Method and apparatus for testing a liquid boost system of a liquid launch vehicle

Abstract

The embodiment of the present application provides a kind of liquid carrier rocket's tank pressurization system test method and device, the method comprises: obtaining the flight state data of liquid carrier rocket;According to the flight state data, the pressure change curve of the tank pressurization system of the liquid carrier rocket is determined;According to the pressure change curve, at least one ground tank pressurization system is carried out pressure simulation;Predetermined fault mode is loaded to the ground tank pressurization system in pressure simulation state and is tested, and the test result of ground tank pressurization system is obtained.The embodiment of the present application can dynamically reproduce the real pressure environment of tank pressurization system in the process of rocket flight, so that test result is more close to actual flight working condition.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle technology, and in particular to a testing method and apparatus for a liquid launch vehicle's tank pressurization system. Background Technology

[0002] The performance of the propellant tank pressurization system in a liquid-fueled launch vehicle directly affects the stability and reliability of the rocket's flight. Currently, testing of propellant tank pressurization systems generally employs static or semi-static simulations. Static simulation involves setting the pressure of the pressurization system to a fixed value and maintaining this pressure constant during testing to verify the system's ability to operate under constant pressure. Semi-static simulation is a limited improvement over static simulation, allowing for phased pressure changes during testing. However, these changes are discontinuous and not real-time, and still cannot fully replicate the dynamic pressure curve of actual flight. This leads to deviations between test results and actual operating conditions. Summary of the Invention

[0003] The technical problem to be solved by the embodiments of the present invention is to provide a test method and device for the pressurization system of a liquid launch vehicle's propellant tank, which can dynamically reproduce the real pressure environment of the propellant tank pressurization system during rocket flight, so that the test results are closer to the actual flight conditions.

[0004] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows:

[0005] A test method for a liquid-fueled launch vehicle's tank pressurization system includes:

[0006] Acquire flight status data of liquid-fueled launch vehicles;

[0007] Based on the flight status data, determine the pressure change curve of the tank pressurization system of the liquid launch vehicle;

[0008] Based on the pressure change curve, pressure simulation was performed on at least one stage of the ground tank pressurization system.

[0009] The preset fault mode was applied to the ground tank pressurization system under pressure simulation and tested to obtain the test results of the ground tank pressurization system.

[0010] Optionally, the flight status data includes: the altitude, acceleration, and fuel consumption rate of the liquid-fueled launch vehicle; based on the flight status data, determining the pressure change curve of the liquid-fueled launch vehicle's tank pressurization system includes:

[0011] Based on the flight status data, the flight phases of the liquid-fueled launch vehicle are determined, including the ascent phase, separation phase, and cruise phase.

[0012] Based on the flight phases of the liquid-fueled launch vehicle, determine the pressure change curve of the liquid-fueled launch vehicle's tank pressurization system.

[0013] Optionally, the flight phase of the liquid-fueled launch vehicle is determined based on the flight status data, including:

[0014] when a ≥ a 1, and b ≤ b 1. The flight phase of the liquid-fueled launch vehicle is determined to be the ascent phase;

[0015] in, a The acceleration of the liquid-fueled launch vehicle. a 1 is the first set value. b The altitude of the liquid-fueled launch vehicle. b 1 is the second set value;

[0016] when c ≤ c 1. The flight phase of the liquid-fueled launch vehicle is determined to be the separation phase;

[0017] in, c The fuel consumption rate of the liquid-fueled launch vehicle. c 1 is the third set value;

[0018] The remaining flight phases of the liquid-fueled launch vehicle, excluding the ascent and separation phases, are defined as the cruise phase.

[0019] Optionally, based on the flight phase of the liquid-fueled launch vehicle, the pressure change curve of the liquid-fueled launch vehicle's tank pressurization system is determined, including:

[0020] according to Determine the pressure change curve of the tank pressurization system of the liquid launch vehicle;

[0021] in, P ( t The pressure of the tank pressurization system is [pressure value missing]. t For time.

[0022] Optionally, based on the pressure change curve, pressure simulation is performed on at least one stage of the ground tank pressurization system, including:

[0023] Based on the pressure change curves, a tiered testing architecture was adopted to simultaneously simulate the pressure of each ground tank pressurization system.

[0024] Optionally, the ground tank pressurization system is tested under a pressure simulation state with a preset fault mode applied to it, and the test results of the ground tank pressurization system are obtained, including:

[0025] Acquire a library of preset fault modes, including pipeline leaks, valve jamming, and sensor failure;

[0026] At least one fault mode from the preset fault mode library is loaded into the ground tank pressurization system under pressure simulation to simulate fault modes in real flight.

[0027] Collect real-time data of the ground tank pressurization system under fault mode;

[0028] Based on the real-time data, the test results of the ground tank pressurization system are determined.

[0029] Optionally, the real-time data includes: the real-time pressure value and pressure change rate in the tank, the flow rate and temperature in the booster pipeline, the valve opening and closing status and action response time, the deviation between the control command and the actual execution status of the tank booster system, and the rotational speed and power of the actuator.

