Method and device for testing storage tank pressurization system of liquid carrier rocket

Abstract

The embodiment of the invention provides a method and a device for testing a storage tank pressurization system of a liquid carrier rocket. The method comprises the following steps: acquiring flight state data of the liquid carrier rocket; determining a pressure change curve of a storage tank pressurization system of the liquid carrier rocket according to the flight state data; according to the pressure change curve, performing pressure simulation on at least one stage of ground storage tank pressurization system; and loading a preset fault mode into the ground storage tank pressurization system in the pressure simulation state for testing to obtain a test result of the ground storage tank pressurization system. According to the embodiment of the invention, the real pressure environment of the storage tank pressurization system in the rocket flight process can be dynamically reproduced, so that the test result is closer to the actual flight condition.

Description

TECHNICAL FIELD

[0001] The embodiment of the present application relates to the technical field of carrier rockets, in particular to a test method and device for a tank pressurization system of a liquid carrier rocket. BACKGROUND

[0002] The performance of the tank pressurization system of a liquid carrier rocket directly affects the stability and reliability of the rocket flight. At present, for the test of the tank pressurization system, static or semi-static simulation is generally adopted. The static simulation refers to setting the pressure of the tank pressurization system as a fixed value during the test, and keeping the pressure state unchanged, so as to verify the working capacity of the system under constant pressure. The semi-static simulation is a limited improvement of the static simulation, allowing the pressure to change in stages during the test, but the change process is not continuous and not real-time, and still cannot completely reproduce the dynamic pressure curve of the real flight. Therefore, there is a deviation between the test result and the actual working condition. SUMMARY

[0003] The technical problem to be solved by the embodiment of the present application is to provide a test method and device for a tank pressurization system of a liquid carrier rocket, which can dynamically reproduce the real pressure environment of the tank pressurization system in the rocket flight process, so that the test result is closer to the actual flight working condition.

[0004] To solve the above technical problem, the technical scheme of the embodiment of the present application is as follows: A test method for a tank pressurization system of a liquid carrier rocket, comprising: obtaining flight state data of the liquid carrier rocket; determining a pressure change curve of the tank pressurization system of the liquid carrier rocket according to the flight state data; performing pressure simulation on at least one level of ground tank pressurization system according to the pressure change curve; loading a preset fault mode into the ground tank pressurization system in the pressure simulation state for testing, and obtaining a test result of the ground tank pressurization system.

[0005] Optionally, the flight state data includes the height, acceleration and fuel consumption rate of the liquid carrier rocket; and determining the pressure change curve of the tank pressurization system of the liquid carrier rocket according to the flight state data comprises: determining a flight phase of the liquid carrier rocket according to the flight state data, the flight phase comprising a climbing segment, a separation segment and a cruising segment; 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.

[0006] Optionally, determining the flight phase of the liquid carrier rocket according to the flight state data comprises: when a ≥ a 1, and b ≤ b 1. The flight phase of the liquid-fueled launch vehicle is determined to be the ascent phase; 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; when c ≤ c 1. The flight phase of the liquid-fueled launch vehicle is determined to be the separation phase; in, c The fuel consumption rate of the liquid-fueled launch vehicle. c 1 is the third set value; The remaining flight phases of the liquid-fueled launch vehicle, excluding the ascent and separation phases, are defined as the cruise phase.

[0007] 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: according to Determine the pressure change curve of the tank pressurization system of the liquid launch vehicle; in, P ( t The pressure of the tank pressurization system is [pressure value missing]. t For time.

[0008] Optionally, based on the pressure change curve, pressure simulation is performed on at least one stage of the ground tank pressurization system, including: Based on the pressure change curves, a tiered testing architecture was adopted to simultaneously simulate the pressure of each ground tank pressurization system.

[0009] 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: Acquire a library of preset fault modes, including pipeline leaks, valve jamming, and sensor failure; 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. Collect real-time data of the ground tank pressurization system under fault mode; Based on the real-time data, the test results of the ground tank pressurization system are determined.

[0010] Optionally, the real-time data comprises: real-time pressure value and pressure change rate in the tank, flow and temperature in the pressurizing pipeline, opening and closing state and action response time of the valve, deviation of control instruction and actual execution state of the tank pressurizing system, and rotating speed and power of the actuator.

