A method for evaluating the consistency between the ground and the average pressure during the separation and pressure building process of rocket stages

Abstract

The present invention relates to a method for evaluating the consistency between the earth and the sky of the average pressure during the separation and pressure building process of rocket stages: for the separation and pressure building process of rocket stages, the pressure rising speed of the temperature rising section and the temperature stable section of the engine flight test state is calculated; under the condition of the determined total enthalpy of the detonation gas product, the product of the outlet section flow rate and the total enthalpy is close to the flight test state, and the outlet flow rate required for the test is obtained; according to the outlet flow rate, the pressure rising speed of the pressure building process of the rocket engine ground simulation device is evaluated, and it is confirmed that the difference between the pressure rising process of the ground simulation device and the flight test state is within the engineering application deviation requirement; the working environment of the ground simulation device is evaluated; and the degree of over-assessment of the pressure rising speed of the pressure building process of the ground simulation device compared with the flight test state is evaluated. The equivalent simulation of the flight state of the internal environment and the external environment in the ground test plan is realized, so that the ground test can reasonably verify the real pressure building process of the interstage thermal separation in the multi-stage rocket flight test.

Description

Technical Field

[0001] The present invention belongs to the technical field of rocket engine devices and relates to a method for evaluating the ground-to-earth consistency of average pressure during the separation and pressure building process between rocket stages. Background Art

[0002] As a key link in the flight process of a multi-stage rocket, the smooth execution of the separation between the upper and lower stage engines is an important condition for ensuring the success of the flight. In order to ensure that the designed separation scheme can make the flight test a complete success, the separation scheme must be evaluated through ground tests. Among them, for the interstage thermal separation scheme, the ground test methods currently commonly used include the system-level test method using the real technical state product, and the recently proposed test method of using the detonation shock wind tunnel to simulate the strong impact of the engine jet. In the system-level test, the upper stage engine, servo mechanism, and separation system all adopt the state of the rocket product, and the real internal gas jet environment is generated through actions such as engine ignition and plug opening, while the external test environment can be selected as an open test site or a vacuum test chamber that is closer to the flight state. In the detonation shock wind tunnel test, the interstage shell and the separation pyrotechnics are basically close to the real product state. The internal environment generated by the engine jet can be equivalently simulated by adjusting the charge amount and detonation method of the detonation chamber, and the external test environment is generally an open test site.

[0003] However, the above two ground test methods cannot simulate the internal and external environments during flight at the same time due to the constraints of test conditions. In existing engineering practice, due to the lack of reliable theoretical guidance, there is no prior parameter formulation method that can support the simulation of the internal and external environments in the ground test plan, making it difficult to conduct a ground-to-earth consistency assessment of the test plan (i.e., the assessment of the consistency between the test environment in the ground simulation device and the flight test environment). The equivalence of the ground test plan mainly depends on the experience of designers and data analysis based on numerical simulation, which leads to an increase in the number of tests, an extension of the cycle, and an increase in development costs. Summary of the invention

[0004] The technical problem solved by the present invention is: in view of the constraint that the existing ground simulation device for interstage thermal separation cannot truly simulate the internal jet environment and the external environment at the same time, the deficiency of the lack of a priori ground-ground consistency assessment method in existing engineering practice is overcome, and a ground-ground consistency assessment method for the average pressure of the rocket interstage separation pressure building process is proposed, so as to realize the equivalent simulation of the flight state of the internal environment and the external environment in the ground test plan, so that the ground test can reasonably verify the actual pressure building process of interstage thermal separation in the multi-stage rocket flight test.