[0030] Optionally, the test results of the ground tank pressurization system are determined based on the real-time data, including:

[0031] Based on the real-time pressure value and pressure change rate inside the tank, the first test result of the pressure system of the ground tank pressurization system is determined;

[0032] Based on the flow rate and temperature in the pressurization pipeline, determine the second test result of the pipeline fluid state assessment of the ground tank pressurization system;

[0033] Based on the valve's on / off state and action response time, the third test result of the valve's performance in the ground tank pressurization system is determined.

[0034] Based on the deviation between the control commands and the actual execution state of the tank pressurization system, the fourth test result of the control command execution deviation of the ground tank pressurization system is determined;

[0035] The fifth test result is used to determine the operating status of the actuator of the ground tank pressurization system based on the rotational speed and power of the actuator.

[0036] Based on the first test result, the second test result, the third test result, the fourth test result, and the fifth test result, the test results of the ground tank pressurization system are determined.

[0037] Embodiments of the present invention also provide a test apparatus for a liquid-fueled launch vehicle's tank pressurization system, comprising:

[0038] The acquisition module is used to acquire flight status data of liquid-fueled launch vehicles;

[0039] The processing module is used to determine the pressure change curve of the propellant tank pressurization system of the liquid launch vehicle based on the flight status data; to perform pressure simulation on at least one stage ground propellant tank pressurization system based on the pressure change curve; and to load a preset fault mode into the ground propellant tank pressurization system under the pressure simulation state for testing, thereby obtaining the test results of the ground propellant tank pressurization system.

[0040] Embodiments of the present invention also provide a computing device, comprising:

[0041] One or more processors;

[0042] A storage device for storing one or more programs that, when executed by one or more processors, cause the one or more processors to perform the method as described in any of the preceding methods.

[0043] The above-described solutions of the embodiments of the present invention have at least the following beneficial effects:

[0044] The above-described solution of this invention, by acquiring real flight state data (altitude, acceleration, and fuel consumption rate) and generating corresponding pressure change curves, can dynamically reproduce the real pressure environment of the propellant tank pressurization system during rocket flight, overcoming the defects of discontinuous and non-real-time pressure changes in static simulation of fixed pressure and semi-static simulation of pressure changes, making the test results closer to actual flight conditions.

[0045] By loading preset fault modes on the basis of dynamic pressure simulation, it is possible to more realistically simulate fault scenarios that may occur in actual flight, thereby more accurately testing the performance of the tank pressurization system under fault conditions, which helps to discover potential problems and improve the reliability and stability of the system.

[0046] It can perform pressure simulations on at least one ground-based propellant tank pressurization system, including the first and second stages, and can comprehensively verify the collaborative working capability of multi-stage propellant tank pressurization systems under dynamic pressure environments, meeting the testing requirements of complex rocket systems. Attached Figure Description

[0047] Figure 1 This is a flowchart of a test method for the tank pressurization system of a liquid-fueled launch vehicle according to an embodiment of the present invention;

[0048] Figure 2 This is a schematic diagram of the test device for the tank pressurization system of a liquid-fueled launch vehicle according to an embodiment of the present invention. Detailed Implementation

[0049] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0050] like Figure 1 As shown, an embodiment of the present invention provides a test method for a liquid-fueled launch vehicle's tank pressurization system, comprising:

[0051] Step 11: Obtain flight status data of the liquid-fueled launch vehicle; specifically, the flight status data includes: altitude, acceleration, and fuel consumption rate of the liquid-fueled launch vehicle.

[0052] Step 12: Based on the flight status data, determine the pressure change curve of the tank pressurization system of the liquid launch vehicle;

[0053] Step 13: Based on the pressure change curve, perform pressure simulation on at least one stage of the ground tank pressurization system;

[0054] Step 14: Apply the preset fault mode to the ground tank pressurization system under pressure simulation and test it to obtain the test results of the ground tank pressurization system.

[0055] In this embodiment, by acquiring real flight state data (altitude, acceleration, and fuel consumption rate) and generating corresponding pressure change curves, the real pressure environment of the propellant tank pressurization system during rocket flight can be dynamically reproduced. This overcomes the shortcomings of static simulation of fixed pressure and semi-static simulation of pressure changes being discontinuous and not real-time, making the test results closer to actual flight conditions.

[0056] By loading preset fault modes on the basis of dynamic pressure simulation, it is possible to more realistically simulate fault scenarios that may occur in actual flight, thereby more accurately testing the performance of the tank pressurization system under fault conditions, which helps to discover potential problems and improve the reliability and stability of the system.

[0057] It can perform pressure simulations on at least one ground-based propellant tank pressurization system, including the first and second stages, and can comprehensively verify the collaborative working capability of multi-stage propellant tank pressurization systems under dynamic pressure environments, meeting the testing requirements of complex rocket systems.

[0058] In an optional embodiment of the present invention, step 12, determining the pressure change curve of the propellant tank pressurization system of the liquid launch vehicle based on the flight status data, includes:

[0059] Step 121: Based on the flight status data, determine the flight phase of the liquid-fueled launch vehicle, which includes the ascent phase, separation phase, and cruise phase.

[0060] Step 122: Determine the pressure change curve of the liquid launch vehicle's tank pressurization system based on the flight phase of the liquid launch vehicle.