[0011] Optionally, according to the real-time data, the test result of the ground tank pressurizing system is determined, comprising: determining a first test result of a pressure system of the ground tank pressurizing system according to the real-time pressure value and pressure change rate in the tank; determining a second test result of pipeline fluid state evaluation of the ground tank pressurizing system according to the flow and temperature in the pressurizing pipeline; determining a third test result of valve execution performance of the ground tank pressurizing system according to the opening and closing state and action response time of the valve; determining a fourth test result of control instruction execution deviation of the ground tank pressurizing system according to the deviation of control instruction and actual execution state of the tank pressurizing system; determining a fifth test result of actuator running state of the ground tank pressurizing system according to the rotating speed and power of the actuator; determining the test result of the ground tank pressurizing system according to the first test result, the second test result, the third test result, the fourth test result and the fifth test result.

[0012] Embodiments of the present application also provide a test device for a tank pressurizing system of a liquid carrier rocket, comprising: an acquisition module configured to acquire flight state data of the liquid carrier rocket; a processing module configured to determine a pressure change curve of a tank pressurizing system of the liquid carrier rocket according to the flight state data, perform pressure simulation on at least one ground tank pressurizing system according to the pressure change curve, load a preset fault mode into the ground tank pressurizing system in the pressure simulation state to perform testing, and obtain a test result of the ground tank pressurizing system.

[0013] Embodiments of the present application also provide a computing device, comprising: 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, the one or more processors implement the method according to any one of the above.

[0014] The above scheme of the embodiments of the present application at least has the following beneficial effects: The above scheme of the embodiment of the present application can dynamically reproduce the real pressure environment of the tank pressurization system of the rocket during flight by acquiring real flight state data (altitude, acceleration and fuel consumption rate) and generating a corresponding pressure change curve, and overcomes the defects of static simulation of fixed pressure and semi-static simulation of discontinuous and non-real-time pressure change, so that the test result is closer to the actual flight working condition.

[0015] Loading a preset fault mode on the basis of dynamic pressure simulation can more realistically simulate the fault scene that may occur in actual flight, so as to more accurately test the performance of the tank pressurization system under a fault state, and help to find potential problems and improve the reliability and stability of the system.

[0016] At least one ground tank pressurization system including a primary stage and a secondary stage can be subjected to pressure simulation, and the cooperative working capability of the multi-stage tank pressurization system under a dynamic pressure environment can be comprehensively tested, so as to meet the test requirements of a complex rocket system. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a flowchart of a test method for a tank pressurization system of a liquid launch vehicle according to an embodiment of the present application; Figure 2 is a module schematic diagram of a test device for a tank pressurization system of a liquid launch vehicle according to an embodiment of the present application. DETAILED DESCRIPTION

[0018] Exemplary embodiments of the present application will be described in greater detail below with reference to the accompanying drawings. Although exemplary embodiments of the present application are shown in the drawings, it should be understood that the present application can be implemented in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that the present application can be more thoroughly understood and the scope of the present application can be accurately conveyed to those skilled in the art.

[0019] As shown in Figure 1 , an embodiment of the present application provides a test method for a tank pressurization system of a liquid launch vehicle, comprising: Step 11, acquiring flight state data of the liquid launch vehicle; specifically, the flight state data includes altitude, acceleration and fuel consumption rate of the liquid launch vehicle; Step 12, determining a pressure change curve of the tank pressurization system of the liquid launch vehicle according to the flight state data; Step 13, performing pressure simulation on at least one ground tank pressurization system according to the pressure change curve; Step 14, loading a preset fault mode into the ground tank pressurization system in the pressure simulation state for testing, and obtaining a test result of the ground tank pressurization system.

[0020] In this embodiment, by acquiring real flight state data (altitude, acceleration and fuel consumption rate) and generating the corresponding pressure change curve, the real pressure environment of the tank pressurization system during the rocket flight process can be dynamically reproduced, overcoming the defects of fixed pressure in static simulation and discontinuous and non-real-time pressure change in semi-static simulation, making the test results closer to the actual flight working condition.

[0021] On the basis of dynamic pressure simulation, the preset fault mode is loaded, which can more realistically simulate the fault scene that may occur in actual flight, so as to more accurately test the performance of the tank pressurization system under the fault state, help to find potential problems and improve the reliability and stability of the system.

[0022] The pressure simulation can be performed on at least one ground tank pressurization system including a first stage and a second stage, which can comprehensively test the cooperative working capability of the multi-stage tank pressurization system under the dynamic pressure environment, and meet the test requirements of complex rocket systems.

