage, the softened water inlet stage, the steam generator startup stage, and the steam generator stabilization stage; The fault warning module is used to receive the abnormal diagnosis result of the abnormal diagnosis module and send an emergency shutdown signal.

2. The real-time fault warning system for high-altitude simulation test of liquid attitude and orbit control engine according to claim 1 is characterized by: The abnormality diagnosis module includes an I / O card relay and a three-out-of-two voting circuit connected in series with the I / O card relay, the three-out-of-two voting circuit being used to receive the output signal of the I / O card relay and perform three-out-of-two voting; The three-out-of-two voting circuit includes a first double-pole double-throw switch, a second double-pole double-throw switch, and a third double-pole double-throw switch. The input end of the first double-pole double-throw switch and the first channel input end of the second double-pole double-throw switch are both connected to the power supply end. The output end of the first double-pole double-throw switch is connected to the second channel input end of the second double-pole double-throw switch and the second channel input end of the third double-pole double-throw switch. The second channel output end of the second double-pole double-throw switch is connected to the second channel output end of the third double-pole double-throw switch and is connected to the input end of the fault warning module for outputting a signal to the fault warning module. The control ends of the first double-pole double-throw switch, the second double-pole double-throw switch, and the third double-pole double-throw switch are all connected to the I / O board relay to receive the output signal of the I / O board relay. The first channel output end of the second double-pole double-throw switch is connected to the first channel input end of the third double-pole double-throw switch, and the first channel output end of the third double-pole double-throw switch is connected to the input end of the fault warning module.

3. The real-time fault warning system for high-altitude simulation test of liquid attitude and orbit control engine according to claim 2 is characterized by: The fault warning module includes an audible and visual alarm device, a fault warning control relay and an emergency stop button; the input end of the fault warning control relay is connected to the output end of the three-out-of-two voting circuit, and one output end of the fault warning control relay is connected to the emergency stop button; The fault warning control relay is used to receive the judgment signal output by the abnormal diagnosis module and control the emergency stop button to be on or off according to the judgment signal, so as to control the opening or closing of the ejector system and the engine system; Another output terminal of the fault warning control relay is connected to an audible and visual alarm device for issuing an early warning through an audible and visual alarm.

4. The real-time fault warning system for high-altitude simulation test of liquid attitude and orbit control engine according to any one of claims 1 to 3, characterized in that: The measuring sensor is a high-precision sensor, and the accuracy of the measuring sensor is better than 2‰.

5. The real-time fault warning system for high-altitude simulation test of liquid attitude and orbit control engine according to claim 4 is characterized by: The abnormality diagnosis module is connected to an external server and is used to make the access to the real-time fault warning system of the liquid attitude and orbit control engine high-altitude simulation test lightweight.

6. A real-time fault warning method for high-altitude simulation test of liquid attitude and orbit control engine, characterized in that: The real-time fault warning system for high-altitude simulation tests of liquid attitude and orbit control engines according to claim 1 comprises the following steps: S1. Obtain classifiers for each running stage Existing simulation test data is used and divided into corresponding training sets according to the operation stages. The training sets are trained using an anomaly detection algorithm to obtain classifiers corresponding to each operation stage. Each operation stage includes the igniter startup stage, the softened water inlet stage, the steam generator startup stage, and the steam generator stabilization stage. The corresponding classifiers include the igniter startup stage classifier, the softened water inlet stage classifier, the steam generator startup stage classifier, and the steam generator stabilization stage classifier. S2, start the steam generator system; S3. Using the real-time monitoring module to collect data from each measurement sensor in real time to obtain the parameter set data at the current moment; S4, based on the anomaly detection algorithm, using the anomaly diagnosis module, select the corresponding classifier according to the operation stage corresponding to the current moment parameter set data, input the current moment parameter set data in step S3 into the corresponding classifier, and the classifier calculates the credibility C of the current moment parameter set data. θ (x), the calculation formula is as follows: C θ (x)=f θ (x 1 )f θ (x 2 )…f θ (x n ) Among them, θ is the probability density parameter after training, n is the number of data in the parameter set data at the current moment, and f θ (x) is the probability density function of each data in the current parameter time set data; If C θ (x)>λ, then the parameter set data at the current moment is normal, and step S7 is executed; If C θ (x)≤λ, then the parameter set data at the current moment is abnormal, and step S5 is executed; λ is the confidence threshold of the classifier after training corresponding to the parameter set data at the current moment; S5. If the parameter set data are abnormal for three consecutive times, it is determined that the steam generator system is faulty, and a fault signal is sent to the fault warning module, and step S6 is executed; if the number of consecutive abnormal parameter set data is less than 3, step S7 is executed; S6, the fault warning module shuts down the ejection system and the engine system in an emergency according to the fault signal; S7. Return to step S3 and monitor the operation of the steam generator system in real time until the test is completed.

7. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by the processor, the real-time fault warning method for high-altitude simulation test of liquid attitude and orbit control engine described in claim 6 is implemented.

8. An electronic device comprising a processor and a memory, wherein the memory is configured to store executable instructions of the processor, wherein: The processor executes the executable instructions to implement the real-time fault warning method for high-altitude simulation test of liquid attitude and orbit control engine according to claim 6.

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