[0061] In step 121, the flight phase of the liquid-fueled launch vehicle is determined based on the flight status data, including:

[0062] Step 1211, when a ≥ a 1, and b ≤ b 1. The flight phase of the liquid-fueled launch vehicle is determined to be the ascent phase;

[0063] in, a The acceleration of the liquid-fueled launch vehicle. a 1 is the first set value. b The altitude of the liquid-fueled launch vehicle. b 1 is the second set value;

[0064] Step 1212, when c ≤ c 1. The flight phase of the liquid-fueled launch vehicle is determined to be the separation phase;

[0065] in, c The fuel consumption rate of the liquid-fueled launch vehicle. c 1 is the third set value;

[0066] Step 1213: The remaining flight phases of the liquid-fueled launch vehicle, excluding the ascent and separation phases, are defined as the cruise phase.

[0067] In step 122, based on the flight phase of the liquid-fueled launch vehicle, the pressure change curve of the liquid-fueled launch vehicle's tank pressurization system is determined, including:

[0068] Step 1221, according to Determine the pressure change curve of the tank pressurization system of the liquid launch vehicle;

[0069] in, P ( t The pressure of the tank pressurization system is [pressure value missing]. t For time.

[0070] In this embodiment, a quantitative standard for judging flight stages was established using key flight status data such as acceleration, altitude, and fuel consumption rate. This upgrades the division of flight stages from qualitative judgment to quantitative analysis, avoiding the subjectivity of manual division and ensuring the consistency and accuracy of stage division. It also provides a reliable basis for subsequently determining the pressure change curves in stages.

[0071] To address the unique characteristics of different flight phases (ascent, separation, and cruise), pressure variation curves are determined for each phase, allowing for a more accurate reflection of the actual physical environment and system requirements at each stage. For instance, the ascent phase may involve dramatic acceleration changes and rapid altitude gain, resulting in pressure variation patterns that differ significantly from the stable flight of the cruise phase. Designing curves for each phase allows pressure simulations to better reflect the dynamic characteristics of real flight, further reducing the discrepancy between testing and actual operating conditions.

[0072] Because the pressure environment and system operating conditions differ at different flight phases, the manifestation and impact of failure modes may also vary. By applying failure modes based on precisely defined flight phases and corresponding pressure change curves, it is possible to more specifically test the system's failure response capability under specific flight phases. This makes failure testing more scenario-based and practical, and helps to discover potential problems unique to each phase.

[0073] The quantitative criteria for judging flight phases and the method for determining pressure curves in stages make the parameter setting and execution logic of the entire testing process clearer and more standardized, reducing ambiguity and uncertainty in the operation process. This not only makes it easier for testers to execute accurately, but also improves the repeatability of test results and facilitates comparative analysis of test data from different batches and under different environments.

[0074] In an optional embodiment of the present invention, step 13, based on the pressure change curve, involves performing a pressure simulation on at least one stage of the ground tank pressurization system, including:

[0075] Step 131: Based on the pressure change curve, a graded test architecture is adopted to simultaneously simulate the pressure of each ground tank pressurization system.

[0076] Specifically, simulation modules adapted to the characteristics of the first-stage and second-stage ground-based propellant tank pressurization systems are adopted respectively. The first-stage tank simulation module is configured to support rapid response to high-pressure signals to simulate the high-pressure pressurization requirements of the rocket's first-stage flight phase. The second-stage tank simulation module is designed to handle pulsed pressure changes and adapt to the rapid pressure fluctuation scenarios that may occur during the second-stage flight phase.

[0077] Multi-channel parallel data acquisition is achieved through a high-performance FPGA (Field Programmable Gate Array), and real-time data recording is performed on the pressure simulation process of the primary and secondary tanks to ensure the synchronization and accuracy of the pressure simulation of each tank.

[0078] The test command transmission and data feedback are carried out using the high-speed Ethernet protocol, and the system response delay is controlled at the millisecond level. This enables the coordinated linkage of the primary and secondary ground tank pressurization systems during the pressure simulation process, thereby completing the system-level integrated test and verification.

[0079] In this embodiment, tailored simulation modules are configured to address the differences in characteristics between the first-stage and second-stage ground-based propellant tank pressurization systems (first-stage supports rapid response to high-pressure signals, and second-stage is adapted for pulsed pressure surges). This allows for precise matching of the actual pressurization requirements of different rocket stages. This avoids the accuracy loss associated with generalized simulations, making the pressure simulation of each propellant tank more closely resemble its real-world operating scenario and improving the effectiveness of subsystem testing.

[0080] By implementing multi-channel parallel data acquisition using a high-performance FPGA, the pressure simulation process of both the primary and secondary tanks can be recorded in real time simultaneously. This solves the time lag problem that may occur with traditional serial acquisition and ensures the synchronization of pressure simulation across multiple systems. Simultaneously, the parallel processing capability improves the efficiency and completeness of data acquisition, providing high-quality raw data for subsequent analysis of the collaborative working characteristics of each system level.

[0081] By employing a high-speed Ethernet protocol, system response latency is controlled to the millisecond level, ensuring coordinated operation of the primary and secondary tank pressurization systems during pressure simulation. This low-latency coordination capability upgrades the testing from individual subsystem simulations to system-level integrated verification, enabling a more realistic reproduction of the coordinated operation of the multi-stage tank pressurization system during rocket flight and effectively verifying the compatibility and coordination between systems.