[0023] In an optional embodiment of the present application, in step 12, the pressure change curve of the tank pressurization system of the liquid carrier rocket is determined according to the flight state data, comprising: In step 121, the flight phase of the liquid carrier rocket is determined according to the flight state data, and the flight phase comprises a climbing segment, a separation segment and a cruising segment. In step 122, the pressure change curve of the tank pressurization system of the liquid carrier rocket is determined according to the flight phase of the liquid carrier rocket.

[0024] In step 121, the flight phase of the liquid carrier rocket is determined according to the flight state data, comprising: In step 1211, when a ≥ a 1, and b ≤ b 1, it is determined that the flight phase of the liquid carrier rocket is the climbing segment. 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. In step 1212, when c ≤ c 1, it is determined that the flight phase of the liquid carrier rocket is the separation segment. Wherein, c is the fuel consumption rate of the liquid carrier rocket, c 1 is a third set value. Step 1213, in addition to the rising section and the separation section, the remaining flight phase is determined as the cruise section.

[0025] In step 122, according to the flight phase of the liquid carrier rocket, the pressure change curve of the tank pressurization system of the liquid carrier rocket is determined, including: In step 1221, according to , the pressure change curve of the tank pressurization system of the liquid carrier rocket is determined; Wherein, P ( t ) is the pressure of the tank pressurization system, t is the time.

[0026] In this embodiment, the quantitative flight phase judgment standard is established by the key flight state data of acceleration, altitude and fuel consumption rate, which upgrades the flight phase division from qualitative judgment to quantitative analysis, avoids the subjectivity of manual division, ensures the consistency and accuracy of the phase division, and provides a reliable basis for subsequent determination of the pressure change curve.

[0027] According to the characteristic differences of different flight phases (the rising section, the separation section and the cruise section), the pressure change curve is determined in stages, which can better fit the actual physical environment and system requirements of each stage. For example, the rising section may face severe acceleration changes and rapid altitude increases, and the corresponding pressure change law is significantly different from the smooth flight of the cruise section. The stage design curve can make the pressure simulation more consistent with the dynamic characteristics of the real flight, further reducing the deviation between the test and the actual working condition.

[0028] Because the pressure environment and system working state are different in different flight phases, the manifestation and influence of the fault mode may also be different. Based on the accurate division of the flight phase and the corresponding pressure change curve, the fault mode is loaded, which can more targetedly test the fault response ability of the system in a specific flight phase, make the fault test more scene-based and practical, and help to find potential problems specific to each phase.

[0029] The quantitative flight phase judgment standard and the stage-based pressure curve determination method make the parameter setting and execution logic of the entire test process more clear and standardized, reduce the ambiguity and uncertainty in the operation process, not only facilitate the accurate execution of the test personnel, but also improve the repeatability of the test results, which is beneficial to the comparative analysis of test data in different batches and different environments.

[0030] In an optional embodiment of the present application, in step 13, according to the pressure change curve, the pressure simulation is performed on at least one ground tank pressurization system, including: Step 131, according to the pressure change curve, using a hierarchical test architecture, simultaneously carries out pressure simulation for each ground tank pressurization system.

[0031] Specifically, for the first and second ground tank pressurization systems, simulation modules suitable for their characteristics are used, wherein the first tank simulation module is configured to support fast response of high pressure signals to simulate the high pressure pressurization requirement in the first stage of rocket flight; the second tank simulation module is designed for pulse pressure mutation, which is suitable for the possible rapid pressure fluctuation scenario in the second stage of flight.

[0032] Through high-performance FPGA (Field Programmable Gate Array), multi-channel parallel data acquisition is realized, and real-time data recording is carried out for the pressure simulation process of the first and second tanks, ensuring the synchronization and data accuracy of the pressure simulation of each tank.

[0033] High-speed Ethernet protocol is used for test instruction transmission and data feedback, and the system response delay is controlled within milliseconds, realizing the coordinated linkage of the first and second ground tank pressurization systems in the pressure simulation process, thereby completing the system-level integrated test verification.

[0034] In this embodiment, according to the characteristic differences of the first and second ground tank pressurization systems, suitable simulation modules are configured (the first supports fast response of high pressure signals, and the second adapts to pulse pressure mutation), which can accurately match the actual pressurization requirements of different stages of rockets. Avoiding the precision loss caused by general simulation, the pressure simulation of each tank is more consistent with its real working scenario, improving the effectiveness of subsystem testing.

[0035] Through high-performance FPGA, multi-channel parallel data acquisition is realized, and real-time recording is carried out for the pressure simulation process of the first and second tanks, solving the time difference problem that may be caused by traditional serial acquisition, and ensuring the synchronization of multi-stage system pressure simulation. At the same time, the parallel processing capability improves the efficiency and integrity of data acquisition, providing high-quality raw data for subsequent analysis of the cooperative working characteristics of each stage system.