[0005] The technical solution of the present invention is: a method for evaluating the consistency between the average pressure of the rocket stage separation and pressure building process and the ground, comprising the following steps:

[0006] S1. For the rocket interstage separation and pressure building process, calculate the approximate value of the interstage separation and pressure building process in the engine flight test state, obtain the characteristic time in the pressure building process, the pressure rise rate proportional coefficient of the temperature rise section and the temperature stable section, and then obtain the pressure rise rate of the temperature rise section and the temperature stable section;

[0007] S2. Adjust the operating parameters of the ground simulation device so that under the condition of the determined total enthalpy of the detonation gas products, the product of the outlet flow rate and the total enthalpy is close to the flight test state, and the outlet flow rate required for the test is obtained;

[0008] S3. According to the outlet flow rate obtained in step S2, the pressure rise rate of the rocket engine ground simulation device during the pressure buildup process is evaluated, and compared with the pressure rise rate of the flight test state obtained in step S1, to confirm that the difference between the pressure rise process of the ground simulation device and the flight test state is within the engineering application deviation requirement;

[0009] S4. Evaluate the working environment of the ground simulation device until it meets the consistency of engineering application;

[0010] S5. Based on step S4, evaluate the degree of over-test of the pressure rise rate during the pressure building process of the ground simulation device compared with the flight test state, and confirm that the over-test degree is within the engineering application deviation requirements to avoid damage to the test product.

[0011] Furthermore, the characteristic time calculation method during the pressure buildup process of the engine flight test state is as follows:

[0012]

[0013] is the initial density, is the cavity volume, is the engine outlet flow rate during the pressure buildup process, and are the gas constants of fuel gas and air respectively; characteristic time Indicates the duration for the temperature to reach a stable level.

[0014] Furthermore, the calculation method of the pressure rise rate proportionality coefficient of the temperature rise section and the temperature stable section of the engine flight test state is as follows:

[0015] ,

[0016] is the proportional coefficient of the pressure rise rate in the temperature rise section of the engine flight test state, is the proportional coefficient of the pressure rise rate in the temperature stable section of the engine flight test state, is the constant volume specific heat of the engine gas, is the specific heat at constant volume of air.

[0017] Furthermore, the calculation method of the pressure rise rate in the temperature rise section and the temperature stable section of the engine flight test state is as follows:

[0018] Pressure rise rate in the temperature rise stage :

[0019]

[0020] Pressure rise rate in the temperature stable section :

[0021]

[0022] in, is the total enthalpy in the engine combustion chamber, K is the empirical coefficient of heat loss.

[0023] Furthermore, the outlet flow rate required for the test described in step S2 is calculated as follows:

[0024] Total enthalpy of detonation gas products at the known outlet section Under the condition of , so that it satisfies the following relationship:

[0025]

[0026] is the specific heat ratio of the detonation gas products, is the pressure rise rate proportional coefficient of the temperature rise stage during the pressure buildup process of the ground simulation device for rocket stage separation. is the nozzle throat area of ​​the ground simulation device;

[0027] According to the total pressure of the outlet section , select the operating parameters of the ground simulation device, including the charge amount, charging method and ignition sequence, and evaluate the outlet flow rate of the ground simulation device during the pressure build-up process of the interstage separation simulation test by searching the test equipment operating parameter relationship table under the selected parameters .

[0028] Furthermore, the method for calculating the pressure rise rate during the pressure building process of the ground simulation device is as follows:

[0029] Calculation of characteristic time of pressure buildup process in ground simulation device for rocket stage separation :

[0030]

[0031] is the gas constant of the detonation gas product;

[0032] Calculate the proportional coefficient of pressure rise rate in the temperature rise phase and temperature stable phase of the pressure building process of the ground simulation device for rocket stage separation and :

[0033] ,

[0034] is the constant volume specific heat of the detonation gas products;

[0035] For the temperature rise stage, the pressure rise rate as follows:

[0036]

[0037] For the temperature plateau, the pressure rise rate as follows:

[0038] .

[0039] Furthermore, it is confirmed that the difference between the pressure rise process of the ground simulator and the flight test state is within the engineering application deviation requirements, as follows:

[0040] Compare the pressure rise rate in the temperature stable section of the flight test state and the ground simulation device to confirm that the deviation value does not exceed the engineering application deviation requirements. If the engineering application deviation requirements are not met, the outlet flow rate Make fine adjustments in an amplitude of ±2% until the pressure rise rate in the temperature stable section of the ground simulation device and the pressure rise rate in the temperature stable section of the flight test state are within the engineering application deviation requirements.