[0082] The specialized design for complex scenarios such as high-pressure requirements in the first stage and sudden pressure surges in the second stage enables the testing system to cover extreme pressure environments that may occur during rocket flight. This not only enhances the comprehensiveness of the testing but also provides more stringent testing standards for verifying the stability and reliability of the tank pressurization system under complex operating conditions.

[0083] In an optional embodiment of the present invention, step 14 involves testing the ground tank pressurization system under a pressure simulation state with a preset fault mode applied, and obtaining the test results of the ground tank pressurization system, including:

[0084] Step 141: Obtain a library of preset fault modes, including pipeline leakage, valve jamming, and sensor failure.

[0085] Step 142: Load at least one fault mode from the preset fault mode library into the ground tank pressurization system under pressure simulation to simulate fault modes in actual flight. Specifically, for pipeline leakage: by preset controllable miniature solenoid valves in the pressurization pipeline, the control system sends pulse signals to control the valve opening to simulate leakage faults with different leakage amounts; at the same time, the flow sensor monitors the flow changes before and after leakage in real time to ensure that the leakage amount is consistent with the preset fault level; for valve jamming: by connecting a time delay relay or signal interference module to the control circuit of the valve drive motor, the valve action lag is simulated by setting a delay time, or the valve jamming at a fully open, fully closed, or intermediate position is simulated by sending an erroneous electrical signal; for sensor failure: by tampering with the original signal through the sensor signal acquisition module, including: sending fixed deviation signals, random noise signals, and signal interruptions, to simulate sensor drift, distortion, and complete failure fault states, respectively.

[0086] Step 143: Collect real-time data of the ground tank pressurization system in fault mode;

[0087] Step 144: Determine the test results of the ground tank pressurization system based on the real-time data.

[0088] In step 143, the real-time data includes: the real-time pressure value and pressure change rate in the tank, the flow rate and temperature in the booster pipeline, the valve opening and closing status and action response time, the deviation between the control command and the actual execution status of the tank booster system, and the rotational speed and power of the actuator.

[0089] In step 144, based on the real-time data, the test results of the ground tank pressurization system are determined, including:

[0090] Step 1441: Determine the first test result of the pressure system of the ground tank pressurization system based on the real-time pressure value and pressure change rate in the tank.

[0091] Step 1442: Determine the second test result of the pipeline fluid state assessment of the ground tank pressurization system based on the flow rate and temperature in the pressurization pipeline;

[0092] Step 1443: Based on the valve's opening and closing status and action response time, determine the third test result of the valve's performance of the ground tank pressurization system;

[0093] Step 1444: Based on the deviation between the control command and the actual execution state of the tank pressurization system, determine the fourth test result of the control command execution deviation of the ground tank pressurization system;

[0094] Step 1445: Determine the fifth test result of the operating status of the actuator of the ground tank pressurization system based on the rotational speed and power of the actuator;

[0095] Step 1446: Determine the test results of the ground tank pressurization system based on the first test result, the second test result, the third test result, the fourth test result, and the fifth test result.

[0096] Specifically, according to Determine the pressure deviation coefficient of the pressure system;

[0097] in, d This is the pressure deviation coefficient. x 1 ( t The real-time pressure value inside the tank is . x 2 ( t The pressure value (i.e., the target pressure value inside the tank) is the pressure value of the pressure change curve of the tank pressurization system.

[0098] according to Determine the pressure rate deviation coefficient of the pressure system;

[0099] in, e This is the pressure-rate deviation coefficient. y 1 ( t The real-time pressure rate value within the storage tank is denoted as . y 2 ( t ) represents the pressure rate value of the pressure change curve of the tank pressurization system (i.e., the target pressure rate value inside the tank).

[0100] according to Determine the result of the first test;

[0101] in, f The result of the first test. d 1 represents the threshold value for the pressure deviation coefficient. e 1 represents the threshold value for the pressure-rate deviation coefficient;

[0102] according to Determine the flow fluctuation coefficient of the booster pipeline;

[0103] in, g For flow fluctuation coefficient, maxz 1 ( t The maximum real-time flow rate of the booster pipeline is denoted as . mint 1 ( t The minimum real-time flow rate of the booster pipeline is denoted as . z 2 represents the set nominal flow rate of the booster pipeline;

[0104] according to Determine the percentage of time the temperature in the booster pipeline exceeds the limit;

[0105] in, h The percentage of time the temperature exceeded the limit in the pressurization pipeline. t 0 is the start time. t 1 represents the end time. m ( t ( ) represents the real-time temperature of the pressurization pipeline. m min The lower limit of the temperature of the pressurization pipeline, m max This is the upper temperature limit for the pressurization pipeline;

[0106] according to Determine the result of the second test;

[0107] in, i The result of the second test. g 1 represents the threshold for the flow fluctuation coefficient;

[0108] according to Determine the state consistency ratio of valve performance;

[0109] in, j The state consistency ratio, t 0 is the start time. t 1 represents the end time. k 1 ( t () represents the valve response status. k 2 ( t () indicates the valve command status;

[0110] according to Determine the number of times the valve's response time exceeds the limit;

[0111] in, k For the number of times the response time exceeds the limit, u=1,2,3...,v,v This represents the total number of responses. l u For each response time, l max This is the maximum allowable response time.