[0036] Using high-speed Ethernet protocol, the system response delay is controlled within milliseconds, ensuring the coordinated linkage of the first and second tank pressurization systems in the pressure simulation process. This low-delay coordination capability enables the test to upgrade from subsystem simulation to system-level integrated verification, which can more realistically reproduce the linkage working state of the multi-stage tank pressurization system in rocket flight, effectively verifying the matching and coordination between systems.

[0037] The special design for the first high pressure demand and the second pulse pressure mutation and other complex scenes enables the test system to cover the extreme pressure environment that may occur in rocket flight. This not only improves the comprehensiveness of the test, but also provides a more stringent test standard for verifying the stability and reliability of the tank pressurization system under complex working conditions.

[0038] In an optional embodiment of the present application, in step 14, the preset fault mode is loaded to the ground tank pressurization system in the pressure simulation state for testing to obtain the test result of the ground tank pressurization system, including: Step 141, obtain a preset fault mode library containing pipeline leakage, valve sticking and sensor failure; Step 142, load at least one fault mode in the preset fault mode library to the ground tank pressurization system under pressure simulation to simulate the fault mode in real flight; specifically, for pipeline leakage: by presetting a controllable micro electromagnetic valve in the pressurization pipeline, the valve opening degree is controlled by sending a pulse signal from the control system to simulate leakage faults of different leakage amounts; at the same time, the flow change before and after leakage is monitored in real time by the flow sensor to ensure that the leakage amount is consistent with the preset fault level; for valve sticking: a time delay relay or a signal interference module is connected in the control loop of the valve drive motor, the time delay time is set to simulate the valve action delay, or an error electric signal is sent to simulate the fault that the valve is stuck in full opening, full closing or a certain intermediate position; for sensor failure: the original signal is tampered by the sensor signal acquisition module, including: sending a fixed deviation signal, a random noise signal and a signal interruption to simulate the fault states of sensor drift, distortion and complete failure, respectively; Step 143, collect real-time data of the ground tank pressurization system under the fault mode; Step 144, determine the test result of the ground tank pressurization system according to the real-time data.

[0039] In step 143, the real-time data includes: real-time pressure value and pressure change rate in the tank, flow and temperature in the pressurization pipeline, opening and closing state and action response time of the valve, deviation of control instruction and actual execution state of the tank pressurization system, and rotation speed and power of the execution mechanism.

[0040] In step 144, according to the real-time data, the test result of the ground tank pressurization system is determined, including: Step 1441, according to the real-time pressure value and pressure change rate in the tank, determine the first test result of the pressure system of the ground tank pressurization system; Step 1442, according to the flow and temperature in the pressurization pipeline, determine the second test result of the pipeline fluid state evaluation of the ground tank pressurization system; Step 1443, according to the opening and closing state of the valve and the action response time, determine the third test result of the valve execution performance of the ground tank pressurization system; Step 1444, according to the deviation between the control instruction and the actual execution state of the tank pressurization system, determine the fourth test result of the control instruction execution deviation of the ground tank pressurization system; Step 1445, according to the rotation speed and power of the execution mechanism, determine the fifth test result of the execution mechanism running state of the ground tank pressurization system; Step 1446, according to the first test result, the second test result, the third test result, the fourth test result and the fifth test result, determine the test result of the ground tank pressurization system.