[0041] Further, the method for evaluating the working environment of the ground simulator is as follows:

[0042] S41, calculate the nozzle exit parameters of the rocket stage separation ground simulation device based on the one-dimensional variable cross-section adiabatic steady flow relationship, including the pressure at the nozzle exit of the engine in the ground simulation device ,density ;

[0043] S42, based on the Rankine-Hugoniot relationship, calculate the shock wave velocity at the initial moment of the pressure buildup process of the ground simulation device for rocket stage separation The velocity of gas after the wave :

[0044]

[0045] in , are the initial pressure and density in the test environment, respectively;

[0046] S43, evaluate the quantitative difference between the initial shock wave's "shock wave-contact discontinuity-expansion wave" three-wave structure in the flight test state and the ground simulation device test: calculate the shock wave velocity at the initial moment The velocity of gas after the wave The difference

[0047]

[0048] If satisfied:

[0049]

[0050] If the deviation of the ground simulation device for separation between rocket stages from the flight test state meets the requirements of the consistency between the sky and the earth in engineering applications, otherwise, the environmental parameters of the test device are adjusted to reduce the initial pressure in the test environment. and density , re-execute steps S42~S43.

[0051] Furthermore, the pressure rise rate during the pressure building process of the ground simulation device is evaluated to see if it is over the flight test state. The method is as follows:

[0052] The total time of the pressure buildup process achieved according to the pressure rise rate during the separation and pressure buildup process of the rocket stages and the separation sequence of the flight test , evaluate the maximum pressure during the interstage separation and pressure building process of the flight test :

[0053]

[0054] According to the pressure rise rate of the interstage separation ground simulation device during the pressure building process and the total time of the ground simulation test pressure building process , evaluate the maximum pressure in the ground simulation test :

[0055]

[0056] Comparison of maximum pressure in ground simulation tests The maximum pressure during the pressure buildup during stage separation , calculate the degree of ground simulation test passing assessment, express;

[0057] If you pass the assessment and If it is within the scope of product engineering application requirements, the passing degree of the ground simulation test will be accepted, otherwise it will not be accepted.

[0058] A computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps of a method for evaluating the ground-to-space consistency of the average pressure during the separation and pressure building process between rocket stages.

[0059] The beneficial effects of the present invention compared with the prior art are:

[0060] (1) The present invention adopts a two-stage linear ascent and pressure-building process approximate model to realize the characteristic parameter analysis and quantitative evaluation method of the pressure rise rate during the separation and pressure-building process of multi-stage rocket stages, and realizes the ground-to-earth consistency evaluation process based on the theoretical model of the pressure-building process. Compared with the bottleneck of relying on a posteriori results in existing engineering practice, under the premise of meeting the engineering application deviation allowance, it can more accurately and effectively evaluate the consistency between the internal flow process of the ground simulation device and the flight test, and can effectively support the ground test to achieve equivalent simulation of the flight environment.

[0061] (2) The present invention uses a theoretical model based on the relationship between the parameters before and after the shock wave, which realizes the characteristic parameter analysis and quantitative evaluation method of the shock wave flow during the separation and pressure building process between multi-stage rocket stages, and realizes the ground-to-space consistency evaluation process based on the shock wave system model. Compared with the bottleneck of relying on a posteriori results in existing engineering practice, under the premise of meeting the allowable deviation of engineering application, it can more accurately and effectively evaluate the consistency between the external test environment of the ground simulation device and the flight test, and can effectively support the ground test to achieve equivalent simulation of the flight environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0062] Figure 1 This is a flow chart of the method for evaluating the consistency between the ground and the average pressure during the separation and pressure building process of rocket stages proposed by the present invention;

[0063] Figure 2 This is a schematic diagram of the separation and pressure building process between rocket stages in Example 1, which can be approximated as two stages of linear rise over time, with the first stage representing the temperature rise stage and the second stage representing the temperature stable stage. DETAILED DESCRIPTION

[0064] like Figure 1 As shown, the method for evaluating the consistency between the ground and the average pressure during the separation and pressure building process of rocket stages proposed by the present invention includes the following steps:

