Fault diagnosis and fault processing method for pressurization system of carrier rocket

Abstract

The invention provides a fault diagnosis and fault processing method for a pressurization system of a carrier rocket, and belongs to the technical field of rocket fault analysis. The system comprises a temperature control autonomous supercharger, a first / second cold helium tank, an inlet valve, a first / second / third supercharging electromagnetic valve, a temperature sensor, a plurality of groups of pressure sensors, a liquid oxygen tank, a liquid oxygen tank safety valve, a liquid oxygen tank exhaust valve and a supercharging diagnosis controller. Wherein the temperature control autonomous supercharger is connected with the liquid oxygen tank through an inlet valve and a first supercharging electromagnetic valve, and the two cold helium gas cylinders are connected with the liquid oxygen tank through a pipeline with a throttling ring and a corresponding electromagnetic valve; the multiple sets of sensors monitor the states of all the branches, and the pressurization diagnosis controller is electrically connected with all the components to control the branches to work. According to the system, the size is reduced through a simplified redundant framework of temperature control self-generation pressurization and double cold helium cylinders, the reliability is improved through multi-branch backup, full-dimension monitoring and a safety device, meanwhile, helium consumption is reduced, and the system is suitable for a carrier rocket liquid oxygen tank pressurization scene.

Description

Technical Field

[0001] This invention relates to the field of rocket fault analysis technology, and in particular to a fault diagnosis and fault handling method for a launch vehicle pressurization system. Background Technology

[0002] The pressurization system of a launch vehicle is used to provide the pressure of the gas cushion in the liquid rocket propellant tank to meet the working pressure of the propellant inlet required during engine start-up and flight. However, to simultaneously ensure long distance and high efficiency, as well as the structural strength and rigidity requirements of the tank, the pressurization pressure cannot be too high. Therefore, the pressure control and diagnostic technology of the pressurization system is particularly important. Currently, the main working process of the launch vehicle pressurization system is as follows: pressurized gas enters the propellant tank, expands, occupies the space where the propellant is discharged, and applies working pressure to the liquid propellant.

[0003] Currently, liquid oxygen and kerosene propellants are the main propellants used in the aerospace field. The liquid oxygen tank pressurization method employed includes a gas-storage pressurization system with independently stored pressurization medium, primarily helium. However, to ensure the reliability of the pressurization system and meet the requirements of long-endurance flight while utilizing helium pressurization, three redundant helium pressurization systems need to be designed. This results in a relatively large overall size of the pressurization system and a higher risk of system failure. Summary of the Invention

[0004] In view of this, the present invention provides a method for fault diagnosis and fault handling of launch vehicle pressurization systems, in order to solve the problems of the current launch vehicle pressurization systems being large in size and having low reliability.

[0005] The technical solution adopted in this invention is: In a first aspect, the present invention provides a launch vehicle pressurization system, comprising a temperature-controlled autonomous pressurizer, an inlet valve, a pressurizer pressure sensor, a temperature sensor, a first cold helium cylinder, a second cold helium cylinder, a first pressurization solenoid valve, a second pressurization solenoid valve, a third pressurization solenoid valve, a first pressurization outlet pressure sensor, a second pressurization outlet pressure sensor, a third pressurization outlet pressure sensor, a liquid oxygen tank, a liquid oxygen tank pressure sensor group, a liquid oxygen tank safety valve, a liquid oxygen tank exhaust valve, a liquid oxygen tank backup exhaust valve, and a pressurization diagnostic controller; The inlet of the temperature-controlled autonomous booster is connected to the liquid oxygen tank through the inlet valve, and the outlet of the temperature-controlled autonomous booster is connected to the liquid oxygen tank through the first booster solenoid valve. The temperature sensor is located inside the temperature-controlled autonomous booster; the booster pressure sensor is located in the outlet pipeline of the temperature-controlled autonomous booster; the first booster outlet pressure sensor is located in the outlet pipeline of the first booster solenoid valve. The outlet of the first cold helium cylinder is connected to the liquid oxygen tank through the second pressure boosting solenoid valve, and the outlet of the second cold helium cylinder is connected to the liquid oxygen tank through the third pressure boosting solenoid valve. Throttling coils are provided on the pipelines between the two cold helium cylinders and the corresponding pressure boosting solenoid valves. The second pressure boosting outlet pressure sensor is located in the outlet pipeline of the second pressure boosting solenoid valve, and the third pressure boosting outlet pressure sensor is located in the outlet pipeline of the third pressure boosting solenoid valve. The liquid oxygen tank pressure sensor group is used to collect the pressure inside the liquid oxygen tank when the first cold helium cylinder and the second cold helium cylinder are pressurized respectively; the liquid oxygen tank safety valve is located in the main pressurization pipeline of the liquid oxygen tank, and the liquid oxygen tank exhaust valve is connected to the liquid oxygen tank. The booster diagnostic controller is electrically connected to the inlet valve, the temperature-controlled self-boosting unit, the temperature sensor, the booster pressure sensor, the third booster outlet pressure sensor, the first booster solenoid valve, the second booster solenoid valve, the second booster outlet pressure sensor, the third booster solenoid valve, the first booster outlet pressure sensor, the liquid oxygen tank safety valve, the liquid oxygen tank exhaust valve, the liquid oxygen tank backup exhaust valve, and the liquid oxygen tank pressure sensor group.