[0041] Specifically, according to , determine the pressure deviation coefficient of the pressure system; Wherein, d is the pressure deviation coefficient, x 1( t ) is the real-time pressure value in the tank, x 2( t ) is the pressure value of the pressure change curve of the tank pressurization system (i.e. the target pressure value in the tank); According to , determine the pressure rate deviation coefficient of the pressure system; Wherein, e is the pressure rate deviation coefficient, y 1( t ) is the real-time pressure rate value in the tank, y 2( t ) is the pressure rate value of the pressure change curve of the tank pressurization system (i.e. the target pressure rate value in the tank); According to , determine the first test result; Wherein, f is the first test result, d 1 is the pressure deviation coefficient threshold, e 1 is the pressure rate deviation coefficient threshold; According to , determine the flow fluctuation coefficient of the pressurization pipeline; Wherein, g is the flow fluctuation coefficient, maxz 1( t ) is the maximum value of the real-time flow of the pressurization pipeline, minz 1( t ) is the minimum value of the real-time flow of the pressurization pipeline, z 2 is the set nominal flow of the pressurization pipeline; According to , determine the temperature overrun time length ratio of the supercharging pipeline; Wherein, h is the temperature overrun time length ratio of the supercharging pipeline, t 0 is the starting time, t 1 is the end time, m ( t ) is the real-time temperature of the supercharging pipeline, m min is the lower limit of the temperature of the supercharging pipeline, m max is the upper limit of the temperature of the supercharging pipeline; According to , determine the second test result; Wherein, i is the second test result, g 1 is the flow fluctuation coefficient threshold; According to , determine the state consistency ratio of the valve execution performance; Wherein, j is the state consistency ratio, t 0 is the starting time, t 1 is the end time, k 1( t ) is the valve response state, k 2( t ) is the valve command state; According to , determine the response time overrun times of the valve execution performance; Wherein, k is the response time overrun times, u=1,2,3...,v,v is the total response times, l u is the response time of each time, l max is the maximum allowed response time; According to , determine the third test result; Wherein, o is the third test result, j 1 is the state consistency ratio threshold; According to , determine the deviation of the control command and the actual execution state; Wherein, p is the deviation, q 1 is the control command, q 2 is the actual execution state; According to , determine the root mean square of the deviation; Wherein, r is the root mean square of the deviation, s=1,2,3...,w,w is the total deviation times, p s is the amount of each deviation; According to , the fourth test result is determined; Wherein, α is the fourth test result, r 1 is the root mean square threshold of the deviation; According to , the speed deviation coefficient of the actuator is determined; Wherein, β is the speed deviation coefficient, γ 1 is the real-time speed of the actuator, γ 2 is the rated speed of the actuator; According to , the power overrun proportion of the actuator is determined; Wherein, δ is the power overrun proportion, t 0 is the starting time, t 1 is the end time, ε 1( t ) is the real-time power of the actuator, ε 2 is the rated power of the actuator, and 1.1 is the safety coefficient; According to , the fifth test result is determined; Wherein, φ is the fifth test result, β 1 is the speed deviation coefficient threshold; According to λ=η 1× f+η 2× i+η 3× o+η 4× o+η 5× φ , the test score of the ground tank pressurization system is determined; Wherein, λ is the test score, η 1、 η 2、 η 3、 η 4、 η 5 are the first, second, third, fourth and fifth score coefficients respectively; If λ≧ 0.9, the test result of the ground tank pressurization system is test passed; If 0.7 ≦λ≦ 0.9, the test result of the ground tank pressurization system is basically available; Ifλ< 0.7, the test result of the ground tank pressurization system is fail.

[0042] In this embodiment, a preset fault mode library is established, which contains pipeline leakage, valve jamming and sensor failure, and accurately corresponds to the core failure risk points of the rocket tank pressurization system. Each fault is realized by controllable simulation through hardware modification (such as micro electromagnetic valve, delay relay) and signal processing (such as signal tampering), which not only ensures the authenticity of the fault scene, but also accurately controls the fault level (such as different leakage amounts, jamming degrees), providing standardized scenes for comprehensive testing of system fault response capability.

[0043] Real-time collection of multi-dimensional data such as pressure, flow, temperature, valve state, control deviation, actuator parameters, covers the core links of pressure regulation, fluid transmission, mechanism action, control logic of the tank pressurization system. This full-dimensional data collection ensures comprehensive insight into system performance and avoids the limitations of single indicator evaluation.

[0044] By defining quantitative indicators such as pressure deviation coefficient, flow fluctuation coefficient, and state consistency ratio through mathematical formulas, the abstract system performance is converted into calculable numerical parameters. At the same time, based on threshold judgment and weighted scoring, a grading judgment standard is established, completely getting rid of the qualitative judgment relying on experience in traditional testing, making the test results more objective, comparable and persuasive.

[0045] Generating test results (first to fifth test results) by module (pressure system, pipeline fluid, valve performance, control execution, actuator) can accurately locate the specific impact of faults on each link of the system. For example, valve jamming fault can directly reflect its impact on the actuator through the third test result (state consistency ratio, response time over-limit times), and indirectly reflect its impact on overall pressure regulation through the first test result (pressure deviation), providing a clear direction for fault tracing and system optimization.

[0046] From fault mode library establishment, fault loading method, data collection items to result calculation method, a standardized process is formed, which not only ensures the consistency and repeatability of different batches of tests, but also provides a flexible framework for subsequent expansion of new fault modes or optimization of evaluation indicators, improving the adaptability and vitality of the test method.