[0112] according to Determine the third test result;

[0113] in, o The third test result, j 1 represents the state consistency ratio threshold;

[0114] according to The deviation between the control command and the actual execution state is determined.

[0115] in, p For the aforementioned deviation, q 1 represents the control command. q 2 represents the actual execution state;

[0116] according to Determine the root mean square of the deviation;

[0117] in, r The root mean square of the deviation is... s=1,2,3...,w,w The total number of deviations. p s This represents the deviation amount for each instance.

[0118] according to Determine the result of the fourth test;

[0119] in, α The fourth test result, r 1 represents the root mean square threshold of the deviation;

[0120] according to Determine the rotational speed deviation coefficient of the actuator;

[0121] in, β The speed deviation coefficient is... c 1 represents the real-time rotational speed of the actuator. c 2. Rated speed of the actuator;

[0122] according to Determine the percentage of power exceeding the limit of the actuator;

[0123] in, d The percentage of power exceeding the limit. t 0 is the start time. t 1 represents the end time. e 1 ( t ( ) represents the real-time power of the actuator. e 2 represents the rated power of the actuator, and 1.1 represents the safety factor;

[0124] according to Determine the result of the fifth test;

[0125] in, f The fifth test result, β 1 represents the threshold value of the rotational speed deviation coefficient;

[0126] according to λ=η 1× f+h 2× i+n 3× o+h 4× o+h 5× fDetermine the test score of the ground tank pressurization system;

[0127] in, l The test score is... or 1. or 2. or 3. or 4. or 5 represents the score coefficients for the first, second, third, fourth, and fifth places, respectively.

[0128] like λ≧ If the value is 0.9, then the test result for the ground tank pressurization system is that the test passed.

[0129] If 0.7 ≦λ≦ If the value is 0.9, then the test result of the ground tank pressurization system is basically usable;

[0130] like λ< If the value is 0.7, the test result for the ground tank pressurization system is "fail".

[0131] In this embodiment, a preset fault mode library is established, including pipeline leakage, valve jamming, and sensor failure, which accurately corresponds to the core failure risk points of the rocket propellant tank pressurization system. Each fault is simulated in a controllable manner through hardware modification (such as miniature solenoid valves and time-delay relays) and signal processing (such as signal tampering), which not only ensures the realism of the fault scenarios but also allows for precise control of the fault level (such as different leakage amounts and jamming degrees), providing a standardized scenario for comprehensively testing the system's fault response capabilities.

[0132] Real-time acquisition of multi-dimensional data, including pressure, flow rate, temperature, valve status, control deviation, and actuator parameters, covers core aspects of the tank pressurization system such as pressure regulation, fluid transmission, mechanism action, and control logic. This comprehensive data acquisition ensures a complete understanding of system performance and avoids the limitations of evaluating a single indicator.

[0133] By defining quantitative indicators such as pressure deviation coefficient, flow fluctuation coefficient, and state consistency ratio using mathematical formulas, abstract system performance is transformed into calculable numerical parameters. Simultaneously, a grading standard is established based on threshold judgment and weighted scoring, completely eliminating the reliance on experience-based qualitative judgments in traditional testing, making the test results more objective, comparable, and persuasive.

[0134] The test results (first to fifth test results) are generated by dividing the system into modules (pressure system, pipeline fluid, valve performance, control execution, and actuator), which can accurately pinpoint the specific impact of faults on each part of the system. For example, valve jamming faults can be directly reflected in the third test result (state consistency ratio, number of response time exceedances) on the actuator, while the first test result (pressure deviation) shows its indirect impact on overall pressure regulation, providing a clear direction for fault tracing and system optimization.

[0135] Standardized processes have been established for everything from the establishment of the fault mode library, fault loading methods, data collection items to result calculation methods. This not only ensures the consistency and repeatability of tests in different batches, but also provides a flexible framework for expanding new fault modes or optimizing evaluation indicators, thereby improving the adaptability and survivability of the testing methods.

[0136] In an optional embodiment of the present invention, the method further includes:

[0137] Step 15: Construct a virtual simulation model for testing the ground tank pressurization system to achieve real-time synchronization between physical testing and virtual simulation.

[0138] Specifically, based on the physical structure and working principle of the ground-based tank pressurization system, a high-fidelity virtual simulation model is constructed using multi-domain modeling tools.

[0139] In this embodiment, pressure change curves are determined by acquiring flight status data, ground system pressure is simulated in real time, preset fault modes are loaded, and virtual simulation is combined to achieve dynamic and accurate testing. This improves realism and accuracy, covers multiple system levels, reduces cost risks, and provides strong support for system optimization and reliability.

[0140] Example 1

[0141] Example 1 provides a test method for the tank pressurization system of a liquid-fueled launch vehicle, which requires testing. The method includes:

[0142] Step 21: Retrieve flight status data for typical missions from the rocket flight database: time-series curves of altitude, acceleration, and fuel consumption rate for the ascent phase (altitude < 100km, acceleration ≥ 5g), separation phase (fuel consumption rate ≤ 0.1kg / s), and cruise phase (altitude > 100km and fuel consumption rate > 0.1kg / s).