[0006] Furthermore, the booster diagnostic controller has three built-in CPU units: a first CPU unit, a second CPU unit, and a third CPU unit, which are independent of each other and communicate via an onboard CAN bus; wherein, The first CPU unit is electrically connected to the inlet valve, the temperature-controlled autonomous booster, the temperature sensor, the booster pressure sensor, the third booster outlet pressure sensor, the first booster solenoid valve, and the liquid oxygen tank pressure sensor group, respectively. The second CPU unit is electrically connected to the second booster solenoid valve, the second booster outlet pressure sensor, and the liquid oxygen tank pressure sensor group, respectively. The third CPU unit is electrically connected to the third booster solenoid valve, the first booster outlet pressure sensor, and the liquid oxygen tank pressure sensor group, respectively.

[0007] Furthermore, the liquid oxygen tank pressure sensor group includes a first liquid oxygen tank pressure sensor, a second liquid oxygen tank pressure sensor, and a third liquid oxygen tank pressure sensor; wherein, The first liquid oxygen tank pressure sensor is electrically connected to the first CPU unit and is used to collect the liquid oxygen tank pressure when the temperature-controlled autonomous pressurizer is autonomously pressurizing. The second liquid oxygen tank pressure sensor is electrically connected to the second CPU unit and is used to collect the liquid oxygen tank pressure when the first cold helium cylinder is pressurized. The third liquid oxygen tank pressure sensor is electrically connected to the third CPU unit and is used to collect the liquid oxygen tank pressure when the second cold helium cylinder is pressurized.

[0008] Secondly, the present invention also provides a method for fault diagnosis and fault handling of a launch vehicle pressurization system as described in the first aspect, the method comprising: S1: The booster diagnostic controller receives the booster start command from the rocket engine. The first CPU unit starts the temperature-controlled autonomous booster to boost the pressure, opens the inlet valve to allow liquid oxygen to enter, and at the same time controls the heating coil of the temperature-controlled autonomous booster to work to raise the internal temperature T1 of the temperature-controlled autonomous booster to the target temperature T0. S2: The first CPU unit performs multi-dimensional fault diagnosis, specifically including: S21: Perform heating coil abnormality diagnosis, calculate the theoretical heating current If according to the first current diagnosis formula, and if the actual collected current deviates from the heating coil If by more than ±10%, the heating coil is determined to be abnormal. S22: Heating timeout diagnosis. Calculate the theoretical heating time t according to the target time calculation formula. If the actual heating time is greater than 1.5 times the theoretical heating time t, and the heating temperature has not reached the target temperature T0, then heating timeout is determined. S23: Pressure build-up timeout diagnosis. The outlet pressure P1 of the temperature-controlled autonomous booster is collected by the booster pressure sensor. If P1 does not reach the target pressure within the preset time... If the pressure build-up timeout occurs, then the pressure build-up timeout is determined; if the target pressure is reached within the preset time, then the pressure build-up timeout is determined. Then, the first pressurization solenoid valve is opened to automatically pressurize the liquid oxygen tank. S24: Diagnosis of abnormal current of the first booster solenoid valve. Collect the drive current of the first booster solenoid valve. If the first drive current is greater than 1.2 times the rated current or less than 0.8 times the rated current, the current of the first booster solenoid valve is determined to be abnormal. S25: Diagnosis of failure to establish opening pressure for the first booster solenoid valve. If the liquid oxygen tank pressure does not rise to the target pressure within 10 seconds after the first booster solenoid valve opens. If the first booster solenoid valve is found to be abnormally open, then the liquid oxygen tank pressure is determined to be abnormal within 10 seconds after the first booster solenoid valve opens. If the pressure increase is successful, the closed-loop pressure increase control will end. S3: If any diagnosis in S2 is abnormal, the first CPU unit determines that the temperature control autonomous boosting branch has failed to boost, records the fault type, and synchronizes the fault abnormality information to the second CPU unit.

[0009] Furthermore, the method includes: Step 1: After the first CPU unit determines that the temperature-controlled autonomous booster branch has failed to boost pressure, it shuts down the first booster solenoid valve, the inlet valve, and the heating coil of the temperature-controlled autonomous booster. Step 2: The first CPU unit sends a helium pressurization command to the second CPU unit. After the second CPU unit confirms that the temperature control autonomous pressurization branch valve is closed, it opens the second pressurization solenoid valve, allowing the helium in the first cold helium cylinder to enter the liquid oxygen tank through the throttling coil. Step 3: The second CPU unit collects the second driving current of the second booster solenoid valve in real time. If the second driving current exceeds the rated current ±15%, the boosting of the first cold helium cylinder branch is determined to be a failure; if the second driving current does not exceed the rated current ±15%, proceed to step 4. Step 4: The second CPU unit collects the pressure P3 at the outlet of the first cold helium cylinder in real time. If P3 does not reach the target pressure within the preset time, the unit will take action. If the pressure build-up timeout is determined, the pressurization of the first cold helium cylinder branch fails; if P3 reaches the target pressure within the preset time... Then proceed to step 5; Step 5: If the liquid oxygen tank pressure P7 does not rise to the target pressure within 10 seconds after the second booster solenoid valve is opened. If the second booster solenoid valve is found to be abnormally open, the boosting of the first cold helium cylinder branch will fail; if the liquid oxygen tank pressure P7 rises to the target pressure within 10 seconds after the second booster solenoid valve opens. If the pressure increase is successful, the closed-loop pressure increase control will end.