[0065] Step 1: For the rocket interstage separation and pressure building process, calculate the approximate value of the interstage separation and pressure building process in the engine flight test state, obtain the characteristic time in the pressure building process, the pressure rise rate proportional coefficient of the temperature rise section and the temperature stable section, and then obtain the pressure rise rate of the temperature rise section and the temperature stable section;

[0066] Step 2: Adjust the operating parameters of the ground simulation device so that under the determined total enthalpy of the detonation gas products, the product of the outlet flow rate and the total enthalpy is close to the flight test state, and the outlet flow rate required for the test is obtained;

[0067] Step 3: Based on the outlet flow rate obtained in step 2, evaluate the pressure rise rate of the rocket engine ground simulation device during the pressure buildup process, and compare it with the pressure rise rate of the flight test state obtained in step 1 to confirm that the difference between the pressure rise process of the ground simulation device and the flight test state is controlled within the engineering application deviation requirements;

[0068] Step 4: Evaluate the working environment of the ground simulation device until it meets the consistency of engineering application;

[0069] Step 5. Based on step 4, evaluate the degree of over-test of the pressure rise rate during the pressure building process of the ground simulation device compared with the flight test state, and confirm that the over-test degree is within the engineering application deviation requirements to avoid damage to the test product.

[0070] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0071] Example 1

[0072] Step S1: Figure 2 The approximate model of the rocket interstage separation and pressure building process shown is used to calculate the approximate value of the interstage separation and pressure building process in the engine flight test state, and the characteristic time in the pressure building process, the proportional coefficient of the pressure rise rate in the temperature rise section and the temperature stable section are obtained, and then the pressure rise rate in the temperature rise section and the temperature stable section is obtained.

[0073] Step S1 is specifically as follows:

[0074] Sub-step S11, calculate the characteristic time of the pressure building process of the rocket engine flight test state according to the following formula :

[0075]

[0076] in, is the initial density, is the cavity volume, is the engine outlet flow rate during the pressure buildup process, and are the gas constants of fuel gas and air respectively. It indicates the duration for the temperature to reach a stable state, and is also the duration of the first temperature rise section of the pressure curve during the pressure buildup process. Since the interstage separation point is at a high altitude under the flight test state, if no special sealing measures are taken, the gas pressure in the interstage is close to the external static pressure, the pressure is lower, and the density is smaller, so the characteristic time For a typical solid rocket engine, the characteristic time Generally it is 0.4ms.

[0077] Sub-step S12, calculate the pressure rise rate proportionality coefficient of the temperature rise stage and the temperature stable stage of the pressure build-up process of the rocket engine flight test state according to the following formula and :

[0078] ,

[0079] Furthermore, according to the above two proportional coefficients , , calculate the amplification factor of the pressure rise rate in the temperature rise stage relative to the pressure rise rate in the temperature stable stage according to the following formula:

[0080]

[0081] in: are the specific heat at constant volume and specific heat ratio of the engine gas respectively; are the constant volume specific heat and specific heat ratio of air respectively; the coefficient The value is generally greater than 1, that is, the pressure rise rate in the temperature rise phase is higher than the pressure rise rate in the temperature stable phase. For a typical solid rocket engine, the proportionality coefficient is and Generally 0.4 and 0.16.

[0082] Sub-step S13, calculate the pressure rise rate during the separation and pressure building process between rocket stages according to the following formula.

[0083] For the temperature rise section, calculate the pressure rise rate as follows: :

[0084]

[0085] For the temperature stable section, the pressure rise rate is calculated according to the following formula: :

[0086]

[0087] in, is the total enthalpy in the engine combustion chamber, K is the empirical coefficient of heat loss, which is generally 0.6~0.9 and can be calibrated according to test results or simulation results. The above formula shows that under the conditions of the chamber volume and the total enthalpy of the gas, the pressure rise rate is proportional to the flow rate.

[0088] Sub-step S14, calculating the consistency evaluation index of the pressure rise rate.