[0143] Step 22, automatically divide the flight phase according to the preset threshold: when the real-time collected acceleration a = 6g ( a 1=5g) and height b =80km ( b When 1=100km), it is determined to be an ascending segment, and the function is called. P( t ) = 5 + 0.02 t Pressure curve; when fuel consumption rate c =0.08kg / s ( c When 1 = 0.1 kg / s, switch to the pulse pressure curve of the separation section; for the remaining time periods, simulate the steady curve of the cruise section;

[0144] Step 23: The first-stage tank simulation module achieves millisecond-level response of 0-10MPa pressure through a high-pressure solenoid valve group to simulate the high-pressure environment when the first-stage engine is working; the second-stage tank simulation module is equipped with a pressure shock generator to reproduce the pulse fluctuation of ±2MPa during the separation stage; at the same time, the FPGA module synchronously collects the pressure data of the two tanks (sampling rate 1kHz) and transmits it to the control console via gigabit Ethernet to ensure that the data delay is <5ms.

[0145] Step 24, during the fault test, first activate the pipeline leakage mode: control the 0.5mm diameter miniature solenoid valve to open 30%, the flow sensor displays a real-time leakage rate of 0.2L / min (consistent with the preset fault level), and simultaneously record the tank pressure drop rate increasing from 0.1MPa / s to 0.3MPa / s; then apply a valve jamming fault, delaying the action of the secondary filling valve by 1.2s via a time delay relay (exceeding the 0.8s threshold), causing the pressure fluctuation coefficient to increase from 5% to 18%;

[0146] Step 25: Calculate the pressure deviation coefficient. d =0.07 (<d1=0.1), flow fluctuation coefficient g =0.15 (> g 1=0.1), final weighted score l =0.82, which was determined to be "basically usable", and the root cause of the fault was identified as the sluggish response of the secondary valve, providing a clear direction for subsequent structural optimization.

[0147] This invention generates pressure change curves by acquiring real flight status data, and combines phased (ascent, separation, and cruise) quantitative judgments with targeted pressure curve design to dynamically reproduce the real flight pressure environment. This completely overcomes the limitations of static and semi-static simulations, significantly improves test realism, and reduces deviations from actual operating conditions.

[0148] A tiered testing architecture is adopted, with characteristic-adapted simulation modules configured for the first and second level ground tanks. By leveraging FPGA multi-channel parallel acquisition and high-speed Ethernet communication (millisecond-level latency), synchronous simulation and collaborative linkage of multi-level systems are achieved, upgrading from subsystem testing to system-level integrated verification. This accurately matches the pressurization requirements of different stages and ensures comprehensive testing in complex scenarios.

[0149] A model library containing core faults such as pipeline leakage and valve jamming is constructed. Controllable simulation is achieved through hardware modification and signal processing. Combined with multi-dimensional data acquisition (pressure, flow, valve status, etc.) and a quantitative evaluation system (pressure deviation coefficient, flow fluctuation coefficient, etc.), a closed loop of "fault loading - data acquisition - quantitative judgment" is formed, which makes the test shift from experience-driven to data-driven, and improves the objectivity of the results and the efficiency of fault tracing.

[0150] The addition of real-time synchronization between physical testing and virtual simulation complements the limitations of physical testing through high-fidelity virtual models, reduces resource consumption in high-risk and high-cost testing, supports in-depth analysis of system dynamic characteristics and rapid verification of design iterations, and further strengthens the technical support for system optimization and reliability improvement.

[0151] like Figure 2 As shown, an embodiment of the present invention also provides a test apparatus 20 for a liquid launch vehicle's tank pressurization system, comprising:

[0152] Acquisition module 21 is used to acquire flight status data of the liquid-fueled launch vehicle;

[0153] Processing module 22 is used to determine the pressure change curve of the liquid launch vehicle's tank pressurization system based on the flight status data; perform pressure simulation on at least one stage ground tank pressurization system based on the pressure change curve; load a preset fault mode into the ground tank pressurization system under the pressure simulation state for testing, and obtain the test results of the ground tank pressurization system.

[0154] Optionally, the flight status data includes: the altitude, acceleration, and fuel consumption rate of the liquid-fueled launch vehicle; based on the flight status data, determining the pressure change curve of the liquid-fueled launch vehicle's tank pressurization system includes:

[0155] Based on the flight status data, the flight phases of the liquid-fueled launch vehicle are determined, including the ascent phase, separation phase, and cruise phase.

[0156] Based on the flight phases of the liquid-fueled launch vehicle, determine the pressure change curve of the liquid-fueled launch vehicle's tank pressurization system.

[0157] Optionally, the flight phase of the liquid-fueled launch vehicle is determined based on the flight status data, including:

[0158] when a ≥ a 1, and b ≤ b 1. The flight phase of the liquid-fueled launch vehicle is determined to be the ascent phase;

[0159] in, aThe acceleration of the liquid-fueled launch vehicle. a 1 is the first set value. b The altitude of the liquid-fueled launch vehicle. b 1 is the second set value;

[0160] when c ≤ c 1. The flight phase of the liquid-fueled launch vehicle is determined to be the separation phase;

[0161] in, c The fuel consumption rate of the liquid-fueled launch vehicle. c 1 is the third set value;

[0162] The remaining flight phases of the liquid-fueled launch vehicle, excluding the ascent and separation phases, are defined as the cruise phase.