[0010] Furthermore, the method also includes: Step 6: After the first cold helium cylinder branch pressurization fails, the second CPU unit closes the second pressurization solenoid valve and sends a helium pressurization command to the third CPU unit. Step 7: After the third CPU unit confirms that the branch valve of the first cold helium cylinder is closed, it opens the third pressurization solenoid valve to allow the helium in the second cold helium cylinder to enter the liquid oxygen tank through the throttling coil. Step 8: The third CPU unit collects the third driving current of the third booster solenoid valve in real time. If the third driving current exceeds the rated current ±15%, the booster of the second cold helium cylinder branch is determined to be in failure; if the third driving current does not exceed the rated current ±15%, proceed to step 9. Step 9: The third CPU unit collects the pressure P2 at the outlet of the second cold helium cylinder in real time. If P2 does not reach the target pressure within the preset time, the unit will take action. If the pressure build-up timeout is determined, the pressurization of the second cold helium cylinder branch fails; if P3 reaches the target pressure within the preset time... Then proceed to step 10; Step 10: If the liquid oxygen tank pressure P8 does not rise to the target pressure within 10 seconds after the third booster solenoid valve is opened. If the third booster solenoid valve is found to be abnormally open, the booster in the second cold helium cylinder branch will fail; if the liquid oxygen tank pressure P8 rises to the target pressure within 10 seconds after the third booster solenoid valve opens. If the pressure increase is successful, the closed-loop pressure increase control will end. Step 11: After the third CPU unit determines that the pressurization of the second cold helium cylinder branch has failed, it closes the third pressurization solenoid valve and sends an emergency handling signal to the rocket engine via the onboard bus. At the same time, it triggers the liquid oxygen tank exhaust valve to enter the pre-opening state.

[0011] In summary, the beneficial effects of the present invention are as follows: This invention designs a triple-redundant architecture consisting of a temperature-controlled autonomous booster branch, a first cold helium cylinder branch, and a second cold helium cylinder branch. The temperature-controlled autonomous booster replaces one helium system, reducing the triple-redundant architecture's dependence on helium and the number of helium cylinders, and compressing the overall volume of the booster system. In the triple redundancy architecture of this invention, each booster branch is independently controlled by the booster diagnostic controller, and key parameters such as temperature, pressure, and valve outlet pressure of each branch are collected in real time through multiple sensors. Through multi-dimensional sensing and monitoring, the faults of the booster system can be effectively monitored and located, thereby improving the reliability of the system. Attached Figure Description

[0012] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments of the present invention will be briefly introduced below. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort, and these are all within the protection scope of the present invention.

[0013] Figure 1 This is a schematic diagram of the launch vehicle pressurization system of the present invention; Figure 2 This is a schematic diagram of the internal structure of the booster diagnostic controller of the present invention; Figure 3 This is a flowchart of the fault diagnosis and fault handling method for the launch vehicle pressurization system of the present invention; Figure 4 This is a flowchart of the fault diagnosis and fault handling method for the launch vehicle pressurization system of the present invention; Appendix Figure 1 The components are as follows: 1. Rocket liquid oxygen / kerosene engine; 2. Inlet valve; 3. Temperature-controlled autonomous booster; 4. Booster diagnostic controller; 5. First booster solenoid valve; 6. Cold helium cylinder group; 601. First cold helium cylinder; 602. Second cold helium cylinder; 7. Second booster solenoid valve; 8. Third booster solenoid valve; 9. Liquid oxygen tank safety valve; 10. Liquid oxygen tank exhaust valve; 11. Liquid oxygen tank spare exhaust valve; 12. Temperature sensor; 13. Booster pressure sensor; 14. Third booster outlet pressure sensor; 15. Second booster outlet pressure sensor; 16. First booster outlet pressure sensor; 17. Liquid oxygen tank pressure gauge; 18. First liquid oxygen tank pressure sensor; 19. Second liquid oxygen tank pressure sensor; 20. Third liquid oxygen tank pressure sensor. Detailed Implementation

[0014] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Unless otherwise specified, the present invention and the various features in the embodiments can be combined with each other, all of which are within the protection scope of the present invention.

[0015] Currently, liquid oxygen and kerosene propellants are the main propellants in the aerospace field. There are three current methods for pressurizing oxygen tanks: (1) gas pressurization using engine combustion products as the pressurizing medium; (2) self-generated pressurization using rocket propellant evaporated and vaporized by the engine as the pressurizing medium; and (3) gas-storage pressurization equipped with an independent storage system for pressurizing medium, primarily helium. Self-generated pressurization relies on the engine's heat to evaporate and vaporize, requiring the engine to ignite before providing pressurization, and other pressures and temperatures during pressurization cannot be controlled. Using helium for pressurization requires a large amount of helium. To ensure the reliability of the pressurization system while meeting the demands of long-endurance flight, existing designs employ a helium pressurization system with three redundant structures. This necessitates a larger space to accommodate more helium cylinders, and the corresponding valves, pipelines, orifice plates must all be compatible to meet the requirements. Helium is a well-known and irreplaceable key element in modern high-tech industries, and is considered an important strategic resource. my country's helium resources are extremely scarce. It is estimated that the total helium resources amount to approximately 1.1 billion cubic meters, of which only about 0.5 billion cubic meters are directly recoverable, less than 0.1% of global reserves. Reducing helium usage is crucial for lowering rocket costs and reducing rocket mass.

[0016] Meanwhile, the pressurization system is a critical system in the propulsion system, affecting engine operation and thus the entire rocket's flight. The pressurization system is complex and highly sensitive to failure; a malfunction can have a fatal impact on mission completion. Statistics from various US launch vehicles indicate that pressurization system failures account for over 60% of all spacecraft failures, including launch vehicles. Especially for the second-stage pressurization system, which requires multiple engine ignitions, any anomalies or malfunctions that cannot be addressed promptly can lead to launch failure. Improving the reliability and fault handling capabilities of pressurization systems is an urgent and challenging research focus, and applying fault diagnosis and redundant fault handling schemes to pressurization systems has become a development trend.