[0089] Step S2, adjusting the operating parameters of the ground simulation device so that under the determined total enthalpy of the detonation gas products, the product of the outlet flow rate and the total enthalpy is close to the flight test state, thereby obtaining the outlet flow rate required for the test.

[0090] Taking the explosion shock tube device as an example, the device uses TNT explosives to produce high-temperature and high-pressure detonation gas products in the explosion chamber. The gas drives the air in the tube to form a shock wave, which reaches the outlet after shaping. The outlet section has a secondary shaping function and can form a relatively stable waveform. When its pressure reaches a certain value, the plug at the entrance of the simulated nozzle opens, and the high-temperature and high-pressure airflow enters the interstage cabin, simulating the jet of the upper stage rocket engine. The specific steps are:

[0091] Sub-step S21, adjusting the total pressure of the explosion shock tube outlet section so that under the condition of the total enthalpy of the detonation gas products determined by the explosion shock tube, the product of the outlet section flow rate and the total enthalpy is close to the flight test state. Specifically, since the outlet section of the explosion shock tube simulation test is generally designed as a throat, using the one-dimensional isentropic compressible flow relationship, under the known total enthalpy of the TNT detonation gas products at the outlet section Under the condition of , so that it satisfies the following relationship proposed by the present invention:

[0092]

[0093] in, is the specific heat ratio of TNT detonation gas products, is the pressure rise rate ratio coefficient of the temperature rise section of the pressure buildup process in the shock tube simulation test of rocket interstage separation explosion. is the nozzle throat area of ​​the ground simulation device.

[0094] Thereby, the product of the explosion shock tube outlet flow rate and the total enthalpy is made consistent with the product of the outlet flow rate and the total enthalpy adopted in the flight test state in step S1.

[0095] Sub-step S22, according to the total pressure of the outlet section obtained in sub-step S21 , select appropriate explosion shock tube operating parameters, including charge amount, charge method and ignition sequence. Under the selected parameters, by looking up the test equipment operating parameter relationship table, evaluate the shock tube outlet flow rate during the pressure build-up process of the interstage separation simulation test .

[0096] Step S3, based on the outlet flow obtained in step S2, evaluate the pressure rise rate during the pressure building process of the rocket engine ground simulation device, and compare it with the pressure rise rate of the flight test state obtained in step S1, to confirm that the difference between the pressure rise process of the ground simulation device and the flight test state is controlled within the engineering application deviation requirements.

[0097] Taking the explosion shock tube device as an example, the following describes the evaluation method of the device for simulating the interstage separation pressure building process.

[0098] Sub-step S31, calculate the characteristic time of the pressure building process of the rocket interstage separation explosion shock tube simulation test according to the following formula :

[0099]

[0100] in, is the initial density, is the volume of the cavity. Under the test scale simulation of 1:1, It is consistent with the corresponding parameters in sub-step S11. The shock tube outlet flow rate during the pressure buildup process of the interstage separation simulation test determined in step 2, and are the gas constants of TNT detonation gas products and air respectively. For a typical explosion shock tube, the characteristic time Generally it is 14.4ms.

[0101] Sub-step S32, calculate the pressure rise rate ratio coefficient of the temperature rise section and the temperature stable section of the pressure build-up process of the rocket interstage separation explosion shock tube simulation test according to the following formula and :

[0102] ,

[0103] Furthermore, based on the above two coefficients, the proportional coefficient of the pressure rise rate in the temperature rise stage relative to the pressure rise rate in the temperature stable stage is calculated as follows:

[0104]

[0105] in, are the constant volume specific heat and specific heat ratio of TNT detonation gas products respectively; are the specific heat at constant volume and specific heat ratio of air respectively.

[0106] Sub-step S33, calculating the pressure rise rate during the pressure building process of the rocket inter-stage separation explosion shock tube simulation test according to the following formula.

[0107] For the temperature rise section, calculate the pressure rise rate as follows: :

[0108]

[0109] For the temperature stable section, the pressure rise rate is calculated according to the following formula: :

[0110]

[0111] in, is the total enthalpy of the gas at the outlet of the explosion shock tube simulation test, K It is the empirical coefficient of heat loss, which is generally between 0.6 and 0.9 and can be calibrated according to test results or simulation results.