[0047] In an optional embodiment of the present application, the above method further comprises: Step 15, constructing a virtual simulation model of the ground tank pressurization system test to realize real-time synchronization of physical testing and virtual simulation.

[0048] Specifically, based on the physical structure and working principle of the ground tank pressurization system, a high-fidelity virtual simulation model is constructed using multi-domain modeling tools.

[0049] In this embodiment, the pressure change curve is determined by acquiring flight state data, the ground system pressure is simulated in real time, the preset fault mode is loaded, and virtual simulation is combined to realize dynamic and accurate testing. The method can improve the authenticity and accuracy, cover multiple systems, reduce cost risks, and provide strong support for system optimization and reliability.

[0050] Example 1 For the tank pressurization system of a liquid carrier rocket that needs to be tested, example 1 provides a test method for a tank pressurization system of a liquid carrier rocket, comprising: Step 21, the flight state data of a typical mission is retrieved from a rocket flight database: the height, acceleration and fuel consumption rate time curve of the ascent phase (height < 100 km, acceleration ≥ 5g), the separation phase (fuel consumption rate ≤ 0.1 kg / s), and the cruise phase (height > 100 km and fuel consumption rate > 0.1 kg / s); Step 22, automatically divide the flight phase according to the preset threshold: when the real-time collected acceleration a = 6g (a1 = 5g) and the height h = 80km (h1 = 100km), it is determined that it is the ascent phase, and the pressure curve of (p(t)) = 5 + 0.02t is called; when the fuel consumption rate f = 0.08kg / s (f1 = 0.1kg / s), switch to the pulse pressure curve of the separation phase; the rest of the period is simulated according to the smooth curve of the cruise phase; a b b P t t c c Step 23: The primary tank simulation module realizes millisecond-level response of 0-10MPa pressure through a high-pressure electromagnetic valve group, simulating the high-pressure environment when the primary engine is working; the secondary tank simulation module carries a pressure shock generator to reproduce the ±2MPa pulse fluctuation in the separation phase; at the same time, the FPGA module synchronously collects the pressure data of the two-stage tank (sampling rate 1kHz), and transmits the data to the control console through gigabit Ethernet, ensuring that the data delay is <5ms; Step 24, when fault testing, first activate the pipeline leakage mode: control the 0.5mm diameter miniature electromagnetic valve to open 30%, the flow sensor displays the real-time leakage amount 0.2L / min (consistent with the preset fault level), and the tank pressure drop rate is recorded from 0.1MPa / s to 0.3MPa / s; then load the valve sticking fault, delay the action of the secondary filling valve by 1.2s (exceeding the threshold of 0.8s) through the time delay relay, causing the pressure fluctuation coefficient to rise from 5% to 18%; Step 25, calculate the pressure deviation coefficient d = 0.07 (<d1 = 0.1), the flow fluctuation coefficient​​​​​​​​g =0.15 (> g 1=0.1), the final weighted score λ =0.82, determined as "basically available", and the root cause of the fault is located as the secondary valve response delay, providing a clear direction for subsequent structural optimization.

[0051] The application generates a pressure change curve by obtaining real flight state data, combines quantitative determination in stages (the ascending stage, the separation stage and the cruising stage) and targeted pressure curve design, dynamically reproduces the real flight pressure environment, completely overcomes the limitations of static and semi-static simulation, greatly improves the test authenticity, and reduces the deviation from the actual working condition. A hierarchical test architecture is adopted, simulation modules suitable for the characteristics of the first and second ground storage tanks are configured, and multi-channel parallel acquisition and high-speed Ethernet communication (millisecond level delay) are used to realize synchronous simulation and collaborative linkage of multi-level systems, so that the system level integrated verification is upgraded from the subsystem test, the pressurization requirements of different stages are accurately matched, and the test comprehensiveness under complex scenes is ensured.

[0052] A mode library containing core faults such as pipeline leakage and valve sticking is constructed, controllable simulation is realized through hardware modification and signal processing, multi-dimensional data acquisition (pressure, flow, valve state, etc.) and quantitative evaluation system (pressure deviation coefficient, flow fluctuation coefficient, etc.) are combined, a "fault loading-data acquisition-quantitative determination" closed loop is formed, the test is changed from experience-driven to data-driven, and the result objectivity and fault tracing efficiency are improved. New physical test and virtual simulation are synchronized in real time, the limitations of physical test are complemented through high-fidelity virtual model, the resource consumption of high-risk and high-cost test is reduced, the dynamic characteristics of the system are deeply analyzed and the design iteration is quickly verified, and the technical support for system optimization and reliability improvement is further strengthened.