[0017] Therefore, this invention designs a fault diagnosis and troubleshooting method for a launch vehicle pressurization system. The method employs a redundant parallel pressurization system with temperature-controlled heating self-generated pressurization and helium-assisted pressurization, and ensures the reliability of the pressurization system through a pressurization diagnostic controller 4. The detailed implementation process of this invention is shown in the following embodiments.

[0018] Example 1: Refer to Figure 1 As shown, Figure 1 This is a block diagram illustrating the principle of a launch vehicle pressurization system according to the present invention. The launch vehicle pressurization system in this embodiment includes a temperature-controlled autonomous pressurizer 3, an inlet valve 2, a pressurizer pressure sensor 13, a temperature sensor 12, a first cold helium cylinder, a second cold helium cylinder, a first pressurization solenoid valve 5, a second pressurization solenoid valve 7, a third pressurization solenoid valve 8, a first pressurization outlet pressure sensor 16, a second pressurization outlet pressure sensor 15, a third pressurization outlet pressure sensor 14, a liquid oxygen tank, a liquid oxygen tank pressure sensor group, a liquid oxygen tank safety valve 9, a liquid oxygen tank exhaust valve 10, a liquid oxygen tank backup exhaust valve 11, and a pressurization diagnostic controller 4. Among these, The inlet of the temperature-controlled autonomous booster 3 is connected to the liquid oxygen tank through the inlet valve 2, and the outlet of the temperature-controlled autonomous booster 3 is connected to the liquid oxygen tank through the first booster solenoid valve 5; the liquid oxygen tank is connected to the rocket liquid oxygen kerosene engine 1.

[0019] Temperature sensor 12 is located inside temperature-controlled autonomous booster 3 to collect medium temperature; booster pressure sensor 13 is located in the outlet pipeline of temperature-controlled autonomous booster 3 to collect outlet pressure; first booster outlet pressure sensor 16 is located in the outlet pipeline of first booster solenoid valve 5 to collect real-time booster pressure P4 of branch of temperature-controlled autonomous booster 3.

[0020] The outlet of the first cold helium cylinder is connected to the liquid oxygen tank through the second pressurization solenoid valve 7, and the outlet of the second cold helium cylinder is connected to the liquid oxygen tank through the third pressurization solenoid valve 8. Throttling coils are installed on the pipelines between the two cold helium cylinders and their corresponding pressurization solenoid valves. The second pressurization outlet pressure sensor 15 is installed in the outlet pipeline of the second pressurization solenoid valve 7 to collect the pressurization outlet pressure P3 when the first cold helium cylinder is pressurized. The third pressurization outlet pressure sensor 14 is installed in the outlet pipeline of the third pressurization solenoid valve 8 to collect the pressurization outlet pressure P2 when the second cold helium cylinder is pressurized.

[0021] The liquid oxygen tank pressure sensor group is used to collect the pressure inside the liquid oxygen tank when the first cold helium cylinder and the second cold helium cylinder are pressurized respectively; the liquid oxygen tank safety valve 9 is located in the main pressurization pipeline of the liquid oxygen tank, and the liquid oxygen tank exhaust valve 10 is connected to the liquid oxygen tank.

[0022] The booster diagnostic controller 4 is electrically connected to the inlet valve 2, the temperature-controlled autonomous booster 3, the temperature sensor 12, the booster pressure sensor 13, the third booster outlet pressure sensor 14, the first booster solenoid valve 5, the second booster solenoid valve 7, the second booster outlet pressure sensor 15, the third booster solenoid valve 8, the first booster outlet pressure sensor 16, the liquid oxygen tank safety valve 9, the liquid oxygen tank exhaust valve 10, the liquid oxygen tank backup exhaust valve 11, and the liquid oxygen tank pressure sensor group.

[0023] The first and second cold helium cylinders can form a cold helium cylinder group 6, and the rated pressure of both the first and second cold helium cylinders is 35 MPa. The liquid oxygen tank is also equipped with a liquid oxygen tank pressure gauge 17 (i.e., corresponding to...). Figure 1 The pressure gauge 17 (P5 in the figure) is used to display the pressure inside the liquid oxygen tank in real time and provides direct monitoring data. It can serve as an independent pressure reference, cross-comparing the data collected by the pressure sensors in the liquid oxygen tank pressure sensor group. If its reading deviates from the digital data of the liquid oxygen tank pressure sensor group beyond a preset range, a faulty sensor (such as drift or failure) can be identified in a timely manner, avoiding misjudgments in pressurization control due to a single sensor error and ensuring the reliability of pressure monitoring data. In this embodiment, the pressurization system includes a backup liquid oxygen tank exhaust valve 11 as a backup for the liquid oxygen tank exhaust valve 10. The backup exhaust valve 11 and the liquid oxygen tank exhaust valve 10 open synchronously to prevent the liquid oxygen tank exhaust valve 10 from failing to close.

[0024] In this embodiment, refer to Figure 2 As shown, the booster diagnostic controller 4 has a first CPU unit (i.e., CPU1), a second CPU unit (i.e., CPU2), and a third CPU unit (i.e., CPU3) that are independent of each other and communicate via the onboard CAN bus.

[0025] The first CPU unit is electrically connected to the inlet valve 2, the temperature-controlled self-pressurizing unit 3, the temperature sensor 12, the pressurizing unit pressure sensor 13, the third pressurizing outlet pressure sensor 14, the first pressurizing solenoid valve 5, and the liquid oxygen tank pressure sensor group.

[0026] The second CPU unit is electrically connected to the second booster solenoid valve 7, the second booster outlet pressure sensor 15, and the liquid oxygen tank pressure sensor group, respectively.

[0027] The third CPU unit is electrically connected to the third booster solenoid valve 8, the first booster outlet pressure sensor 16, and the liquid oxygen tank pressure sensor group, respectively.