[0112] In the flight test state, the characteristic time described in sub-step S11 The pressure rise rate in the temperature stable section of the flight test state is relatively small, that is, the duration of the temperature rise section is relatively short. The present invention proposes to use the pressure rise rate in the temperature stable section of the flight test state as the primary evaluation basis, and then adjust the parameters of the ground simulation device to make its pressure rise rate in the temperature stable section consistent with the flight test state.

[0113] Specifically, according to sub-step S33 and sub-step S13, the pressure rise rate in the temperature stable section of the flight test state and the ground simulator is compared to confirm that the deviation value does not exceed the engineering application deviation requirement, which is generally 10%. If this condition is not met, the outlet flow obtained in step 2 is fine-tuned by ±2% until the pressure rise rate in the temperature stable section of the ground simulator and the pressure rise rate in the temperature stable section of the flight test state are within the engineering application deviation requirement.

[0114] Step S4: Evaluate the working environment of the ground simulation device until it meets the engineering application consistency.

[0115] Sub-step S41, according to the one-dimensional variable cross-section adiabatic steady flow relationship (existing theory), calculate the nozzle outlet parameters of the rocket stage separation ground simulation device. Specifically, it includes calculating the pressure at the nozzle outlet of the engine in the ground simulation device ,density .

[0116] Sub-step S42, according to the Rankine-Hugoniot relationship (existing theory), calculate the shock wave velocity at the initial moment of the pressure building process of the ground simulation device for rocket stage separation Specifically, the shock wave velocity at the initial moment is calculated according to the following formula: The velocity of gas after the wave

[0117]

[0118] in , are the initial pressure and density in the test environment, respectively.

[0119] Sub-step S43, the present invention proposes that another important basis for evaluating the consistency between the earth and the sky during the interstage separation and pressure building process is the quantitative difference between the three-wave structure of the initial shock wave, "shock wave-contact discontinuity-expansion wave", in the flight test state and the ground simulation device test. Specifically, considering that in the flight test state, the shock wave velocity at the initial moment and the gas movement velocity after the wave are very close, in order to evaluate the quantitative difference between the three-wave structure in the flight test state and the ground simulation device test, the shock wave velocity at the initial moment is calculated according to the following formula The velocity of gas after the wave The difference

[0120]

[0121] And use the following formula to evaluate whether this deviation value is much smaller than the shock wave velocity at the initial moment: In this embodiment, the difference of 2 orders of magnitude is used as the judgment standard, namely:

[0122]

[0123] If the requirements are met, the deviation of the ground simulation device for separation between rocket stages from the flight test state meets the requirements of the consistency between heaven and earth in engineering applications; otherwise, the environmental parameters of the test device should be adjusted to reduce the initial pressure in the test environment as much as possible. and density , and re-execute steps S42~S43.

[0124] Step S5, based on step S4, evaluate the degree of over-test of the pressure rise rate during the pressure building process of the ground simulation device compared with the flight test state, and confirm that the over-test degree is within the engineering application deviation requirements to avoid damage to the test product.

[0125] Since the ground simulation device cannot fully cover the flight state, the pressure buildup process it generates is longer than the temperature rise period in the flight test state. According to the calculation results of step S1 and step S3, the degree of assessment is evaluated based on its characteristic time and the proportional coefficient of the pressure rise rate of the two pressure buildup processes.

[0126] Sub-step S51, according to the pressure rise rate of the rocket stage separation pressure buildup process calculated in step S1 and the total time of the pressure buildup process achieved by the flight test separation sequence , the maximum pressure during the interstage separation and pressure building process of the flight test is evaluated according to the following formula :

[0127]

[0128] Sub-step S52, according to the pressure rise rate of the inter-stage separation ground simulation device pressure building process and the total time of the ground simulation test pressure building process calculated in step S3 , the maximum pressure in the ground simulation test is evaluated according to the following formula :

[0129]

[0130] Sub-step S53, comparing the maximum pressure in the ground simulation test The maximum pressure during the pressure buildup during stage separation , calculate the degree of ground simulation test passing assessment, According to the load-bearing capacity of the test product, if the calculated parameters and If it is within the scope of product engineering application requirements, the over-assessment degree of the ground simulation test (that is, the degree of deviation from the consistency between heaven and earth in the direction of a more severe environment) can be accepted, otherwise it is unacceptable.