[0163] Optionally, based on the flight phase of the liquid-fueled launch vehicle, the pressure change curve of the liquid-fueled launch vehicle's tank pressurization system is determined, including:

[0164] according to Determine the pressure change curve of the tank pressurization system of the liquid launch vehicle;

[0165] in, P ( t The pressure of the tank pressurization system is [pressure value missing]. t For time.

[0166] Optionally, based on the pressure change curve, pressure simulation is performed on at least one stage of the ground tank pressurization system, including:

[0167] Based on the pressure change curves, a tiered testing architecture was adopted to simultaneously simulate the pressure of each ground tank pressurization system.

[0168] Optionally, the ground tank pressurization system is tested under a pressure simulation state with a preset fault mode applied to it, and the test results of the ground tank pressurization system are obtained, including:

[0169] Acquire a library of preset fault modes, including pipeline leaks, valve jamming, and sensor failure;

[0170] At least one fault mode from the preset fault mode library is loaded into the ground tank pressurization system under pressure simulation to simulate fault modes in real flight.

[0171] Collect real-time data of the ground tank pressurization system under fault mode;

[0172] Based on the real-time data, the test results of the ground tank pressurization system are determined.

[0173] Optionally, the real-time data includes: the real-time pressure value and pressure change rate in the tank, the flow rate and temperature in the booster pipeline, the valve opening and closing status and action response time, the deviation between the control command and the actual execution status of the tank booster system, and the rotational speed and power of the actuator.

[0174] Optionally, the test results of the ground tank pressurization system are determined based on the real-time data, including:

[0175] Based on the real-time pressure value and pressure change rate inside the tank, the first test result of the pressure system of the ground tank pressurization system is determined;

[0176] Based on the flow rate and temperature in the pressurization pipeline, determine the second test result of the pipeline fluid state assessment of the ground tank pressurization system;

[0177] Based on the valve's on / off state and action response time, the third test result of the valve's performance in the ground tank pressurization system is determined.

[0178] Based on the deviation between the control commands and the actual execution state of the tank pressurization system, the fourth test result of the control command execution deviation of the ground tank pressurization system is determined;

[0179] The fifth test result is used to determine the operating status of the actuator of the ground tank pressurization system based on the rotational speed and power of the actuator.

[0180] Based on the first test result, the second test result, the third test result, the fourth test result, and the fifth test result, the test results of the ground tank pressurization system are determined.

[0181] It should be noted that this device is a device corresponding to the above method. All implementation methods in the above method embodiments are applicable to this embodiment and can achieve the same technical effect.

[0182] Embodiments of the present invention also provide a computing device, including: one or more processors; and a storage device for storing one or more programs, wherein when the one or more programs are executed by the one or more processors, the one or more processors implement the method described above. All implementations in the above method embodiments are applicable to this embodiment and can achieve the same technical effect.

[0183] Embodiments of the present invention also provide a computing device readable storage medium storing instructions that, when executed on a computing device, cause the computing device to perform the method described above. All implementations in the above method embodiments are applicable to this embodiment and can achieve the same technical effect.

[0184] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed in this invention can be implemented in electronic hardware, or a combination of computing device software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementations should not be considered beyond the scope of this invention.

[0185] Those skilled in the art will understand that, for the sake of convenience and brevity, the specific working processes of the systems, devices, and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0186] In the embodiments provided by this invention, it should be understood that the disclosed apparatus and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative. For instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some interfaces; the indirect coupling or communication connection between devices or units may be electrical, mechanical, or other forms.

[0187] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0188] In addition, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit.

[0189] If the aforementioned functions are implemented as software functional units and sold or used as independent products, they can be stored in a computing device-readable storage medium. Based on this understanding, the technical solution of this invention, essentially, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computing device software product is stored in a storage medium and includes several instructions to cause a computing device (which may be a personal computing device, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, ROM, RAM, magnetic disks, or optical disks.

[0190] Furthermore, it should be noted that in the apparatus and method of the present invention, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered equivalent solutions of the present invention. Moreover, the steps performing the above-described series of processes can naturally be executed in the order described, but are not necessarily required to be executed in chronological order; some steps can be executed in parallel or independently of each other. Those skilled in the art will understand that all or any step or component of the method and apparatus of the present invention can be implemented in any computing device (including processors, storage media, etc.) or network of computing devices, in hardware, firmware, software, or a combination thereof. This is something that those skilled in the art can achieve using basic programming skills after reading the description of the present invention.

[0191] Therefore, the object of the present invention can also be achieved by running a program or a set of programs on any computing device. The computing device can be a known general-purpose device. Therefore, the object of the present invention can also be achieved simply by providing a program product containing program code implementing the method or apparatus. That is, such a program product also constitutes the present invention, and the storage medium storing such a program product also constitutes the present invention. Obviously, the storage medium can be any known storage medium or any storage medium developed in the future. It should also be noted that in the apparatus and method of the present invention, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered equivalent to the present invention. Furthermore, the steps performing the above series of processes can naturally be performed in the order described, but are not necessarily required to be performed in chronological order. Some steps can be performed in parallel or independently of each other.