[0028] All three CPU units pass through a current detection unit (i.e. Figure 2 In section A), the corresponding electromagnetic current detection unit is connected to collect the magnitude of the solenoid valve's drive current.

[0029] In this embodiment, the liquid oxygen tank pressure sensor group includes a first liquid oxygen tank pressure sensor 18, a second liquid oxygen tank pressure sensor 19, and a third liquid oxygen tank pressure sensor 20; wherein... The first liquid oxygen tank pressure sensor 18 is electrically connected to the first CPU unit and is used to collect the liquid oxygen tank pressure P6 when the temperature-controlled autonomous pressurizer 3 is autonomously pressurizing.

[0030] The second liquid oxygen tank pressure sensor 19 is electrically connected to the second CPU unit and is used to collect the liquid oxygen tank pressure P7 when the first cold helium cylinder is pressurized.

[0031] The third liquid oxygen tank pressure sensor 20 is electrically connected to the third CPU unit and is used to collect the liquid oxygen tank pressure P8 when the second cold helium cylinder is pressurized.

[0032] Specifically, when the booster diagnostic controller 4 receives the booster start command, the CPU1 controls the liquid oxygen from the liquid oxygen tank to enter the temperature-controlled autonomous booster 3 by controlling the inlet valve 2 of the temperature-controlled autonomous booster 3, and controls the temperature of the temperature-controlled autonomous booster 3 to the target temperature T0 by controlling the heating coil. As the temperature of the autonomous booster increases, the liquid oxygen evaporates to produce gas, and the pressure increases. When the pressure P1 at the outlet of the autonomous booster exceeds the target temperature T0... The first pressurization solenoid valve 5 is opened to allow the liquid oxygen tank to be pressurized autonomously.

[0033] Specifically, in this embodiment, a liquid oxygen tank safety valve 9 is installed in the main line of the liquid oxygen tank pressurization pipeline, and a liquid oxygen tank exhaust valve 10 is installed in the liquid oxygen tank. If any branch pressurization exceeds the pressure (such as continuous pressurization caused by a stuck solenoid valve), the liquid oxygen tank safety valve 9 can automatically release pressure to prevent damage to the liquid oxygen tank due to excessive pressure. If all redundant branches fail, the liquid oxygen tank exhaust valve 10 can cooperate with the rocket engine emergency control to adjust the liquid oxygen tank pressure to a safe range, avoiding engine power supply interruption or rocket body structural risks due to pressurization failure. Together, they constitute the ultimate safety protection of the system, solving the reliability shortcomings of traditional systems that lack overpressure / emergency protection.

[0034] In this embodiment, a simplified and redundant architecture of a temperature-controlled autonomous booster 3 + dual-cooled helium cylinders is used to replace one traditional helium system with temperature-controlled autonomous booster. Combined with dual-cooled helium cylinders and optimized piping with throttling coils, compared to the redundant structure of the traditional 3-system helium system, one helium cylinder and 1 / 3 of the helium-related hardware are reduced, the system size is reduced, the reliability of the booster system is greatly improved, and the problem of the large size of the existing booster system is solved.

[0035] Example 2: Based on Example 1, this example further provides a method for fault diagnosis and troubleshooting of a launch vehicle pressurization system, referring to... Figure 3 As shown, the method includes: S1: The booster diagnostic controller 4 receives the booster start command from the rocket engine. The first CPU unit starts the temperature-controlled autonomous booster 3 to boost the pressure, opens the inlet valve 2 to allow liquid oxygen to enter, and at the same time controls the heating coil of the temperature-controlled autonomous booster 3 to work to raise the internal temperature of the temperature-controlled autonomous booster 3 to the target temperature T0. S2: The first CPU unit performs multi-dimensional fault diagnosis, specifically including: S21: Perform heating coil abnormality diagnosis, calculate the theoretical heating current If according to the first current diagnosis formula, and if the actual collected current deviates from the heating coil If by more than ±10%, the heating coil is determined to be abnormal. S22: Heating timeout diagnosis. Calculate the theoretical heating time t according to the target time calculation formula. If the actual heating time is greater than 1.5 times the theoretical heating time t, and the heating temperature has not reached the target temperature T0, then heating timeout is determined. S23: Pressure build-up timeout diagnosis. The outlet pressure P1 of the temperature-controlled autonomous booster 3 is collected by the booster pressure sensor 13. If P1 does not reach the target pressure within the preset time, the timeout will be determined. If the pressure build-up timeout occurs, then the pressure build-up timeout is determined; if the target pressure is reached within the preset time, then the pressure build-up timeout is determined. If the first booster solenoid valve 5 is opened, the liquid oxygen tank will be automatically pressurized. However, if the inlet valve 2 fails to open successfully or the booster leaks, the booster pressure will not be established. Given the evaporation characteristics of liquid oxygen, there is a significant risk that the booster outlet pressure may not be established within a certain timeframe; therefore, if the pressure establishment timeout is exceeded, the automatic pressurization is considered a failure.

[0036] S24: Diagnosis of abnormal current in the first booster solenoid valve 5. The drive current of the first booster solenoid valve 5 is collected. If the first drive current is greater than 1.2 times the rated current or less than 0.8 times the rated current, the current of the first booster solenoid valve 5 is determined to be abnormal. The principle of current abnormality judgment is to check the solenoid valve coil and then collect the drive current of the current valve. If it is not within a certain range (short circuit or open circuit in the solenoid valve), the solenoid valve current is determined to be abnormal.