[0131] The present application provides a computer-readable storage medium, wherein the computer-readable storage medium stores computer instructions, and when the computer instructions are executed on a computer, the computer executes Figure 1 The method described.

[0132] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may take the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware. Moreover, the present application may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage and optical storage, etc.) containing computer-usable program codes.

[0133] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0134] These computer program instructions may also be stored in a computer readable memory capable of directing a computer or other programmable data processing device to operate in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture including an instruction device, which implements the process Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0135] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0136] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

[0137] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A method for evaluating the consistency between the average pressure of the separation and pressure building process between rocket stages, characterized in that: The following steps are involved: S1. For the rocket interstage separation and pressure building process, calculate the approximate value of the interstage separation and pressure building process in the engine flight test state, obtain the characteristic time in the pressure building process, the pressure rise rate proportional coefficient of the temperature rise section and the temperature stable section, and then obtain the pressure rise rate of the temperature rise section and the temperature stable section; S2. Adjust the operating parameters of the ground simulation device so that under the condition of the determined total enthalpy of the detonation gas products, the product of the outlet flow rate and the total enthalpy is close to the flight test state, and the outlet flow rate required for the test is obtained; S3. According to the outlet flow rate obtained in step S2, the pressure rise rate of the rocket engine ground simulation device during the pressure buildup process is evaluated, and compared with the pressure rise rate of the flight test state obtained in step S1, to confirm that the difference between the pressure rise process of the ground simulation device and the flight test state is within the engineering application deviation requirement; S4. Evaluate the working environment of the ground simulation device until it meets the consistency of engineering application; including: to evaluate the quantitative difference between the three-wave structure of "shock wave-contact discontinuity-expansion wave" in the flight test state and the ground simulation device test, calculate the difference between the initial shock wave velocity and the gas movement velocity behind the wave, and evaluate whether this difference is much smaller than the initial shock wave velocity; S5. Based on step S4, evaluate the degree of over-test of the pressure rise rate during the pressure building process of the ground simulation device compared with the flight test state, and confirm that the over-test degree is within the engineering application deviation requirements to avoid damage to the test product.

2. The method for evaluating the consistency of the average pressure of the rocket stage separation and pressure building process between the rocket stages according to claim 1 is characterized in that: The characteristic time calculation method of the pressure buildup process in the engine flight test state is as follows: is the initial density, is the cavity volume, is the engine outlet flow rate during the pressure buildup process, and are the gas constants of fuel gas and air respectively; characteristic time Indicates the duration for the temperature to reach a stable level.

3. The method for evaluating the consistency of the average pressure of the rocket stage separation and pressure building process between the rocket stages according to claim 2 is characterized in that: The calculation method of the proportional coefficient of the pressure rise rate in the temperature rise section and the temperature stable section of the engine flight test state is as follows: ， is the proportional coefficient of the pressure rise rate in the temperature rise section of the engine flight test state, is the proportional coefficient of the pressure rise rate in the temperature stable section of the engine flight test state, is the constant volume specific heat of the engine gas, is the specific heat at constant volume of air.

4. The method for evaluating the consistency of the average pressure between rocket stages during separation and pressure building according to claim 3 is characterized in that: The calculation method of the pressure rise rate in the temperature rise section and temperature stable section of the engine flight test state is as follows: Pressure rise rate in the temperature rise stage : Pressure rise rate in the temperature stable section : in, is the total enthalpy in the engine combustion chamber, K is the empirical coefficient of heat loss.