[0192] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method of testing a liquid-boosted rocket tank pressurization system, comprising: The method comprises the following steps: acquiring flight state data of a liquid carrier rocket; determining a pressure change curve of a tank pressurization system of the liquid carrier rocket according to the flight state data; performing pressure simulation on at least one ground tank pressurization system according to the pressure change curve; loading preset fault modes into the ground tank pressurization system in the pressure simulation state for testing to obtain a test result of the ground tank pressurization system. The flight state data comprises the height, acceleration and fuel consumption rate of the liquid carrier rocket. The method of determining the pressure change curve of the tank pressurization system of the liquid carrier rocket according to the flight state data comprises the following steps: determining a flight phase of the liquid carrier rocket according to the flight state data, wherein the flight phase comprises a climbing phase, a separation phase and a cruising phase; determining the pressure change curve of the tank pressurization system of the liquid carrier rocket according to the flight phase of the liquid carrier rocket. According to , determining a pressure variation curve of a tank pressurization system of the liquid carrier rocket; wherein P ( t ) is the pressure of the tank pressurization system, t is time.

2. The method of testing a liquid boost vehicle tank pressurization system of claim 1, wherein, The method of determining the pressure change curve of the tank pressurization system of the liquid carrier rocket according to the flight phase of the liquid carrier rocket comprises the following steps: When a ≥ a 1, and b ≤ b 1, determine the flight phase of the liquid carrier rocket as an ascending phase; wherein, a is the acceleration of the liquid carrier rocket, a 1 is a first set value, b is the altitude of the liquid carrier rocket, b 1 is a second set value; When c ≤ c 1, determining that the flight phase of the liquid carrier rocket is a separation phase; wherein, c is the fuel consumption rate of the liquid carrier rocket, c 1 is a third set value; determining the flight phase of the liquid carrier rocket according to the flight state data comprises the following steps:

3. The method of testing a liquid boost rocket tank pressurization system of claim 1, wherein, determining the flight phase of the liquid carrier rocket as the cruising phase except for the climbing phase and the separation phase. The method of performing pressure simulation on at least one ground tank pressurization system according to the pressure change curve comprises the following steps:

4. The method of testing a liquid boost rocket tank pressurization system of claim 1, wherein, performing pressure simulation on each ground tank pressurization system simultaneously according to the pressure change curve by using a hierarchical test architecture. The method of loading preset fault modes into the ground tank pressurization system in the pressure simulation state for testing to obtain a test result of the ground tank pressurization system comprises the following steps: acquiring a preset fault mode library comprising pipeline leakage, valve sticking and sensor failure; loading at least one fault mode in the preset fault mode library into the ground tank pressurization system in the pressure simulation state to simulate the fault mode in the real flight; collecting real-time data of the ground tank pressurization system in the fault mode; 5. The method of testing a liquid boost rocket tank pressurization system of claim 4, wherein, determining the test result of the ground tank pressurization system according to the real-time data.

6. The method of testing a liquid boost rocket tank pressurization system of claim 5, wherein, The real-time data comprises the real-time pressure value and pressure change rate in the tank, the flow rate and temperature in the pressurization pipeline, the opening and closing state and action response time of the valve, the deviation between the control instruction and the actual execution state of the tank pressurization system, and the rotation speed and power of the execution mechanism. The method of determining the test result of the ground tank pressurization system according to the real-time data comprises the following steps: determining a first test result of the pressure system of the ground tank pressurization system according to the real-time pressure value and pressure change rate in the tank; determining a second test result of the pipeline fluid state evaluation of the ground tank pressurization system according to the flow rate and temperature in the pressurization pipeline; determining a third test result of the valve execution performance of the ground tank pressurization system according to the opening and closing state and action response time of the valve; determining a fourth test result of the control instruction execution deviation of the ground tank pressurization system according to the deviation between the control instruction and the actual execution state of the tank pressurization system. Determine a fifth test result of the actuator operation state of the ground tank pressurization system according to the rotation speed and power of the actuator; Determine a test result of the ground tank pressurization system according to the first test result, the second test result, the third test result, the fourth test result and the fifth test result.

7. A test apparatus for a liquid boost system of a liquid launch vehicle tank, characterized by, Comprise: An acquisition module, configured to acquire flight state data of a liquid carrier rocket; A processing module, configured to determine a pressure change curve of a tank pressurization system of the liquid carrier rocket according to the flight state data, perform pressure simulation on at least one ground tank pressurization system according to the pressure change curve, load a preset fault mode into the ground tank pressurization system in the pressure simulation state to perform testing, and obtain a test result of the ground tank pressurization system; The flight state data comprises height, acceleration and fuel consumption rate of the liquid carrier rocket; the pressure change curve of the tank pressurization system of the liquid carrier rocket is determined according to the flight state data, and comprises: Determine a flight phase of the liquid carrier rocket according to the flight state data, wherein the flight phase comprises an ascending segment, a separation segment and a cruising segment; Determine the pressure change curve of the tank pressurization system of the liquid carrier rocket according to the flight phase of the liquid carrier rocket; Determine the pressure change curve of the tank pressurization system of the liquid carrier rocket according to the flight phase of the liquid carrier rocket, and comprises: According to , determining a pressure variation curve of a tank pressurization system of the liquid carrier rocket; wherein P ( t ) is the pressure of the tank pressurization system, t is time.

8. A computing device, comprising: Comprise: One or more processors; A storage device configured to store one or more programs, when the one or more programs are executed by the one or more processors, so that the one or more processors implement the method in any one of claims 1 to 6.

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