[0037] S25: Diagnosis of failure to establish opening pressure for the first booster solenoid valve 5. If the liquid oxygen tank pressure does not rise to the target pressure within 10 seconds after the first booster solenoid valve 5 opens. If the first booster solenoid valve 5 is found to be abnormally open, then the liquid oxygen tank pressure is determined to be abnormal within 10 seconds after the first booster solenoid valve 5 is opened. If the pressure increase is successful, the closed-loop pressure increase control will end. S3: If any diagnosis in S2 is abnormal, the first CPU unit determines that the temperature control autonomous boosting branch has failed to boost, records the fault type, and synchronizes the fault abnormality information to the second CPU unit.

[0038] Specifically, the first CPU unit primarily diagnoses the potential failure of the entire pressurization process during the temperature-controlled autonomous pressurization system's pressurization control. An abnormal heating coil may cause instability in the rocket's electrical system and even lead to localized overheating; therefore, current diagnosis of the heating coil is necessary. The resistance of the heating coil changes to a certain extent with temperature variations. Therefore, when diagnosing heating coil abnormalities, the theoretical heating current If is calculated using the first current diagnosis formula. If the actual sampled current deviates from the theoretical heating current If by more than ±10%, the heating coil is considered abnormal. The specific first current diagnosis formula is shown below: .

[0039] Where Ri is the coil resistance at the initial coil temperature; Ti is the initial coil temperature; Tf is the current coil temperature; and U is the heating voltage of the heating coil. If the actual current sampled deviates from the calculated heating current by a certain value (e.g., ±10%), the heating coil is considered abnormal.

[0040] During the heating timeout diagnosis process, the theoretical heating target time t can be calculated based on the current volume of the temperature-controlled self-pressurizing unit 3, the specific heat of the medium, and the power of the heater.

[0041] Where C represents the heat capacity of liquid oxygen, m represents the mass of liquid oxygen in the temperature-controlled autonomous booster, t2 represents the final heating time, t1 represents the initial heating time, and P represents the booster pressure.

[0042] If the theoretical heating time t exceeds a certain value of the calculated time, and the heating temperature has not reached the current temperature T0, then the heating is judged to have exceeded the time limit.

[0043] The second CPU unit (CPU2) is responsible for helium pressurization control. CPU2 maintains communication with CPU1 through internal communication. When a pressurization failure is detected in CPU1, CPU2 controls the second pressurization solenoid valve 7 at the outlet of the first cold helium cylinder to open. It also collects the pressurization pressure at the outlet of the first cold helium cylinder through the second pressurization outlet pressure sensor 15 and collects the pressure inside the liquid oxygen tank through the second liquid oxygen tank pressure sensor 19. CPU2 also has current diagnosis and pressurization pressure diagnosis for the pressurization valve. If the pressurization of the second CPU unit fails, it sends a pressurization command to the third CPU unit (CPU3) to activate the backup helium pressurization control.

[0044] In this embodiment, refer to Figure 4 As shown, when the temperature-controlled autonomous pressurizer branch (the branch where the first CPU unit is located) fails to pressurize, the system automatically switches to the first cold helium cylinder branch (the branch where the second CPU unit is located) for pressurization. The specific process is as follows: Step 1: After the first CPU unit determines that the temperature-controlled autonomous booster branch has failed to boost pressure, it shuts off the heating coils of the first booster solenoid valve 5, the inlet valve 2, and the temperature-controlled autonomous booster 3. Step 2: The first CPU unit sends a helium pressurization command to the second CPU unit. After the second CPU unit confirms that the temperature control autonomous pressurization branch valve is closed, it opens the second pressurization solenoid valve 7, so that the helium in the first cold helium cylinder enters the liquid oxygen tank through the throttling ring. Step 3: The second CPU unit collects the second driving current of the second booster solenoid valve 7 in real time. If the second driving current exceeds the rated current ±15%, the boosting of the first cold helium cylinder branch is determined to be a failure; if the second driving current does not exceed the rated current ±15%, proceed to step 4. Step 4: The second CPU unit collects the pressure P3 at the outlet of the first cold helium cylinder in real time. If P3 does not reach the target pressure within the preset time, the unit will take action. If the pressure build-up timeout is determined, the pressurization of the first cold helium cylinder branch fails; if P3 reaches the target pressure within the preset time... Then proceed to step 5; Step 5: If the liquid oxygen tank pressure P7 does not rise to the target pressure within 10 seconds after the second booster solenoid valve 7 is opened. If the second booster solenoid valve 7 is found to be abnormally open, the boosting of the first cold helium cylinder branch will fail; if the liquid oxygen tank pressure P7 rises to the target pressure within 10 seconds after the second booster solenoid valve 7 is opened. If the pressure increase is successful, the closed-loop pressure increase control will end.