[0053] As Figure 2 shown in the figure, the embodiment of the application further provides a test device 20 of a storage tank pressurization system of a liquid carrier rocket, comprising: An acquisition module 21 is configured to acquire flight state data of the liquid carrier rocket. A processing module 22 is configured to determine a pressure change curve of the storage tank pressurization system of the liquid carrier rocket according to the flight state data, perform pressure simulation on at least a first ground storage tank pressurization system according to the pressure change curve, load a preset fault mode into the ground storage tank pressurization system in the pressure simulation state for testing, and obtain a test result of the ground storage tank pressurization system.

[0054] Optionally, the flight state data comprises height, acceleration and fuel consumption rate of the liquid carrier rocket, and determining the pressure change curve of the storage tank pressurization system of the liquid carrier rocket according to the flight state data comprises: determining a flight phase of the liquid carrier rocket according to the flight state data, the flight phase comprising a boost phase, a separation phase and a cruise phase; determining a pressure change curve of the tank pressurization system of the liquid carrier rocket according to the flight phase of the liquid carrier rocket.

[0055] Optionally, determining the flight phase of the liquid carrier rocket according to the flight state data comprises: when a ≥ a 1, and b ≤ b 1, determining the flight phase of the liquid carrier rocket as the boost phase; wherein, a is an acceleration of the liquid carrier rocket, a 1 is a first set value, b is a height of the liquid carrier rocket, b 1 is a second set value; when c ≤ c 1, determining the flight phase of the liquid carrier rocket as the separation phase; wherein, c is a fuel consumption rate of the liquid carrier rocket, c 1 is a third set value; determining the flight phase of the liquid carrier rocket as the cruise phase except the boost phase and the separation phase.

[0056] Optionally, 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: determining the pressure change curve of the tank pressurization system of the liquid carrier rocket according to ; wherein, P is a pressure of the tank pressurization system, t is time. t

[0057] Optionally, performing pressure simulation on at least one ground tank pressurization system according to the pressure change curve comprises: performing pressure simulation on each ground tank pressurization system simultaneously according to the pressure change curve by using a hierarchical test architecture.

[0058] Optionally, loading a preset fault mode to the ground tank pressurization system in the pressure simulation state for testing to obtain a test result of the ground tank pressurization system comprises: obtaining a preset fault mode library containing pipeline leakage, valve sticking and sensor failure;​ loading at least one fault mode in the preset fault mode library to the ground tank pressurization system under pressure simulation to simulate the fault mode in real flight; collecting real-time data of the ground tank pressurization system under the fault mode; determining a test result of the ground tank pressurization system according to the real-time data.

[0059] Optionally, the real-time data includes: real-time pressure value and pressure change rate in the tank, flow and temperature in the pressurization pipeline, on-off state and action response time of the valve, deviation of control instruction and actual execution state of the tank pressurization system, and rotating speed and power of the execution mechanism.

[0060] Optionally, determining the test result of the ground tank pressurization system according to the real-time data includes: determining a first test result of a 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 pipeline fluid state evaluation of the ground tank pressurization system according to the flow and temperature in the pressurization pipeline; determining a third test result of valve execution performance of the ground tank pressurization system according to the on-off state and action response time of the valve; determining a fourth test result of control instruction execution deviation of the ground tank pressurization system according to the deviation of control instruction and actual execution state of the tank pressurization system; determining a fifth test result of execution mechanism running state of the ground tank pressurization system according to the rotating speed and power of the execution mechanism; determining the 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.

[0061] It should be noted that the device corresponds to the above method, and all implementation manners in the above method embodiments are applicable to this embodiment and can achieve the same technical effects.

[0062] Embodiments of the application also provide a computing device, including: one or more processors; a storage device for storing 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 as described above. All implementation manners in the above method embodiments are applicable to this embodiment and can achieve the same technical effects.

[0063] The embodiment of the present application further provides a computer device readable storage medium, which stores instructions, and when the instructions are run on the computer device, the computer device executes the method as described above. All implementation manners in the above method embodiment are applicable to this embodiment, and the same technical effects can be achieved.

[0064] Those skilled in the art can clearly understand that the units and algorithm steps of the examples described in combination with the embodiments disclosed in the present application can be realized by electronic hardware or a combination of software and electronic hardware of a computing device. Whether the functions are realized 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 realize the described functions for each specific application, but such implementation should not be considered beyond the scope of the present application.

[0065] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the above-described system, device and unit can refer to the corresponding processes in the foregoing method embodiments, which will not be repeated here.