5. The method for evaluating the consistency of the average pressure between rocket stages during separation and pressure building according to claim 4 is characterized in that: The outlet flow rate required for the test described in step S2 is calculated as follows: Total enthalpy of detonation gas products at the known outlet section Under the condition of , so that it satisfies the following relationship: is the specific heat ratio of the detonation gas products, is the pressure rise rate proportional coefficient of the temperature rise stage during the pressure buildup process of the ground simulation device for rocket stage separation. is the nozzle throat area of ​​the ground simulation device; According to the total pressure of the outlet section , select the operating parameters of the ground simulation device, including the charge amount, charging method and ignition sequence, and evaluate the outlet flow rate of the ground simulation device during the pressure build-up process of the interstage separation simulation test by searching the test equipment operating parameter relationship table under the selected parameters .

6. The method for evaluating the consistency of the average pressure between rocket stages during separation and pressure building according to claim 5, characterized in that: The calculation method of pressure rise rate during the pressure building process of the ground simulation device is as follows: Calculation of characteristic time of pressure buildup process in ground simulation device for rocket stage separation : is the gas constant of the detonation gas product; Calculate the proportional coefficient of pressure rise rate in the temperature rise phase and temperature stable phase of the pressure building process of the ground simulation device for rocket stage separation and : ， is the constant volume specific heat of the detonation gas products; For the temperature rise stage, the pressure rise rate as follows: For the temperature plateau, the pressure rise rate as follows: 。 7. The method for evaluating the consistency of the average pressure between rocket stages during separation and pressure building according to claim 6, characterized in that: Confirm that the difference between the pressure rise process of the ground simulator and the flight test state is within the engineering application deviation requirements, as follows: Compare the pressure rise rate in the temperature stable section of the flight test state and the ground simulation device to confirm that the deviation value does not exceed the engineering application deviation requirements. If the engineering application deviation requirements are not met, the outlet flow rate Make fine adjustments in an amplitude of ±2% until the pressure rise rate in the temperature stable section of the ground simulation device and the pressure rise rate in the temperature stable section of the flight test state are within the engineering application deviation requirements.

8. The method for evaluating the consistency of the average pressure between rocket stages during separation and pressure building according to claim 7, characterized in that: The method for evaluating the working environment of the ground simulator is as follows: S41, calculate the nozzle exit parameters of the rocket stage separation ground simulation device based on the one-dimensional variable cross-section adiabatic steady flow relationship, including the pressure at the nozzle exit of the engine in the ground simulation device ,density ; S42, based on the Rankine-Hugoniot relationship, calculate the shock wave velocity at the initial moment of the pressure buildup process of the ground simulation device for rocket stage separation The velocity of gas after the wave : in , are the initial pressure and density in the test environment, respectively; S43, evaluate the quantitative difference between the initial shock wave's "shock wave-contact discontinuity-expansion wave" three-wave structure in the flight test state and the ground simulation device test: calculate the shock wave velocity at the initial moment The velocity of gas after the wave The difference If satisfied: If the deviation of the ground simulation device for rocket stage separation from the flight test state meets the requirements of the earth-sky consistency in engineering applications, otherwise, the environmental parameters of the test device are adjusted to reduce the initial pressure in the test environment. and density , re-execute steps S42~S43.

9. The method for evaluating the consistency of the average pressure between rocket stages during separation and pressure building according to claim 8, characterized in that: The method for evaluating the degree of pass of the pressure rise rate of the ground simulation device during the pressure build-up process compared with the flight test state is as follows: The total time of the pressure buildup process achieved according to the pressure rise rate during the separation and pressure buildup process of the rocket stages and the separation sequence of the flight test , evaluate the maximum pressure during the interstage separation and pressure building process of the flight test : According to the pressure rise rate of the interstage separation ground simulation device during the pressure building process and the total time of the ground simulation test pressure building process , evaluate the maximum pressure in the ground simulation test : Comparison of maximum pressure in ground simulation tests The maximum pressure during the pressure buildup during stage separation , calculate the degree of ground simulation test passing assessment, express; If you pass the assessment and If it is within the scope of product engineering application requirements, the passing degree of the ground simulation test will be accepted, otherwise it will not be accepted.

10. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 9 are implemented.

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