[0045] In this embodiment, after the pressurization of the second CPU unit fails, the method activates the backup helium pressurization branch where the third CPU unit is located to pressurize. The method specifically includes: Step 6: After the first cold helium cylinder branch pressurization fails, the second CPU unit closes the second pressurization solenoid valve 7 and sends a helium pressurization command to the third CPU unit. Step 7: After the third CPU unit confirms that the branch valve of the first cold helium cylinder is closed, it opens the third pressurization solenoid valve 8 to allow the helium in the second cold helium cylinder to enter the liquid oxygen tank through the throttling coil. Step 8: The third CPU unit collects the third driving current of the third booster solenoid valve 8 in real time. If the third driving current exceeds the rated current ±15%, the booster of the second cold helium cylinder branch is determined to be in failure; if the third driving current does not exceed the rated current ±15%, proceed to step 9. Step 9: The third CPU unit collects the pressure P2 at the outlet of the second cold helium cylinder in real time. If P2 does not reach the target pressure within the preset time, the unit will take action. If the pressure build-up timeout is determined, the pressurization of the second cold helium cylinder branch fails; if P3 reaches the target pressure within the preset time... Then proceed to step 10; Step 10: If the liquid oxygen tank pressure P8 does not rise to the target pressure within 10 seconds after the third booster solenoid valve 8 is opened. If the third pressurization solenoid valve 8 is found to be abnormally open, the pressurization of the second cold helium cylinder branch will fail; if the liquid oxygen tank pressure P8 rises to the target pressure within 10 seconds after the third pressurization solenoid valve 8 opens. If the pressure increase is successful, the closed-loop pressure increase control will end. Step 11: After the third CPU unit determines that the pressurization of the second cold helium cylinder branch has failed, it closes the third pressurization solenoid valve 8 and sends an emergency handling signal to the rocket engine via the onboard bus. At the same time, it triggers the liquid oxygen tank exhaust valve 10 to enter the ready-to-open state. After the oxygen tank exhaust valve enters the ready-to-open state, the CPU3 will continuously send a ready status signal of the exhaust valve to the rocket engine until the rocket engine issues an opening or cancellation command.

[0046] Specifically, this embodiment prioritizes using a temperature-controlled self-generating pressurizer to pressurize the launch vehicle, reducing the amount of helium used and lowering the helium demand. At the same time, this embodiment has automatic pressurization control and automatic fault handling functions for automatic diagnostics, reducing the complexity of use and improving the reliability of use.

[0047] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A launch vehicle pressurization system, characterized in that, Includes a temperature-controlled autonomous booster, inlet valve, booster pressure sensor, temperature sensor, first cold helium cylinder, second cold helium cylinder, first booster solenoid valve, second booster solenoid valve, third booster solenoid valve, first booster outlet pressure sensor, second booster outlet pressure sensor, third booster outlet pressure sensor, liquid oxygen tank, liquid oxygen tank pressure sensor group, liquid oxygen tank safety valve, liquid oxygen tank exhaust valve, liquid oxygen tank spare exhaust valve, and booster diagnostic controller; The inlet of the temperature-controlled autonomous booster is connected to the liquid oxygen tank through the inlet valve, and the outlet of the temperature-controlled autonomous booster is connected to the liquid oxygen tank through the first booster solenoid valve. The temperature sensor is located inside the temperature-controlled autonomous booster; the booster pressure sensor is located in the outlet pipeline of the temperature-controlled autonomous booster; the first booster outlet pressure sensor is located in the outlet pipeline of the first booster solenoid valve. The outlet of the first cold helium cylinder is connected to the liquid oxygen tank through the second pressure boosting solenoid valve, and the outlet of the second cold helium cylinder is connected to the liquid oxygen tank through the third pressure boosting solenoid valve. Throttling coils are provided on the pipelines between the two cold helium cylinders and the corresponding pressure boosting solenoid valves. The second pressure boosting outlet pressure sensor is located in the outlet pipeline of the second pressure boosting solenoid valve, and the third pressure boosting outlet pressure sensor is located in the outlet pipeline of the third pressure boosting solenoid valve. The liquid oxygen tank pressure sensor group is used to collect the pressure inside the liquid oxygen tank when the first cold helium cylinder and the second cold helium cylinder are pressurized respectively; the liquid oxygen tank safety valve is located in the main pressurization pipeline of the liquid oxygen tank, and the liquid oxygen tank exhaust valve is connected to the liquid oxygen tank. The booster diagnostic controller is electrically connected to the inlet valve, the temperature-controlled self-boosting unit, the temperature sensor, the booster pressure sensor, the third booster outlet pressure sensor, the first booster solenoid valve, the second booster solenoid valve, the second booster outlet pressure sensor, the third booster solenoid valve, the first booster outlet pressure sensor, the liquid oxygen tank safety valve, the liquid oxygen tank exhaust valve, the liquid oxygen tank backup exhaust valve, and the liquid oxygen tank pressure sensor group.

2. The launch vehicle pressurization system according to claim 1, characterized in that, The booster diagnostic controller has three built-in CPU units: a first CPU unit, a second CPU unit, and a third CPU unit, which are independent of each other and communicate via an onboard CAN bus; wherein... The first CPU unit is electrically connected to the inlet valve, the temperature-controlled autonomous booster, the temperature sensor, the booster pressure sensor, the third booster outlet pressure sensor, the first booster solenoid valve, and the liquid oxygen tank pressure sensor group, respectively. The second CPU unit is electrically connected to the second booster solenoid valve, the second booster outlet pressure sensor, and the liquid oxygen tank pressure sensor group, respectively. The third CPU unit is electrically connected to the third booster solenoid valve, the first booster outlet pressure sensor, and the liquid oxygen tank pressure sensor group, respectively.

3. The launch vehicle pressurization system according to claim 1, characterized in that, The liquid oxygen tank pressure sensor group includes a first liquid oxygen tank pressure sensor, a second liquid oxygen tank pressure sensor, and a third liquid oxygen tank pressure sensor; wherein... The first liquid oxygen tank pressure sensor is electrically connected to the first CPU unit and is used to collect the liquid oxygen tank pressure when the temperature-controlled autonomous pressurizer is autonomously pressurizing. The second liquid oxygen tank pressure sensor is electrically connected to the second CPU unit and is used to collect the liquid oxygen tank pressure when the first cold helium cylinder is pressurized. The third liquid oxygen tank pressure sensor is electrically connected to the third CPU unit and is used to collect the liquid oxygen tank pressure when the second cold helium cylinder is pressurized.