[0066] In the embodiments provided by the present application, it should be understood that the disclosed device and method can be implemented in other ways. For example, the device embodiments described above are only schematic. The division of the units is only a logical function division. There can be another division manner in actual implementation. For example, a plurality of units or components can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the displayed or discussed mutual couplings or direct couplings or communication connections between the units can be indirect couplings or communication connections through some interfaces, devices or units, and can be electrical, mechanical or in other forms.

[0067] The units described as separate components can or can not be physically separate, and the components displayed as units can or can not be physical units, i.e. can be located in one place, or can be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the embodiment.

[0068] In addition, each functional unit in each embodiment of the present application can be integrated into a processing unit, or each unit can exist physically independently, or two or more units can be integrated into one unit.

[0069] If the functions are implemented in the form of software function units and sold or used as independent products, they can be stored in a storage medium readable by a computing device. Based on this understanding, the technical solutions of the present application or the parts that essentially contribute to the prior art or the parts of the technical solutions can be embodied in the form of software products. The computing device software product is stored in a storage medium and includes a plurality of instructions for causing a computing device (which can be a personal computing device, a server, or a network device, etc.) to execute all or part of the steps of the method described in the various embodiments of the present application. The aforementioned storage medium includes a U disk, a mobile hard disk, a ROM, a RAM, a magnetic disk or an optical disk, and various program code storage media.

[0070] In addition, it should be noted that in the device and method of the present application, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered as equivalent solutions of the present application. Moreover, the steps of performing the above series of processes can naturally be executed in time sequence according to the order of description, but do not necessarily have to be executed in time sequence. Some steps can be executed in parallel or independently of each other. It can be understood by those skilled in the art that all or any steps or components of the method and device of the present application can be implemented in hardware, firmware, software or a combination thereof in any computing device (including a processor, a storage medium, etc.) or a network of computing devices, which can be implemented by those skilled in the art with basic programming skills after reading the description of the present application.

[0071] Therefore, the object of the present application can also be achieved by running a program or a set of programs on any computing device. The computing device can be a commonly known general-purpose device. Therefore, the object of the present application can also be achieved by merely providing a program product containing program code for implementing the method or device. That is, such a program product also constitutes the present application, and a storage medium storing such a program product also constitutes the present application. Obviously, the storage medium can be any commonly known storage medium or any storage medium developed in the future. It should be noted that in the device and method of the present application, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered as equivalent solutions of the present application. Moreover, the steps of performing the above series of processes can naturally be executed in time sequence according to the order of description, but do not necessarily have to be executed in time sequence. Some steps can be executed in parallel or independently of each other.

[0072] The above is the preferred embodiment of the present application. It should be noted that for those skilled in the art, without departing from the principles of the present application, a number of improvements and refinements can be made, which should also be considered within the scope of protection of the present application.

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.

2. The method of testing a liquid boost vehicle tank pressurization system of claim 1, wherein, 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: 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.

3. The method of testing a liquid boost rocket tank pressurization system of claim 2, wherein, The method of determining the flight phase of the liquid carrier rocket according to the flight state data comprises: When a ≥ a 1, and b ≤ b 1, determine the flight phase of the liquid carrier rocket as the ascending segment; 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 as the cruising phase except for the climbing phase and the separation phase.

4. The method of testing a liquid boost rocket tank pressurization system of claim 2, 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: 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.

5. The method of testing a liquid boost system of a liquid launch vehicle tank as defined in claim 1, wherein, performing pressure simulation on at least one ground tank pressurization system according to the pressure change curve comprises: performing pressure simulation on each ground tank pressurization system simultaneously according to the pressure change curve by using a hierarchical test architecture.

6. The method of testing a liquid boost system of a liquid launch vehicle tank as defined in claim 1, wherein, 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: 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; determining the test result of the ground tank pressurization system according to the real-time data.

7. The method of testing a liquid boost rocket tank pressurization system of claim 6, 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 actual execution state of the tank pressurization system, and the rotation speed and power of the execution mechanism.

8. The method of testing a liquid boost rocket tank pressurization system of claim 7, wherein, The method of determining the test result of the ground tank pressurization system according to the real-time data comprises: 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 actual execution state of the tank pressurization system; and determining a fifth test result of the rotation speed and power of the execution mechanism of the ground tank pressurization system according to the rotation speed and power of the execution mechanism. 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.

9. 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 level of 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 for testing, and obtain a test result of the ground tank pressurization system.

10. 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 8.

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