4. A method for fault diagnosis and fault handling of the pressurization system of a launch vehicle according to any one of claims 1 to 3, characterized in that, The method includes: S1: The booster diagnostic controller receives the booster start command from the rocket engine. The first CPU unit starts the temperature-controlled autonomous booster to boost the pressure, opens the inlet valve to allow liquid oxygen to enter, and at the same time controls the heating coil of the temperature-controlled autonomous booster to work to raise the internal temperature of the temperature-controlled autonomous booster to the target temperature T0. S2: The first CPU unit performs multi-dimensional fault diagnosis, specifically including: S21: Perform heating coil abnormality diagnosis, calculate the theoretical heating current If according to the first current diagnosis formula, and if the actual collected current deviates from the heating coil If by more than ±10%, the heating coil is determined to be abnormal. S22: Heating timeout diagnosis. Calculate the theoretical heating time t according to the target time calculation formula. If the actual heating time is greater than 1.5 times the theoretical heating time t, and the heating temperature has not reached the target temperature T0, then heating timeout is determined. S23: Pressure build-up timeout diagnosis. The outlet pressure P1 of the temperature-controlled autonomous booster is collected by the booster pressure sensor. If P1 does not reach the target pressure within the preset time... If the pressure build-up timeout occurs, then the pressure build-up timeout is determined; if the target pressure is reached within the preset time, then the pressure build-up timeout is determined. t Then, the first pressurization solenoid valve is opened to automatically pressurize the liquid oxygen tank. S24: Diagnosis of abnormal current of the first booster solenoid valve. Collect the drive current of the first booster solenoid valve. If the first drive current is greater than 1.2 times the rated current or less than 0.8 times the rated current, the current of the first booster solenoid valve is determined to be abnormal. S25: Diagnosis of failure to establish opening pressure for the first booster solenoid valve. If the liquid oxygen tank pressure does not rise to the target pressure within 10 seconds after the first booster solenoid valve opens. If the first booster solenoid valve is found to be abnormally open, then the liquid oxygen tank pressure is determined to be abnormal within 10 seconds after the first booster solenoid valve opens. If the pressure increase is successful, the closed-loop pressure increase control will end. S3: If any diagnosis in S2 is abnormal, the first CPU unit determines that the temperature control autonomous boosting branch has failed to boost, records the fault type, and synchronizes the fault abnormality information to the second CPU unit.

5. The method for fault diagnosis and fault handling of the launch vehicle pressurization system according to claim 4, characterized in that, The method includes: Step 1: After the first CPU unit determines that the temperature-controlled autonomous booster branch has failed to boost pressure, it shuts down the first booster solenoid valve, the inlet valve, and the heating coil of the temperature-controlled autonomous booster. Step 2: The first CPU unit sends a helium pressurization command to the second CPU unit. After the second CPU unit confirms that the temperature control autonomous pressurization branch valve is closed, it opens the second pressurization solenoid valve, allowing the helium in the first cold helium cylinder to enter the liquid oxygen tank through the throttling coil. Step 3: The second CPU unit collects the second driving current of the second booster solenoid valve in real time. If the second driving current exceeds the rated current ±15%, the boosting of the first cold helium cylinder branch is determined to be a failure; if the second driving current does not exceed the rated current ±15%, proceed to step 4. Step 4: The second CPU unit collects the pressure P3 at the outlet of the first cold helium cylinder in real time. If P3 does not reach the target pressure within the preset time, the unit will take action. If the pressure build-up timeout is determined, the pressurization of the first cold helium cylinder branch fails; if P3 reaches the target pressure within the preset time... Then proceed to step 5; Step 5: If the liquid oxygen tank pressure P7 does not rise to the target pressure within 10 seconds after the second booster solenoid valve is opened. If the second booster solenoid valve is found to be abnormally open, the boosting of the first cold helium cylinder branch will fail; if the liquid oxygen tank pressure P7 rises to the target pressure within 10 seconds after the second booster solenoid valve opens. If the pressure increase is successful, the closed-loop pressure increase control will end.

6. The method for fault diagnosis and fault handling of a launch vehicle pressurization system according to claim 5, characterized in that, The method further includes: Step 6: After the first cold helium cylinder branch pressurization fails, the second CPU unit closes the second pressurization solenoid valve and sends a helium pressurization command to the third CPU unit. Step 7: After the third CPU unit confirms that the branch valve of the first cold helium cylinder is closed, it opens the third pressurization solenoid valve to allow the helium in the second cold helium cylinder to enter the liquid oxygen tank through the throttling coil. Step 8: The third CPU unit collects the third driving current of the third booster solenoid valve in real time. If the third driving current exceeds the rated current ±15%, the booster of the second cold helium cylinder branch is determined to be in failure; if the third driving current does not exceed the rated current ±15%, proceed to step 9. Step 9: The third CPU unit collects the pressure P2 at the outlet of the second cold helium cylinder in real time. If P2 does not reach the target pressure within the preset time, the unit will take action. If the pressure build-up timeout is determined, the pressurization of the second cold helium cylinder branch fails; if P3 reaches the target pressure within the preset time... Then proceed to step 10; Step 10: If the liquid oxygen tank pressure P8 does not rise to the target pressure within 10 seconds after the third booster solenoid valve is opened. If the third booster solenoid valve is found to be abnormally open, the booster in the second cold helium cylinder branch will fail; if the liquid oxygen tank pressure P8 rises to the target pressure within 10 seconds after the third booster solenoid valve opens. If the pressure increase is successful, the closed-loop pressure increase control will end. Step 11: After the third CPU unit determines that the pressurization of the second cold helium cylinder branch has failed, it closes the third pressurization solenoid valve and sends an emergency handling signal to the rocket engine via the onboard bus. At the same time, it triggers the liquid oxygen tank exhaust valve to enter the pre-opening state.

Images